2064 Federal Register / Vol. 75, No. 9 / Thursday, January 14, 2010 / Rules and Regulations 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA 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 AD: 

2010–02–04 The Boeing Company: 

Amendment 39–16175. Docket No. 

FAA–2009–0657; Directorate Identifier 

2009–NM–048–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective February 18, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to The Boeing 

Company Model 737–600, –700, –700C, 

–800, –900, and –900ER series airplanes, 

certificated in any category; as identified in 

Boeing Service Bulletin 737–28–1272, dated 

October 31, 2008. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 28: Fuel. 

Unsafe Condition 

(e) This AD requires replacing engine fuel 

shutoff valves for the left and right main 

tanks. This AD results from a report of a 

failed engine start, which was caused by an 

internally fractured engine fuel shutoff valve. 

We are issuing this AD to prevent the failure 

of the valve in the closed position, open 

position, or partially open position, which 

could result in engine fuel flow problems and 

possible uncontrolled fuel leak or fire. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Replacement of the Engine Fuel Spar Valve 

Body of the Left and Right Wing Main Tanks 

(g) Within 60 months after the effective 

date of this AD: Replace the engine fuel spar 

valve bodies of the left and right wing main 

tanks in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 737–28–1272, dated October 

31, 2008. 

Note 1: Boeing Service Bulletin 737–28– 

1272, dated October 31, 2008, refers to ITT 

Aerospace Controls Service Bulletin 

125334D–28–02, dated August 27, 2008, as 

an additional source of guidance for 

modifying the valve body assembly. 

Parts Installation 

(h) As of the effective date of this AD, no 

person may install any engine fuel shutoff 

valve with ITT Aerospace Controls part 

number 125334D–1 (Boeing part number 

S343T003–40) on any airplane at the spar 

valve location. A valve that has been 

modified in accordance with Boeing Service 

Bulletin 737–28–1272, dated October 31, 

2008, to the new ITT 125334D–2 part number 

(Boeing part number S343T003–67) may be 

installed at the spar valve location. 

(i) As of the effective date of this AD, no 

valve with ITT Aerospace Controls part 

number 125334D–1 (Boeing part number 

S343T003–40) that has been removed from 

the spar location may be reinstalled on any 

airplane in any location unless it has been 

modified in accordance with Boeing Service 

Bulletin 737–28–1272, dated October 31, 

2008, to the new ITT 125334D–2 part number 

(Boeing part number S343T003–67). 

Alternative Methods of Compliance 

(AMOCs) 

(j)(1) The Manager, Seattle Aircraft 

Certification Office, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Send information to ATTN: Samuel Spitzer, 

Aerospace Engineer, Propulsion Branch, 

ANM–140S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; telephone 

(425) 917–6510; fax (425) 917–6590. Or, 

e-mail information to 9-ANM-Seattle-ACOAMOC-Requests@faa.gov. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

Material Incorporated by Reference 

(k) You must use Boeing Service Bulletin 

737–28–1272, dated October 31, 2008, to do 

the actions required by this AD, unless the 

AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; e-mail me.boecom@boeing.com; 

Internet https://www.myboeingfleet.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221 or 425–227–1152. 

(4) You may also review copies of the 

service information that is incorporated by 

reference 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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on 

December 30, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–398 Filed 1–13–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0236; Directorate 

Identifier 2009–NE–06–AD; Amendment 39– 

16162; AD 2010–01–05] 

RIN 2120–AA64 

Airworthiness Directives; CFM 

International, S.A. CFM56–7B Series 

Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for CFM 

International, S.A. CFM56–7B series 

turbofan engines. This AD requires 

initial and repetitive eddy current 

inspections (ECIs) of certain part 

number (P/N) low-pressure (LP) turbine 

rear frames. This AD results from a 

refined life analysis by the engine 

manufacturer that shows the need to 

identify an initial and repetitive 

inspection threshold for inspecting 

certain LP turbine rear frames. We are 

issuing this AD to prevent failure of the 

LP turbine rear frame from low-cyclefatigue cracks. Failure of the LP turbine 

rear frame could result in engine 

separation from the airplane, possibly 

leading to loss of control of the airplane. 

DATES: This AD becomes effective 

February 18, 2010. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulations as 

of February 18, 2010. 

ADDRESSES: You can get the service 

information identified in this AD from 

CFM International, Technical 

Publications 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. 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
Federal Register / Vol. 75, No. 9 / Thursday, January 14, 2010 / Rules and Regulations 2065 

FOR FURTHER INFORMATION CONTACT: 

Antonio Cancelliere, Aerospace 

Engineer, Engine Certification Office, 

FAA, Engine and 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 CFM International, S.A. 

CFM56–7B series turbofan engines. We 

published the proposed AD in the 

Federal Register on May 11, 2009 (74 

FR 21772). That action proposed to 

require initial and repetitive ECIs of 

certain P/N LP turbine rear frames. 

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. 

Request To Supersede or Revise 

Existing AD 2008–03–09 

One commenter, the Air Transport 

Association (ATA), requests that we 

should supersede or revise existing AD 

2008–03–09 to incorporate the 

requirements and P/Ns affected by the 

proposed AD. 

We do not agree. Superseding or 

revising that AD to incorporate these 

requirements would make the 

requirements of existing AD 2008–03– 

09 and this AD confusing. AD 2008–03– 

09 requires a change to the 

Airworthiness Limitations Section 

(ALS) for the introduction of the new LP 

turbine rear frame life limits, with 

inspections, while this AD introduces 

limits for LP turbine rear frame P/Ns 

that were introduced to the field before 

the ALS changes occurred. We did not 

change the AD. 

Request To Reference the Latest Service 

Bulletins (SBs) 

ATA and CFM International, S.A. 

request that we reference the latest 

version of CFM International, S.A. SB 

No. CFM56–7B S/B 72–0579, which is 

Revision 5, dated March 30, 2009. CFM 

International also requests that we 

reference the latest version of CFM 

International, S.A. SB No. CFM56–7B 

S/B 72–0558, which is Revision 3, dated 

March 30, 2009. 

We agree and changed the SB 

references in the AD. 

Request To Include LP Turbine Rear 

Frame P/Ns 

ATA requests that we include turbine 

rear frame P/Ns 340–166–251–0; 340– 

166–252–0; and 340–166–253–0. These 

P/Ns are included in the effectivity 

section of CFM International, S.A. SB 

No. CFM56–7B S/B 72–0579, and 

Engine Manual 05–21–03. ATA also 

requests that we include LP turbine rear 

frame P/Ns 340–027–110–0 and 370– 

027–120–0. These P/Ns are included in 

the effectivity section of CFM 

International, S.A. SB No. CFM56–7B 

S/B 72–0568. 

We do not agree. This AD addresses 

LP turbine rear frame P/Ns introduced 

in the field by CFM International, S.A. 

through SB No. CFM56–7B S/B 72– 

0527, before the ALS could be modified 

to include the LP turbine rear frame 

P/Ns affected by this AD. The LP 

turbine rear frame P/Ns listed by ATA 

are already listed in the ALS. We did 

not change the AD. 

Question Regarding Inclusion of LP 

Turbine Rear Frame P/Ns 

Japan Airlines (JAL) questions 

whether the LP turbine rear frame P/Ns 

340–166–251–0; 340–166–252–0; and 

340–166–253–0 should be listed in this 

AD. 

The LP turbine rear frame P/Ns 

referred to by JAL are already listed in 

the ALS. We did not change the AD. 

Request To Remove Engine Models 

ATA requests that we remove engine 

models CFM56–7B26/B2; CFM56–7B26/ 

3B2; and CFM56–7B26/3B2F from the 

proposed AD, as they are not affected. 

We agree and removed those models 

from the AD. We also advised CFM 

International, S.A., to remove those 

models from the effectivity list of SB 

No. CFM56–7B S/B 72–0579. 

Request To Remove Repeated P/Ns 

ATA requests that we remove the 

repeated listings of LP turbine rear 

frame P/N 340–166–254–0 from the AD. 

We agree and removed the repeated 

P/N listings from the AD. 

Request To Review and Correct an 

Engine Model 

ATA and CFM International, S.A. 

request that we review the engine model 

–7B27/3 in the proposed AD, as it 

appears to be incorrect. ATA states also 

that engine model –7B27/B3 is missing 

from the proposed AD. 

We agree. We corrected the –7B27/3 

engine model in paragraph (g) to read 

‘‘–7B27/B3’’. We also corrected the 

typographical error in paragraph (c)(1) 

so that engine model –7B27/3 is not 

duplicated. We changed the duplicate 

model to read ‘‘–7B27/B3’’. 

Request To Remove an Engine Model 

ATA requests that we remove engine 

model –7B27A from paragraph (f) of the 

proposed AD, as it is not affected by the 

AD action. 

We agree and removed that engine 

model from the AD. 

Previous Credit Paragraphs Added 

Since we issued the proposed AD, we 

became aware that we need to allow 

previous credit for initial inspections 

done before the effective date of the AD, 

using earlier versions of the applicable 

SBs. We added two previous credit 

paragraphs to the compliance section of 

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 

1,228 CFM56–7B series turbofan 

engines installed on airplanes of U.S. 

registry. We estimate that it will take 

about 3 work-hours to perform an eddy 

current inspection of an LP turbine rear 

frame. The average labor rate is $80 per 

work-hour. A new replacement LP 

turbine rear frame costs about $275,000. 

We estimate that all but the first of the 

recurrent inspections would occur 

during normally scheduled 

maintenance. Therefore, the cost of only 

the first inspection is included as 

directly attributable to this AD and we 

included that cost in the first year. Also, 

while we estimate that all 1,228 LP 

turbine rear frames will need 

replacement at some point in their 30- 

year useful life, only the unused cost of 

the part is attributable to this AD. 

Therefore, based on the service history 

of the LP turbine rear frame, we estimate 

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

to be less than $11,266,490 annually 

based on a 30-year fleet life expectation. 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
2066 Federal Register / Vol. 75, No. 9 / Thursday, January 14, 2010 / Rules and Regulations 

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: 

2010–01–05 CFM International, S.A: 

Amendment 39–16162. Docket No. 

FAA–2009–0236; Directorate Identifier 

2009–NE–06–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective February 18, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to: 

(1) CFM International, S.A. CFM56–7B20; 

–7B22; –7B24; –7B26; –7B27; –7B22/B1; 

–7B24/B1; –7B27/B1; –7B26/B1; –7B20/3; 

–7B22/3; –7B24/3; –7B26/3; –7B27/3; –7B22/ 

3B1; –7B24/3B1; –7B27/3B1; –7B26/3B1; 

–7B26/3F; –7B27/B3; –7B27/3F; –7B27/3B1F; 

and –7B27/3B3 turbofan engines assembled 

with a low-pressure (LP) turbine rear frame, 

part number (P/N) 340–166–254–0; 340–166– 

255–0; 340–166–256–0; 340–166–257–0; 

340–166–258–0; or 340–166–259–0; and 

(2) CFM International, S.A. CFM56–7B20/ 

2; –7B22/2; –7B24/2; –7B26/2; and –7B27/2 

turbofan engines assembled with a dual 

annular combustor and an LP turbine rear 

frame, P/N 340–177–551–0; 340–177–552–0; 

340–177–553–0; 340–177–554–0; 340–177– 

555–0; or 340–177–556–0. 

(3) These engines are installed on, but not 

limited to, Boeing 737–600, 737–700, 737– 

800, and 737–900 series airplanes. 

Unsafe Condition 

(d) This AD results from a refined life 

analysis by the engine manufacturer that 

shows the need to identify an initial and 

repetitive inspection threshold for inspecting 

certain LP turbine rear frames. We are issuing 

this AD to prevent failure of the LP turbine 

rear frame from low-cycle-fatigue cracks. 

Failure of the LP turbine rear frame could 

result in engine separation from the airplane, 

possibly leading to loss of control of 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. 

Inspections of LP Turbine Rear Frames 

(f) For CFM International, S.A. CFM56– 

7B20; –7B22; –7B24; –7B26; –7B27; –7B22/ 

B1; –7B24/B1; –7B27/B1; –7B20/3; –7B22/3; 

–7B24/3; –7B26/3; –7B27/3; –7B22/3B1; 

–7B24/3B1; –7B27/3B1; –7B26/3F; –7B27/3F; 

and –7B27/3B1F turbofan engines with an LP 

turbine rear frame, P/N 340–166–254–0; 340– 

166–255–0; 340–166–256–0; 340–166–257–0; 

340–166–258–0; or 340–166–259–0, do the 

following: 

(1) Perform an initial eddy current 

inspection (ECI) of the LP turbine rear frame 

within 25,000 cycles-since-new (CSN) on the 

LP turbine rear frame. 

(2) For engines with unknown LP turbine 

rear frame CSN, perform an initial ECI within 

300 cycles from the effective date of this AD. 

(3) Perform repetitive ECIs of the LP 

turbine rear frame, using the inspection 

intervals in paragraph 3.A. (8) of the 

Accomplishment Instructions of CFM 

International, S.A. SB No. CFM56–7B S/B 

72–0579, Revision 5, dated March 30, 2009. 

(4) Use paragraphs 3.A. through 3.A. (7)(d) 

of the Accomplishment Instructions of CFM 

International, S.A. Service Bulletin (SB) No. 

CFM56–7B S/B 72–0579, Revision 5, dated 

March 30, 2009, to do the ECIs. 

(5) Remove LP turbine rear frames from 

service that have a total cumulated crack 

length at any location, of 0.79 inch (20 mm) 

or longer. 

(g) For CFM International, S.A. CFM56– 

7B26/B1; –7B27/B3; –7B26/3B1; and –7B27/ 

3B3 turbofan engines with an LP turbine rear 

frame, P/N 340–166–254–0; 340–166–255–0; 

340–166–256–0; 340–166–257–0; 340–166– 

258–0; or 340–166–259–0, do the following: 

(1) Perform an initial ECI of the LP turbine 

rear frame within 19,000 CSN on the LP 

turbine rear frame. 

(2) For engines with unknown LP turbine 

rear frame CSN, perform an initial ECI within 

300 cycles from the effective date of this AD. 

(3) Perform repetitive ECIs of the LP 

turbine rear frame, using the inspection 

intervals in paragraph 3.A. (9) of the 

Accomplishment Instructions of CFM 

International, S.A. SB No. CFM56–7B S/B 

72–0579, Revision 5, dated March 30, 2009. 

(4) Use paragraphs 3.A. through 3.A. (7)(d) 

of the Accomplishment Instructions of CFM 

International, S.A. Service Bulletin (SB) No. 

CFM56–7B S/B 72–0579, Revision 5, dated 

March 30, 2009, to do the ECIs. 

(5) Remove LP turbine rear frames from 

service that have a total cumulated crack 

length at any location, of 0.79 inch (20 mm) 

or longer. 

(h) For CFM International, S.A. CFM56– 

7B20/2; –7B22/2; –7B24/2; –7B26/2; and 

–7B27/2 turbofan engines assembled with a 

dual annular combustor and an LP turbine 

rear frame, P/N 340–177–551–0; 340–177– 

552–0; 340–177–553–0; 340–177–554–0; 

340–177–555–0; or 340–177–556–0, do the 

following: 

(1) Perform an initial ECI of the LP turbine 

rear frame within 16,350 CSN on the LP 

turbine rear frame. 

(2) For engines with unknown LP turbine 

rear frame CSN, perform an initial ECI within 

300 cycles from the effective date of this AD. 

(3) Perform repetitive ECIs of the LP 

turbine rear frame, using the inspection 

intervals in paragraph 3.A. (8) of the 

Accomplishment Instructions of CFM 

International, S.A. SB No. CFM56–7B S/B 

72–0558, Revision 3, dated March 30, 2009. 

(4) Use paragraphs 3.A. through 3.A. (7)(d) 

of the Accomplishment Instructions of CFM 

International, S.A. SB No. CFM56–7B S/B 

72–0558, Revision 3, dated March 30, 2009, 

to do the ECIs. 

(5) Remove LP turbine rear frames from 

service that have a total cumulated crack 

length at any location, of 0.43 inch (11 mm) 

or longer. 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
Federal Register / Vol. 75, No. 9 / Thursday, January 14, 2010 / Rules and Regulations 2067 

Previous Credit 

(i) Initial inspection of LP turbine rear 

frames before the effective date of this AD 

performed using the Accomplishment 

Instructions of CFM International, S.A. SB 

No. CFM56–7B S/B 72–0579, original issue, 

Revision 1, Revision 2, Revision 3, or 

Revision 4, satisfy the requirements of 

paragraphs (f)(1), (f)(2), (g)(1), and (g)(2) of 

this AD. 

(j) Initial inspection of LP turbine rear 

frames before the effective date of this AD 

performed using the Accomplishment 

Instructions of CFM International, S.A. SB 

No. CFM56–7B S/B 72–0558, original issue, 

Revision 1, or Revision 2, satisfy the 

requirements of paragraphs (h)(1) and (h)(2) 

of this AD. 

Alternative Methods of Compliance 

(k) 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 

(l) European Aviation Safety Agency AD 

2009–0009 (corrected), dated January 27, 

2009, also addresses the subject of this AD. 

(m) Contact Antonio Cancelliere, 

Aerospace Engineer, Engine Certification 

Office, FAA, Engine and 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. 

Material Incorporated by Reference 

(n) You must use the service information 

specified in the following Table 1 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 1 in accordance 

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

Contact CFM International, Technical 

Publications 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/federal-register/cfr/ibrlocations.html. 

TABLE 1—INCORPORATION BY REFERENCE

Service Bulletin No. Page Revision Date 

CFM56–7B S/B 72–0558 ................................................................................. All ................................ 3 March 30, 2009. 

Total Pages: 22 

CFM56–7B S/B 72–0579 ................................................................................. All ................................ 5 March 30, 2009 

Total Pages: 23 

Issued in Burlington, Massachusetts, on 

December 23, 2009. 

Francis A. Favara, 

Manager, Engine and Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–31043 Filed 1–13–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0503; Directorate 

Identifier 2009–NE–12–AD; Amendment 39– 

16172; AD 2010–02–01] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

S.A. Model Arriel 1B, 1D, and 1D1 

Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), 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) 

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: 

The rupture of the Reduction Gear Box 

Intermediate Pinion may result in an 

overspeed of the Power Turbine and, 

subsequently, an uncommanded engine inflight shutdown. This could lead to an 

emergency autorotation landing on a singleengine helicopter. 

We are issuing this AD to prevent the 

rupture of the reduction gear box 

intermediate pinion, which could result 

in an overspeed of the power turbine, an 

uncommanded in-flight shutdown of the 

engine, and an emergency autorotation 

landing. 

DATES: This AD becomes effective 

February 18, 2010. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD as of 

February 18, 2010. 

ADDRESSES: 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: 

James Lawrence, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: james.lawrence@faa.gov; 

telephone (781) 238–7176; fax (781) 

238–7199. 

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 June 12, 2009 (74 FR 27946). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

Several events of rupture of the Arriel 1 

Reduction Gear Box Intermediate Pinion 

have been reported in service. The ruptures 

have been determined to be originated at the 

pinion teeth root due to increased vibratory 

stresses. This increase in vibratory stresses is 

mainly caused by increased teeth wear over 

engine life time. 

The rupture of the Reduction Gear Box 

Intermediate Pinion may result in an 

overspeed of the Power Turbine and, 

subsequently, an uncommanded engine inflight shutdown. This could lead to an 

emergency autorotation landing on a singleengine helicopter. 

To reduce the level of vibratory stresses 

and improve tooth resistance, Turbome ́ca 

modification incorporates the addition of a 

damping ring below the teeth and a shot 

peening of the teeth roots. These 

modifications reduce the risk of incipient 

fatigue cracks. 

This AD requires the replacement of all 

Reduction Gear Box Intermediate Pinions 

with Pinions incorporating Turbome ́ca 

modification TU 232. 

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 


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