Federal Register / Vol. 75, No. 51 / Wednesday, March 17, 2010 / Rules and Regulations 12661 

TABLE 1 

For helicopter model: Refer to paragraph 1.A.1 of ASB: 

AS 332 C, L, L1, and L2 ................................................................................................................. No. 67.00.37, dated February 19, 2007. 

AS 350 B3 ....................................................................................................................................... No. 67.00.40, dated February 19, 2007. 

AS 355 F, F1, F2, and N ................................................................................................................ No. 67.00.28, dated February 19, 2007. 

AS 365 N and N1 ............................................................................................................................ No. 67.00.13, dated February 19, 2007. 

SA 366 G1 ...................................................................................................................................... No. 67.08, dated February 19, 2007. 

EC 130 B4 ....................................................................................................................................... No. 67A010, dated February 19, 2007. 

EC 155B and B1 ............................................................................................................................. No. 67A010, dated February 19, 2007. 

Differences Between This AD and the MCAI 

AD 

(f) This AD differs from the MCAI AD in 

that it: 

(1) Is not applicable to the Model AS 332 

C1 helicopters because they are not type 

certificated in the United States; 

(2) Does not require returning the servocontrols to the manufacturer; 

(3) Does not address servo-control ‘‘spares’’ 

(parts not installed on a helicopter); 

(4) Uses the term ‘‘inspect’’ rather than 

‘‘check’’; and 

(5) Includes information explaining that 

there are 2 ASBs with the same number and 

date. 

Other Information 

(g) Alternative Methods of Compliance 

(AMOCs): The Manager, Safety Management 

Group, 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: Uday Garadi, Aviation 

Safety Engineer, Regulations and Policy 

Group, Rotorcraft Directorate, FAA, Fort 

Worth, Texas 76137, telephone (817) 222– 

5123, fax (817) 222–5961. 

Related Information 

(h) MCAI EASA Airworthiness Directive 

2007–0099, dated April 11, 2007, contains 

related information. 

Joint Aircraft System/Component (JASC) 

Code 

(i) JASC Code 6700: Rotorcraft Flight 

Control. 

Material Incorporated by Reference 

(j) You must use the portions of the service 

information specified in Table 2 to do the 

actions required. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information specified in Table 2 

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

(2) For service information identified in 

this AD, contact American Eurocopter 

Corporation, 2701 Forum Drive, Grand 

Prairie, TX 75053–4005, telephone (972) 

641–3460, fax (972) 641–3527, or at http:// 

www.eurocopter.com. 

(3) You may review copies at the FAA, 

Office of the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd., Room 663, Fort 

Worth, Texas; 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/ibr-locations.html. 

TABLE 2—MATERIAL INCORPORATED BY REFERENCE

Eurocopter Alert Service Bulletin Date For helicopter model 

No. 67.00.37 ............................................................................... February 19, 2007 ................................................. AS 332 C, L, L1, and L2. 

No. 67.00.40 ............................................................................... February 19, 2007 ................................................. AS 350 B3. 

No. 67.00.28 ............................................................................... February 19, 2007 ................................................. AS 355 F, F1, F2, and N. 

No. 67.00.13 ............................................................................... February 19, 2007 ................................................. AS 365 N and N1. 

No. 67.08 .................................................................................... February 19, 2007 ................................................. SA 366 G1. 

No. 67A010 ................................................................................ February 19, 2007 ................................................. EC 130 B4. 

No. 67A010 ................................................................................ February 19, 2007 ................................................. EC 155B and B1. 

Issued in Fort Worth, Texas, on February 

18, 2010. 

Mark R. Schilling, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–5288 Filed 3–16–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0068; Directorate 

Identifier 2010–NE–05–AD; Amendment 39– 

16240; AD 2010–06–15] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company CF6–45 and CF6–50 

Series Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for General 

Electric Company (GE) CF6–45 and 

CF6–50 series turbofan engines with 

certain low-pressure turbine (LPT) stage 

3 disks installed. This AD requires 

fluorescent penetrant inspection (FPI) of 

the LPT stage 3 disk under certain 

conditions and removal of the disk from 

service before further flight if found 

cracked. This AD also requires initial 

and repetitive borescope inspections of 

the high-pressure turbine (HPT) rotor 

stage 1 and stage 2 blades for wear and 

damage, including excessive airfoil 

material loss. This AD results from three 

reports of uncontained failures of LPT 

stage 3 disks and eight reports of 

cracked LPT stage 3 disks found during 

shop visit inspections. We are issuing 

this AD to prevent critical life-limited 

rotating engine part failure, which could 

result in an uncontained engine failure 

and damage to the airplane. 

DATES: This AD becomes effective April 

1, 2010. 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
12662 Federal Register / Vol. 75, No. 51 / Wednesday, March 17, 2010 / Rules and Regulations 

We must receive any comments on 

this AD by May 17, 2010. 

ADDRESSES: Use one of the following 

addresses to comment on this AD: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: U.S. Docket Management 

Facility, 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. 

FOR FURTHER INFORMATION CONTACT: 

Christopher J. Richards, Aerospace 

Engineer, Engine Certification Office, 

FAA, Engine & Propeller Directorate, 12 

New England Executive Park, 

Burlington, MA 01803; e-mail: 

christopher.j.richards@faa.gov; 

telephone (781) 238–7133; fax (781) 

238–7199. 

SUPPLEMENTARY INFORMATION: Since July 

2008, we received three reports of 

uncontained failures of LPT stage 3 

rotor disks and eight reports of cracked 

LPT rotor stage 3 disks found during 

shop visit inspections. GE reports that 

these failures were caused by HPT rotor 

blade airfoil material loss which leads to 

LPT rotor unbalance, vibration, and LPT 

disk separation. GE’s investigation also 

revealed that certain part number LPT 

stage 3 rotor disks could have microcracking on the inner diameter surface 

forward cone body (forward spacer arm) 

that, when exposed to rotor unbalance 

and other conditions, would allow crack 

growth and disk failure. This condition, 

if not corrected, could result in critical 

life-limited rotating engine part failure, 

which could result in an uncontained 

engine failure and damage to the 

airplane. 

FAA’s Determination and Requirements 

of This AD 

The unsafe condition described 

previously is likely to exist or develop 

on other GE CF6–45 and CF6–50 series 

turbofan engines of the same type 

design. For that reason, we are issuing 

this AD to prevent critical life-limited 

rotating engine part failure, which could 

result in an uncontained engine failure 

and damage to the airplane. This AD 

requires FPI of the LPT stage 3 disk 

under the conditions described 

previously and permanent removal from 

service of the disk before further flight 

if found cracked. This AD also requires 

an initial borescope inspection of the 

HPT rotor for evidence of stage 1 and 

stage 2 blade excessive airfoil material 

loss, within 50 cycles-in-service (CIS) 

after the effective date of this AD, and 

thereafter repetitive borescope 

inspections within every 175 CIS. 

FAA’s Determination of the Effective 

Date 

Since an unsafe condition exists that 

requires the immediate adoption of this 

AD, we have found that notice and 

opportunity for public comment before 

issuing this AD are impracticable, and 

that good cause exists for making this 

amendment effective in less than 30 

days. 

Interim Action 

These actions are interim actions and 

we may take further rulemaking actions 

in the future. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to send us any 

written relevant data, views, or 

arguments regarding this AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘AD Docket No. 

FAA–2010–0068; Directorate Identifier 

2010–NE–05–AD’’ in the subject line of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the rule that might suggest a 

need to modify it. 

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 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 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. 

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 the 

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, Safety. 

Adoption of the Amendment 

■ Under the authority delegated to me 

by the Administrator, the Federal 

Aviation Administration amends part 39 

of the Federal Aviation Regulations (14 

CFR part 39) as follows: 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
Federal Register / Vol. 75, No. 51 / Wednesday, March 17, 2010 / Rules and Regulations 12663 

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: 

2010–06–15 General Electric Company: 

Amendment 39–16240. Docket No. 

FAA–2010–0068; Directorate Identifier 

2010–NE–05–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective April 1, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to General Electric 

Company (GE) CF6–45A, CF6–45A2, CF6– 

50A, CF6–50C, CF6–50CA, CF6–50C1, CF6– 

50C2, CF6–50C2B, CF6–50C2D, CF6–50C2F, 

CF6–50C2R, CF6–50E, CF6–50E1, and CF6– 

50E2, series turbofan engines, with any of the 

following low-pressure turbine (LPT) stage 3 

disks installed: 

9061M23P06 9061M23P07 9061M23P08 9061M23P09 9224M75P01 

9061M23P10 1473M90P01 1473M90P02 1473M90P03 1473M90P04 

9061M23P12 9061M23P14 9061M23P15 9061M23P16 1479M75P01 

1479M75P02 1479M75P03 1479M75P04 1479M75P05 1479M75P06 

1479M75P07 1479M75P08 1479M75P09 1479M75P11 1479M75P13 

1479M75P14 N/A N/A N/A N/A 

These engines are installed on, but not 

limited to, Airbus A300 series, Boeing 747 

series, McDonnell Douglas DC–10 series, and 

DC–10–30F (KDC–10) airplanes. 

Unsafe Condition 

(d) This AD results from three reports of 

uncontained failures of LPT stage 3 disks and 

eight reports of cracked LPT stage 3 disks 

found during shop visit inspections. We are 

issuing this AD to prevent critical life-limited 

rotating engine part failure, which could 

result in an uncontained engine failure 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. 

Borescope Inspection of High-Pressure 

Turbine (HPT) Stage 1 and Stage 2 Rotor 

Blades 

(f) Within 50 cycles-in-service (CIS) after 

the effective date of this AD, borescopeinspect the HPT stage 1 and stage 2 rotor 

blades for wear and damage, including 

excessive airfoil material loss. 

(g) Thereafter, within every 175 CIS, 

repetitively borescope-inspect the HPT stage 

1 and stage 2 rotor blades for wear and 

damage, including excessive airfoil material 

loss. 

Actions Required Whenever the HPT Rotor 

Blade Cumulative Airfoil Material Loss is 

50% of a Blade or More 

(h) Whenever the HPT rotor blade 

cumulative airfoil material loss is 50% of a 

blade or more, then before further flight, 

fluorescent penetrant inspect the inner 

diameter surface forward cone body (forward 

spacer arm) of the LPT stage 3 disk. 

(i) If the LPT stage 3 disk is cracked or if 

a circumferential band of fluorescence 

appears, permanently remove the disk from 

service. 

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 Christopher J. Richards, 

Aerospace Engineer, Engine Certification 

Office, FAA, Engine & Propeller Directorate, 

12 New England Executive Park, Burlington, 

MA 01803; e-mail: 

christopher.j.richards@faa.gov; telephone 

(781) 238–7133; fax (781) 238–7199, for more 

information about this AD. 

Material Incorporated by Reference 

(l) None. 

Issued in Burlington, Massachusetts on 

March 10, 2010. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–5777 Filed 3–16–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0331; Directorate 

Identifier 2008–NE–40–AD; Amendment 39– 

16235; AD 2010–06–11] 

RIN 2120–AA64 

Airworthiness Directives; Honeywell 

International Inc. TFE731 Series 

Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for 

Honeywell International Inc. TFE731 

series turbofan engines with certain 

second stage low-pressure compressor 

rotor (LPCR) discs and/or certain third 

stage LPCR discs installed. This AD 

requires removing from service certain 

second stage LPCR discs and/or certain 

third stage LPCR discs. This AD results 

from a report of cracks found during a 

fluorescent penetrant inspection (FPI) of 

the disc bore. We are issuing this AD to 

prevent an uncontained failure of a 

second stage LPCR disc and/or a third 

stage LPCR disc due to cracks in the 

bore, which could result in damage to 

the airplane. 

DATES: This AD becomes effective April 

21, 2010. The Director of the Federal 

Register approved the incorporation by 

reference of certain publications listed 

in the regulations as of April 21, 2010. 

ADDRESSES: You can get the service 

information identified in this AD from 

Honeywell Engines and Systems 

Technical Publications and Distribution, 

M/S 2101–201, P.O. Box 52170, 

Phoenix, AZ 85072–2170, telephone: 

Global Customer Care toll free (800) 

601–3099; International callers (602) 

365–3099. 

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: 

Joseph Costa, Aerospace Engineer, Los 

Angeles Aircraft Certification Office, 

FAA, Transport Airplane Directorate, 

3960 Paramount Blvd., Lakewood, CA 

90712–4137; e-mail: 

joseph.costa@faa.gov; telephone: (562) 

627–5246; fax: (562) 627–5210. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

a notice of proposed rulemaking 

(NPRM) and a supplemental NPRM, to 

amend 14 CFR part 39 to add an AD, for 

Honeywell International Inc. TFE731 

series turbofan engines with certain 

second stage LPCR discs and/or certain 

third stage LPCR discs installed. That 

NPRM was published in the Federal 

Register on April 13, 2009 (74 FR 

16807) and proposed to remove from 

service certain second stage LPCR discs 


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