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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12664 Federal Register / Vol. 75, No. 51 / Wednesday, March 17, 2010 / Rules and Regulations 

and certain third stage LPCR discs. That 

supplemental NPRM was published in 

the Federal Register on December 11, 

2009 (74 FR 65697). The supplemental 

NPRM proposed to remove from service 

certain second stage LPCR discs and/or 

certain third stage LPCR discs. It also 

revised the proposed AD to correct a P/ 

N error, to clarify the applicability, and 

to clarify the instructions in the 

compliance section. 

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 developing 

this AD. We responded to the comments 

received on the NPRM, in the 

supplemental NPRM. We received no 

comments on the supplemental NPRM 

or on the determination of the cost to 

the public. 

Conclusion 

We have carefully reviewed the 

available data 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 

27 engines installed on airplanes of U.S. 

registry. We also estimate that it will 

take about 4 work-hours per engine to 

perform the actions during scheduled 

maintenance and 140 work-hours per 

engine for the actions during 

unscheduled maintenance. The average 

labor rate is $80 per work-hour. 

Required parts will cost about $31,000 

per engine. Based on these figures, we 

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

operators to be $900,000. 

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: 

2010–06–11 Honeywell International Inc. 

(Formerly AlliedSignal Inc., formerly 

Garrett Turbine Engine Company): 

Amendment 39–16235. Docket No. 

FAA–2009–0331; Directorate Identifier 

2008–NE–40–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective April 21, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Honeywell 

International Inc. TFE731–2, TFE731–2A, 

TFE731–2C, TFE731–3, TFE731–3A, 

TFE731–3AR, TFE731–3B, TFE731–3BR, 

TFE731–3C, TFE731–3CR, TFE731–3D, 

TFE731–3DR, TFE731–3R, TFE731–4, 

TFE731–4R, TFE731–5, TFE731–5AR, 

TFE731–5BR, and TFE731–5R series turbofan 

engines with certain second stage lowpressure compressor rotor (LPCR) discs, part 

number (P/N) 3072396–1 or 3075190–1, and/ 

or certain third stage LPCR discs, P/N 

3072397–1 or 3075192–1, installed. These 

engines are installed on, but not limited to, 

the airplanes listed in Table 1 of this AD. 

TABLE 1—INSTALLED ON AIRPLANES BY MANUFACTURER

Manufacturer Model 

Dassault-Aviation or Dassault Aviation .................................................... Falcon 10 (Falcon 100) and Mystere-Falcon 20, 50, 900 and MF900 

series. 

Cessna Aircraft Company ........................................................................ Model 650, Citation III, VI, and VII. 

Gulfstream Aerospace LP ........................................................................ 1125 Westwind Astra. 

Israel Aircraft Industries ............................................................................ 1124 and 1124A (Westwind). 

Learjet Inc. ................................................................................................ 31, 31A, 35, 35A, 36, 36A, 55, 55B, 55C, and M31. 

Lockheed Martin Corporation (formerly Lockheed-Georgia) .................... 1329–23A, 1329–23D, 1329–23E, and 1329–25. 


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Federal Register / Vol. 75, No. 51 / Wednesday, March 17, 2010 / Rules and Regulations 12665 

TABLE 1—INSTALLED ON AIRPLANES BY MANUFACTURER—Continued 

Manufacturer Model 

Raytheon Corporate Jets (formerly British Aerospace and Hawker 

Beechcraft Corporation).

DH.125 Series 1A, 3A, and 3A/RA, HS.125 Series F3B and F3B/RA, 

BH.125 and DH.125 Series 400A, HS.125 Series 403B, F400B, and 

F403B, HS.125 Series 600A, BH.125 Series 600A, HS.125 Series 

F600B, 700A, and 700B, BAe.125 Series 800 and 1000, and Hawker 

800 and 850XP series. 

Unsafe Condition 

(d) 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. 

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. 

Removing LPCR Discs From Service 

(f) For engines with any of the serial 

number (S/N) LPCR discs listed in Table 5 of 

Honeywell International Inc. Alert Service 

Bulletins (ASBs) TFE731–72–A3748, dated 

August 21, 2008, and/or Table 5 of TFE731– 

72–A3749, dated August 21, 2008, remove 

those LPCR discs from service within 100 

cycles-in-service (CIS) after the effective date 

of this AD. 

(g) For engines with any of the S/N LPCR 

discs listed in Table 6 of Honeywell 

International Inc. ASBs TFE731–72–A3748, 

dated August 21, 2008, and/or Table 6 of 

TFE731–72–A3749, dated August 21, 2008, 

do the earlier of the following: 

(1) Remove the LPCR disc from service 

within 2,000 CIS after the effective date of 

this AD, or 

(2) Remove the LPCR disc from service the 

next time the intermediate case is removed 

from the low-pressure compressor case. 

Installation Prohibition 

(h) After the effective date of this AD, do 

not install any of the S/Ns of LPCR discs 

listed in Table 5 of Honeywell International 

Inc. ASBs TFE731–72–A3748, dated August 

21, 2008, and the discs listed in Table 5 of 

TFE731–72–A3749, dated August 21, 2008, 

into any engine. Also, do not install any of 

the S/Ns of LPCR discs listed in Table 6 of 

Honeywell International Inc. ASBs TFE731– 

72–A3748, dated August 21, 2008, and the 

discs listed in Table 6 of TFE731–72–A3749, 

dated August 21, 2008, into any engine. 

Alternative Methods of Compliance 

(i) The Manager, Los Angeles Aircraft 

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 

(j) 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, for more information about this AD. 

Material Incorporated by Reference 

(k) You must use the service information 

specified in the following Table 2 to identify 

the affected discs requiring removal. 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 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, 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

Honeywell International Inc. Alert Service Bulletin No. Page Revision Date 

TFE731–72–A3748; Total Pages: 18 ............................... All ........................................ Original ................................ August 21, 2008. 

TFE731–72–A3749; Total Pages: 14 ............................... All ........................................ Original ................................ August 21, 2008. 

Issued in Burlington, Massachusetts, on 

March 5, 2010. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–5507 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–2010–0242; Directorate 

Identifier 2009–SW–27–AD; Amendment 39– 

16232; AD 2010–06–08] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation Model S–76C 

Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) for the 

specified Sikorsky Aircraft Corporation 

(Sikorsky) Model S–76C helicopters. 

This action requires inspecting the 

emergency flotation system squib 

connector (flotation system connector) 

to determine if a metallic foil shunt is 

installed. This amendment is prompted 

by a discovery that a metallic foil shunt 

meant to prevent inadvertent activation 

of a flotation system during installation 

was still installed in the left-hand 

flotation system connector of a Model 

S–76C helicopter. The actions specified 

in this AD are intended to determine if 

a metallic foil shunt is installed in the 

flotation system, which could prevent 

the flotation system from deploying and 

could prevent the helicopter from 

staying afloat long enough to enable 


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