This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

32649 

Vol. 75, No. 110 

Wednesday, June 9, 2010 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0068; Directorate 

Identifier 2010–NE–05–AD; Amendment 

39–16331; AD 2010–12–10] 

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 superseding an 

existing airworthiness directive (AD) for 

General Electric Company (GE) CF6–45 

and CF6–50 series turbofan engines 

with certain low-pressure turbine (LPT) 

rotor stage 3 disks installed. That AD 

required 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. That AD 

also required fluorescent penetrant 

inspection (FPI) of the LPT rotor stage 

3 disk under certain conditions and 

removal of the disk from service before 

further flight if found cracked. This ad 

requires the same inspections at 

reduced intervals and additional 

borescope inspections. This AD also 

requires repetitive exhaust gas 

temperature (EGT) system checks. This 

AD results from reports received of two 

additional LPT rotor stage 3 disk events. 

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: Effective June 24, 2010. 

We must receive any comments on 

this AD by August 9, 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: Docket Management Facility, 

U.S. 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; phone: 

(781) 238–7133; fax: (781) 238–7199. 

SUPPLEMENTARY INFORMATION: The FAA 

amends 14 CFR part 39 by superseding 

AD 2010–06–15, Amendment 39–16240 

(75 FR 12661, March 17, 2010). That AD 

required initial and repetitive borescope 

inspections of the HPT rotor stage 1 and 

stage 2 blades for wear and damage, 

including excessive airfoil material loss. 

That AD also required FPI of the LPT 

rotor stage 3 disk under certain 

conditions and removal of the disk from 

service before further flight if found 

cracked. That AD was the result of three 

reports of uncontained failures of LPT 

rotor stage 3 disks and eight reports of 

cracked LPT rotor stage 3 disks found 

during shop visit inspections. That 

condition, if not corrected, could result 

in an uncontained engine failure and 

damage to the airplane. 

Actions Since AD 2010–06–15 Was 

Issued 

Since AD 2010–06–15 was issued, we 

received reports of two additional LPT 

rotor stage 3 disk events, bringing the 

total number of events to five. 

Additionally, the National 

Transportation Safety Board issued 

Safety Recommendations A–10–98 

through A–10–101. These 

recommendations include performing a 

borescope inspection of the HPT rotor 

blades more frequently than was 

originally required in AD 2010–06–15. 

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 initial and repetitive borescope 

inspections of the HPT rotor stage 1 and 

stage 2 blades. This AD also requires 

additional borescope inspections and 

FPI of the LPT rotor stage 3 disk, 

depending on the results of the 

borescope inspection. This AD also 

requires repetitive EGT system checks. 

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 ‘‘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 


erowe on DSK5CLS3C1PROD with RULES
32650 Federal Register / Vol. 75, No. 110 / Wednesday, June 9, 2010 / Rules and Regulations 

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 (phone: 

(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: 

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 

removing Amendment 39–16240 (75 FR 

12661, March 17, 2010), and by adding 

a new airworthiness directive, 

Amendment 39–16331, to read as 

follows: 

2010–12–10 General Electric Company: 

Amendment 39–16331. Docket No. 

FAA–2010–0068; Directorate Identifier 

2010–NE–05–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective June 24, 2010. 

Affected ADs 

(b) This AD supersedes AD 2010–06–15, 

Amendment 39–16240. 

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, CF6–50C2–F, 

CF6–50C2–R, CF6–50E, CF6–50E1, and CF6– 

50E2 series turbofan engines, with any of the 

following low-pressure turbine (LPT) rotor 

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, Boeing 747–200/–300, DC–10, 

MD–10, and KC–10 aircraft, and Airbus A300 

series aircraft. 

Unsafe Condition 

(d) This AD results from reports received 

of two additional LPT rotor stage 3 disk 

events. 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 Inspections of High-Pressure 

Turbine (HPT) Rotor Stage 1 and Stage 2 

Blades 

(f) Borescope-inspect the HPT rotor stage 1 

and stage 2 blades from the forward and aft 

directions within 10 cycles from the effective 

date of this AD. You can find further 

guidance about borescoping in Table 2 of this 

AD. 

(g) Thereafter, borescope-inspect the HPT 

rotor stage 1 and stage 2 blades from the 

forward and aft directions within every 75 

cycles-since-last-inspection (CSLI). You can 

find further guidance about borescoping in 

Table 2 of this AD. 

Additional Borescope Inspections 

(h) Borescope-inspect the HPT rotor stage 

1 and stage 2 blades from the forward and aft 

directions within the cycle limits after the 

engine has experienced the events specified 

in Table 1 of this AD. You can find further 

guidance about borescoping in Table 2 of this 

AD. 

TABLE 1—ADDITIONAL BORESCOPE

INSPECTION CRITERIA

If the engine has 

experienced: 

Then borescope 

inspect: 

(1) An exhaust gas 

temperature (EGT) 

above redline.

Within 10 cycles. 


erowe on DSK5CLS3C1PROD with RULES
Federal Register / Vol. 75, No. 110 / Wednesday, June 9, 2010 / Rules and Regulations 32651 

TABLE 1—ADDITIONAL BORESCOPE

INSPECTION CRITERIA—Continued 

If the engine has 

experienced: 

Then borescope 

inspect: 

(2) A shift in the 

smoothed EGT 

trending data that 

exceeds 18° F (10° 

C), but is less than 

or equal to 36° F 

(20° C).

Within 10 cycles. 

(3) A shift in the 

smoothed EGT 

trending data that 

exceeds 36° F (20° 

C).

Before further flight. 

(4) A flightcrew reported vibration determined to be 

caused by the highpressure rotor (N2).

Within 10 cycles from 

the report. 

Actions Required for Engines With Damaged 

HPT Rotor Blades 

(i) Remove the engine before further flight 

if the engine fails the borescope inspection in 

paragraph (f), (g), or (h) of this AD. 

(j) Before returning the engine to service, 

fluorescent penetrant inspect the inner 

diameter surface forward cone body (forward 

spacer arm) of the LPT rotor stage 3 disk. If 

a crack is found or if a circumferential band 

of fluorescence appears, permanently remove 

the disk from service. 

EGT System Checks 

(k) Inspect the turbine midframe (TMF) 

liner for clocking and subsequent damage to 

the EGT probes, within 50 cycles from the 

effective date of this AD or before 

accumulating 750 CSLI of the TMF liner for 

clocking, whichever occurs later. You can 

find further guidance about TMF liner 

inspections in Table 2 of this AD. 

(l) Thereafter, inspect the TMF liner for 

clocking and subsequent damage to the EGT 

probes within every 750 CSLI. You can find 

further guidance about TMF liner inspections 

in Table 2 of this AD. 

(m) If the engine shows TMF liner clocking 

resulting in wear through 100% of the wall 

thickness of the thermocouple guide sleeve, 

remove the engine and repair the TMF and 

any damage to the EGT probes before further 

flight. You can find further guidance about 

TMF liner inspections in Table 2 of this AD. 

(n) Check the resistance of the EGT system 

within 50 cycles from the effective date of 

this AD or before accumulating 750 cyclessince-the-last-resistance check of the EGT 

system, whichever occurs later. You can find 

further guidance about the EGT resistance 

check in Table 2 of this AD. 

(o) Thereafter, check the resistance of the 

EGT system within every 750 CSLI. You can 

find further guidance about EGT resistance 

checks in Table 2 of this AD. 

(p) Repair or replace any EGT system 

component that fails this check, before 

further flight. You can find further guidance 

about the EGT resistance check in Table 2 of 

this AD. 

Definitions 

(q) For the purposes of this AD, an EGT 

above redline is a confirmed over 

temperature indication that is not a result of 

EGT system error. You can find further 

guidance about troubleshooting EGT above 

redline in Table 2 of this AD. 

(r) For the purposes of this AD, a shift in 

the smoothed EGT trending data is a shift in 

a rolling average of EGT that can be 

confirmed by a corresponding shift in the 

trending of fuel flow or fan speed/core speed 

relationship. You can find further guidance 

about evaluating EGT trend data in GE 

Company Service Rep Tip 373 ‘‘Guidelines 

For Parameter Trend Monitoring.’’ 

TABLE 2—AMM REFERENCES FOR FURTHER GUIDANCE

Engine inspections 

Boeing 

747/CF6–50/–45 AMM 

ATA 

Boeing 

DC–10/CF6–50 AMM 

ATA 

Boeing 

MD–10/CF6–50 AMM 

ATA 

Airbus 

A300/CF6–50 AMM 

ATA 

Borescope Inspection of 

HPT Rotor Stage 1 and 

Stage 2 Blades.

72–00–00, 601 .................. 72–53–00 .......................... 72–53–00 .......................... 72–53–00. 

Exceeded EGT Limit ......... 72–00–00, 601 .................. 72–00–00, 601 .................. 72–00–00, 6–1 .................. 72–00–00, 601. 

EGT Resistance Check ..... 77–21–00, 501 .................. 77–21–00 .......................... 77–21–01 .......................... 77–21–00. 

TMF Liner Clocking ........... 72–00–00, 601, and 72– 

52–00.

72–54–00 .......................... 72–54–00 and 77–21–01 .. 72–54–00. 

Previous Credit 

(s) A borescope inspection performed 

before the effective date of this AD using AD 

2010–06–15 and within the last 75 cycles, 

satisfies the initial borescope inspection 

requirement in paragraph (f) of this AD. 

Alternative Methods of Compliance 

(t) Alternative methods of compliance 

previously approved for AD 2010–06–15, are 

not approved for this AD. 

(u) 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 

(v) 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; phone: (781) 

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

information about this AD. 

Material Incorporated by Reference 

(w) None. 

Issued in Burlington, Massachusetts, on 

June 4, 2010. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–13873 Filed 6–7–10; 11:15 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2010–0053; Airspace 

Docket No. 10–ASO–12] 

Establishment of Class E Airspace; 

Quitman, GA 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Direct final rule; confirmation of 

effective date. 

SUMMARY: This action confirms the 

effective date of a direct final rule 

published in the Federal Register April 

1, 2010 that establishes Class E Airspace 

at Quitman Brooks County Airport, 

Quitman, GA. 

DATES: Effective Date: 0901 UTC, June 9, 

2010. 

FOR FURTHER INFORMATION CONTACT: 

Melinda Giddens, Operations Support 

Group, Eastern Service Center, Federal 

Aviation Administration, P.O. Box 

20636, Atlanta, Georgia 30320; 

telephone (404) 305–5610. 

SUPPLEMENTARY INFORMATION: 

Confirmation of Effective Date 

The FAA published this direct final 

rule with a request for comments in the 

Federal Register on April 1, 2010 (75 FR 

16333), Docket No. FAA–2010–0053; 

Airspace Docket No. 10–ASO–12. The 

FAA uses the direct final rulemaking 

procedure for a non-controversial rule 

where the FAA believes that there will 


erowe on DSK5CLS3C1PROD with RULES