10950 Federal Register / Vol. 77, No. 37 / Friday, February 24, 2012 / Rules and Regulations 

SMALL BUSINESS SIZE STANDARDS BY NAICS INDUSTRY—Continued 

NAICS 

codes NAICS U.S. industry title Size standards in millions of dollars 

Size standards in 

number of 

employees 

*******

488510 ............... Freight Transportation Arrangement 10 ........................................................................... 10 14.0 ............................

* * * * * * * 

Footnotes 

* * * * * 

10. NAICS codes 488510 (part) 

531210, 541810, 561510, 561520, and 

561920—As measured by total revenues, 

but excluding funds received in trust for 

an unaffiliated third party, such as 

bookings or sales subject to 

commissions. The commissions 

received are included as revenues. 

* * * * * 

Dated: December 21, 2011. 

Karen G. Mills, 

Administrator. 

[FR Doc. 2012–4330 Filed 2–23–12; 8:45 am] 

BILLING CODE 8025–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–25738; Directorate 

Identifier 2006–NE–27–AD; Amendment 39– 

16961; AD 2012–04–05] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company (GE) Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

all GE CF6–80C2B series turbofan 

engines. That AD currently requires 

installing software version 8.2.Q1 to the 

engine electronic control unit (ECU), 

which increases the engine’s margin to 

flameout. This new AD requires the 

removal of the affected ECUs from 

service. This AD was prompted by two 

reports of engine flameout events during 

flight in inclement weather conditions, 

eight reports of engine in-flight 

shutdown (IFSD) events caused by dualchannel central processing unit (CPU) 

faults in the ECU, and four reports of 

engine flameout ground events. We are 

issuing this AD to prevent engine 

flameout or un-commanded engine IFSD 

of one or more engines, leading to an 

emergency or forced landing of the 

airplane. 

DATES: This AD is effective March 30, 

2012. 

ADDRESSES: 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility 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 address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Tomasz Rakowski, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7735; fax: 781–238– 

7199; email: tomasz.rakowski@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2007–12–07, 

Amendment 39–15085 (72 FR 31174, 

June 6, 2007). That AD applies to the 

specified products. The NPRM was 

published in the Federal Register on 

November 14, 2011 (76 FR 70382). That 

NPRM proposed to remove the affected 

ECUs from service. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal and the FAA’s 

response to each comment. 

Request To Change Unsafe Condition 

Commenter GE stated that in all of the 

events of flameout the engines relit and 

in all dual-channel CPU fault in-flight 

shutdowns the engines were capable of 

restarting. GE stated that these events 

should not be considered unsafe 

conditions. 

We do not agree. Although a flameout 

with a consecutive relight or an in-flight 

shutdown with a consecutive restart 

during cruise flight is not in itself an 

unsafe condition, these types of loss of 

thrust can be unsafe conditions during 

takeoff or during approach and landing. 

We did not change the AD. 

Request To Clarify Engine Flight Cycle 

and ECU Cycle Count 

Commenter All Nippon Airways 

(ANA) requested that we clarify the 

relationship between the engine flight 

cycles and ECU cycles of operation in 

the engine, and whether previous ECU 

history affects the flight cycle count. 

We do not agree. The flight cycle 

intervals in paragraph (g) of the AD refer 

to the engine start-stop cycles with the 

affected ECU part numbers (P/Ns) 

installed, rather than ECU operational 

cycles. Engine flight cycles accrued 

before the effective date of the AD are 

not accounted for in the cycle count. We 

did not change the AD. 

Request To Remove Certain Affected 

ECU P/Ns From the AD 

Commenters Atlas Air, ANA, KLM, 

and China Airlines requested that we 

remove from the list of affected ECU 

P/Ns in Table 2 of the AD, ECUs with 

software version 8.2.Q1 and 8.2.R, a 

new front panel assembly (FPA) and an 

old pressure subsystem (PSS), or an old 

FPA and a new PSS generation circuit 

boards. 

We do not agree. Dual-channel CPU 

faults have not been ruled out for the 

new FPA or the new PSS, therefore any 

ECU with either a new FPA or a new 

PSS must be addressed regardless of the 

version of software installed. We did not 

change the AD. 

Request To Add ECU P/Ns to the AD 

Commenter Atlas Air stated that ECUs 

P/Ns 1471M63P41, 1519M89P31, and 

1820M33P14 are not listed in the 

proposed AD, but should be listed. 

We do not agree. Those ECUs have the 

old generation of FPA and PSS circuit 


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Federal Register / Vol. 77, No. 37 / Friday, February 24, 2012 / Rules and Regulations 10951 

boards and, therefore, are not 

susceptible to dual-channel CPU faults. 

The referenced ECUs also have the latest 

available version of software installed. 

We did not change the AD. 

Request To Mandate Software Version 

8.2.R or Later 

Commenter Atlas Air requested to add 

a requirement to install software version 

8.2.R or later in all affected engines at 

specified times, without regard to FPA 

and PSS circuit board hardware 

configuration. 

We do not agree. Certain ECU P/Ns 

that have software version 8.2.R are 

susceptible to CPU channel faults. We 

did not change the AD. 

Request To Modify ECUs 

Commenter Atlas Air requested to 

modify ECU P/Ns 1471M63P42, 

1519M89P32, and 1820M33P15 to ECU 

P/Ns 1471M63P41, 1519M89P31, and 

1820M33P14, respectively. 

We do not agree. No approved 

procedure exists to downgrade the 

ECUs. Engine owners and operators may 

propose such a procedure for approval, 

and request an alternative method of 

compliance to the AD, as specified in 

paragraph (i) of the AD. We did not 

change the AD. 

Request To Add ECU Rework 

Procedures 

Commenter ANA requested that we 

add rework procedures to the AD to 

modify affected ECUs into serviceable 

configurations of ECUs. 

We do not agree. The AD is written 

to only remove affected ECU P/Ns from 

service. Refer to the manufacturer’s 

service information for upgrading 

affected ECUs. We did not change the 

AD. 

Conclusion 

We reviewed the relevant data, 

considered the comments 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 

697 GE CF6–80C2B series turbofan 

engines installed on airplanes of U.S. 

registry. We also estimate that it will 

take about 4 work-hours per engine to 

perform a removal and replacement of 

the ECU, and that the average labor rate 

is $85 per work-hour. A replacement 

ECU costs about $4,600. Based on these 

figures, we estimate the total cost of the 

AD to U.S. operators to be $3,443,180. 

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), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) 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. 

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 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 

removing airworthiness directive (AD) 

2007–12–07, Amendment 39–15085 (72 

FR 31174, June 6, 2007), and adding the 

following new AD: 

2012–04–05 General Electric Company 

(GE): Amendment 39–16961; Docket No. 

FAA–2006–25738; Directorate Identifier 

2006–NE–27–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective March 30, 2012. 

(b) Affected ADs 

This AD supersedes AD 2007–12–07, 

Amendment 39–15085 (72 FR 31174, June 6, 

2007). 

(c) Applicability 

This AD applies to GE CF6–80C2B1F, CF6– 

80C2B1F1, CF6–80C2B1F2, CF6–80C2B2F, 

CF6–80C2B3F, CF6–80C2B4F, CF6– 

80C2B5F, CF6–80C2B6F, CF6–80C2B6FA, 

CF6–80C2B7F, and CF6–80C2B8F turbofan 

engines, including engines marked on the 

engine data plate as CF6–80C2B7F1. 

(d) Unsafe Condition 

This AD results from: 

(1) Two reports of engine flameout events 

during flight in inclement weather 

conditions; and 

(2) Eight reports of engine in-flight 

shutdown (IFSD) events caused by dualchannel central processing unit (CPU) faults 

in the electronic control unit (ECU); and 

(3) Four reports of engine flameout ground 

events. 

(e) We are issuing this AD to prevent 

engine flameout or un-commanded engine 

IFSD of one or more engines, leading to an 

emergency or forced landing of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) ECU Removal 

(1) Remove from service ECUs with part 

numbers (P/Ns) listed in Table 1 of this AD 

within 6 months or 450 engine flight cycles 

after the effective date of this AD, whichever 

occurs first. 

TABLE 1—AFFECTED ECU P/NS

1471M63P01 1471M63P02 1471M63P03 1471M63P04 1471M63P05 

1471M63P06 1471M63P07 1471M63P08 1471M63P09 1471M63P10 

1471M63P11 1471M63P12 1471M63P13 1471M63P14 1471M63P15 

1471M63P16 1471M63P17 1471M63P18 1471M63P23 1471M63P24 


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10952 Federal Register / Vol. 77, No. 37 / Friday, February 24, 2012 / Rules and Regulations 

TABLE 1—AFFECTED ECU P/NS—Continued 

1471M63P25 1471M63P26 1471M63P27 1471M63P28 1471M63P29 

1471M63P30 1471M63P31 1471M63P32 1471M63P33 1471M63P34 

1471M63P35 1471M63P36 1519M89P01 1519M89P02 1519M89P03 

1519M89P04 1519M89P05 1519M89P06 1519M89P07 1519M89P08 

1519M89P09 1519M89P10 1519M89P13 1519M89P14 1519M89P15 

1519M89P16 1519M89P17 1519M89P18 1519M89P19 1519M89P20 

1519M89P21 1519M89P22 1519M89P23 1519M89P24 1519M89P25 

1519M89P26 1820M33P01 1820M33P02 1820M33P03 1820M33P04 

1820M33P05 1820M33P06 1820M33P07 1820M33P08 1820M33P09 

(2) Remove from service ECUs with P/Ns 

2121M37P01, 2121M37P02, 2121M38P01, 

2121M38P02, 2121M41P01 and 2121M41P02 

within 14 months or 1,050 engine flight 

cycles after the effective date of this AD, 

whichever occurs first. 

(3) Remove from service ECUs with P/Ns 

listed in Table 2 of this AD within 60 months 

or 4,500 engine flight cycles after the 

effective date of this AD, whichever occurs 

first. 

TABLE 2—AFFECTED ECU P/NS

1471M63P37 1471M63P38 1471M63P39 1471M63P40 1471M63P42 

1519M89P27 1519M89P28 1519M89P29 1519M89P30 1519M89P32 

1820M33P10 1820M33P11 1820M33P12 1820M33P13 1820M33P15 

2121M25P01 2121M25P02 2121M26P01 2121M26P02 2121M29P01 

2121M29P02 2121M37P03 2121M38P03 2121M41P03 

(h) Installation Prohibition 

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

not install any ECU P/N listed in Table 1 of 

this AD onto any airplane. 

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

not operate any airplane with more than one 

ECU P/N 2121M37P02, 2121M38P02, or 

2121M41P02 installed. 

(i) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs for this AD. Use 

the procedures in 14 CFR 39.19 to make your 

request. 

(j) Related Information 

For more information about this AD, 

contact Tomasz Rakowski, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7735; fax: 781–238– 

7199; email: tomasz.rakowski@faa.gov. 

(k) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

February 17, 2012. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–4284 Filed 2–23–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–1245; Directorate 

Identifier 2008–NE–27–AD; Amendment 39– 

15912; AD 2009–11–02] 

RIN 2120–AA64 

Airworthiness Directives; CFM 

International S.A. Model CFM56 

Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; correction. 

SUMMARY: The FAA is correcting an 

airworthiness directive (AD) that 

published in the Federal Register. That 

AD applies to CFM International S.A. 

CFM56–2, CFM56–3, CFM56–5A, 

CFM56–5B, CFM56–5C, and CFM56–7B 

series turbofan engines with certain part 

number (P/N) and serial number (SN) 

high-pressure compressor (HPC) 4–9 

spools installed. In Table 1 of the AD, 

the HPC 4–9 spool SN GWN05AMO in 

the 2nd column of the Table is 

incorrect. This document corrects that 

error. In all other respects, the original 

document remains the same. 

DATES: This final rule is effective 

February 24, 2012. The effective date for 

AD 2009–11–02 (74 FR 23305, May 19, 

2009) remains June 23, 2009. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility 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 address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Martin Adler, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7157; fax: 781–238– 

7199; email: martin.adler@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Airworthiness Directive 2009–11–02, 

Amendment 39–15912 (74 FR 23305, 

May 19, 2009), currently requires 

removing certain HPC 4–9 spools listed 

by P/N and SN in the AD. 

As published, in Table 1 of the AD, 

the HPC 4–9 spool SN GWN05AMO in 

the 2nd column of the Table is 

incorrect. 

No other part of the preamble or 

regulatory information has been 

changed; therefore, only the changed 

portion of the final rule is being 

published in the Federal Register. 

The effective date of this AD remains 

June 23, 2009. 

Correction of Regulatory Text 

§ 39.13 [Corrected] 

■ In the Federal Register of May 19, 

2009, on page 23306, in the 3rd column, 

in Table 1, under the HPC 4–9 Spool SN 

heading, in the twentieth line of AD 


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