Federal Register / Vol. 76, No. 219 / Monday, November 14, 2011 / Proposed Rules 70379 

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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 (AD): 

The Boeing Company: Docket No. FAA– 

2011–1229; Directorate Identifier 2011– 

NM–132–AD. 

(a) Comments Due Date 

We must receive comments by December 

29, 2011. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

airplanes, certificated in any category, as 

identified in paragraphs (c)(1) through (c)(8) 

of this AD, and equipped with auxiliary fuel 

tanks. 

(1) Model DC–9–11, DC–9–12, DC–9–13, 

DC–9–14, DC–9–15, and DC–9–15F airplanes. 

(2) Model DC–9–21 airplanes. 

(3) Model DC–9–31, DC–9–32, DC–9–32 

(VC–9C), DC–9–32F, DC–9–33F, DC–9–34, 

DC–9–34F, and DC–9–32F (C–9A, C–9B) 

airplanes. 

(4) Model DC–9–41 airplanes. 

(5) Model DC–9–51 airplanes. 

(6) Model DC–9–81 (MD–81), DC–9–82 

(MD–82), DC–9–83 (MD–83), and DC–9–87 

(MD–87) airplanes. 

(7) Model MD–88 airplanes. 

(8) Model MD–90–30 airplanes. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 28: Fuel. 

(e) Unsafe Condition 

This AD was prompted by fuel system 

reviews conducted by the manufacturer. We 

are issuing this AD to reduce the potential of 

ignition sources inside fuel tanks, which, in 

combination with flammable fuel vapors, 

could result in fuel tank explosions and 

consequent loss of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Criteria for Operation 

As of 60 months after the effective date of 

this AD, no person may operate any airplane 

affected by this AD unless an amended type 

certificate or supplemental type certificate 

that incorporates the design features and 

requirements described in paragraphs (g)(1), 

(g)(2), and (g)(3) of this AD has been 

approved by the Manager, Los Angeles 

Aircraft Certification Office (ACO), FAA, and 

those design features are installed on the 

airplane. 

(1) Each electrically powered fuel pump 

installed in the center wing tank or auxiliary 

fuel tank must have a protective device 

installed to detect electrical faults that can 

cause arcing and burn through the fuel pump 

housing. The same device must shut off the 

pump by automatically removing electrical 

power from the pump when such faults are 

detected. When a fuel pump is shut off as the 

result of detection of an electrical fault, the 

device must stay latched off until the fault is 

cleared through maintenance action and 

verified that the pump and the electrical 

power feed is safe for operation. 

(2) Additional design features must be 

installed to detect when any center wing tank 

or auxiliary fuel tank pump is running in an 

empty fuel tank. The prospective pump 

shutoff system must shut off each pump no 

later than 60 seconds after the fuel tank is 

emptied. The pump shutoff system design 

must preclude undetected running of a fuel 

pump in an empty tank, after the pump was 

commanded off manually or automatically. 

(3) The implementation of the design 

features defined in paragraphs (g)(1) and 

(g)(2) of this AD must ensure that a fuel 

pump cannot be shut off due to system 

failures including nuisance shutoffs sooner 

than 100,000 hours’ mean time between 

failures (MTBF). 

Note 1: After accomplishing the 

installation specified in paragraph (g) of this 

AD, maintenance and/or preventative 

maintenance under 14 CFR part 43 is 

permitted provided the maintenance does not 

result in changing the AD-mandated 

configuration (reference 14 CFR 39.7). 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles ACO, FAA, 

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. In accordance with 14 CFR 

39.19, send your request to your principal 

inspector or local Flight Standards District 

Office, as appropriate. If sending information 

directly to the manager of the ACO, send it 

to the attention of the person identified in the 

Related Information section of this AD. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(i) Related Information 

For more information about this AD, 

contact Serj Harutunian, Aerospace Engineer, 

Propulsion Branch, ANM–140L, FAA, Los 

Angeles ACO, 3960 Paramount Boulevard, 

Lakewood, California 90712–4137; phone: 

(562) 627–5254; fax: (562) 627–5210; email: 

serj.harutunian@faa.gov. 

Issued in Renton, Washington, on October 

28, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–29303 Filed 11–10–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1245; Directorate 

Identifier 2011–CE–033–AD; RIN 2120– 

AA64] 

Airworthiness Directives; Cessna 

Aircraft Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to certain Cessna Aircraft 

Company (Cessna) Models 172R and 

172S airplanes. The existing AD 

requires you to inspect the fuel return 

line assembly for chafing; replace the 

fuel return line assembly if chafing is 

found; and inspect the clearance 

between the fuel return line assembly 

and both the right steering tube 

assembly and the airplane structure, 

adjusting as necessary. Since we issued 

that AD, we have received a field report 

of a fuel return line chafing incident on 

a Cessna Model 172 airplane with a 

serial number (S/N) that was not 

included in the AD. This proposed AD 

would retain the actions of the current 

AD and add S/Ns to the Applicability 

section of the AD. Chafing of the fuel 

return line assembly could lead to fire. 

We are proposing this AD to correct the 

unsafe condition on these products. 

DATES: We must receive comments on 

this proposed AD by December 29, 

2011. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 


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70380 Federal Register / Vol. 76, No. 219 / Monday, November 14, 2011 / Proposed Rules 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Cessna 

Aircraft Company, Product Support, 

P.O. Box 7706, Wichita, KS 67277; 

telephone: (316) 517–6000; fax: (316) 

517–8500; email: 

Customercare@cessna.textron.com; 

Internet: http://www.cessna.com. You 

may review copies of the referenced 

service information at the FAA, Small 

Airplane Directorate, 901 Locust, 

Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call (816) 329– 

4148. 

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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: (800) 647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Trenton Shepherd, Aerospace Engineer, 

Wichita Aircraft Certification Office, 

FAA, 1801 Airport Road, Room 100, 

Wichita, Kansas 67209; phone: (316) 

946–4143; fax: (316) 946–4107; email: 

trent.shepherd@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2011–1245; Directorate Identifier 

2011–CE–033–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

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 we receive 

about this proposed AD. 

Discussion 

On January 22, 2008, we issued AD 

2008–03–02, Amendment 39–15351 (73 

FR 5737, January 31, 2008), for certain 

Cessna Models 172R and 172S 

airplanes. That AD requires you to 

inspect the fuel return line assembly for 

chafing; replace the fuel return line 

assembly if chafing is found; and 

inspect the clearance between the fuel 

return line assembly and both the right 

steering tube assembly and the airplane 

structure, adjusting as necessary. That 

AD resulted from reports of chafed fuel 

return line assemblies, which were 

caused by the fuel return line assembly 

rubbing against the right steering tube 

assembly during full rudder pedal 

actuation. We issued that AD to detect 

and correct chafing of the fuel return 

line assembly, which could result in 

fuel leaking under the floor and fuel 

vapors entering the cabin. This 

condition could lead to fire under the 

floor or in the cabin area. 

Actions Since Existing AD Was Issued 

Since we issued AD 2008–03–02 (73 

FR 5737, January 31, 2008), we received 

a field report of a fuel return line 

chafing incident on a Cessna Model 172 

airplane with an S/N that was not 

included in the AD. 

Relevant Service Information 

We reviewed Cessna Mandatory 

Service Bulletin SB07–28–01, dated 

June 18, 2007, and Cessna Service 

Bulletin SB07–28–01, Revision 1, dated 

September 22, 2011. The service 

information describes the following 

procedures: 

• Inspecting the fuel return line 

assembly; 

• Replacing the fuel return line 

assembly if chafing is found; and 

• Inspecting the clearance between 

the fuel return line assembly and both 

the right steering tube assembly and the 

airplane structure, adjusting as 

necessary. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would retain all of 

the requirements of AD 2008–03–02 (73 

FR 5737, January 31, 2008). This 

proposed AD would add airplanes to the 

applicability statement of the current 

AD. 

Change to Existing AD 

This proposed AD would retain all 

requirements of AD 2008–03–02 (73 FR 

5737, January 31, 2008). Since AD 

2008–03–02 was issued, the AD format 

has been revised, and certain paragraphs 

have been rearranged. As a result, the 

corresponding paragraph identifiers 

have changed in this proposed AD, as 

listed in the following table: 

REVISED PARAGRAPH IDENTIFIERS

Requirement in AD 

2008–03–02 

Corresponding 

requirement in this 

proposed AD 

paragraph (e)(1) ........ paragraph (g)(1) and 

(g)(2) 

paragraph (e)(2) ........ paragraph (h) 

paragraph (e)(3) ........ paragraph (i) 

Costs of Compliance 

We estimate that this proposed AD 

affects 768 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on 

U.S. 

operators 

Inspection of the fuel return line assembly for chafing 

and clearance.

1 work-hour × $85 per hour 

= $85.

Not applicable .................... $85 $65,280 

The difference in estimated costs of 

this proposed AD and AD 2008–03–02 

(73 FR 5737, January 31, 2008) is an 

increase in the estimated labor cost for 

those airplanes affected by AD 2008– 


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Federal Register / Vol. 76, No. 219 / Monday, November 14, 2011 / Proposed Rules 70381 

03–02 and the costs of the additional 

airplanes added to the proposed AD. 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

proposed inspection. We have no way of 

determining the number of aircraft that 

might need these replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replacement of the fuel return line assembly and adjustment of the clearance between the fuel return line assembly and both the right steering 

tube assembly and the airplane structure.

0.5 work-hour × $85 per hour = 

$42.50.

$123 $165.50 

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 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 the proposed regulation: 

(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), 

(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, Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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) 

2008–03–02, Amendment 39–15351 (73 

FR 5737, January 31, 2008), and adding 

the following new AD: 

Cessna Aircraft Company: Docket No. FAA– 

2011–1245; Directorate Identifier 2011– 

CE–033–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by December 29, 2011. 

(b) Affected ADs 

This AD supersedes AD 2008–03–02 (73 

FR 5737, January 31, 2008), Amendment 39– 

15351. 

(c) Applicability 

This AD applies to the following Cessna 

Aircraft Company airplanes, certificated in 

any category: 

(1) Group 1: Model 172R, serial numbers 

(S/N) 17281188 through 17281390; 

(2) Group 2: Model 172S, S/N 172S9491 

through 172S10489; 

(3) Group 3: Model 172R, S/N 17281391 

through 17281572; and 

(4) Group 4: Model 172S, S/N 172S10490 

through 172S11073. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code Fuel, 28. 

(e) Unsafe Condition 

This AD was prompted by a field report of 

a fuel return line chafing incident on a 

Cessna Model 172 airplane with a serial 

number that was not in the Applicability 

statement of AD 2008–03–02. Chafing of the 

fuel return line assembly could result in fuel 

leaking and fuel vapors, which could lead to 

fire. We are issuing this AD to correct the 

unsafe condition on these products. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection Requirement Retained From 

AD 2008–03–02, Amendment 39–15351 (73 

FR 5737, January 31, 2008) 

(1) For Group 1 and Group 2 Airplanes: 

within the next 100 hours time-in-service 

(TIS) after March 6, 2008 (the effective date 

retained from AD 2008–03–02) or within the 

next 12 months after March 6, 2008 (the 

effective date retained from AD 2008–03–02), 

whichever occurs first, inspect the fuel return 

line assembly (Cessna part number (P/N) 

0500118–49) for chafing. Do the inspection 

following Cessna Service Bulletin SB07–28– 

01, dated June 18, 2007. 

(2) For Group 3 and Group 4 Airplanes: 

within the next 100 hours TIS after the 

effective date of this AD or within the next 

12 months after the effective date of this AD, 

whichever occurs first, inspect the fuel return 

line assembly (Cessna P/N 0500118–49) for 

chafing. Do the inspection following Cessna 

Service Bulletin SB07–28–01, Revision 1, 

dated September 22, 2011. 

(h) Replacement Requirement Retained 

From AD 2008–03–02, Amendment 39–15351 

(73 FR 5737, January 31, 2008) 

For All Airplanes: before further flight after 

the inspection required in paragraph (g)(1) or 

(g)(2) of this AD where evidence of chafing 

was found, replace the fuel return line 

assembly (Cessna P/N 0500118–49). Do the 

replacement following Cessna Service 

Bulletin SB07–28–01, dated June 18, 2007; or 

Cessna Service Bulletin SB07–28–01, 

Revision 1, dated September 22, 2011. 

(i) Inspection and Adjustment Requirement 

Retained From AD 2008–03–02, Amendment 

39–15351 (73 FR 5737, January 31, 2008) 

For All Airplanes: before further flight after 

the inspection required in paragraph (g)(1) or 

(g)(2) of this AD if no chafing is found or after 

the replacement required in paragraph (h) of 

this AD, whichever of the previous situations 

applies, inspect for a minimum clearance of 

0.5 inch between the following parts 

throughout the entire range of copilot rudder 

pedal travel. If less than 0.5 inch clearance 

is found, before further flight, adjust the 

clearance. Follow paragraph 6 of the 

Instructions section of Cessna Service 

Bulletin SB07–28–01, dated June 18, 2007; or 

Cessna Service Bulletin SB07–28–01, 

Revision 1, dated September 22, 2011. This 

AD requires a minimum clearance of 0.5 


jlentini on DSK4TPTVN1PROD with PROPOSALS
70382 Federal Register / Vol. 76, No. 219 / Monday, November 14, 2011 / Proposed Rules 

inch. The requirements of this AD take 

precedence over the actions required in the 

service information. 

(1) The fuel return line assembly (Cessna 

P/N 0500118–49) and the steering tube 

assembly (Cessna P/N MC0543022–2C); and 

(2) The fuel return line assembly (Cessna 

P/N 0500118–49) and the airplane structure. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Wichita Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(k) Related Information 

(1) For more information about this AD, 

Trenton Shepherd, Aerospace Engineer, 

Wichita ACO, FAA, 1801 Airport Road, 

Room 100, Wichita, Kansas 67209; phone: 

(316) 946–4143; fax: (316) 946–4107; email: 

trent.shepherd@faa.gov. 

(2) For service information identified in 

this AD, contact Cessna Aircraft Company, 

Product Support, P.O. Box 7706, Wichita, KS 

67277; telephone: (316) 517–6000; fax: (316) 

517–8500; email: 

Customercare@cessna.textron.com; Internet: 

http://www.cessna.com. You may review 

copies of the referenced service information 

at the FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. 

For information on the availability of this 

material at the FAA, call (816) 329–4148. 

Issued in Kansas City, Missouri, on 

November 7, 2011. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2011–29315 Filed 11–10–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–25738; Directorate 

Identifier 2006–NE–27–AD] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company (GE) CF6–80C2B 

Series Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to all GE CF6–80C2B series 

turbofan engines. The existing AD 

currently requires installing software 

version 8.2.Q1 to the engine electronic 

control unit (ECU), which increases the 

engine’s margin to flameout. Since we 

issued that AD, we have received 

reports of additional engine events. This 

proposed AD would require the removal 

of the affected ECUs from service. We 

are proposing this AD to prevent engine 

flameout or un-commanded engine inflight shutdown (IFSD) of one or more 

engines, leading to an emergency or 

forced landing of the airplane. 

DATES: We must receive comments on 

this proposed AD by January 13, 2012. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: (800) 647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2006–25738; Directorate Identifier 

2006–NE–27–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

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 we receive 

about this proposed AD. 

Discussion 

On May 30, 2007, we issued AD 

2007–12–07, Amendment 39–15085 (72 

FR 31174, June 6, 2007), for all GE CF6– 

80C2B series turbofan engines. That AD 

requires installing software version 

8.2.Q1 to the ECU, which increases the 

engine’s margin to flameout. That AD 

was prompted by multiple reports of 

flameout events during flight on engines 

with an ECU software version preceding 

version 8.2.Q1, including reports of 

events where all engines simultaneously 

experienced a flameout. Investigation 

showed that exposure to ice crystals 

during flight was associated with these 

flameout events. That AD action was 

intended to minimize the potential of an 

engine flameout event caused by ice 

accretion and shedding during flight. 

Actions Since Existing AD Was Issued 

Since we issued AD 2007–12–07 (72 

FR 31174, June 6, 2007), we received 

two reports of ice crystal condition 

flameouts on engines equipped with 

ECU software version 8.2.Q1. Prompted 

by these reports, GE developed ECU 

software version 8.2.R with improved 

inclement weather capability, and 

enhanced fuel metering valve (FMV) 

fault handling logic to reduce the risk of 

engine IFSD caused by intermittent 

FMV feedback signals. 

Subsequently, we received reports of 

eight engine IFSD events and four 

engine flameout ground events. These 

events were caused by ignition system 

induced noise creating dual-channel 

faults in the CPU. The event engines 

were operating with 8.2.Q1 and 8.2.R 

versions of ECU software and equipped 

with the new generation of front panel 

assembly (FPA) and pressure subsystem 

(PSS) circuit boards. Prompted by these 

reports, GE developed an ECU hardware 

fix to eliminate the potential for dualchannel CPU faults due to ignition 

system-induced noise. This proposed 

AD supersedure removes the affected 

ECUs from the fleet. These ECUs, if not 

corrected, could result in flameout or 


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