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

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.


### 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:



### R EVISED 

### PARAGRAPH 

### I DENTIFIERS

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:



### E STIMATED 

### 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–


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

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:



### O N 

### -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


### 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 engineflameout 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 hardwarefix 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