### 14796 Federal Register / Vol. 76, No. 53 / Friday, March 18, 2011 / Rules and Regulations

Applicability

As discussed above, these special conditions are applicable to the GVI. Should Gulfstream apply at a later date for a change to the type certificate to include another model on the same type certificate incorporating the same novel or unusual design feature, the special conditions would apply to that model as well.

Conclusion

This action affects only certain novel or unusual design features on one airplane model. It is not a rule of general applicability. List of Subjects in 14 CFR Part 25

Aircraft, Aviation safety, Reporting and recordkeeping requirements.

The authority citation for these special conditions is as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704. The Special Conditions

Accordingly, pursuant to the authority delegated to me by the Administrator, the following special conditions are issued as part of the type certification basis for Gulfstream GVI airplanes.

If the design of the flight control system has multiple modes of operation, a means must be provided to indicate to the flight crew any mode that significantly changes or degrades the normal handling or operational characteristics of the airplane.

Issued in Renton, Washington, on March 9,
2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2011–6333 Filed 3–17–11; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2006–24145; Directorate Identifier 2006–NE–06–AD; Amendment 39–**  **16638; AD 2011–07–01]**

**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.

**SUMMARY :**  We are superseding an existing airworthiness directive (AD) for General Electric Company (GE) CF6–45 and CF6–50 series turbofan engines. That AD currently requires replacing certain forward and aft centerbodies of the long fixed core exhaust nozzle (LFCEN) assembly. This AD adds certain new forward and aft centerbody part numbers (P/Ns) to the list requiring replacement. This AD was prompted by the discovery of more LFCEN forward and aft centerbody P/Ns that require replacement. We are issuing this AD to prevent the forward and aft centerbody of the LFCEN assembly from separating from the engine, causing damage to the engine, and damage to the airplane.

**DATES :**  This AD is effective April 22,
2011.

**ADDRESSES :**  For service information identified in this AD, contact GE– Aviation M/D Rm. 285, One Neumann Way, Cincinnati, OH 45215, telephone 513–552–3272; e-mail: geae.aoc@ge.com. You may review copies of the referenced service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. 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; phone: 781– 238–7735; fax: 781–238–7199; e-mail: tomasz.rakowski@faa.gov.

**SUPPLEMENTARY INFORMATION :** 
Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede airworthiness directive (AD) 2009–04–17, Amendment 39–15823 (74 FR 8735, February 26, 2009). That AD applies to the specified products. The NPRM published in the Federal Register on January 4, 2011 (76 FR 292). That NPRM proposed to add forward centerbody P/Ns 9076M28G05, G06, and G08, P/Ns 9076M82G01 and G03, and aft centerbody P/Ns 9076M46G02 and G04 to the P/Ns in AD 2009–04–17 that are required to be removed from service.

Comments

We gave the public the opportunity to participate in developing this AD. The following presents the comment received on the proposal and the FAA’s response to the comment.
Request

One commenter, Boeing Commercial Airplanes, pointed out that the McDonnell Douglas airplanes affected by the proposed AD should be listed out as DC–10–15, DC–10–30, DC–10–30F, KC–10, KDC–10, and MD–10–30F. The commenter stated that the proposed AD only listed these airplanes as a series.

We agree. We revised this AD as requested, except we listed KC–10 as KC–10A as it appears in the Type Certificate Data Sheet.

Conclusion

We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting the AD with the change described previously. Costs of Compliance

We estimate that this AD will affect 383 GE CF6–45 and CF6–50 series turbofan engines installed on airplanes of U.S. registry. We also estimate that it will take about 44 work hours per engine to perform the actions required by this AD, and that the average labor rate is $85 per work-hour. Required parts will cost about $11,000 per engine. Based on these figures, we estimate the total cost of this AD to U.S. operators to be $5,645,420. 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


### 14797 Federal Register / Vol. 76, No. 53 / Friday, March 18, 2011 / Rules and Regulations

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, 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) 2009–04–17, Amendment 39–15823 (74 FR 8735; February 26, 2009), and adding the following new AD: 2011–07–01 General Electric Company: Amendment 39–16638 ; Docket No. FAA–2006–24145; Directorate Identifier 2006–NE–06–AD.

Effective Date

(a) This airworthiness directive (AD) is effective April 22, 2011.

Affected ADs

(b) This AD supersedes AD 2009–04–17, Amendment 39–15823.
Applicability

(c) This AD applies to the following engines with a long fixed core exhaust nozzle (LFCEN) assembly forward centerbody, part number (P/N) 1313M55G01 or G02, P/N 9076M28G05, G06, G08, G09, or G10, P/N 9076M82G01 or G03, and aft centerbody P/ N 1313M56G01, or P/N 9076M46G02, G04, or G05, installed in:

(1) General Electric Company (GE) CF6– 45A, CF6–45A2, CF6–50A, CF6–50C, CF6– 50CA, CF6–50C1, CF6–50C2, CF6–50C2B, CF6–50C2D, CF6–50E, CF6–50E1, CF6–50E2, and CF6–50E2B turbofan engines, including engines marked on the engine data plate as CF6–50C2–F and CF6–50C2–R.

(2) These engines are installed on, but not limited to, Airbus A300 series, Boeing 747– 200B, 747–200C, 747–200F, 747–300 and 747SR, McDonnell Douglas DC–10–15, DC– 10–30, DC–10–30F (KC–10A, KDC–10), and MD–10–30F airplanes.

Unsafe Condition

(d) This AD was prompted by the discovery of more LFCEN forward and aft centerbody P/Ns that require replacement. We are issuing this AD to prevent the forward and aft centerbody of the LFCEN assembly from separating from the engine, causing damage to the engine, and damage to the airplane.
Compliance

(e) Comply with this AD within the compliance times specified, unless already done.

(1) Within 18 months after the effective date of this AD, replace forward centerbody, P/N 1313M55G01 and G02, P/N 9076M28G05, G06, G08, G09, and G10, P/N 9076M82G01 and G03, and aft centerbody P/N 1313M56G01, P/N 9076M46G02, G04, and G05 with a forward and aft centerbody that has been modified using the Accomplishment Instructions, Section 3, of GE Service Bulletin (SB) No. CF6–50 S/B 78– 0244, Revision 1, dated March 13, 2008, CF6–50 S/B 78–0244, dated July 30, 2007, or CF6–50 S/B 78–0242, dated September 26,
2005. Centerbody Installation Prohibition

(2) After 18 months from the effective date of this AD, do not install any engine with forward centerbody, P/N 1313M55G01 or G02, P/N 9076M28G05, G06, G08, G09, or G10, P/N 9076M82G01 or G03, or aft centerbody P/N 1313M56G01, P/N 9076M46G02, G04, or G05 on any airplane.
Alternative Methods of Compliance (AMOCs)

(f) The Manager, Engine Certification Office, FAA, may approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19.

Related Information

(g) For more information about this AD, contact Tomasz Rakowski, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate; phone: 781– 238–7735; fax: 781–238–7199; e-mail: tomasz.rakowski@faa.gov.

(h) For service information identified in this AD, contact GE–Aviation M/D Rm. 285, One Neumann Way, Cincinnati, OH 45215, telephone 513–552–3272; e-mail: geae.aoc@ge.com. You may review copies of the referenced service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125.

Issued in Burlington, Massachusetts, on March 14, 2011. Peter A. White, Acting Manager, Engine & Propeller Directorate, Aircraft Certification Service.
[FR Doc. 2011–6300 Filed 3–17–11; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2011–0176; Directorate Identifier 2011–NE–05–AD; Amendment 39–**  **16636; AD 2011–06–11]**

**RIN 2120–AA64**

**Airworthiness Directives; Rolls-Royce plc (RR) RB211–Trent 900 Series**  **Turbofan Engines**

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Final rule; request for
comments.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:

An uncontained engine failure has recently occurred on a Rolls-Royce RB211 Trent 900 involving release of high energy debris and resulting in damage to the aeroplane. Analysis of the available elements from the incident investigation shows that an oil fire in the High Pressure/Intermediate Pressure (HP/IP) structure cavity may have initiated a sequence of events leading to rupture of the drive arm of the IP Turbine (IPT) disc and subsequent overspeed and burst of that same disc. We are issuing this AD to prevent overspeed of the intermediate pressure turbine, which could result in loss of disc integrity, an uncontained failure of the engine, and damage to the airplane.

**DATES :**  This AD becomes effective April 4, 2011.

We must receive comments on this AD by April 18, 2011.

**ADDRESSES :**  You may send comments by any of the following methods:

• Federal eRulemaking Portal: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically.

• Mail: U.S. Department of Transportation, 1200 New Jersey