### 52215 Federal Register / Vol. 76, No. 162 / Monday, August 22, 2011 / Rules and Regulations

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 adding the following new airworthiness directive (AD):
2011–18–01 General Electric Company: Amendment 39–16783; Docket No. FAA–2010–0998; Directorate Identifier
2010–NE–29–AD.

Effective Date

(a) This AD is effective September 26,

2011. Affected ADs
(b) None.
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, CF6–50E, CF6–50E1, and CF6–50E2 series turbofan engines, including engines marked on the engine data plate as CF6–50C2–F and CF6– 50C2–R, with a low-pressure turbine (LPT) rotor stage 3 disk that has a part number (P/ N) listed in Table 1 of this AD installed.



### TABLE 

### 1—LPT ROTOR 

### STAGE 

### 3 D ISK 

### P/N S

1473M90P01 1473M90P02 1473M90P03 1473M90P04 1479M75P01 1479M75P02 1479M75P03 1479M75P04 1479M75P05 1479M75P06 1479M75P07 1479M75P08 1479M75P09 1479M75P11 1479M75P13 1479M75P14 9061M23P06 9061M23P07 9061M23P08 9061M23P09 9061M23P10 9061M23P12 9061M23P14 9061M23P15 9061M23P16 9224M75P01

Unsafe Condition

(d) This AD results from seven 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. We are issuing this AD to prevent LPT rotor separation, 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 at each shop visit after the effective date of this AD, at which the LPT module assembly is separated from the engine.
Initial Inspection

(f) At the next shop visit after the effectivedate of this AD, clean and fluorescentpenetrant inspect the LPT rotor stage 3 disk forward spacer arm, including the use of a wet-abrasive blast to eliminate residual or background fluorescence before inspecting. You can find guidance on cleaning the disk and performing the FPI in the CF6–50 Engine Manual, GEK 50481 72–57–02.
Repetitive Inspection

(g) Thereafter, clean and inspect the LPT rotor stage 3 disk forward spacer arm, as specified in paragraph (f) of this AD, at each engine shop visit that occurs after 1,000 cycles since the last FPI of the LPT rotor stage 3 disk forward spacer arm.

(h) If a crack or a band of fluorescence is present, remove the disk from service.

Definitions

(i) For the purpose of this AD: (1) The LPT module assembly is defined as consisting of turbine mid-frame, LPT stage 1 nozzle, LPT stator cases and vanes, LPT rotor, and turbine rear frame.

(2) An engine shop visit is the induction of an engine into the shop for maintenance involving the separation of the turbine midframe forward flange from the compressor rear frame aft flange, except that the separation of these engine flanges solely for the purposes of transportation without subsequent engine maintenance does not constitute an engine shop visit.
Alternative Methods of Compliance

(j) 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

(k) 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; e-mail: tomasz.rakowski@faa.gov.
Material Incorporated by Reference

(l) None. Issued in Burlington, Massachusetts on August 15, 2011. Peter A. White, Manager, Engine & Propeller Directorate, Aircraft Certification Service.
[FR Doc. 2011–21312 Filed 8–19–11; 8:45 am]

**BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION** 

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2011–0187; Directorate Identifier 2011–NE–07–AD; Amendment 39–**  **16784; AD 2011–18–02]**

**RIN 2120–AA64**

**Airworthiness Directives; General Electric Company CF34–10E2A1;**  **CF34–10E5; CF34–10E5A1; CF34– 10E6; CF34–10E6A1; CF34–10E7; and**  **CF34–10E7–B Turbofan Engines**

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

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for the products listed above with certain part number (P/N) fan rotor spinners installed. This AD requires removing from service certain fan rotor blade retainers, and removing from service the fan rotor spinner support that was installed with those fan rotor blade retainers. This AD was prompted by a fan rotor spinner support found cracked at the attachment lugs. We are issuing this AD to prevent high-cycle fatigue cracking of the fan rotor spinner support attachment lugs, leading to separation of the fan rotor spinner assembly, uncontained failure of the engine, and damage to the airplane.

**DATES :**  This AD is effective September 26, 2011.


### 52216 Federal Register / Vol. 76, No. 162 / Monday, August 22, 2011 / Rules and Regulations

**ADDRESSES :**  For service information identified in this AD, contact GE– Aviation, M/D Rm. 285, One Neumann Way, Cincinnati, OH 45215, phone: 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 :**  John Frost, Aerospace Engineer, Engine Certification Office, FAA, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7756; fax: 781– 238–7199; e-mail: john.frost@faa.gov.

**SUPPLEMENTARY INFORMATION :** 

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM published in the Federal Register on May 11, 2011 (76 FR 27282). Investigation of a General Electric Company CF34–10E turbofan engine experiencing high fan frame vibrations led to removal of the fan rotor spinner. Eight of the twelve attachment lugs on the fan rotor spinner support were found cracked. The cause of thevibration was determined to be a nonsynchronous vibration induced by a spinner redesign that removed an interference between the fan blade retainers and the spinner. That NPRM proposed to require removing from service certain fan rotor blade retainers, and removing from service the fan rotor spinner support that was installed with those fan rotor blade retainers. We are issuing this AD to prevent high-cycle fatigue cracking of the fan rotor spinner support attachment lugs, leading to separation of the fan rotor spinner assembly, uncontained failure of the engine, and damage to the airplane. Comments We gave the public the opportunity to participate in developing this AD. We received one comment which is presented below. Request for Compliance Clarification

One commenter, Regionla Compagnie Aerienne Europeene, requests that we clarify the AD as to what parts are allowed to be reinstalled when affected parts are removed for either scheduled or unscheduled maintenance before the AD compliance time is reached.

We do not agree. When the affected parts are removed from the engine, paragraphs (h) and (i) of this AD are clear that those parts are not to bereinstalled into the engine. Any FAAapproved part except those prohibited by paragraphs (h) and (i), is eligible for installation. We did not change the AD.

Conclusion

We reviewed the relevant data, considered the comment 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 164 engines installed on airplanes of U.S. registry. We also estimate that it will take about 2 work-hours per engine to perform the actions required by this AD, and that the average labor rate is $85 per work-hour. If all removed parts get replaced, required parts will cost about $10,458 per engine. Based on these figures, we estimate the total cost of the AD to U.S. operators to be $1,742,992. 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
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 adding the following new airworthiness directive (AD): 2011–18–02 General Electric Company: Amendment 39–16784 ; Docket No. FAA–2011–0187; Directorate Identifier 2011–NE–07–AD.

Effective Date

(a) This AD is effective September 26,
2011.

Affected ADs

(b) None. Applicability

(c) This AD applies to General Electric Company (GE) CF34–10E2A1; CF34–10E5; CF34–10E5A1; CF34–10E6; CF34–10E6A1; CF34–10E7; and CF34–10E7–B turbofan engines, with a fan rotor spinner part number (P/N) 2050M34G03; 2050M34G04; 2050M34G05; 2050M34G06; 2437M60G01; or 2437M60G02, installed.

Unsafe Condition

(d) This AD was prompted by a fan rotor spinner support found cracked at the


### 52217 Federal Register / Vol. 76, No. 162 / Monday, August 22, 2011 / Rules and Regulations

attachment lugs. We are issuing this AD to prevent high-cycle fatigue cracking of the fan rotor spinner support attachment lugs, leading to separation of the fan rotor spinner assembly, uncontained failure of the engine, and damage to the airplane.
Compliance

(e) Comply with this AD within 1,800 hours-in-service after the effective date of this AD, unless already done.

Removal of Fan Rotor Blade Retainers

(f) Remove from service the 24 fan rotor blade retainers, P/N 2050M56P02.
Removal of Fan Rotor Spinner Support

(g) Remove from service the fan rotor spinner support that operated with the fan rotor blade retainers removed in paragraph (f) of this AD.

Installation Prohibition

(h) After the effective date of this AD, do not install any fan rotor blade retainer, P/N 2050M56P02, into any engine. Do notattempt to repair, make serviceable, or reinstall, this part.

(i) After the effective date of this AD, do not install any fan rotor spinner support removed in paragraph (g) of this AD, into any engine. Do not attempt to repair, make serviceable, or re-install, this part.
Alternative Methods of Compliance (AMOCs)

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

Related Information

(k) For more information about this AD, contact John Frost, Aerospace Engineer, Engine Certification Office, FAA, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7756; fax: 781–238– 7199; e-mail: john.frost@faa.gov.

(l) Refer to GE Service Bulletin No. CF34– 10E S/B 72–0186, for related information. Contact GE–Aviation, M/D Rm. 285, One Neumann Way, Cincinnati, OH 45215, phone: 513–552–3272; e-mail: geae.aoc@ge.com, for a copy of this service information. 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 August 15, 2011. Peter A. White, Manager, Engine & Propeller Directorate, Aircraft Certification Service.
[FR Doc. 2011–21313 Filed 8–19–11; 8:45 am]

**BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION** 

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2011–0385; Directorate Identifier 2010–NM–256–AD; Amendment**  **39–16780; AD 2011–17–16]**

**RIN 2120–AA64**

**Airworthiness Directives; Airbus Model A330–200, A330–300, A340–300, A340–**  **500, and A340–600 Series Airplanes**

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

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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:

During a Back-up Control Module (BCM) retrofit campaign * * *, some BCMs have been found with loose gyrometer screws.

* * * When the aeroplane is in control back up configuration (considered to be an extremely remote case), an oscillation of the BCM output order may cause degradation of the BCM piloting laws, potentially leading to erratic motion of the rudder and possible subsequent impact on the Dutch Roll, which constitutes an unsafe condition.
* * * * *

* * * [S]everal Pedal Feel Trim Units (PFTU) have been found with loose or broken screws during the accomplishment of maintenance tasks on A330 fitted with electrical rudder and A340–600. The loose or failed screws could lead to the loss of the coupling between the Rotary Variable Differential Transducer (RVDT) shaft and the PFTU shaft, and consequently to a potential rudder runaway when the BCM is activated.
* * * * *

The unsafe condition is loss of control of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.

**DATES :**  This AD becomes effective September 26, 2011.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of September 26, 2011.

**ADDRESSES :**  You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. **FOR FURTHER INFORMATION CONTACT :**  Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1138; fax (425) 227–1149.

**SUPPLEMENTARY INFORMATION :** 

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on April 26, 2011 (76 FR 23218). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states:

During a Back-up Control Module (BCM) retrofit campaign in accordance with [European Aviation Safety Agency] (EASA) AD 2006–0313 requirements, some BCMs have been found with loose gyrometer

screws.

The gyrometer is installed on the DELRIN plate by internal screws and the DELRIN plate is installed on BCM casing by external

screws.

Investigations done by the BCM manufacturer SAGEM have shown that the root cause of these events is a lack of design robustness of the BCM[.] When the aeroplane is in control back up configuration (considered to be an extremely remote case), an oscillation of the BCM output order may cause degradation of the BCM piloting laws, potentially leading to erratic motion of the rudder and possible subsequent impact on the Dutch Roll, which constitutes an unsafe condition.

EASA AD 2008–0131 was issued to prohibit aeroplane dispatch with FCPC3 [flight control primary computer] inoperative (from GO IF to NO GO) as an interim solution, limited to A330 and A340–300 fitted with electrical rudder.

After EASA AD 2008–0131 issuance, several Pedal Feel Trim Units (PFTU) have been found with loose or broken screws during the accomplishment of maintenance tasks on A330 fitted with electrical rudder and A340–600. The loose or failed screws could lead to the loss of the coupling between the Rotary Variable Differential Transducer (RVDT) shaft and the PFTU shaft, and consequently to a potential rudder runaway when the BCM is activated.

EASA AD 2009–0153 retained the requirements of EASA AD 2008–0131 and extended the applicability to A340–500/600 aeroplanes.

This [EASA] AD, which supersedes EASA AD 2009–0153 retaining its requirements, requires the installation of:
—a new BCM on A330 and A340–200/–300 series aeroplanes fitted with electrical rudder, and —an improved PFTU on A330 and A340– 200/–300 series aeroplanes fitted with an electrical rudder and A340–500/&600 series aeroplanes,