### 5710 Federal Register / Vol. 78, No. 18 / Monday, January 28, 2013 / Rules and Regulations

amends chapter I of Title 14, Code of Federal Regulations as follows:

**PART 121—OPERATING REQUIREMENTS: DOMESTIC, FLAG,**  **AND SUPPLEMENTAL OPERATIONS**

■ 1. The authority citation for part 121 continues to read as follows:

Authority: 49 U.S.C. 106(g), 1153, 40113, 40119, 41706, 44101, 44701–44702, 44705, 44709–44711, 44713, 44716–44717, 44722, 44901, 44903–44904, 44912, 46105.
**Subpart DD—Special Federal Aviation Regulations** 

■ 2. Revise § 121.1500 to read as follows:

**§ 121.1500 SFAR No. 111—Lavatory Oxygen Systems.** 

(a) Applicability. This SFAR applies to the following persons:

(1) All operators of transport category airplanes that are required to comply with AD 2012–11–09, but only for airplanes on which the actions required by that AD have not been accomplished.

(2) Applicants for airworthiness certificates.

(3) Holders of production certificates. (4) Applicants for type certificates, including changes to type certificates.

(b) Regulatory relief. Except as noted in paragraph (d) of this section and contrary provisions of 14 CFR part 21, and 14 CFR 25.1447, 119.51, 121.329, 121.333 and 129.13, notwithstanding, for the duration of this SFAR:

(1) A person described in paragraph (a) of this section may conduct flight operations and add airplanes to operations specifications with disabled lavatory oxygen systems, modified in accordance with FAA Airworthiness Directive 2011–04–09, subject to the following limitations:

(i) This relief is limited to regulatory compliance of lavatory oxygen systems.

(ii) Within 30 days of March 29, 2013, all oxygen masks must be removed from affected lavatories, and the mask stowage location must be reclosed.

(iii) Within 60 days of March 29, 2013 each affected operator must verify that crew emergency procedures specifically include a visual check of the lavatory as a priority when checking the cabin following any event where oxygen masks were deployed in the cabin.

(2) An applicant for an airworthiness certificate may obtain an airworthiness certificate for airplanes to be operated by a person described in paragraph (a) of this section, although the airplane lavatory oxygen system is disabled.

(3) A holder of a production certificate may apply for an airworthiness certificate or approval for airplanes to be operated by a person described in paragraph (a) of this section.

(4) An applicant for a type certificate or change to a type certificate may obtain a design approval without showing compliance with § 25.1447(c)(1) of this chapter for lavatory oxygen systems, in accordance with this SFAR.

(5) Each person covered by paragraph (a) of this section may inform passengers that the lavatories are not equipped with supplemental oxygen.

(c) Return to service documentation. When a person described in paragraph (a) of this section has modified airplanes as required by Airworthiness Directive 2011–04–09, the affected airplanes must be returned to service with a note in the airplane maintenance records that the modification was done under the provisions of this SFAR.

(d) Expiration. This SFAR expires on September 10, 2015, except this SFAR will continue to apply to any airplane for which the FAA approves an extension of the AD compliance time for the duration of the extension.

Issued in Washington, DC, on January 18,
2013. Michael P. Huerta,
Administrator.
[FR Doc. 2013–01695 Filed 1–25–13; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2012–1293; Directorate Identifier 2012–NE–45–AD; Amendment 39–**  **17327; AD 2013–02–06]**

**RIN 2120–AA64**

**Airworthiness Directives; Engine Alliance Turbofan Engines** 

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

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

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for all Engine Alliance GP7270 and GP7277 turbofan engines. This AD requires initial and repetitive borescope inspections and removal from service before further flight if one or more burnholes are detected, in certain highpressure turbine (HPT) stage 2 nozzles. This AD also requires mandatory removal from service of these HPT stage 2 nozzles at the next engine shop visit. This AD was prompted by a report received of inadequate cooling of the HPT stage 2 nozzle, leading to damage to the HPT stage 2 nozzle, burn-through of the turbine case, and engine shutdown. We are issuing this AD to prevent HPT stage 2 nozzle failure, leading to uncontrolled fire, engine shutdown, and damage to the airplane.

**DATES :**  This AD is effective February 12,
2013.

We must receive comments on this AD by March 14, 2013.

**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: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590, 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 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 :**  Martin Adler, Aerospace Engineer, Engine & Propeller Directorate, FAA, 12 New England Executive Park, Burlington, MA 01803; phone: 781– 238–7157; fax: 781–238–7199; email: martin.adler@faa.gov

. **SUPPLEMENTARY INFORMATION :** 

Discussion

We received a report of an engineshutdown and turbine case burnthrough, preceded by exceedance of the engine exhaust gas temperature (EGT) limit and loss of engine oil. Investigation revealed that the event was caused by damage to the HPT stage 2 nozzle due to inadequate part cooling. HPT stage 2 nozzles, part numbers (P/ Ns) 2101M24G01, 2101M24G02, and 2101M24G03, are identified as having


### 5711 Federal Register / Vol. 78, No. 18 / Monday, January 28, 2013 / Rules and Regulations

the inadequate cooling design. This condition, if not corrected, could result in HPT stage 2 nozzle failure, leading to uncontrolled fire, engine shutdown, and damage to the airplane.

FAA’s Determination

We are issuing 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.
AD Requirements

This AD requires initial and repetitive borescope inspections and removal from service before further flight if burn holes are detected, in HPT stage 2 nozzles, P/Ns 2101M24G01, 2101M24G02, and 2101M24G03. This AD also requires mandatory removal from service of these HPT stage 2 nozzles at the next engine shop visit.
FAA’s Justification and Determination of the Effective Date

No domestic operators use this product. Therefore, we find that notice and opportunity for prior public comment are unnecessary, and that good cause exists for making this amendment effective in less than 30 days.

Comments Invited

This AD is a final rule that involves requirements affecting flight safety and was not preceded by notice and an opportunity for public comment. However, we invite you to send any written data, views, or arguments about this AD. Send your comments to an address listed under the **ADDRESSES** section. Include the Docket Number FAA–2012–1293 and Directorate Identifier 2012–NE–45–AD at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this 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 AD. Costs of Compliance

We estimate that this AD will affect no engines installed on airplanes of U.S. registry. We also estimate that it would take about two hours per engine to perform a borescope inspection of the HPT stage 2 nozzle. The average labor rate is $85 per work hour. Required parts would cost about $487,312 per engine. Based on these figures, we estimate the cost of this proposed AD to U.S. operators to be $0. 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 to the extent that it justifies making a regulatory distinction, 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):
2013–02–06 Engine Alliance: Amendment 39–17327; Docket No. FAA–2012–1293; Directorate Identifier 2012–NE–45–AD.

(a) Effective Date

This AD is effective February 12, 2013.

(b) Affected ADs

None. (c) Applicability

This AD applies to all Engine Alliance GP7270 and GP7277 turbofan engines with a high-pressure turbine (HPT) stage 2 nozzle, part number (P/N) 2101M24G01, 2101M24G02, or 2101M24G03, installed.

(d) Unsafe Condition

This AD was prompted by a report received of inadequate cooling of the HPT stage 2 nozzle, leading to damage to the HPT stage 2 nozzle, burn-through of the turbine case, and engine shutdown. Investigation revealed that the event was caused by damage to the HPT stage 2 nozzle due to inadequate part cooling. We are issuing this AD to prevent HPT stage 2 nozzle failure, leading to uncontrolled fire, engine shutdown, and damage to the airplane.
(e) Compliance

Comply with this AD within the compliance times specified, unless already done.
(f) Borescope Inspections of the HPT Stage 2 Nozzle

(1) Initially borescope inspect (360 degrees) the HPT stage 2 nozzle at the following:

(i) Before accumulating 1,500 cycles-sincenew (CSN), if the nozzle has fewer than 1,450 CSN on the effective date of this AD.

(ii) Within the next 50 cycles, if the nozzle has 1,450 or more CSN on the effective date of this AD.

(2) Thereafter, repetitively borescope inspect (360 degrees) the HPT stage 2 nozzle within every 100 additional cycles-in-service.

(3) If during any inspection required by this AD, any burn holes are detected through the surface of the nozzle, remove the nozzle from service before further flight.
(g) Mandatory Removal From Service of the HPT Stage 2 Nozzles

At the next engine shop visit, remove HPT stage 2 nozzles P/N 2101M24G01, 2101M24G02, and 2101M24G03 from service.

(h) Definition

For the purpose of this AD, an ‘‘engine shop visit’’ is the induction of an engine into the shop for maintenance involving the separation of pairs of major mating engine


### 5712 Federal Register / Vol. 78, No. 18 / Monday, January 28, 2013 / Rules and Regulations

flanges except that the separation of engine flanges solely for the purposes of transportation without subsequent engine maintenance does not constitute an engine shop visit.
(i) Alternative Methods of Compliance (AMOCs)

The Manager, Engine Certification Office, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. (j) Related Information

For more information about this AD, contact Martin Adler, Aerospace Engineer, Engine & Propeller Directorate, FAA, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7157; fax: 781–238– 7199; email: martin.adler@faa.gov

. (k) Material Incorporated by Reference

None. Issued in Burlington, Massachusetts, on January 15, 2013. Thomas A. Boudreau, Acting Manager, Engine & Propeller Directorate, Aircraft Certification Service.
[FR Doc. 2013–01552 Filed 1–25–13; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2012–1289; Directorate Identifier 2012–NE–43–AD; Amendment 39–**  **17323; AD 2013–02–02]**

**RIN 2120–AA64**

**Airworthiness Directives; CFM International, S.A. Turbofan Engines**  **Modified by Supplemental Type Certificate SE00034EN** 

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

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

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for CFM International, S.A. CFM56–3, CFM56– 3B, and CFM56–3C turbofan engines. This AD requires removal from service of certain high-pressure turbine (HPT) disks manufactured by Global Material Solutions of Pratt & Whitney, at reduced maximum life limits. This AD was prompted by a report of a forging process error during manufacture of these HPT disks. We are issuing this AD to prevent uncontained release of multiple turbine blades, damage to the engine, and damage to the airplane.

**DATES :**  This AD is effective January 28,
2013.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of January 28, 2013.

We must receive comments on this AD by March 14, 2013.

**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: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this AD, contact Pratt & Whitney, 400 Main St., East Hartford, CT 06108; phone: 860–565–7700; fax: 860–565– 1605. You may view this 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 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 :**  Kenneth Steeves, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7765; fax: 781–238– 7199; email: kenneth.steeves@faa.gov

. **SUPPLEMENTARY INFORMATION :** 

Discussion

We received a report from Global Material Solutions of Pratt & Whitney, of a forging process error that occurred during manufacture of HPT disks, part number (P/N) 880026, serial numbers (S/Ns) GLKBAA9307, GLKBAA9335, GLKBAA9404, GLKBAA9407, and GLKBAA9409. During the last forging operation of the manufacturing process, the forging temperature at the disk rim was incorrect. This resulted in below allowable creep properties of the HPT disk, which reduced the calculated maximum life limits. This condition, if not corrected, could result in uncontained release of multiple turbine blades, damage to the engine, and damage to the airplane.

FAA’s Determination

We are issuing 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.
AD Requirements

This AD requires removal of the affected HPT disks at reduced maximum life limits, as follows:

• For CFM56–3, CFM56–3B and CFM56–3C turbofan engines operating to 20,100 lbs maximum takeoff (MTO) thrust, remove the HPT disk on orbefore accumulating 8,000 cycles-sincenew (CSN).

• For CFM56–3B and CFM56–3C turbofan engines operating to 22,100 lbs MTO thrust, remove the HPT disk on or before accumulating 8,000 CSN.

• For CFM56–3C turbofan engines operating to 23,500 lbs MTO thrust, remove the HPT disk on or before accumulating 4,000 CSN.

• For HPT disks that have been used in multiple models or thrust installations, the formula in the ADDED DATA section of Pratt & Whitney Special Instruction 6F–12 dated December 21, 2012 must be used to calculate the remaining life on the disk.
FAA’s Justification and Determination of the Effective Date

No domestic operators use this product. Therefore, we find that notice and opportunity for prior public comment are unnecessary and that good cause exists for making this amendment effective in less than 30 days. Accordingly, this AD is effective upon publication.

Comments Invited

This AD is a final rule that involves requirements affecting flight safety and was not preceded by notice and an opportunity for public comment. However, we invite you to send any written data, views, or arguments about this AD. Send your comments to an address listed under the **ADDRESSES** section. Include ‘‘Docket Number FAA– 2012–1289; Directorate Identifier 2012– NE–43–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory,