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 burn 

holes 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 engine 

shutdown 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 


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

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 


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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 or 

before 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, 


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