72348 Federal Register / Vol. 76, No. 226 / Wednesday, November 23, 2011 / Proposed Rules 

if so equipped. Before beginning the test, the 

conventional oven shall be at its normal 

nonoperating temperature as defined in 

section 1.8 and described in section 2.6. Set 

the conventional oven test block W1

approximately in the center of the usable 

baking space. If there is a selector switch for 

selecting the mode of operation of the oven, 

set it for normal baking. If an oven permits 

baking by either forced convection by using 

a fan, or without forced convection, the oven 

is to be tested in each of those two modes. 

The oven shall remain on for at least one 

complete thermostat ‘‘cut-off/cut-on’’ of the 

electrical resistance heaters or gas burners 

after the test block temperature has increased 

234 °F (130 °C) above its initial temperature. 

3.1.1.1 Self-cleaning operation of a 

conventional oven. Establish the test 

conditions set forth in section 2, ‘‘TEST 

CONDITIONS,’’ of this Appendix. Adjust any 

pilot lights of a conventional gas oven in 

accordance with the manufacturer’s 

instructions and turn off the gas flow to the 

conventional cooking top. The temperature of 

the conventional oven shall be its normal 

nonoperating temperature as defined in 

section 1.8 and described in section 2.6. 

Then set the conventional oven’s selfcleaning process in accordance with the 

manufacturer’s instructions. If the selfcleaning process is adjustable, use the 

average time recommended by the 

manufacturer for a moderately soiled oven. 

* * * * * 

3.1.2 Conventional cooking top. Establish 

the test conditions set forth in section 2, 

‘‘TEST CONDITIONS,’’ of this Appendix. 

Adjust any pilot lights of a conventional gas 

cooking top in accordance with the 

manufacturer’s instructions and turn off the 

gas flow to the conventional oven(s), if so 

equipped. The temperature of the 

conventional cooking top shall be its normal 

nonoperating temperature as defined in 

section 1.8 and described in section 2.6. Set 

the test block in the center of the surface unit 

under test. The small test block, W2, shall be 

used on electric surface units of 7 inches (178 

mm) or less in diameter. The large test block, 

W3, shall be used on electric surface units 

over 7 inches (177.8 mm) in diameter and on 

all gas surface units. Turn on the surface unit 

under test and set its energy input rate to the 

maximum setting. When the test block 

reaches 144 °F (80 °C) above its initial test 

block temperature, immediately reduce the 

energy input rate to 25 ± 5 percent of the 

maximum energy input rate. After 15 ± 0.1 

minutes at the reduced energy setting, turn 

off the surface unit under test. 

* * * * * 

3.1.3 Microwave oven. 

3.1.3.1 Microwave oven test standby 

mode and off mode power. Establish the 

testing conditions set forth in section 2, 

‘‘TEST CONDITIONS,’’ of this Appendix. For 

microwave ovens that drop from a higher 

power state to a lower power state as 

discussed in Section 5, Paragraph 5.1, Note 

1 of IEC 62301 (Second Edition) 

(incorporated by reference; see § 430.3), 

allow sufficient time for the microwave oven 

to reach the lower power state before 

proceeding with the test measurement. 

Follow the test procedure as specified in 

Section 5, Paragraph 5.3.2 of IEC 62301 

(Second Edition). For units in which power 

varies as a function of displayed time in 

standby mode, set the clock time to 3:23 and 

use the average power approach described in 

Section 5, Paragraph 5.3.2(a) of IEC 62301 

(First Edition), but with a single test period 

of 10 minutes +0/¥2 sec after an additional 

stabilization period until the clock time 

reaches 3:33. If a microwave oven is capable 

of operation in either standby mode or off 

mode, as defined in sections 1.13 and 1.9, 

respectively, or both, test the microwave 

oven in each mode in which it can operate. 

* * * * * 

3.2.3 Microwave oven test standby mode 

and off mode power. Make measurements as 

specified in Section 5, Paragraph 5.3 of IEC 

62301 (Second Edition) (incorporated by 

reference; see § 430.3). If the microwave oven 

is capable of operating in standby mode, 

measure the average standby mode power of 

the microwave oven, PSB, in watts as 

specified in section 3.1.3.1. If the microwave 

oven is capable of operating in off mode, 

measure the average off mode power of the 

microwave oven, POFF, as specified in section 

3.1.3.1. 

* * * * * 

3.3.13 Record the average standby mode 

power, PSB, for the microwave oven standby 

mode, as determined in section 3.2.3 for a 

microwave oven capable of operating in 

standby mode. Record the average off mode 

power, POFF, for the microwave oven off 

mode power test, as determined in section 

3.2.3 for a microwave oven capable of 

operating in off mode. 

* * * * * 

[FR Doc. 2011–30234 Filed 11–22–11; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1176; Directorate 

Identifier 2011–NE–35–AD] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for Pratt & 

Whitney JT9D–7R4D, –7R4D1, –7R4E, 

–7R4E1, –7R4G2, –7R4H1, and –7R4E4 

turbofan engines. This proposed AD 

would establish a new lower life limit 

for high-pressure turbine (HPT) 1st stage 

air seals, part number (P/N) 735907, and 

would require removing them from 

service using a drawdown schedule. 

This proposed AD was prompted by the 

determination that a new lower life 

limit for the HPT 1st stage air seals, 

P/N 735907, is necessary. We are 

proposing this AD to prevent critical 

life-limited rotating engine part failure 

and damage to the airplane. 

DATES: We must receive comments on 

this proposed AD by January 23, 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: 

Stephen Sheely, Aerospace Engineer, 

Engine & Propeller Directorate, FAA, 12 

New England Executive Park, 

Burlington, MA 01803; phone: (781) 

238–7750; fax: (781) 238–7199; email: 

stephen.k.sheely@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2011–1176; Directorate Identifier 2011– 

NE–35–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:// 

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Federal Register / Vol. 76, No. 226 / Wednesday, November 23, 2011 / Proposed Rules 72349 

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 

We received two reports of HPT 1st 

stage air seals, P/N 735907, found 

cracked by fluorescent penetrant 

inspection during engine overhaul. The 

cracks were located on the flat section 

of the seal, between the bolted flange 

and the knife edge seals. One of the air 

seals had accumulated 11,150 cyclessince-new (CSN), and the other air seal 

had accumulated 13,340 CSN. The 

current published life limit for these 

seals is 15,000 CSN. Pratt & Whitney has 

informed us that they are preparing to 

issue service information which will 

require reducing the published life limit 

from 15,000 CSN to 9,000 CSN. This 

condition, if not corrected, could result 

in critical life-limited rotating engine 

part failure and damage to the airplane. 

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 require 

establishing a new lower life limit for 

HPT 1st stage air seals, P/N 735907, 

from 15,000 CSN, to 9,000 CSN, and 

would require removing them from 

service using a drawdown schedule. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 257 Pratt & Whitney JT9D– 

7R4D, –7R4D1, –7R4E, –7R4E1, –7R4G2, 

–7R4H1, and –7R4E4 turbofan engines 

installed on airplanes of U.S. registry. 

We also estimate that it would take 

about 28.8 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 $37,200 per engine. Based on 

these figures, we estimate the total cost 

of the AD to U.S. operators to be 

$10,189,536. 

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 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 this 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, 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): 

Pratt & Whitney: Docket No. FAA–2011– 

1176; Directorate Identifier 2011–NE– 

35–AD. 

(a) Comments Due Date 

We must receive comments by January 23, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Pratt & Whitney JT9D– 

7R4D, –7R4D1, –7R4E, –7R4E1, –7R4G2, 

–7R4H1, and –7R4E4 turbofan engines. 

(d) Unsafe Condition 

This AD was prompted by the 

determination that a new lower life limit of 

9,000 cycles-since-new (CSN) for highpressure turbine (HPT) 1st stage air seals, 

part number (P/N) 735907, is necessary. We 

are issuing this AD to prevent critical lifelimited rotating engine part failure, and 

damage to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(f) Removal of HPT 1st Stage Air Seals, 

P/N 735907 

Remove HPT 1st stage air seals, P/N 

735907, from service as follows: 

(1) For air seals that have fewer than 6,500 

CSN on the effective date of this AD, remove 

from service before exceeding 9,000 CSN. 

(2) For air seals that have 6,500 CSN or 

more on the effective date of this AD, do the 

following: 

(i) If the engine has a shop visit before the 

air seal exceeds 9,000 CSN, remove the air 

seal from service before exceeding 9,000 

CSN. 

(ii) If the engine does not have a shop visit 

before the air seal exceeds 9,000 CSN, 

remove the air seal from service at the next 

shop visit, not to exceed 2,500 cycles from 

the effective date of this AD or 15,000 CSN, 

whichever occurs first. 

(3) Remove from service any HPT 1st stage 

air seal, P/N 735907, that is installed or reinstalled after the effective date of this AD, 

before the air seal exceeds the new life limit 

of 9,000 CSN. 

(g) Installation Prohibition 

After the effective date of this AD, do not 

install or reinstall into any engine any HPT 

1st stage air seal, P/N 735907, that exceeds 

the new life limit of 9,000 CSN. 

(h) Engine Shop Visit Definition 

For the purposes of this AD, an engine 

shop visit is the induction of an engine into 

the shop after the effective date of this AD, 

where the separation of a major engine flange 

occurs, except that the following 

maintenance actions, or any combination, are 

not considered engine shop visits: 

(1) Introduction of an engine into a shop 

solely for removal of the compressor top or 

bottom case for airfoil maintenance or 

variable stator vane bushing replacement. 

(2) Introduction of an engine into a shop 

solely for removal or replacement of the stage 

1 fan disk. 

(3) Introduction of an engine into a shop 

solely for replacement of the turbine rear 

frame. 

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(4) Introduction of an engine into a shop 

solely for replacement of the accessory 

gearbox or transfer gearbox, or both. 

(5) Introduction of an engine into a shop 

solely for replacement of the fan forward 

case. 

(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 Stephen Sheely, Aerospace Engineer, 

Engine & Propeller Directorate, FAA, 12 New 

England Executive Park, Burlington, MA 

01803; phone: (781) 238–7750; fax: (781) 

238–7199; email: stephen.k.sheely@faa.gov. 

Issued in Burlington, Massachusetts, on 

November 15, 2011. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–30137 Filed 11–22–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1253; Directorate 

Identifier 2011–NM–079–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Airbus Model A319, A320, and A321 

airplanes that would supersede an 

existing AD. This proposed 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: 

Several cases of corrosion of the Main 

Landing Gear (MLG) support Rib 5 fitting lug 

bores have been reported on A320 family 

aeroplanes. * * * If not detected, the 

cracking may lead to the complete failure of 

the fitting and thus could affect the structural 

integrity of the MLG installation. 

EASA AD 2007–0213 was issued to 

address this condition * * *. 

After that AD was issued, a case of Rib 5, 

ruptured at the 4 o’clock position, was 

discovered on an aeroplane on which the 

terminating action of EASA AD 2007–0213 

had already been embodied * * *. 

Investigation of that case revealed that 

corrosion damage and cracking that should 

have been removed by repair machining was 

below the level of detectability of the Non 

Destructive Test (NDT) technique that 

cleared the surfaces prior to bush 

installation. 

* * * * * 

The proposed AD would require actions 

that are intended to address the unsafe 

condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by January 9, 2012. 

ADDRESSES: You may send comments 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, between 

9 a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact Airbus, 

Airworthiness Office—EAS, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; email: 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, Washington. 

For information on the availability of 

this material at the FAA, call (425) 227– 

1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://www.regulations.

gov; or in person at the Docket 

Operations office 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 Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: (425) 

227–1405; fax: (425) 227–1149. 

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–2011–1253; Directorate Identifier 

2011–NM–079–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 based on 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 March 31, 2008, we issued AD 

2008–08–04, Amendment 39–15456 (73 

FR 19975, April 14, 2008). That AD 

required actions intended to address an 

unsafe condition on Airbus Model 

A318, A319, A320, and A321 airplanes. 

Since we issued AD 2008–08–04, 

Amendment 39–15456 (73 FR 19975, 

April 14, 2008), we have been advised 

that the existing AD is inadequate to 

address the unsafe condition. We have 

determined that certain airplanes need 

additional detailed inspections for 

cracks of the MLG support 5 fitting, and 

repair of any cracks found. The 

European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2011–0011, 

dated January 21, 2011 (referred to after 

this as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

Several cases of corrosion of the Main 

Landing Gear (MLG) support Rib 5 fitting lug 

bores have been reported on A320 family 

aeroplanes. In some instances, corrosion pits 

caused the cracking of the forward lug 

(sometimes through its complete thickness). 

If not detected, the cracking may lead to the 

complete failure of the fitting and thus could 

affect the structural integrity of the MLG 

installation. 

EASA AD 2007–0213 [dated August 7, 

2007, which corresponds to FAA AD 2008– 

08–04, Amendment 39–15456 (73 FR 19975, 

April 14, 2008)] was issued to address this 

condition and required a repetitive 

inspection program of the MLG support Rib 

5 fitting forward lugs and, as terminating 

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