Federal Register / Vol. 76, No. 226 / Wednesday, November 23, 2011 / Proposed Rules 72353 

TABLE 1—COMPLIANCE TIMES—Continued 

Airplanes Initial inspection Repetitive interval 

If the most recent inspection is an ultrasonic inspection done in accordance with paragraph (h) of this AD, inspect within 940 flight cycles after the most recent ultrasonic inspection.Within 940 flight cycles after an ultrasonic inspection. 

Model A321 airplanes ..................... If the most recent inspection is a detailed inspection done in accordance with paragraph (g) of this AD, inspect within 100 flight cycles 

after the most recent detailed inspection.

Within 100 flight cycles after a visual inspection. 

If the most recent inspection is an ultrasonic inspection done in accordance with paragraph (h) of this AD, inspect within 630 flight cycles after the most recent ultrasonic inspection.Within 630 flight cycles after an ultrasonic inspection. 

Corrective Action 

(l) If any cracking is found during any 

inspection required by paragraph (k) of this 

AD: Before further flight, repair or replace the 

cracked MLG fitting using a method 

approved by either the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, or the EASA (or 

its delegated agent). 

Rib Bushing Modification 

(m) Except for airplanes on which the 

actions specified in paragraph (j)(3) have 

been done: Within 60 months after May 19, 

2008, modify the rib bushings of the left and 

right MLG, by accomplishing all of the 

applicable actions specified in the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–57–1118, Revision 03, 

dated April 23, 2007; or Revision 04, dated 

June 4, 2008. Accomplishing this 

modification terminates the requirements of 

paragraphs (g) and (k) of this AD, and then 

the requirements of paragraph (o) of this AD 

must be done. 

Credit for Actions Done According to 

Previous Issue of Service Bulletin 

(n) Modifying the lugs of the support rib 

5 fitting of the left and right MLG is 

acceptable for compliance with the 

requirements of paragraph (m) of this AD if 

done before May 19, 2008, in accordance 

with one of the following service bulletins: 

Airbus Service Bulletin A320–57–1118, 

dated September 5, 2002; Revision 01, dated 

August 28, 2003; or Revision 02, dated 

August 2, 2006. 

NEW REQUIREMENTS OF THIS AD 

Post-Modification/Post-Repair Inspections 

(o) For airplanes on which the actions 

specified in paragraph (j)(1) or (j)(2) of this 

AD have been done: At the later of the times 

specified in paragraphs (o)(1) and (o)(2) of 

this AD, do a detailed inspection for cracks 

of the forward lug of each left-hand and righthand MLG support rib 5 fitting, in 

accordance with Airbus Service Bulletin 

A320–57A1166, dated January 12, 2011. 

Repeat the inspection thereafter at intervals 

not to exceed 500 flight cycles. 

(1) Within 2,000 flight cycles after 

accomplishing the modification specified in 

paragraph (j)(1) or (m) of this AD, or the 

repair specified in paragraph (j)(2) of this AD, 

as applicable. 

(2) Within 250 flight cycles after the 

effective date of this AD, without exceeding 

3 months after the effective date of this AD. 

(p) If any crack is detected during any 

inspection required by paragraph (o) of this 

AD: Before further flight, repair using a 

method approved by either the Manager, 

International Branch, ANM–116, FAA; or 

EASA (or its delegated agent). 

Optional Terminating Action 

(q) Replacement of a MLG support rib 5 

fitting at any position (LH or RH) as specified 

in paragraph (j)(3) of this AD terminates the 

requirements of this AD for the MLG support 

rib 5 fitting at that position. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: 

Although the MCAI or service information 

allows further flight after cracks are found 

during compliance with certain required 

actions, paragraphs (l) and (p) of this AD 

require repair or replacement before further 

flight. 

Other FAA AD Provisions 

(r) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

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. Information may be emailed to: 

9-ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. AMOCs approved previously in 

accordance with AD 2006–11–04, 

Amendment 39–14608 (71 FR 29578, May 23, 

2006), and AD 2008–08–04, Amendment 39– 

15456 (73 FR 19975, April 14, 2008), are not 

approved as AMOCs for the corresponding 

provisions of this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to ensure the product is airworthy before it 

is returned to service. 

Related Information 

(s) For related information, refer to MCAI 

EASA Airworthiness Directive 2011–0011, 

dated January 21, 2011; Airbus Service 

Bulletin A320–57–1118, Revision 03, dated 

April 23, 2007, Airbus Mandatory Service 

Bulletin A320–57–1118, Revision 04, dated 

June 4, 2008; Airbus Service Bulletin A320– 

57–1138, Revision 01, dated October 27, 

2006; Airbus A319 Structural Repair Manual 

(SRM), Paragraph 5.C., 57–26–13, Revision 

dated November 1, 2004; Airbus A320 SRM, 

Paragraph 5.D., 57–26–13, Revision dated 

November 1, 2004; Airbus A321 SRM, 

Paragraph 5.D., 57–26–13, Revision dated 

February 1, 2005; and Task 57–29–03–270– 

801–A–01, Inspection of the Gear Rib 

Forward and Aft Lug Attachment for the 

Main Gear, of Chapter 57, Wings, of the 

Airbus A318/A319/A320/A321 

Nondestructive Testing Manual, Revision 89, 

dated August 1, 2011. 

Issued in Renton, Washington, on 

November 14, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–30223 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–2011–1194; Directorate 

Identifier 2011–NE–36–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 all Pratt 

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72354 Federal Register / Vol. 76, No. 226 / Wednesday, November 23, 2011 / Proposed Rules 

& Whitney PW4050, PW4052, PW4056, 

PW4056(–3), PW4156, PW4060, 

PW4060(–3), PW4060A, PW4152, 

PW4152(–3), PW4156A, PW4158, 

PW4158(–3), PW4460, PW4460(–3), 

PW4462, and PW4462(–3) turbofan 

engines. This proposed AD was 

prompted by reports of five engine inflight shutdowns and seven unplanned 

engine removals. This proposed AD 

would require inspections, cleaning, 

and engine modifications to address 

coking in the No. 4 bearing 

compartment and oil pressure and 

scavenge tubes. We are proposing this 

AD to prevent an engine fire, a fractured 

fan drive shaft, 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. 

For service information identified in 

this proposed AD, contact Pratt & 

Whitney, 400 Main St., East Hartford, 

CT 06108; phone: (860) 565–8770; fax: 

(860) 565–4503. 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 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– 

2011–1194; Directorate Identifier 2011– 

NE–36–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:// 

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 reports of five engine inflight shutdowns and seven unplanned 

engine removals due to clogging of No. 

4 bearing compartment oil pressure and 

scavenge tubes. Investigation has 

revealed that following all engine 

shutdowns, excessive heat is conducting 

into the No. 4 bearing compartment and 

into the oil pressure and scavenge tubes 

that pass through the turbine exhaust 

case struts. This excessive heat causes 

oil coking and oil flow restriction in the 

pressure and scavenge tubes and oil 

nozzle. This condition, if not corrected, 

could lead to an engine fire, a fractured 

fan drive shaft, and damage to the 

airplane. 

Relevant Service Information 

We reviewed Pratt & Whitney Alert 

Service Bulletin (SB) No. PW4ENG– 

A72–436, Revision 6, dated September 

30, 1999. The SB describes procedures 

for initial and repetitive inspection and 

cleaning of the No. 4 bearing 

compartment. We also reviewed Pratt & 

Whitney SB No. PW4ENG–72–472, 

Revision 5, dated April 14, 1998, and SB 

No. PW4ENG–79–76, Revision 4, dated 

February 14, 2002. The SBs describe 

procedures for modifications to stop 

buildup of coking in the No. 4 bearing 

compartment, and for rerouting of the 

No. 4 bearing pressure and scavenge 

tubes. The rerouted tubes are then 

located below the engine centerline 

which eliminates the coking problem. 

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 

accomplishing the actions specified in 

the service information described 

previously. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 44 Pratt & Whitney 

PW4050, PW4052, PW4056, PW4056(– 

3), PW4156, PW4060, PW4060(–3), 

PW4060A, PW4152, PW4152(–3), 

PW4156A, PW4158, PW4158(–3), 

PW4460, PW4460(–3), PW4462, and 

PW4462(–3) turbofan engines installed 

on airplanes of U.S. registry. We also 

estimate that it would take about 8 

work-hours per engine to perform an 

inspection and cleaning of the No. 4 

bearing compartment, about 7 workhours per engine to perform the 

modification to stop buildup of coking 

in the No. 4 bearing compartment, and 

about 33.7 work-hours per engine to 

perform the rerouting of the No. 4 

bearing pressure and scavenge tubes. 

The average labor rate is $85 per workhour. Required parts would cost about 

$69,322 per engine. Based on these 

figures, we estimate the total cost of the 

AD to U.S. operators to be $3,232,306. 

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 

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Federal Register / Vol. 76, No. 226 / Wednesday, November 23, 2011 / Proposed Rules 72355 

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– 

1194; Directorate Identifier 2011–NE– 

36–AD. 

(a) Comments Due Date 

We must receive comments by January 23, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Pratt & Whitney 

PW4050, PW4052, PW4056, PW4056(–3), 

PW4156, PW4060, PW4060(–3), PW4060A, 

PW4152, PW4152(–3), PW4156A, PW4158, 

PW4158(–3), PW4460, PW4460(–3), PW4462, 

and PW4462(–3) turbofan engines. 

(d) Unsafe Condition 

This AD was prompted by reports of five 

engine in-flight shutdowns and seven 

unplanned engine removals due to clogging 

of No. 4 bearing compartment oil pressure 

and scavenge tubes. We are issuing this AD 

to prevent an engine fire, a fractured fan 

drive shaft, and damage to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(f) Inspection and Cleaning of No. 4 Bearing 

Compartment for Coking 

(1) Within 1,000 cycles-in-service (CIS) 

after the effective date of this AD, initially 

inspect and clean the No. 4 bearing 

compartment in accordance with 

Accomplishment Instructions, paragraphs 

2.A. through 2.A.(4)(b)3 of Pratt & Whitney 

Alert Service Bulletin No. PW4ENG–A72– 

436, Revision 6, dated September 30, 1999. 

(2) Thereafter, within every additional 

1,000 CIS, perform the inspection and 

cleaning specified in paragraph (f)(1) of this 

AD. 

(g) Modification To Stop Buildup of Coking 

in the No. 4 Bearing Compartment 

(1) At the next engine visit to a 

maintenance facility that is capable of 

performing the following on-wing method or 

in-shop method of modification to the No. 4 

bearing compartment, but not to exceed 5 

years after the effective date of this AD, do 

the following: 

(i) Replace the No. 4 bearing packing 

transfer tube assembly; 

(ii) Replace the No. 4 bearing internal 

scavenge tube assembly; 

(iii) Remove the No. 4 bearing shield, and 

the No. 4 bearing shield option; and 

(iv) Install new No. 4 bearing shield 

options. 

(2) For doing the on-wing method of the 

modification, do the work in accordance with 

Accomplishment Instructions, Paragraphs 

2.A. through 2.A.(9)(a)3d of Pratt & Whitney 

Service Bulletin (SB) No. PW4ENG–72–472, 

Revision 5, dated April 14, 1998. 

(3) For doing the in-shop method of the 

modification, do the work in accordance with 

Paragraphs 2.B. through 2.B.(2)(f)2d of Pratt 

& Whitney SB No. PW4ENG–72–472, 

Revision 5, dated April 14, 1998. 

(h) Rerouting of the No. 4 Bearing Pressure 

and Scavenge Tubes 

(1) At the next shop visit at which the 

engine is sufficiently disassembled to 

perform the rerouting, but not to exceed 5 

years after the effective date of this AD, do 

the following: 

(i) Modify the turbine exhaust case to 

relocate the No. 4 bearing pressure and 

scavenge tube ports; 

(ii) Replace the internal No. 4 bearing 

pressure and scavenge tubes; 

(iii) Modify or replace the turbine case 

cooling brackets to support the new No. 4 

bearing pressure and scavenge tubes; 

(iv) Replace the turbine case manifolds as 

necessary; and 

(v) Install the new brackets and clamps to 

support the new routing configuration. 

(2) Do the work specified in paragraph (h) 

of this AD in accordance with 

Accomplishment Instructions paragraph 2 of 

Pratt & Whitney SB No. PW4ENG–79–76, 

Revision 4, dated February 14, 2002. 

(i) Terminating Action to the Repetitive 

Inspections and Cleaning 

Performing the modifications specified in 

both paragraphs (g) and (h), of this AD is 

terminating action to the repetitive 

inspections and cleanings specified in 

paragraph (f)(2) of this AD. 

(j) 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. 

(k) Related Information 

(1) 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. 

(2) For service information identified in 

this AD, contact Pratt & Whitney, 400 Main 

St., East Hartford, CT 06108; telephone: (860) 

565–8770; fax: (860) 565–4503. 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 

November 15, 2011. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–30138 Filed 11–22–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF JUSTICE 

Drug Enforcement Administration 

21 CFR Part 1300 

[Docket No. DEA–341P] 

RIN 1117–AB31 

Classification of Two Steroids, 

Prostanozol and Methasterone, as 

Schedule III Anabolic Steroids Under 

the Controlled Substances Act 

AGENCY: Drug Enforcement 

Administration (DEA), Department of 

Justice. 

ACTION: Notice of proposed rulemaking. 

SUMMARY: This Notice of Proposed 

Rulemaking (NPRM) proposes to 

classify the following two steroids as 

‘‘anabolic steroids’’ under the 

Controlled Substances Act (CSA): 

prostanozol (17b-hydroxy-5aandrostano[3,2-c]pyrazole) and 

methasterone (2a,17a-dimethyl-5aandrostan-17b-ol-3-one). The Drug 

Enforcement Administration (DEA) 

believes that this action is necessary to 

prevent the abuse and trafficking of 

mstockstill on DSK4VPTVN1PROD with PROPOSALS