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

TABLE 

### 1—C OMPLIANCE 

### T IMES

### —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 cracksof 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


## 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 wasprompted 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. 4bearing 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


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

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 (17 b -hydroxy-5 aandrostano[3,2-c]pyrazole) and methasterone (2 a ,17 a -dimethyl-5 aandrostan-17 b -ol-3-one). The Drug Enforcement Administration (DEA) believes that this action is necessary to prevent the abuse and trafficking of