Federal Register / Vol. 78, No. 93 / Tuesday, May 14, 2013 / Proposed Rules 28161 

of the service information identified in 

paragraphs (c)(2)(i), (c)(2)(ii), (c)(2)(iii), 

(c)(2)(iv), and (c)(2)(v) of this AD. 

(i) Airbus Service Bulletin A300–53–6111, 

dated February 4, 1999. 

(ii) Airbus Service Bulletin A300–53–6111, 

Revision 01, dated March 17, 2003. 

(iii) Airbus Service Bulletin A300–53– 

6111, Revision 02, dated September 13, 2004. 

(iv) Airbus Service Bulletin A300–53– 

6111, Revision 03, dated September 30, 2009. 

(v) Airbus Mandatory Service Bulletin 

A300–53–6111, Revision 04, dated August 

25, 2011. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by a report that 

cracking was found in area 2 of the frame 

base fittings between frame 41 and frame 46. 

We are issuing this AD to detect and correct 

cracking in area 2 of the frame base fittings 

between frame 41 and frame 46, which could 

adversely affect the structural integrity of the 

airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Maintenance Records Check and Frame 

Base Fitting Inspection 

Within 1,000 flight hours after the effective 

date of this AD: Check the airplane 

maintenance records to determine if repairs 

were done in area 1 of the frame base fittings 

as defined in Appendix 1 of Airbus Alert 

Operators Transmission A53W001–12, dated 

July 4, 2012. 

(h) Frame Base Fitting Inspection 

If, during any records check required by 

paragraph (g) of this AD, it is determined that 

area 1 of the frame base fittings was repaired: 

Within 1,000 flight hours after the effective 

date of this AD do a detailed inspection of 

the frame base fittings between frame 41 and 

frame 46 in the area 2 defined in Appendix 

1 of Airbus Alert Operators Transmission 

A53W001–12, dated July 4, 2012. 

(i) Corrective Action 

If any cracking is found during any 

detailed inspection required by paragraph (h) 

of this AD: Before further flight, repair the 

cracking using a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or the 

European Aviation Safety Agency (EASA) (or 

its delegated agent). 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–227–2125; 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. 

(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 assure the product is airworthy before it 

is returned to service. 

(k) Related Information 

(1) Refer to MCAI EASA Airworthiness 

Directive 2012–0229, dated October 31, 2012; 

and Airbus Alert Operators Transmission 

A53W001–12, dated July 4, 2012, including 

Appendices 1 and 2, and excluding 

Appendix 3; for related information. 

(2) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, 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.airwortheas@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, WA. For 

information on the availability of this 

material at the FAA, call 425 227–1221. 

Issued in Renton, Washington, on May 6, 

2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–11380 Filed 5–13–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0562; Directorate 

Identifier 2009–NE–29–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to all Rolls-Royce plc (RR) 

model RB211 Trent 553–61, 553A2–61, 

556–61, 556A2–61, 556B–61, 556B2–61, 

560–61, and 560A2–61; and RB211 

Trent 768–60, 772–60, and 772B–60; 

and RB211–Trent 875–17, 877–17, 884– 

17, 884B–17, 892–17, 892B–17, and 

895–17; and RB211–524G2–T–19, 

–524G3–T–19, –524H–T–36, and 

–524H2–T–19 turbofan engines that 

have a high-pressure (HP) compressor 

stage 1 to 4 rotor disc installed, with a 

certain part number (P/N) installed. The 

existing AD requires repetitive 

inspections of the axial dovetail slots, 

and follow-on corrective action 

depending on findings. This proposed 

AD expands the population of affected 

parts. This proposed AD also changes, 

for the purposes of this AD, the 

definition of ‘‘engine shop visit.’’ We are 

proposing this AD to detect cracks in 

the HP compressor stage 1 and 2 disc 

posts, which could result in failure of 

the disc post and HP compressor blades, 

damage to the engine, and damage to the 

airplane. 

DATES: We must receive comments on 

this proposed AD by July 15, 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: 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 AD, contact Rolls-Royce plc, 

Corporate Communications, P.O. Box 

31, Derby, England, DE248BJ; phone: 

011–44–1332–242424; fax: 011–44– 

1332–249936; or email: http:// 

www.rolls-royce.com/contact/ 

civil_team.jsp; or download the 

publication from https:// 

www.aeromanager.com. You may view 

this service information at the FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803. 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 

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28162 Federal Register / Vol. 78, No. 93 / Tuesday, May 14, 2013 / Proposed Rules 

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: 

Frederick Zink, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7779; fax: 781–238– 

7199; email: frederick.zink@faa.gov. 

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–2010–0562; Directorate Identifier 

2009–NE–29–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 

On February 23, 2012, we issued AD 

2012–04–13, Amendment 39–16969 (77 

FR 13483, March 7, 2012), for all RR 

model RB211 Trent 553–61, 553A2–61, 

556–61, 556A2–61, 556B–61, 556B2–61, 

560–61, and 560A2–61; and RB211 

Trent 768–60, 772–60, and 772B–60; 

and RB211–Trent 875–17, 877–17, 884– 

17, 884B–17, 892–17, 892B–17, and 

895–17; and RB211–524G2–T–19, 

–524G3–T–19, –524H–T–36, and 

–524H2–T–19 turbofan engines that 

have a HP compressor stage 1 to 4 rotor 

disc installed, with a P/N listed in Table 

1 of that AD. That AD requires repetitive 

inspections of the axial dovetail slots, 

and follow-on corrective action 

depending on findings. That AD 

changed the definition of a shop visit to 

be less restrictive. We issued that AD to 

detect cracks in the HP compressor stage 

1 and 2 disc posts, which could result 

in failure of the disc post and HP 

compressor blades, damage to the 

engine, and damage to the airplane. 

Actions Since Existing AD Was Issued 

Since we issued AD 2012–04–13, 

Amendment 39–16969 (77 FR 13483, 

March 7, 2012), RR engineering 

identified additional affected HP 

compressor rotor discs that require the 

same action. As a result of the 

additional population of discs, this 

proposed rule would increase the total 

cost to the U.S. fleet. 

Also, since we issued AD 2012–04– 

13, Amendment 39–16969 (77 FR 

13483, March 7, 2012), we changed the 

definition of ‘‘engine shop visit’’ to be 

less restrictive. In the existing AD, we 

define ‘‘engine shop visit’’ to be 

whenever all compressor blades are 

removed from the HP compressor drum. 

In this proposed AD, we define ‘‘engine 

shop visit’’ to be whenever the HP 

compressor rotor is accessible for 

removal of the compressor blades. 

Under the revised definition in this 

proposed AD, engine shop visit will 

occur more frequently, likely resulting 

in earlier inspection of the Stage 1 to 4 

rotor disc than would occur under the 

original definition. This is more in line 

with the instructions in revised RR Alert 

Non-Modification Service Bulletin 

(NMSB) RB.211–72–AF964, Revision 3, 

dated January 11, 2013. 

Relevant Service Information 

We reviewed RR Alert NMSB RB.211– 

72–AF964, Revision 3, dated January 11, 

2013. The Alert NMSB describes 

procedures for cleaning and inspecting 

the axial dovetail slots. We also 

reviewed European Aviation Safety 

Agency AD No. 2013–0042, dated 

February 26, 2013, which requires 

inspection of the new rotor discs. 

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 these same 

type designs. 

Proposed AD Requirements 

This proposed AD would retain all of 

the requirements of AD 2012–04–13, 

Amendment 39–16969 (77 FR 13483, 

March 7, 2012). This proposed AD 

would expand the population of parts to 

be inspected. 

Costs of Compliance 

We estimate that this proposed AD 

would affect about 432 engines installed 

on airplanes of U.S. registry. We also 

estimate that it would take about 20 

hours per product to comply with this 

AD. The average labor rate is $85 per 

hour. No parts would be required per 

product. Based on these figures, we 

estimate the cost of the AD on U.S. 

operators to be $734,400. 

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 have 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 that the 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 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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

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Federal Register / Vol. 78, No. 93 / Tuesday, May 14, 2013 / Proposed Rules 28163 

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 

removing airworthiness directive (AD) 

2012–04–13, Amendment 39–16969 (77 

FR 13483, March 7, 2012), and adding 

the following new AD: 

Rolls-Royce plc: Docket No. FAA–2010– 

0562; Directorate Identifier 2009–NE– 

29–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by July 15, 2013. 

(b) Affected ADs 

This AD supersedes AD 2012–04–13, 

Amendment 39–16969 (77 FR 13483, March 

7, 2012). 

(c) Applicability 

This AD applies to the following RollsRoyce plc (RR) model turbofan engines that 

have a high-pressure (HP) compressor stage 

1 to 4 rotor disc installed, with a part number 

(P/N) listed in Table 1 of this AD: 

(1) RB211 Trent 553–61, 553A2–61, 556– 

61, 556A2–61, 556B–61, 556B2–61, 560–61, 

and 560A2–61; and 

(2) RB211 Trent 768–60, 772–60, and 

772B–60; and 

(3) RB211-Trent 875–17, 877–17, 884–17, 

884B–17, 892–17, 892B–17, and 895–17; and 

(4) RB211–524G2–T–19, –524G3–T–19, 

–524H–T–36, and –524H2–T–19. 

TABLE 1 TO PARAGRAPH (C)—AFFECTED HP COMPRESSOR STAGE 1 TO 4 ROTOR DISC P/NS BY ENGINE MODEL

Engine model HP Compressor stage 1 to 4 rotor disc P/N 

(1) RB211 Trent 553–61, 553A2–61, 556–61, 556A2–61, 556B–61, 

556B2–61, 560–61, and 560A2–61.

FK30524 or FW88340. 

(2) RB211 Trent 768–60, 772–60, and 772B–60 .................................... FK22745, FK24031, FK23313, FK25502, FK26185, FK32129, 

FW20195, FW20196, FW20197, FW20638, FW23711, FW88695, 

FW88696, FW88697, FW88698, FW88699, FW88700, FW88701, 

FW88702, or FW88703. 

(3) RB211 Trent 875–17, 877–17, 884–17, 884B–17, 892–17, 892B– 

17, and 895–17.

FK24009, FK26167, FK32580, FW11590, FW61622, FW88723, 

FW88724, or FW88725. 

(4) RB211–524G2–T–19, –524G3–T–19, –524H–T–36, and –524H2– 

T–19.

FK25502, FW20195, FW23711, FW88695, FW88696, or FW88697. 

(d) Unsafe Condition 

We are issuing this AD to detect cracks in 

the HP compressor stage 1 and 2 disc posts, 

which could result in failure of the disc post 

and HP compressor blades, damage to the 

engine, and damage to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(f) Cleaning and Inspection 

(1) Clean and perform a fluorescentpenetrant inspection of the HP compressor 

stage 1 to 4 rotor disc at the first shop visit 

after accumulating 1,000 cycles since new on 

the stage 1 to 4 rotor disc or at the next shop 

visit after the effective date of this AD, 

whichever occurs later. 

(2) Use paragraphs 3.A. through 3.E.(11) of 

the Accomplishment Instructions of RR Alert 

Non-Modification Service Bulletin (NMSB) 

No. RB.211–72–AF964, Revision 3, dated 

January 11, 2013, to do the cleaning and 

inspection. 

(3) Thereafter, at every engine shop visit, 

perform the cleaning and inspection required 

by paragraph (e) of this AD. 

(4) If on the effective date of this AD, an 

engine with an affected part has 1,000 CSN 

or more, and is in the shop, perform the 

cleaning and inspection required by 

paragraph (e) of this AD before return to 

service. 

(5) If cracks or anomalies are found during 

the inspection required by paragraph (e) of 

this AD, accomplish the applicable corrective 

actions before return to service. 

(g) Definition 

For the purpose of this AD, an ‘‘engine 

shop visit’’ is whenever the HP compressor 

rotor is accessible for removal of the 

compressor blades. 

(h) Credit for Previous Actions 

If you performed cleanings and inspections 

before the effective date of this AD using RR 

NMSB No. RB.211–72–AF964, Revision 1, 

dated June 6, 2008, or Revision 2, dated June 

8, 2011, then you met the requirements of 

paragraph (e)(1) of this AD. 

(i) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA may approve AMOCs for this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. 

(j) Related Information 

(1) For more information about this AD, 

contact Frederick Zink, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7779; fax: 781–238–7199; 

email: frederick.zink@faa.gov. 

(2) Refer to RR Alert NMSB No. RB.211– 

72–AF964, Revision 3, dated January 11, 

2013, and European Aviation Safety Agency 

AD No. 2013–0042, dated February 26, 2013, 

for related information. 

(3) For service information identified in 

this AD, contact Rolls-Royce plc, Corporate 

Communications, P.O. Box 31, Derby, 

England, DE248BJ; phone: 011–44–1332– 

242424; fax: 011–44–1332–249936; or email: 

http://www.rolls-royce.com/contact/ 

civil_team.jsp; or download the publication 

from https://www.aeromanager.com. You 

may view this service information at the 

FAA, Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803. For information on the availability of 

this material at the FAA, call 781–238–7125. 

Issued in Burlington, Massachusetts, on 

May 1, 2013. 

Colleen M. D’Alessandro, 

Assistant Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–11337 Filed 5–13–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HEALTH AND 

HUMAN SERVICES 

Food and Drug Administration 

21 CFR Part 173 

[Docket No. FDA–2008–F–0462] 

Zentox Corporation; Withdrawal of 

Food Additive Petition 

AGENCY: Food and Drug Administration, 

HHS. 

ACTION: Notice of withdrawal. 

SUMMARY: The Food and Drug 

Administration (FDA or we) is 

announcing the withdrawal, without 

prejudice to a future filing, of a food 

additive petition (FAP 8A4775) 

proposing that the food additive 

regulations be amended to provide for 

the safe use of monochloramine as an 

antimicrobial agent in poultry process 

chiller water. 

FOR FURTHER INFORMATION CONTACT: 

Judith Kidwell, Center for Food Safety 

and Applied Nutrition (HFS–265), Food 

and Drug Administration, 5100 Paint 

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