56864 Federal Register / Vol. 71, No. 188 / Thursday, September 28, 2006 / Rules and Regulations 

TABLE 1.—CREDIT SERVICE BULLETINS

Service bulletin Revision 

level Date 

Boeing Service Bulletin 747–53A2409 .................................................................................................................... 1 May 29, 1997. 

Boeing Service Bulletin 747–53A2409 .................................................................................................................... 2 August 6, 1998. 

Boeing Service Bulletin 747–53A2409 .................................................................................................................... 3 October 22, 1998. 

Boeing Service Bulletin 747–53A2409 .................................................................................................................... 4 February 17, 2000. 

Alternative Methods of Compliance (AMOCs) 

(k)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested in accordance with the procedures 

found in 14 CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

(3) AMOCs approved previously in 

accordance with AD 96–23–02, are approved 

as AMOCs for the corresponding provisions 

of paragraph (f) of this AD, except AMOCs for 

terminating action based upon inspection 

results using a sliding probe low frequency 

eddy current (LFEC), sliding probe high 

frequency eddy current (HFEC), or mid 

frequency surface eddy current (MFEC) 

inspection methods; and provided that any 

alternative method for future inspections did 

not incorporate a sliding probe LFEC, sliding 

probe HFEC, or MFEC inspection methods. 

(4) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD, if it is approved by an 

Authorized Representative for the Boeing 

Commercial Airplanes Delegation Option 

Authorization Organization who has been 

authorized by the Manager, Seattle ACO, to 

make those findings. For a repair method to 

be approved, the repair must meet the 

certification basis of the airplane and the 

approval must specifically refer to this AD. 

Material Incorporated by Reference 

(l) You must use Boeing Alert Service 

Bulletin 747–53A2409, dated September 26, 

1996; or Boeing Alert Service Bulletin 747–

53A2409, Revision 5, dated August 18, 2005, 

as applicable, to perform the actions that are 

required by this AD, unless the AD specifies 

otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Boeing Alert Service Bulletin 747–53A2409, 

Revision 5, dated August 18, 2005, in 

accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) On November 27, 1996 (61 FR 57994, 

November 12, 1996), the Director of the 

Federal Register approved the incorporation 

by reference of Boeing Alert Service Bulletin 

747–53A2409, dated September 26, 1996. 

(3) Contact Boeing Commercial Airplanes, 

P.O. Box 3707, Seattle, Washington 98124–

2207, for a copy of this service information. 

You may review copies at the Docket 

Management Facility, U.S. Department of 

Transportation, 400 Seventh Street, SW., 

Room PL–401, Nassif Building, Washington, 

DC; on the Internet at http://dms.dot.gov; or 

at the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at the NARA, 

call (202) 741–6030, or go to http:// 

www.archives.gov/federal_register/code_of_

federal_regulations/ibr_locations.html. 

Issued in Renton, Washington, on 

September 14, 2006. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 06–8227 Filed 9–27–06; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–23392; Directorate 

Identifier 2005–NE–47–AD; Amendment 39–

14776; AD 2006–20–07] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Corporation Models 250–C30, 250–C40, 

and 250–C47 Series Turboshaft 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for RollsRoyce Corporation (RRC) models 250–

C30, 250–40, and 250–C47 series 

turboshaft engines with a third-stage 

turbine wheel, part number (P/N) 

6898663 or P/N 23065843 installed, or 

a fourth-stage turbine wheel, P/N 

6892764 or P/N 23066744, installed. 

This AD adds an additional life limit for 

third- and fourth-stage turbine wheels. 

This AD results from analysis by RRC of 

failures of third-stage turbine wheels. 

We are issuing this AD to prevent loss 

of power, possible engine shutdown, or 

uncontained engine failure. 

DATES: This AD becomes effective 

November 2, 2006. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulations as 

of November 2, 2006. 

ADDRESSES: You can get the service 

information identified in this AD from 

Rolls-Royce Corporation, P.O. Box 420, 

Indianapolis, IN 46206–0420; telephone 

(317) 230–6400; fax (317) 230–4243. 

You may examine the AD docket on 

the Internet at http://dms.dot.gov or in 

Room PL–401 on the plaza level of the 

Nassif Building, 400 Seventh Street, 

SW., Washington, DC. 

FOR FURTHER INFORMATION CONTACT: John 

Tallarovic, Aerospace Engineer, Chicago 

Aircraft Certification Office, FAA, 2300 

East Devon Avenue, Des Plaines, IL 

60018–4696; telephone (847) 294–8180; 

fax (847) 294–7834. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

a proposed AD. The proposed AD 

applies to RRC models 250–C30, 250–

40, and 250–C47 series turboshaft 

engines. We published the proposed AD 

in the Federal Register on January 25, 

2006 (71 FR 4065). That action proposed 

to add an additional life limit for thirdand fourth-stage turbine wheels. 

Examining the AD Docket 

You may examine the docket that 

contains the AD, any comments 

received, and any final disposition in 

person at the Docket Management 

Facility Docket Office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The Docket 

Office (telephone (800) 647–5227) is 

located on the plaza level of the 

Department of Transportation Nassif 

Building at the street address stated in 

ADDRESSES. Comments will be available 

in the AD docket shortly after the DMS 

receives them. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

Request to Correct Factual Errors 

One commenter, RRC, requests that 

we correct factual errors in the NPRM 

and revise the Discussion paragraph, to 

state that: 

• Only third-stage turbine wheels 

actually failed in the past; and 

• Only the third-stage turbine wheel 

(not the third-and-fourth-stage turbine 


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Federal Register / Vol. 71, No. 188 / Thursday, September 28, 2006 / Rules and Regulations 56865 

wheels) could prematurely fail if 

operated too many times in the transient 

overspeed region. 

We agree with these factual 

corrections. We changed the AD by 

removing certain references to the 

fourth-stage turbine wheel and changing 

the AD to state that it results from 

analysis by RRC of failures of third-stage 

turbine wheels. 

Final Rule Should Include the LowerSpeed Avoidance Range 

A private citizen states that the final 

rule should include the lower-speed 

avoidance range (68.4% to 87.1%) in 

addition to the high-speed transient 

range, when counting speed excursions 

and retiring turbine wheels. The 

commenter gave three reasons for the 

request: 

First, that operation in the lowerspeed avoidance range probably does 

more cumulative damage to the turbine 

wheel than operation in the high-speed 

excursion range. The commenter bases 

this on data that he claims shows higher 

stress levels at the low-speed transient 

range compared to the high-speed 

transient range. 

Second, the fact that the engine 

control unit does not record operation 

in the low-speed avoid range, 

emphasizes the importance to inform 

operators about the danger of 

cumulative damage. 

Third, the current commercial engine 

bulletin gives no information about 

cumulative damage in the low-speed 

avoid range. The commenter states that 

currently there is no warning to 

operators of the potential damage to 

turbine wheels operated for any length 

of time in the avoid range which may 

cause more cumulative damage than 

high-speed excursions. 

We do not agree. The supporting data 

the commenter provided includes 

information from a manufacturer 

development configuration that does not 

represent the current production 

configuration. The data also does not 

represent the manufacturer’s current, 

more detailed, knowledge of the stresses 

on the turbine airfoils. Transients in the 

low-speed range do not need to be 

tracked and used to retire turbine 

wheels. The low-speed range from 

22,000 rpm to 28,045 rpm is a speed 

range that is normally passed through 

transiently, during the start up and 

shutdown procedures. The rate of speed 

change during the start up or shutdown 

is high enough that no significant time 

is spent at any resonant speed and no 

significant dynamic stresses are 

encountered that would lead to damage. 

In comparison to the low-speed 

excursions, if an operational situation 

occurs that results in a speed excursion 

above the maximum continuous speed, 

the rate of change of speed goes from 

positive to negative as it accelerates up 

to the maximum speed before returning 

back to the continuous operating range. 

During this transition, speed may hold 

close to constant, or only change very 

slowly, for a number of seconds. In this 

case, there could be sufficient time for 

the dynamic stresses to build to their 

full resonant values and potentially 

cause some level of damage to a turbine 

wheel. This difference between a fast 

acceleration or deceleration through a 

resonant speed, and a potential slow 

motion or hold in a resonant speed is 

why counting of occurrences in the low 

speed range is unnecessary. 

Finally, the inclusion of a specific 

‘‘steady state operation prohibited’’

speed avoid zone denotes that failure 

could occur if operation outside of the 

defined continuous operating range was 

performed. RRC SB No. CEB A–72–

3272, CEB A–72–5048, and CEB A–72–

6054 (combined in one document), all 

Revision 2, dated June 27, 2006, clearly 

instruct operators to avoid the lowspeed region. As stated above, this 

speed range is not of concern for normal 

transient operation of the engine. We 

did not change the AD. 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

received, and determined that air safety 

and the public interest require adopting 

the AD with the changes described 

previously. We have determined that 

these changes will neither increase the 

economic burden on any operator nor 

increase the scope of the AD. 

Costs of Compliance 

We estimate that this AD will affect 

1,300 engines installed on airplanes of 

U.S. registry. We also estimate that it 

will take about 42 work-hours per 

engine to replace the third- and fourthstage turbine wheels, and that the 

average labor rate is $65 per work-hour. 

Required parts will cost about $25,000 

per engine. We estimate that only 10% 

of all turbine wheel replacements will 

result from operators exceeding the new 

transient overspeed event limits. Based 

on these figures, we estimate the total 

potential maximum cost of the AD to 

U.S. operators to be $3,604,900. 

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 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); and 

(3) 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. 

We prepared a summary of the costs 

to comply with this AD and placed it in 

the AD Docket. You may get a copy of 

this summary at the address listed 

under ADDRESSES. 

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 Federal Aviation Administration 

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: 


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56866 Federal Register / Vol. 71, No. 188 / Thursday, September 28, 2006 / Rules and Regulations 

2006–20–07 Rolls-Royce Corporation 

(formerly Allison Engine Company, 

Allison Gas Turbine Division, and 

Detroit Diesel Allison): Amendment 39–

14776. Docket No. FAA–2005–23392; 

Directorate Identifier 2005–NE–47–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective November 2, 2006. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Rolls-Royce 

Corporation (RRC) models 250–C30, –C30G, 

–C30G/2, –C30M, –C30P, –C30R, –C30R/1, 

–C30R/3, –C30R/3M, –C30S, –C30U, –C40B, 

–C47B, and –C47M turboshaft engines, with 

a third-stage turbine wheel, part number 

(P/N) 6898663 or P/N 23065843 installed, or 

a fourth-stage turbine wheel, P/N 6892764 or 

P/N 23066744, installed. These engines are 

installed on, but not limited to, Bell 206L–

3, Bell 206L–4, Bell 230, Bell 407, Bell 430, 

MDHI 369F, MDHI 369FF, MDHI 600N, and 

Sikorsky S–76A helicopters. 

Unsafe Condition 

(d) This AD results from analysis by RRC 

of failures of third-stage turbine wheels. We 

are issuing this AD to prevent loss of power, 

possible engine shutdown, or uncontained 

failure. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified unless the 

actions have already been done. 

(f) Within 30 days after the effective date 

of this AD, record each time the third- and 

fourth-stage turbine wheels enter into the 

speed range between ‘‘Event Threshold’’ and 

‘‘Maximum Overspeed Transient’’. Use 

paragraph 2.A. through 2.A.(5) of the 

Accomplishment Instructions and the 

applicable Figures 1 through 5 of RRC Alert 

Commercial Engine Bulletins (CEBs) No. CEB 

A–72–3272, No. CEB A–72–5048, and No. 

CEB A–72–6054 (combined in one 

document), all Revision 2, dated June 27, 

2006, to determine the speed range. 

(g) Remove and retire any third-stage 

turbine wheel or fourth-stage turbine wheel 

after the sixth time the wheel enters into the 

speed range between ‘‘Event Threshold’’ and 

‘‘Maximum Overspeed Transient’’. 

Third- and Fourth-Stage Turbine Wheel Life 

Limits 

(h) The retirement criteria in this AD are 

in addition to the existing third- and fourthstage turbine wheel hour and cycle life 

limits. You must retire the wheels when you 

exceed any published life limit (transient 

speed excursions, hours, or cycles). 

Alternative Methods of Compliance 

(i) The Manager, Chicago Aircraft 

Certification Office, has the authority to 

approve alternative methods of compliance 

for this AD if requested using the procedures 

found in 14 CFR 39.19. 

Related Information 

(j) None. 

Material Incorporated by Reference 

(k) You must use Rolls-Royce Corporation 

Alert Commercial Engine Bulletins No. CEB 

A–72–3272, No. CEB A–72–5048, and No. 

CEB A–72–6054 (combined in one 

document), all Revision 2, dated June 27, 

2006, to perform the actions required by this 

AD. The Director of the Federal Register 

approved the incorporation by reference of 

this service bulletin in accordance with 5 

U.S.C. 552(a) and 1 CFR part 51. Contact 

Rolls-Royce Corporation, P.O. Box 420, 

Indianapolis, IN 46206–0420; telephone (317) 

230–6400; fax (317) 230–4243 for a copy of 

this service information. You may review 

copies at the FAA, New England Region, 

Office of the Regional Counsel, 12 New 

England Executive Park, Burlington, MA; or 

at the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Burlington, Massachusetts, on 

September 20, 2006. 

Francis A. Favara, 

Manager, Engine and Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 06–8230 Filed 9–27–06; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HEALTH AND 

HUMAN SERVICES 

Food and Drug Administration 

21 CFR Part 520 

Oral Dosage Form New Animal Drugs; 

Neomycin 

AGENCY: Food and Drug Administration, 

HHS. 

ACTION: Final rule. 

SUMMARY: The Food and Drug 

Administration (FDA) is amending the 

animal drug regulations to reflect 

approval of an abbreviated new animal 

drug application (ANADA) filed by 

Sparhawk Laboratories, Inc. The 

ANADA provides for use of neomycin 

sulfate soluble powder in livestock for 

the treatment and control of bacterial 

enteritis. 

DATES: This rule is effective September 

28, 2006. 

FOR FURTHER INFORMATION CONTACT: John 

K. Harshman, Center for Veterinary 

Medicine (HFV–104), Food and Drug 

Administration, 7500 Standish Pl., 

Rockville, MD 20855, 301–827–0169, email: john.harshman@fda.hhs.gov. 

SUPPLEMENTARY INFORMATION: Sparhawk 

Laboratories, Inc., 12340 Santa Fe Trail 

Dr., Lenexa, KS 66215, filed ANADA 

200–378 for the use of Neomycin 

Soluble Powder in cattle, swine, sheep, 

goats, and turkeys for the treatment and 

control of bacterial enteritis. Sparhawk 

Laboratories, Inc.’s Neomycin Soluble 

Powder is approved as a generic copy of 

NEOMIX 325 (neomycin sulfate) 

Soluble Powder, sponsored by 

Pharmacia & Upjohn Co., a Division of 

Pfizer, Inc., under NADA 11–315. The 

ANADA is approved as of August 31, 

2006, and the regulations in 21 CFR 

520.1484 and 520.1485 are amended to 

reflect the approval and a current 

format. The basis of approval is 

discussed in the freedom of information 

summary. 

In addition, a label statement warning 

against the use of these products in 

calves to be processed for veal was not 

codified at the time supplemental 

NADAs or ANADAs for oral neomycin 

products were approved. At this time, 

FDA is amending the animal drug 

regulations to reflect required food 

safety warning statements. 

In accordance with the freedom of 

information provisions of 21 CFR part 

20 and 21 CFR 514.11(e)(2)(ii), a 

summary of safety and effectiveness 

data and information submitted to 

support approval of this application 

may be seen in the Division of Dockets 

Management (HFA–305), Food and Drug 

Administration, 5630 Fishers Lane, rm. 

1061, Rockville, MD 20852, between 9 

a.m. and 4 p.m., Monday through 

Friday. 

FDA has determined under 21 CFR 

25.33(a)(1) that this action is of a type 

that does not individually or 

cumulatively have a significant effect on 

the human environment. Therefore, 

neither an environmental assessment 

nor an environmental impact statement 

is required. 

This rule does not meet the definition 

of ‘‘rule’’ in 5 U.S.C. 804(3)(A) because 

it is a rule of ‘‘particular applicability.’’

Therefore, it is not subject to the 

congressional review requirements in 5 

U.S.C. 801–808. 

List of Subjects in 21 CFR Part 520 

Animal drugs. 

■ Therefore, under the Federal Food, 

Drug, and Cosmetic Act and under 

authority delegated to the Commissioner 

of Food and Drugs and redelegated to 

the Center for Veterinary Medicine, 21 

CFR part 520 is amended as follows: 

PART 520—ORAL DOSAGE FORM 

NEW ANIMAL DRUGS 

■ 1. The authority citation for 21 CFR 

part 520 continues to read as follows: 

Authority: 21 U.S.C. 360b. 

■ 2. Revise § 520.1484 to read as 

follows: 


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