Federal Register / Vol. 69, No. 224 / Monday, November 22, 2004 / Proposed Rules 67867

Directorate, 901 Locust, Room 302, Kansas 

City, MO 64106; telephone: (816) 329–4146; 

facsimile: (816) 329–4090. 

Is There Other Information That Relates to 

This Subject? 

(g) New Zealand Airworthiness Directive 

Number DCA/40XL/1, dated June 24, 2004, 

also addresses the subject of this AD. 

May I Get Copies of the Documents 

Referenced in This AD? 

(h) To get copies of the documents 

referenced in this AD, contact Pacific 

Aerospace Corporation, Ltd., Hamilton 

Airport, Private Bag HN 3027, Hamilton, New 

Zealand; telephone: 64 7 843 6144; facsimile: 

64 7 843 6134. To view the AD docket, go 

to the Docket Management Facility; U.S. 

Department of Transportation, 400 Seventh 

Street, SW., Nassif Building, Room PL–401, 

Washington, DC, or on the Internet at

http://dms.dot.gov. This is docket number 

FAA–2004–19444.

Issued in Kansas City, Missouri, on 

November 15, 2004. 

Scott L. Sedgwick, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–25795 Filed 11–19–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2004–19648; Directorate 

Identifier 2004–NE–31–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Corporation (formerly Allison Engine 

Company) 250–B17B, –B17C, –B17D, 

–B17E, –C20, –C20B, –C20F, –C20J, 

–C20S, and –C20W Turboprop and 

Turboshaft Engines

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

Rolls-Royce Corporation (RRC) 

(formerly Allison Engine Company) 

250–B17B, –B17C, –B17D, –B17E, –C20, 

–C20B, –C20F, –C20J, –C20S, and 

–C20W turboprop and turboshaft 

engines that do not have turbine energy 

absorbing ring, part number (P/N) 

23035175, installed. This proposed AD 

would require installation of a turbine 

energy absorbing ring in the plane of the 

1st stage turbine wheel. This proposed 

AD may also require installation of 1st 

stage turbine nozzles, 2nd stage turbine 

nozzles, and a gas producer support 

assembly, all modified to allow for 

installation of the turbine energy 

absorbing ring. This proposed AD 

results from an unacceptable rate of 

uncontained 1st stage turbine wheel 

failures. We are proposing this AD to 

minimize the risk of uncontained 1st 

stage turbine wheel fragments from 

causing damage to the aircraft or 

damage to the second engine on twinengine installations which could lead to 

loss of control and loss of the aircraft.

DATES: We must receive any comments 

on this proposed AD by January 21, 

2005.

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed AD. 

• DOT Docket Web site: Go to http:/

/dms.dot.gov and follow the instructions 

for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

001. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

You can get the service information 

identified in this proposed 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 comments on 

this proposed AD in the AD docket on 

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

FOR FURTHER INFORMATION CONTACT:

Melissa T. Bradley, Aerospace Engineer, 

Chicago Aircraft Certification Office, 

FAA, 2300 East Devon Avenue, Des 

Plaines, IL 60018–4696; telephone (847) 

294–8110; fax (847) 294–7834.

SUPPLEMENTARY INFORMATION: 

Docket Management System (DMS) 

We have implemented new 

procedures for maintaining AD dockets 

electronically. As of May 17, 2004, we 

post new AD actions on the DMS and 

assign a DMS docket number. We track 

each action and assign a corresponding 

Directorate identifier. The DMS docket 

No. is in the form ‘‘Docket No. FAA–

200X–XXXXX.’’ Each DMS docket also 

lists the Directorate identifier (‘‘Old 

Docket Number’’) as a cross-reference 

for searching purposes. 

Comments Invited 

We invite you to submit any written 

relevant data, views, or arguments 

regarding this proposal. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA–

2004–19648; Directorate Identifier 

2004–NE–31–AD’’ in the subject line of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the proposed AD. We will 

consider all comments received by the 

closing date and may amend the 

proposed AD in light of those 

comments. 

We will post all comments we 

receive, without change, to http://

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this proposed AD. 

Using the search function of the DMS 

Web site, anyone can find and read the 

comments in any of our dockets, 

including the name of the individual 

who sent the comment (or signed the 

comment on behalf of an association, 

business, labor union, etc.). You may 

review the DOT’s complete Privacy Act 

Statement in the Federal Register

published on April 11, 2000 (65 FR 

19477–78), or you may visit http://

dms.dot.gov.

Examining the AD Docket 

You may examine the docket that 

contains the proposal, any comments 

received and, any final disposition in 

person at the DMS Docket Offices 

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. 

Discussion 

RRC conducted an analysis of 

uncontained 1st stage turbine wheel 

failures and the effects on aircraft. The 

1st stage turbine wheel can fail as a 

result of in-service damage or gas 

producer tiebolt failure. The in-service 

damage is caused primarily by thermal 

fatigue to the turbine wheels during hot 

starts but has also been linked to 

improper alignment of the combustion 

liner and oil fires. 

The manufacturer developed a turbine 

energy absorbing ring to render turbine 

wheel fragments non-hazardous. We 

have determined the present rate of 

hazardous 1st stage turbine wheel 

67868 Federal Register / Vol. 69, No. 224 / Monday, November 22, 2004 / Proposed Rules 

failures is unacceptable. This condition, 

if not corrected, could result in 

hazardous uncontained 1st stage turbine 

wheel fragments causing damage to the 

airframe and the second engine on twinengine installations which could lead to 

loss of control and loss of the aircraft.

Relevant Service Information 

We have reviewed and approved the 

technical contents of RRC Alert 

Commercial Engine Bulletin No. CEB–

A–1255, Revision 4, dated September 

29, 2004, that describes procedures for 

installing a turbine energy absorbing 

ring in the plane of the 1st stage turbine 

wheel. We have also reviewed and 

approved the technical contents of RRC 

Alert Commercial Engine Bulletin No. 

CEB–A–1254, Revision 3, dated May 21, 

2004, that describes procedures for 

modifying and installing a certain

P/N gas producer support assembly. We 

have also reviewed and approved the 

technical contents of RRC Alert 

Commercial Engine Bulletin No. CEB–

A–1253, Revision 4, dated May 21, 

2004, that describes procedures for 

modifying and installing a certain

P/N 1st stage turbine nozzle, and certain 

P/N 2nd stage turbine nozzle. The 

actions required by RRC Alert 

Commercial Engine Bulletin No. CEB–

A–1254 and No. CEB–A–1253, if 

necessary, must be done before or 

simultaneously with the actions of Alert 

Commercial Engine Bulletin No. CEB–

A–1255. 

FAA’s Determination and Requirements 

of the Proposed AD 

We have evaluated all pertinent 

information and identified an unsafe 

condition that is likely to exist or 

develop on other products of this same 

type design. We are proposing this AD, 

which would require installation of a 

turbine energy absorbing ring. The 

proposed AD would require that these 

actions be done using Alert Commercial 

Engine Bulletin No. CEB–A–1255. 

Costs of Compliance 

There are about 13,299 RRC 250–

B17B, –B17C, –B17D, –B17E, –C20, 

–C20B, –C20F, –C20J, –C20S, and 

–C20W turboprop and turboshaft 

engines of the affected design in the 

worldwide fleet. We estimate that 5,000 

engines installed on helicopters of U.S. 

registry require the installation of a 

turbine energy absorbing ring. Of those 

5,000 engines, we also estimate that 

4,000 engines require installation of a 

gas producer support assembly, 1st stage 

turbine nozzle, and 2nd stage turbine 

nozzle. It takes about 16 work hours per 

engine to install the turbine energy 

absorbing ring, 35 work hours to install 

the gas producer support assembly, and 

20 work hours to install the 1st stage 

turbine nozzle, and 2nd stage turbine 

nozzle. The average labor rate is $65 per 

work hour. Required turbine energy 

absorbing rings cost about $10,765 per 

engine. Required gas producer support 

assemblies cost about $2,500 per engine. 

Required 1st stage turbine nozzles and 

2nd stage turbine nozzles cost about 

$1,000 per engine. Based on these 

figures, we estimate the total cost of the 

proposed AD to U.S. operators to be 

$87,325,000. 

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); and 

3. Would 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 proposal 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, Safety.

The Proposed Amendment 

Under the authority delegated to me 

by the Administrator, the Federal 

Aviation Administration 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:

Rolls-Royce Corporation (formerly Allison 

Engine Company): Docket No. FAA–

2004–19648; Directorate Identifier 2004–

NE–31–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

(FAA) must receive comments on this 

airworthiness directive (AD) action by 

January 21, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Rolls-Royce 

Corporation (RRC) (formerly Allison Engine 

Company) 250–B17B, –B17C, –B17D, –B17E, 

–C20, –C20B, –C20F, –C20J, –C20S, and 

–C20W turboprop and turboshaft engines that 

do not have turbine energy absorbing ring, 

part number 23035175, installed. These 

engines are installed on, but not limited to, 

the following aircraft:

Agusta A109 

Agusta A109A 

Agusta A109A II 

B–N Group BN–2T 

Bell 206A 

Bell 206B 

Bell 206L 

Eurocopter Deutchland BO–105C 

Eurocopter Deutchland BO–105S 

Eurocopter France AS355E 

Eurocopter France AS355F 

Eurocopter France AS355F1 

Eurocopter France AS355F2 

FH–1100 Manufacturing Corp FH–1100 

MDHI 369D 

MDHI 369E 

MDHI 369HM 

MDHI 369HS 

MDHI 369HE 

SIAI Marchetti s.r.l. SF600

Unsafe Condition 

(d) This AD results from an unacceptable 

rate of uncontained 1st stage turbine wheel 

failures. We are issuing this AD to minimize 

the risk of uncontained 1st stage turbine 

wheel fragments from causing damage to the 

aircraft or damage to the second engine on 

twin-engine installations which could lead to 

loss of control and loss of the aircraft. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed at the 

next time the gas producer turbine rotor is 

disassembled for any reason, or within 1,750 

hours time-since-last-overhaul, time-sincenew, time-since-last-heavy-maintenance, or 

time-since-last-hot section inspection after 

the effective date of this AD, whichever 

occurs first, but no later than October 31, 

2011, unless already done. 

Required Actions 

(f) If not already installed, install a 

modified gas producer support assembly to 

provide installation of the turbine energy 

absorbing ring. Use paragraph 2. of RRC Alert 

Commercial Engine Bulletin No. CEB–A–

1254, Revision 3, dated May 21, 2004, to do 

the modification and installation. 

(g) If not already installed, install a 

modified 1st stage turbine nozzle, 2nd stage 

turbine nozzle, and gas producer support 

assembly to provide installation of the 

turbine energy absorbing ring. Use paragraph 

2. of RRC Alert Commercial Engine Bulletin

Federal Register / Vol. 69, No. 224 / Monday, November 22, 2004 / Proposed Rules 67869

No. CEB–A–1253, Revision 4, dated May 21, 

2004, to do the modification and installation. 

(h) Install a turbine energy absorbing ring 

in the plane of the 1st stage turbine wheel. 

Use paragraphs 2.A. and 2.B. of RRC Alert 

Commercial Engine Bulletin No. CEB–A–

1255, Revision 4, dated September 29, 2004, 

to do the installation. 

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.

Issued in Burlington, Massachusetts, on 

November 16, 2004. 

Jay J. Pardee, 

Manager, Engine and Propeller Directorate, 

Aircraft Certification Service.

[FR Doc. 04–25794 Filed 11–19–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2003–NM–256–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330, A340–200, and A340–300 Series 

Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Supplemental notice of 

proposed rulemaking; reopening of 

comment period. 

SUMMARY: This document revises an 

earlier proposed airworthiness directive 

(AD), applicable to certain Airbus 

Model A330, A340–200, and A340–300 

series airplanes, that would have 

required initial and repetitive 

inspections of certain frame stiffeners to 

detect cracking. If any cracking was 

found, that proposal would have 

required replacement of the stiffener 

with a new, reinforced stiffener. 

Replacement of the stiffener would 

constitute terminating action for certain 

inspections. That proposal would also 

have required a one-time inspection of 

any new, reinforced stiffener; and repair 

or replacement of the new, reinforced 

stiffener if any cracking was found 

during the one-time inspection. That 

proposal also provided for an optional 

terminating action for certain 

requirements of that AD. This new 

action revises the proposed rule by 

reducing the compliance time for the 

initial inspection of the affected frame 

stiffeners. The actions specified by this 

new proposed AD are intended to 

prevent fatigue failure of certain frame 

stiffener fittings, which could result in 

reduced structural integrity of the 

airplane. This action is intended to 

address the identified unsafe condition.

DATES: Comments must be received by 

December 17, 2004.

ADDRESSES: Submit comments in 

triplicate to the Federal Aviation 

Administration (FAA), Transport 

Airplane Directorate, ANM–114, 

Attention: Rules Docket No. 2003–NM–

256–AD, 1601 Lind Avenue, SW., 

Renton, Washington 98055–4056. 

Comments may be inspected at this 

location between 9 a.m. and 3 p.m., 

Monday through Friday, except Federal 

holidays. Comments may be submitted 

via fax to (425) 227–1232. Comments 

may also be sent via the Internet using 

the following address: 9-anmnprmcomment@faa.gov. Comments sent 

via fax or the Internet must contain 

‘‘Docket No. 2003–NM–256–AD’’ in the 

subject line and need not be submitted 

in triplicate. Comments sent via the 

Internet as attached electronic files must 

be formatted in Microsoft Word 97 or 

2000 or ASCII text. 

The service information referenced in 

the proposed rule may be obtained from 

Airbus Industrie, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France. 

This information may be examined at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., 

Renton, Washington.

FOR FURTHER INFORMATION CONTACT: Tim 

Backman, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2797; 

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: 

Comments Invited 

Interested persons are invited to 

participate in the making of the 

proposed rule by submitting such 

written data, views, or arguments as 

they may desire. Communications shall 

identify the Rules Docket number and 

be submitted in triplicate to the address 

specified above. All communications 

received on or before the closing date 

for comments, specified above, will be 

considered before taking action on the 

proposed rule. The proposals contained 

in this action may be changed in light 

of the comments received. 

Submit comments using the following 

format: 

• Organize comments issue-by-issue. 

For example, discuss a request to 

change the compliance time and a 

request to change the service bulletin 

reference as two separate issues. 

• For each issue, state what specific 

change to the proposed AD is being 

requested. 

• Include justification (e.g., reasons or 

data) for each request. 

Comments are specifically invited on 

the overall regulatory, economic, 

environmental, and energy aspects of 

the proposed rule. All comments 

submitted will be available, both before 

and after the closing date for comments, 

in the Rules Docket for examination by 

interested persons. A report 

summarizing each FAA-public contact 

concerned with the substance of this 

proposal will be filed in the Rules 

Docket. 

Commenters wishing the FAA to 

acknowledge receipt of their comments 

submitted in response to this action 

must submit a self-addressed, stamped 

postcard on which the following 

statement is made: ‘‘Comments to 

Docket Number 2003–NM–256–AD.’’

The postcard will be date stamped and 

returned to the commenter. 

Availability of NPRMs 

Any person may obtain a copy of this 

NPRM by submitting a request to the 

FAA, Transport Airplane Directorate, 

ANM–114, Attention: Rules Docket No. 

2003–NM–256–AD, 1601 Lind Avenue, 

SW., Renton, Washington 98055–4056. 

Discussion 

A proposal to amend part 39 of the 

Federal Aviation Regulations (14 CFR 

part 39) to add an airworthiness 

directive (AD), applicable to certain 

Airbus Model A330, A340–200, and 

A340–300 series airplanes, was 

published as a notice of proposed 

rulemaking (NPRM) in the Federal 

Register on April 1, 2004 (69 FR 17084). 

That NPRM would have required initial 

and repetitive inspections of certain 

frame stiffeners to detect cracking. If any 

cracking was found, that proposal 

would have required replacement of the 

stiffener with a new, reinforced 

stiffener. Replacement of the stiffener 

would constitute terminating action for 

certain inspections. That NPRM would 

also have required a one-time inspection 

of any new, reinforced stiffeners; and 

repair or replacement of the new, 

reinforced stiffener if any cracking was 

found during the one-time inspection. 

That NPRM also provided for an 

optional terminating action for certain 

requirements of that AD. That NPRM 

was prompted by issuance of mandatory 

continuing airworthiness information by 

a civil airworthiness authority. Cracking 

and consequent fatigue failure of certain 

frame stiffeners, if not corrected, could