Federal Register / Vol. 69, No. 227 / Friday, November 26, 2004 / Rules and Regulations 68769

Instructions of Hamilton Sundstrand ASB 

No. ASB–4504112–49–22, Revision 2, dated 

October 4, 2004 to inspect and adjust the gap. 

Optional Terminating Action for APU Model 

T–62T–40C14 (APS 500R) 

(j) For APU Model T–62T–40C14 (APS 

500R), installation of a part number fuel filter 

assembly that is not listed in this AD 

constitutes optional terminating action to the 

requirements of this AD. 

Alternative Methods of Compliance 

(k) The Manager, Los Angeles 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. 

Material Incorporated by Reference 

(l) You must use the Alert Service Bulletins 

listed in Table 1 of this AD to perform the 

bracket installations required by this AD. The 

Director of the Federal Register approved the 

incorporation by reference of the documents 

listed in Table 1 of this AD in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. You 

can get a copy from Hamilton Sundstrand 

Technical Publications Department, P.O. Box 

7002, Rockford, IL 61125–7002, U.S.A. You 

can 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/

code_of_federal_regulations/

ibr_locations.html. Table 1 follows:

TABLE 1.—INCORPORATION BY REFERENCE

Alert service bulletin No. Page number(s) shown on the 

page 

Revision level 

shown on the 

page 

Date shown on the 

page 

Hamilton Sundstrand ASB–4503067–49–9 ........................................ All ................................................. Original ......... December 2, 2003.

Hamilton Sundstrand ASB–4504112–49–22 ...................................... All ................................................. 2 ................... October 4, 2004. 

Related Information 

(m) None.

Issued in Burlington, Massachusetts, on 

November 15, 2004. 

Jay J. Pardee, 

Manager, Engine and Propeller Directorate, 

Aircraft Certification Service.

[FR Doc. 04–25792 Filed 11–24–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. 2003–NE–23–AD; Amendment 

39–13880; AD 2004–24–04] 

RIN 2120–AA64

Airworthiness Directives; Rolls-Royce 

Corporation (Formerly Allison Engine 

Company, Allison Gas Turbine 

Division, and Detroit Diesel Allison) 

(RRC) Models 250–C30R/3, –C30R/3M, 

–C47B, and –C47M Turboshaft Engines

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD) for 

RRC models 250–C30R/3, –C30R/3M, 

–C47B, and –C47M turboshaft engines. 

That AD currently requires initial and 

repetitive electrical signal inspections of 

the hydromechanical unit (HMU) Power 

Lever Angle (PLA) potentiometer. This 

ad continues to require those 

inspections and adds replacement of the 

existing HMU with a new design HMU 

as a mandatory terminating action to the 

repetitive inspection requirements. This 

AD results from the manufacturer 

releasing a redesigned HMU that has a 

dual-element potentiometer. We are 

issuing this AD to prevent 

uncommanded and sudden changes in 

engine power.

DATES: This AD becomes effective 

January 3, 2005. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulations as 

of January 3, 2005.

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 at 

the FAA, New England Region, Office of 

the Regional Counsel, 12 New England 

Executive Park, Burlington, MA. You 

may examine the service information, 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/

code_of_federal_regulations/

ibr_locations.html.

FOR FURTHER INFORMATION CONTACT:

Khailaa Hosny, Aerospace Engineer, 

Chicago Aircraft Certification Office, 

FAA, 2300 East Devon Avenue, Des 

Plaines, IL 60018–4696; telephone (847) 

294–7134; 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–C30R/3, 

–C30R/3M, –C47B, and –C47M 

turboshaft engines. We published the 

proposed AD in the Federal Register on 

June 9, 2004 (69 FR 32287). That action 

proposed to require initial and 

repetitive electrical signal inspections of 

the HMU PLA potentiometer and 

replacement of the existing HMU with 

a new design HMU as a mandatory 

terminating action to the repetitive 

inspection requirements. 

Examining the AD Docket 

You may examine the AD Docket 

(including any comments and service 

information), by appointment, between 

8 a.m. and 4:30 p.m., Monday through 

Friday, except Federal holidays. See 

ADDRESSES for the location. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We received no 

comments on the proposal or on the 

determination of the cost to the public. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 

safety and the public interest require 

adopting the AD as proposed. 

Costs of Compliance 

We estimate that 700 engines installed 

on helicopters of U.S. registry will be 

affected by this AD. We estimate that it 

will take about 4 work hours per engine 

to replace a single-element HMU with a 

dual-element HMU. We also estimate 

that 12 percent of the single-element 

HMUs will fail the required inspection 

and require replacing the HMU. The 

average labor rate is $65 per work hour. 

Required parts cost about $615 per 

engine. Based on these figures, we 

estimate the total cost of the AD to U.S. 

operators to be $686,000.

68770 Federal Register / Vol. 69, No. 227 / Friday, November 26, 2004 / Rules and Regulations 

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 by sending a request to us 

at the address listed under ADDRESSES.

Include ‘‘AD Docket No. 2003–NE–23–

AD’’ in your request.

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 

removing Amendment 39–13210 (68 FR 

38590, June 30, 2003) and by adding a 

new airworthiness directive, 

Amendment 39–13880, to read as 

follows:

2004–24–04 Rolls-Royce Corporation 

(formerly Allison Engine Company, 

Allison Gas Turbine Division, and 

Detroit Diesel Allison): Amendment 39–

13880. Docket No. 2003–NE–23–AD. 

Supersedes AD 2003–13–10, 

Amendment 39–13210. 

Effective Date 

(a) This AD becomes effective January 3, 

2005. 

Affected ADs 

(b) This AD supersedes AD 2003–13–10. 

Applicability 

(c) This AD applies to Rolls-Royce 

Corporation (formerly Allison Engine 

Company, Allison Gas Turbine Division, and 

Detroit Diesel Allison) (RRC) models 250–

C30R/3, –C30R/3M, –C47B, and –C47M 

turboshaft engines that have a 

hydromechanical unit (HMU) with a part 

number (P/N) listed in 1.A. Group A of RRC 

Alert Commercial Engine Bulletins (ACEB) 

No. CEB A–73–3103, Revision 4, dated 

December 2, 2003; and No. CEB A–73–6030, 

Revision 4, dated December 2, 2003. These 

engines are installed on, but not limited to, 

Bell OH–58D, Bell Helicopter Textron 407, 

Boeing AH/MH–6M, and MD Helicopters Inc. 

600N helicopters.

Unsafe Condition 

(d) This AD results from the manufacturer 

releasing a redesigned HMU that has a dualelement potentiometer. The actions specified 

in this AD are intended to prevent 

uncommanded and sudden changes in 

engine power. 

Compliance 

(e) Compliance with this AD is required as 

indicated, unless already done. 

Initial Inspection 

(f) Perform an initial electrical signal 

inspection of the HMU Power Lever Angle 

(PLA) potentiometer, within 300 flight hours 

(FH) after the effective date of this AD. Use 

paragraphs 2.B. through 2.B.(8) and 2.B.(10) 

of the Accomplishment Instructions of RRC 

ACEB No. CEB A–73–3103, Revision 4, dated 

December 2, 2003; or No. CEB A–73–6030, 

Revision 4, dated December 2, 2003; to 

perform the inspection. 

(g) Replace the HMU before further flight 

if the electrical signal inspection result is 

unacceptable. 

Repetitive Inspections 

(h) Thereafter, perform repetitive electrical 

signal inspections of the HMU PLA 

potentiometer within 300 FH of the last 

inspection. Use paragraphs 2.B. through 

2.B.(8) and 2.B.(10) of the Accomplishment 

Instructions of RRC ACEB No. CEB A–73–

3103, Revision 4, dated December 2, 2003; or 

No. CEB A–73–6030, Revision 4, dated 

December 2, 2003; to perform the inspection. 

(i) Replace the HMU before further flight if 

the electrical signal inspection result is 

unacceptable. 

Mandatory Terminating Action 

(j) Replace the HMU with an HMU that has 

a P/N not specified in this AD within 600 FH 

after the effective date of this AD, or January 

31, 2005, whichever occurs earlier. Replacing 

the HMU with an HMU that has a P/N not 

specified in this AD terminates the repetitive 

inspection requirement specified in 

paragraph (h) of this AD. 

Alternative Methods of Compliance 

(k) Alternative methods of compliance 

must be requested in accordance with 14 CFR 

part 39.19, and must be approved by the 

Manager, Chicago Aircraft Certification 

Office, FAA. 

Material Incorporated by Reference 

(l) You must use the Rolls-Royce 

Corporation Alert Commercial Engine 

Bulletins (ACEBs) listed in Table 1 of this AD 

to perform the inspections required by this 

AD. The Director of the Federal Register 

approved the incorporation by reference of 

the documents listed in Table 1 of this AD 

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

part 51. You can get a copy from Rolls-Royce 

Corporation, P.O. Box 420, Indianapolis, IN 

46206–0420; telephone (317) 230–6400; fax 

(317) 230–4243. You can 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/code_of_federal_regulations/

ibr_locations.html. Table 1 follows:

TABLE 1.—INCORPORATION BY REFERENCE

Service bulletin Page number(s) shown on the page 

Revision level 

shown on the 

page 

Date shown on the 

page 

CEB A–73–3103, Total Pages: 20 ............................................... All ....................................................... 4 ................... December 2, 2003. 

CEB A–73–6030, Total Pages: 20 ............................................... All ....................................................... 4 ................... December 2, 2003. 

Federal Register / Vol. 69, No. 227 / Friday, November 26, 2004 / Rules and Regulations 68771

Related Information 

(m) None.

Issued in Burlington, Massachusetts, on 

November 15, 2004. 

Jay J. Pardee, 

Manager, Engine and Propeller Directorate, 

Aircraft Certification Service.

[FR Doc. 04–25791 Filed 11–24–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. 2003–CE–67–AD; Amendment 

39–13878; AD 2004–24–02] 

RIN 2120–AA64

Airworthiness Directives; 

Ostmecklenburgische Flugzeugbau 

GmbH ModelOMF–100–160 Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: The FAA adopts a new 

airworthiness directive (AD) for certain 

Ostmecklenburgische Flugzeugbau 

GmbH (OMF) Model OMF–100–160 

airplanes. This AD requires you to 

inspect the outside tube (cage) that 

supports the main landing gear leg for 

cracks, repair if cracks are found, and 

inspect the thickness of the tube if no 

cracks were found and reinforce the 

tube as necessary. This AD results from 

mandatory continuing airworthiness 

information (MCAI) issued by the 

airworthiness authority for Germany. 

We are issuing this AD to detect, 

correct, and prevent future cracks in the 

outside tube of the main landing gear 

leg, which could result in structural 

failure of the fuselage tubing assembly. 

This failure could lead to loss of control 

of the airplane.

DATES: This AD becomes effective on 

December 28, 2004. 

As of December 28, 2004, the Director 

of the Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulation.

ADDRESSES: To get the service 

information identified in this AD, 

contact Ostmecklenburgische 

Flugzeugbau GmbH, Flughafenstrasse, 

17039 Trollenhagen, Federal Republic 

of Germany; telephone: 011 49 395 

42560–0; facsimile: 011 49 395 42560–

20. To review this service information, 

go to the National Archives and Records 

Administration (NARA). For 

information on the availability of this 

material at NARA, go to: http://

www.archives.gov/federal_register/

code_of_federal_regulations/

ibr_locations.html or call (202) 741–

6030. 

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 20590–

001 or on the Internet at http://

dms.dot.gov. The docket number is 

2003–CE–67–AD.

FOR FURTHER INFORMATION CONTACT: Karl 

Schletzbaum, Aerospace Engineer, 

ACE–112, Small Airplane Directorate, 

901 Locust, Room 301, Kansas City, 

Missouri, 64106; telephone: (816) 329–

4146; facsimile: (816) 329–4149.

SUPPLEMENTARY INFORMATION:

Discussion 

What events have caused this AD?

The Luftfahrt-Bundesamt (LBA), which 

is the airworthiness authority for 

Germany, recently notified the FAA that 

an unsafe condition may exist on certain 

OMF Model OMF–100–160 airplanes. 

The LBA reports that the manufacturer 

received a report of cracks in the outside 

fuselage tube that supports the main 

landing gear leg. Further investigation 

revealed that one manufacturer of 

fuselage tubes used out-of-design 

dimensions for the tube elements. 

What is the potential impact if FAA 

took no action? Cracks in the outside 

tube of the main landing gear leg, if not 

detected, corrected, and prevented, 

could result in structural failure of the 

fuselage tubing assembly. This failure 

could lead to loss of control of the 

airplane. 

Has FAA taken any action to this 

point? We issued a proposal to amend 

part 39 of the Federal Aviation 

Regulations (14 CFR part 39) to include 

an AD that would apply to certain OMF 

Model OMF–100–160 airplanes. This 

proposal was published in the Federal 

Register as a notice of proposed 

rulemaking (NPRM) on August 18, 2004, 

(69 FR 51206). The NPRM proposed to 

detect, correct, and prevent future 

cracks in the outside tube of the main 

landing gear leg. These cracks could 

result in structural failure of the 

fuselage tubing assembly and lead to 

loss of control of the airplane. 

Comments 

Was the public invited to comment?

We provided the public the opportunity 

to participate in developing this AD. We 

received no comments on the proposal 

or on the determination of the cost to 

the public. 

Conclusion 

What is FAA’s final determination on 

this issue? We have carefully reviewed 

the available data and determined that 

air safety and the public interest require 

adopting the AD as proposed except for 

minor editorial corrections. We have 

determined that these minor 

corrections: 

—Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

—Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Changes to 14 CFR Part 39—Effect on 

the AD 

How does the revision to 14 CFR part 

39 affect this AD? On July 10, 2002, the 

FAA published a new version of 14 CFR 

part 39 (67 FR 47997, July 22, 2002), 

which governs the FAA’s AD system. 

This regulation now includes material 

that relates to altered products, special 

flight permits, and alternative methods 

of compliance. This material previously 

was included in each individual AD. 

Since this material is included in 14 

CFR part 39, we will not include it in 

future AD actions. 

Costs of Compliance 

How many airplanes does this AD 

impact? We estimate that this AD affects 

11 airplanes in the U.S. registry.

What is the cost impact of this AD on 

owners/operators of the affected 

airplanes? We estimate the following 

costs to accomplish the inspections:

Labor cost Parts cost Total cost 

per airplane 

Total cost on U.S.

operators 

Inspection for cracks—2 workhours est. $65 per hour = $130 ...................... N/A $130 $1,430. 

Inspection for inadequate thickness of tubing that supports the main landing gear leg—2 workhours est. $65 per hour = $130.N/A 130 OMF will cover the cost for the special inspection.