Airworthiness Directives; Rolls-Royce Corporation (Formerly Allison Engine Company, Allison Gas Turbine Division, and Detroit Diesel Allison) Models 250-C30R/3, -C30R/3M, -C47B, and -C47M Turboshaft Engines

[Federal Register Volume 68, Number 125 (Monday, June 30, 2003)]
[Rules and Regulations]
[Pages 38590-38592]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-15993]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NE-23-AD; Amendment 39-13210; AD 2003-13-10]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce Corporation (Formerly 
Allison Engine Company, Allison Gas Turbine Division, and Detroit 
Diesel Allison) Models 250-C30R/3, -C30R/3M, -C47B, and -C47M 
Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
Rolls-Royce Corporation (formerly Allison Engine Company, Allison Gas 
Turbine Division, and Detroit Diesel Allison) models 250-C30R/3, -C30R/
3M, -C47B, and -C47M turboshaft engines. This AD requires initial and 
repetitive electrical signal inspections of the hydromechanical unit 
(HMU) Power Lever Angle (PLA) potentiometer. This AD is prompted by an 
investigation by the National Transportation Safety Board (NTSB), which 
revealed that a potential undetected failure of the PLA potentiometer 
electrical signal could cause uncommanded and sudden changes in engine 
power. The actions specified in this AD are intended to prevent 
uncommanded and sudden changes in engine power.

DATES: Effective July 15, 2003. The Director of the Federal Register 
approved the incorporation by reference of certain publications listed 
in the regulations as of July 15, 2003.
    We must receive any comments on this AD by August 29, 2003.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD:

    [sbull] By mail: The Federal Aviation Administration (FAA), New 
England Region, Office of the Regional Counsel, Attention: Rules Docket 
No. 2003-NE-23-AD, 12 New England Executive Park, Burlington, MA 01803-
5299.
    [sbull] By fax: (781) 238-7055.
    [sbull] By e-mail: [email protected]
    You may get the service information referenced 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 Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

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: This AD applies to Rolls-Royce Corporation 
models 250-C30R/3, -C30R/3M, -C47B, and -C47M turboshaft engines. This 
AD requires initial and repetitive electrical signal inspections of the 
HMU PLA

[[Page 38591]]

potentiometer. This AD is prompted by an investigation by the NTSB into 
uncommanded and sudden changes in engine power on a Bell 407 helicopter 
on March 27, 2003. The NTSB investigation revealed that a potential 
undetected failure of the PLA potentiometer electrical signal, provided 
by the HMU of the full-authority digital electronic control (FADEC) 
system, could cause uncommanded and sudden changes in engine power. The 
actions specified in this AD are intended to prevent uncommanded and 
sudden changes in engine power.

Relevant Service Information

    We have reviewed and approved the technical contents of section 
2.B. of the Accomplishment Instructions of Rolls-Royce Corporation 
combined Service Bulletin (SB) CEB A-73-3103 (250-C30 engines) and CEB 
A-73-6030 (250-C47 engines), Revision 3, dated June 5, 2003, that 
describes procedures for inspecting the PLA potentiometer signal.

Differences Between This Proposed AD and the Manufacturer's Service 
Information

    Although the combined SB CEB A-73-3103 (250-C30 engines) and CEB A-
73-6030 (250-C47 engines), Revision 3, dated June 5, 2003, also 
includes 250-C40 engines, as CEB A-73-5021, the 250-C40 engine model is 
not affected by this AD because it is used in twin engine applications.

FAA's Determination and Requirements of This AD

    The unsafe condition described previously is likely to exist or 
develop on other Rolls-Royce Corporation (formerly Allison Engine 
Company, Allison Gas Turbine Division, and Detroit Diesel Allison) 
models 250-C30R/3, -C30R/3M, -C47B, and -C47M turboshaft engines of the 
same type design. Therefore, we are issuing this AD to prevent 
uncommanded and sudden changes in engine power. This AD requires an 
initial electrical signal inspection of the HMU PLA potentiometer 
within 50 flight hours after the effective date of this AD, but no 
later than July 15, 2003, and thereafter, repetitive inspections every 
300 flight hours. You must do these inspections in accordance with the 
service information described previously.

FAA's Determination of the Effective Date

    Since an unsafe condition exists that requires the immediate 
adoption of this AD, we have found that notice and opportunity for 
prior public comment are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Changes to 14 CFR Part 39--Effect on the AD

    On July 10, 2002, we issued a new version of 14 CFR part 39 (67 FR 
47997, July 22, 2002), which governs our AD system. This regulation now 
includes material that relates to special flight permits, alternative 
methods of compliance, and altered products. 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.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment; however, we invite you to submit any written relevant data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``AD Docket No. 2003-NE-23-AD'' in the 
subject line of your comments. If you want us to acknowledge receipt of 
your mailed comments, send us a self-addressed, stamped postcard with 
the docket number written on it; we will date-stamp your postcard and 
mail it back to you. We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of the rule 
that might suggest a need to modify it. If a person contacts us through 
a nonwritten communication, and that contact relates to a substantive 
part of this AD, we will summarize the contact and place the summary in 
the docket. We will consider all comments received by the closing date 
and may amend the AD in light of those comments.
    We are reviewing the writing style we currently use in regulatory 
documents. We are interested in your comments on whether the style of 
this document is clear, and your suggestions to improve the clarity of 
our communications with you. You may get more information about plain 
language at http://www.plainlanguage.gov.

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 the 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. 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 part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

2003-13-10 Rolls-Royce Corporation (formerly Allison Engine Company, 
Allison Gas Turbine Division, and Detroit Diesel Allison): Amendment 
39-13210. Docket No. 2003-NE-23-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective July 15, 
2003.

Affected ADs

    (b) None.

Applicability

    (c) This AD is applicable to Rolls-Royce Corporation (formerly 
Allison Engine Company, Allison Gas Turbine Division, and Detroit 
Diesel Allison) models 250-C30R/3, -C30R/3M, -C47B, and -C47M 
turboshaft engines. 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 was prompted by an investigation by the National 
Transportation Safety Board that revealed that a potential 
undetected failure of the Power Lever Angle (PLA) potentiometer 
electrical signal could cause uncommanded and sudden changes in

[[Page 38592]]

engine power. 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 
hydromechanical unit (HMU) PLA potentiometer, within 50 flight hours 
after the effective date of this AD, but no later than July 15, 
2003, in accordance with paragraph 2.B. of the Accomplishment 
Instructions of Rolls-Royce Corporation combined service bulletin 
(SB) No. CEB A-73-3103 (250-C30 engines), or CEB A-73-6030 (250-C47 
engines), Revision 3, dated June 5, 2003.
    (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 flight hours of the previous 
inspection, in accordance with section 2.B. of the Accomplishment 
Instructions of Rolls-Royce Corporation combined SB No. CEB A-73-
3103 (250-C30 engines), or CEB A-73-6030 (250-C47 engines), Revision 
3, dated June 5, 2003.
    (i) Replace the HMU before further flight if the electrical 
signal inspection is unacceptable.

Alternative Methods of Compliance

    (j) 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

    (k) The inspections in this AD must be done in accordance with 
section 2.B. of the Accomplishment Instructions of Rolls-Royce 
Corporation combined Service Bulletin (SB) CEB A-73-3103 (250-C30 
engines) and CEB A-73-6030 (250-C47 engines), Revision 3, dated June 
5, 2003. The Director of the Federal Register approved the 
incorporation by reference of this document in accordance with 5 
U.S.C. 552(a) and 1 CFR part 51. You may get a copy from Rolls-Royce 
Corporation, P.O. Box 420, Indianapolis, IN 46206-0420; telephone 
(317) 230-6400; fax (317) 230-4243. 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 Office of the 
Federal Register, 800 North Capitol Street, NW, suite 700, 
Washington, DC.

Related Information

    (l) None.

    Issued in Burlington, Massachusetts, on June 19, 2003.
Robert G. Mann,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 03-15993 Filed 6-27-03; 8:45 am]
BILLING CODE 4910-13-P

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