[Federal Register: June 30, 2003 (Volume 68, Number 125)]
[Rules and Regulations]
[Page 38590-38592]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr30jn03-4]
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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: 9-ane-adcomment@faa.gov
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]
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