Airworthiness Directives; Rolls-Royce Corporation (Formerly Allison Engine Company) 250-C20 Series Turboshaft and 250-B17 Series Turboprop Engines

[Federal Register Volume 66, Number 233 (Tuesday, December 4, 2001)]
[Rules and Regulations]
[Pages 62915-62916]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-29950]



[[Page 62915]]

=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NE-38-AD; Amendment 39-12529; AD 2001-24-12]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce Corporation (Formerly 
Allison Engine Company) 250-C20 Series Turboshaft and 250-B17 Series 
Turboprop Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule, request for comments.

-----------------------------------------------------------------------

SUMMARY: This amendment supersedes an emergency airworthiness directive 
(AD) that was sent previously to all known U.S. owners and operators of 
Rolls-Royce Corporation (formerly Allison Engine Company) models 250-
C20, -C20B, -C20F, -C20R, -C20R/1, -C20R/2, -C20S, and -C20W turboshaft 
engines, and 250-B17, -B17C, -B17D, -B17E, -B17F, -B17F/1, and -B17F/2 
turboprop engines by individual letters. That action required 
replacement of any helical torquemeter gearshaft assembly with 100 
hours or less time-since-new (TSN) with a serviceable helical 
torquemeter gearshaft assembly, before further flight. That amendment 
was prompted by a report of uncontained release of power turbine blades 
and disk fragments caused by engine overspeed, resulting in an 
uncommanded engine shutdown, engine fire, and damage to the aircraft. 
This amendment requires the same replacement, and adds engine model -
250-C20J to the applicability section of this AD. The actions specified 
by this AD are intended to prevent uncontained release of power turbine 
blades and disk fragments caused by engine overspeed, resulting in an 
uncommanded engine shutdown, engine fire, and damage to the aircraft.

DATES: Effective December 19, 2001.
    Comments for inclusion in the Rules Docket must be received on or 
before February 4, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2001-NE-38-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may be inspected at 
this location, by appointment, between 8 a.m. and 4:30 p.m., Monday 
through Friday, except Federal holidays. Comments may also be sent via 
the Internet using the following address: ``[email protected]''. 
Comments sent via the Internet must contain the docket number in the 
subject line.

FOR FURTHER INFORMATION CONTACT: John Tallarovic, Aerospace Engineer, 
Chicago Aircraft Certification Office, FAA, Small Airplane Directorate, 
2300 East Devon Avenue, Des Plaines, IL 60018; telephone (847) 294-
8180, fax (847) 294-7834.

SUPPLEMENTARY INFORMATION: On October 3, 2001, the Federal Aviation 
Administration (FAA) issued Emergency Airworthiness Directive (AD) 
2001-20-51, applicable to Rolls-Royce Corporation (formerly Allison 
Engine Company) models 250-C20, -C20B, -C20F, -C20R, -C20R/1, -C20R/2, 
-C20S, and -C20W turboshaft engines, and 250-B17, -B17C, -B17D, -B17E, 
-B17F, -B17F/1, and -B17F/2 turboprop engines, which requires 
replacement of any helical torquemeter gearshaft assembly with 100 
hours or less time-since-new (TSN) with a serviceable helical 
torquemeter gearshaft assembly, before further flight. That action was 
prompted by a report of uncontained release of power turbine blades and 
disk fragments caused by engine overspeed, resulting in an uncommanded 
engine shutdown, engine fire, and damage to the aircraft. This 
condition, if not corrected, could result in uncontained release of 
power turbine blades and disk fragments caused by engine overspeed, 
resulting in an uncommanded engine shutdown, engine fire, and damage to 
the aircraft. Since that Emergency AD was issued, it has been found 
that engine model 250-C20J was inadvertantly omitted from emergency AD 
2001-20-51, and is added to the applicability section of this AD.

FAA's Determination of an Unsafe Condition and Required Actions

    Since the unsafe condition described is likely to exist or develop 
on other engines of the same type design, the FAA issued emergency AD 
2001-20-51 to prevent uncontained release of power turbine blades and 
disk fragments caused by engine overspeed, resulting in an uncommanded 
engine shutdown, engine fire, and damage to the aircraft. This AD 
requires replacement of any helical torquemeter gearshaft assembly with 
100 hours or less time-since-new (TSN) with a serviceable helical 
torquemeter gearshaft assembly, before further flight.

Immediate Adoption of This AD

    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunuty for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this rule by 
submitting such written data, views, or arguments as they may desire. 
Communications should identify the Rules Docket number and be submitted 
in triplicate to the address specified under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the 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 that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2001-NE-38.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Analysis

    This final rule does not have federalism implications, as defined 
in Executive Order 13132, because it 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. Accordingly, 
the FAA has not consulted with state authorities prior to publication 
of this final rule.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to

[[Page 62916]]

correct an unsafe condition in aircraft, and is not a ``significant 
regulatory action'' under Executive Order 12866. It has been determined 
further that this action involves an emergency regulation under DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979). If 
it is determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, may be obtained from the Rules Docket at the 
location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

    Accordingly, pursuant to 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

    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]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

2001-24-12  Rolls-Royce Corporation (formerly Allison Engine 
Company): Amendment 39-12529. Docket No. 2001-NE-38-AD.

Applicability

    This airworthiness directive (AD) is applicable to Rolls-Royce 
Corporation (formerly Allison Engine Company) models 250-C20, -C20B, 
-C20F, -C20J, -C20R, -C20R/1, -C20R/2, -C20S, and -C20W turboshaft 
engines, and 250-B17, -B17C, -B17D, -B17E, -B17F, -B17F/1, and -
B17F/2 turboprop engines. These engines are used on, but not limited 
to Aerospatiale AS355; Agusta A109; A109A, A109C; Bell 206B, 206L, 
206LT; Enstrom TH28; McDonnell Douglas 500C, 500D, 500E, 520N; 
Rogerson-Hiller FH1100; Schweizer TH330; Soloy Conversions Bell 47/
47G, Hiller UH-12; American Jet Industries/Cessna 402, 414; and 
ASTA/GAF Nomad N-22 aircraft.

    Note 1: This AD applies to each engine identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For engines that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (d) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

Compliance

    Compliance with this AD is required as indicated, unless already 
done.
    To prevent uncontained release of power turbine blades and disk 
fragments caused by engine overspeed, resulting in an uncommanded 
engine shutdown, engine fire, and damage to the aircraft, do the 
following:
    (a) Before further flight, remove helical torquemeter gearshaft 
assemblies part numbers (P/N's) 23035299 and 23038191 that have 
accumulated 100 hours or less time-since-new (TSN). Replace with a 
serviceable helical torquemeter gearshaft assembly.
    (b) After the receipt of this AD, do not install any helical 
torquemeter gearshaft assembly P/N 23035299 or 23038191 that has 
accumulated 100 hours or less TSN.

Definition

    (c) For the purposes of this AD, the following helical 
torquemeter gearshaft assemblies are considered serviceable parts:
    (1) P/N's 23035299 and 23038191 that have greater than 100 hours 
TSN.
    (2) An assembly with a P/N other than P/N's 23035299 and 
23038191.

Alternative Methods of Compliance

    (d) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Chicago Aircraft Certification 
Office. Operators must submit their requests through an appropriate 
FAA Principal Maintenance Inspector, who may add comments and then 
send it to the Manager, Chicago Aircraft Certification Office.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this airworthiness directive, 
if any, may be obtained from the Chicago Aircraft Certification 
Office.

Special Flight Permits

    (e) Special flight permits may be issued in accordance with 
21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 
and 21.199) to operate the aircraft to a location where the 
requirements of this AD can be done.

Effective Date of This AD

    (f) This amendment becomes effective December 19, 2001.

    Issued in Burlington, Massachusetts, on November 27, 2001.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 01-29950 Filed 12-3-01; 8:45 am]
BILLING CODE 4910-13-U

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T04:24:35.813186+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

5ce15630e80c2d06396a2c73ea54cb1e62e6469a1443ecaeca9f9d3c5a79c45b

Text SHA-256

2162d037e6f737c424803727274e7922be14b64586a1696b8f2f74ee52e1770a