[Federal Register Volume 66, Number 203 (Friday, October 19, 2001)]
[Rules and Regulations]
[Pages 53083-53085]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-26323]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2000-NE-39-AD; Amendment 39-12472; AD 2001-21-02]
RIN 2120-AA64
Airworthiness Directives; Honeywell International Inc. (formerly
AlliedSignal Inc. and Garrett Turbine Engine Company) TPE331-8, -10N,
and -12B Turboprop Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to Honeywell International Inc. (formerly AlliedSignal
Inc. and Garrett Turbine Engine Company) TPE331-8, -10N, and -12B
turboprop engines with certain electronic engine controls (EEC's)
installed. This AD requires revising the Emergency and Normal
Procedures section of the applicable Airplane Flight Manual (AFM) until
the existing EEC's are replaced. This amendment is prompted by a report
of an engine experiencing an uncommanded full power increase during an
approach while both engine power levers were at the flight idle gate.
The actions specified in this AD are intended to minimize exposure to
flight and ground operations that could lead to the loss of control of
the airplane due to asymmetric thrust and an uncommanded torque
increase.
DATES: Effective November 19, 2001.
Comments for inclusion in the Rules Docket must be received on or
before December 18, 2001.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), New England Region, Office of the Regional
Counsel, Attention: Rules Docket No. 2000-NE-39-AD, 12 New England
Executive Park, Burlington, MA 01803-5299. 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.
The temporary revisions referenced in this AD may be obtained from
Cessna Propeller Aircraft Customer Service, P.O. Box 7706, Wichita,
Kansas, 67277; telephone: (316) 517-5800, fax: (316) 517-7271.
FOR FURTHER INFORMATION CONTACT: Joseph Costa, Aerospace Engineer, Los
Angeles Aircraft Certification Office, FAA, Transport Airplane
Directorate, 3960 Paramount Blvd., Lakewood, CA 90712-4137; telephone
(562) 627-5246; fax (562) 627-5210. Contact Bob Adamson, Aerospace
Engineer, Wichita Aircraft Certification Office, 1801 Airport Road,
Room 100, Wichita KS 67209; telephone (316) 946-4145; fax (316) 946-
4407 with any questions and comments regarding AFM procedures
pertaining to this AD.
SUPPLEMENTARY INFORMATION: In September 1999, a TPE331-10N turboprop
engine experienced an uncommanded increase to full power during an
approach while both engine power levers were at the flight idle gate.
The pilot aborted the approach and re-established power symmetry by
applying full power to the opposite engine. After reverting to manual
mode, the pilot made a safe landing. Based on engine-propeller stand
testing of certain engine control configurations, and a review of prior
field reports of uncommanded torque or fuel increases, the FAA has
determined that uncommanded torque may peak to 150% within 5 seconds of
an initial torque acceleration. In addition, the number of uncommanded
engine accelerations in service have been gradually increasing. Nine
events of uncommanded power increases have occurred, in varying degrees
of severity, within the past 17 years. This condition, if not
corrected, could result in loss of control of the airplane due to
asymmetric thrust from an uncommanded power increase.
Actions Required by This AD
Since an unsafe condition has been identified that is likely to
exist or develop on other engines of this same type design, this AD
requires a temporary revision to the Emergency and Normal Procedures
section of the applicable FAA Approved AFM for each applicable engine
installation in a multi-engine airplane. The temporary AFM revision
provides procedures for minimizing asymmetric thrust resulting from
uncommanded power increases in flight and on ground. The temporary AFM
revision is effective for an individual multi-engine airplane until the
existing EEC for each engine is replaced with a redesigned and reworked
EEC. These AFM changes have been coordinated with the FAA Certification
Office responsible for the certification of the airplanes involved.
The rework and testing of the EEC can only be accomplished at
Honeywell's Repair Station in Tucson, Arizona, whose repair capacity
and rate-of-repair is limited. The FAA has determined that the July 23,
2003 date was the earliest date to complete the rework and testing of
all 775 existing EEC's. This determination assumes that the operator
act expeditiously and coordinate this EEC repair with the Honeywell
Repair Station.
Finding That Immediate Adoption Is Necessary
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity 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
[[Page 53084]]
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 2000-NE-39-AD.'' The postcard will be date stamped and
returned to the commenter.
Regulatory Impact
This amendment 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 rule.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to 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:
2001-21-02 Honeywell International Inc.: Amendment 39-12472. Docket
2000-NE-39-AD.
Applicability
This airworthiness directive (AD) is applicable to Honeywell
International Inc. (formerly AlliedSignal Inc. and Garrett Turbine
Engine Company) TPE331-8, -10N, and -12B turboprop engines with
electronic engine controls (EEC's) part numbers (P/N's) 2101322-1, -
4, -11, -12, -13, -14, -15 or -16 installed. These engines are
installed on but not limited to Cessna Aircraft Company Model 441
Conquest airplanes.
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 or operator must request approval for
an alternative method of compliance in accordance with paragraph (g)
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 minimize exposure to flight and ground operations that could
lead to the loss of control of the airplane due to asymmetric thrust
and an uncommanded torque increase, do the following:
Amending of the Airplane Flight Manual
(a) Within 30 days after the effective date of this AD, amend
the applicable FAA Approved Cessna Airplane Flight Manual (AFM)
Emergency Procedures and Normal Procedures Section to provide
interim emergency procedures to flight crews, by inserting the
Temporary Revisions specified in the following table:
Temporary Revisions by Airplane Model and Serial Number (SN) and AFM
Affected
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Airplane model and serial
No. (SN) AFM affected Temporary revision
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(1) Cessna Model 441; SN's D1561-14-13PH D1561-14TR2 through
441-0001 through 441-0172. through Revision D1561-14, dated
14, dated January 14TR8 dated
9, 1998. November 20, 2000
D1561-14TR9 dated
April 11, 2001.
(2) Cessna Model 441; SN's D1586-11-13PH D1586-11TR2 through
441-0173 and higher. through Revision D1586-11TR5 dated
11, dated January November 20, 2000.
9, 1998.
D1586-11TR7 and
D1586-11TR8 dated
November 20, 2000.
D1586-11TR9 dated
March 7, 2001.
D1586-11TR10 dated
April 11, 2001.
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(b) Owners or operators of airplanes that have been modified by
supplemental type certificate, where the AFM conflicts with the TR's
specified in (a)(1) and (a)(2) of this AD, must contact Los Angeles
Aircraft Certification Office (LAACO) to have their AFM's reviewed
and approved.
Replacement of Electronic Engine Controls
(c) Replace all existing EEC's P/N's 2101322-1, -4, -11, -12, -
13, -14, -15 and -16 with serviceable EECs before August 31, 2003.
(d) Information regarding the replacement of existing EEC's is
available in Honeywell Alert Service Bulletins TPE331-A76-0035 dated
July 23, 2001, TPE331-A76-0036 dated
[[Page 53085]]
July 23, 2001, and TPE331-A76-0037 dated July 23, 2001.
Removal of Temporary Revisions
(e) When all EEC's have been replaced in the airplane with
serviceable EEC's, remove the applicable Temporary Revisions,
specified in the preceding table, from the airplane flight manual.
Definitions
(f) For the purposes of the AD, a serviceable EEC is an EEC with
a P/N that is not specified in this AD.
Alternative Methods of Compliance
(g) 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, LAACO. Operators must submit their
requests through an appropriate FAA Principal Maintenance Inspector,
who may add comments and then send it to the Manager, LAACO.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this airworthiness directive,
if any, may be obtained from the LAACO.
Effective Date of This AD
(h) This amendment becomes effective on November 19, 2001.
Issued in Burlington, Massachusetts, on October 12, 2001.
Thomas A. Boudreau,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 01-26323 Filed 10-18-01; 8:45 am]
BILLING CODE 4910-13-U