[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