[Federal Register Volume 71, Number 45 (Wednesday, March 8, 2006)]
[Proposed Rules]
[Pages 11546-11549]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-3260]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 71, No. 45 / Wednesday, March 8, 2006 / 
Proposed Rules  

[[Page 11546]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23706; Directorate Identifier 2006-NE-03-AD]
RIN 2120-AA64


Airworthiness Directives; Honeywell International Inc. TPE331 
Series Turboprop Engines

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for Honeywell International Inc. TPE331 series turboprop engines with 
certain part numbers of Woodward fuel control assemblies installed. 
This proposed AD would require initial and repetitive dimensional 
inspections of the splines between the fuel pump and fuel control, for 
wear or damage. This proposed AD would also require replacing those 
fuel control assemblies with serviceable modified fuel control 
assemblies with improved overspeed protection. This proposed AD results 
from reports of loss of the drive between the fuel pump and fuel 
control, leading to engine overspeed, overtorque, overtemperature, 
uncontained rotor failure, and asymmetric thrust in multi-engine 
airplanes. We are proposing this AD to prevent rapid, uncommanded, 
uncontrolled increase in fuel flow to the engine, asymmetric thrust, 
uncontained rotor failure, and damage to the airplane.

DATES: We must receive any comments on this proposed AD by May 8, 2006.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD.
     DOT Docket Web site: Go to
http://dms.dot.gov and follow the instructions for sending your 
comments electronically.
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-0001.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    You can get the service information identified in this proposed AD 
from Honeywell Engines, Systems & Services, Technical Data 
Distribution, M/S 2101-201, P.O. Box 52170, Phoenix, AZ 85072-2170; 
telephone: (602) 365-2493 (General Aviation); (602) 365-5535 
(Commercial); fax: (602) 365-5577 (General Aviation and Commercial).
    You may examine the comments on this proposed AD in the AD docket 
on the Internet at http://dms.dot.gov.

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.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send us any written relevant data, views, or 
arguments regarding this proposal. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2006-23706; 
Directorate Identifier 2006-NE-03-AD'' in the subject line of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://dms.dot.govROW including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of the 
DOT Web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You may review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78) or you 
may visit http://dms.dot.gov.

Examining the AD Docket

    You may examine the docket that contains the proposal, any comments 
received and, any final disposition in person at the DOT Docket Office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Office (telephone (800) 647-5227) is located on 
the plaza level of the Department of Transportation Nassif Building at 
the street address stated in ADDRESSES. Comments will be available in 
the AD docket shortly after the Docket Management Facility receives 
them.

Discussion

    Within the past 30 years, we have received reports of 51 broken, 
sheared, or excessively worn fuel pump/fuel control drive splines on 
TPE331 series engines, which have resulted in operational anomalies 
such as uncontrollable fuel flow, overtorques, or overspeeds. In 11 of 
these reports, failed fuel pump drive shafts led to engine overspeed. 
Five of those overspeed events caused a turbine wheel to separate.
    While investigating the noted service events, we determined that 
the loss of drive between the engine-driven fuel pump and the fuel 
control governor system, results in a rapid, uncommanded, and 
uncontrolled increase in engine fuel flow. The effects of fuel flow 
increase could include overspeed, overtorque, overtemperature of the 
engine, significant asymmetric thrust, inability to produce reverse 
thrust, and uncontained separation of high speed rotating components. 
This condition, if not corrected, could result in rapid, uncommanded, 
uncontrolled increase in fuel flow to the engine, uncontained failure, 
and damage to the aircraft.
    This proposed AD would require initial and repetitive dimensional 
inspections of the splines between the fuel pump and fuel control, for 
wear or damage, and replacement of the fuel control if an unserviceable 
condition

[[Page 11547]]

exists. The proposed AD would also require eventual replacement of 
affected fuel controls with an improved fuel control, which better 
accommodates drive spline failure by eliminating the overspeed 
condition. This remove and replace requirement is a terminating action 
to inspections for all installations. However, for the optional method 
of compliance explained in paragraph (l), for agricultural operations, 
removal and replacement is not required, as discussed below.
    Agricultural operations at low altitude and heavy loads place 
special demands on aircraft operating in that environment. For example, 
high power and, therefore, high fuel flow, is necessary for an aircraft 
engaged in agricultural spraying to avoid power lines, utility poles, 
trees, and buildings (including silos). We consider a sudden power loss 
or inability to maintain altitude close to the ground more hazardous 
than managing an engine overspeed and overtorque event. Operations 
other than agricultural operations, are not exposed to these hazards. 
Therefore, we propose to allow continued use of existing fuel control 
assemblies in agricultural operations, and control the rate of failure 
with a repetitive inspection program for those limited number of 
engines.
    The Agency is committed to updating the aviation community of 
expected costs associated with the MU-2B series airplane safety 
evaluation conducted in 2005. As a result of that commitment, the 
accumulating expected costs of all ADs related to the MU-2B series 
airplane safety evaluation may be found at the following Web site: 
http://www.faa.gov/aircraft/air_cert/design_approvals/small_airplanes/cos/mu2_foia_reading_library/.

Relevant Service Information

    We have reviewed and approved the technical contents of Honeywell 
International Inc. Alert Service Bulletin (ASB) No. TPE331-A73-0254, 
Revision 2, dated June 17, 2005; ASB No. TPE331-A73-0262, Revision 2, 
dated June 17, 2005; and ASB No. TPE331-A73-0271, Revision 1, dated 
January 25, 2006, that describe procedures for replacing affected fuel 
control assemblies with serviceable modified fuel control assemblies. 
Also we have reviewed the dimensional inspection requirements of the 
fuel control/fuel pump mating splines in the applicable maintenance 
manuals.

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

    This proposed AD adds a compliance time of no later than December 
31, 2012. Also, this proposed AD provides repetitive inspection 
requirements as an optional method of compliance to installing modified 
fuel control assemblies for single-engine airplanes used for 
agricultural operations.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other products 
of this same type design. We are proposing this AD, which would 
require:
     Performing initial and repetitive fuel control/fuel pump 
mating spline inspections.
     Replacing the Woodward fuel control assemblies listed by 
part number in the compliance section, with serviceable modified fuel 
control assemblies with improved overspeed protection, the next time 
the fuel control assembly is removed, but not later than December 31, 
2012.
     As an optional method of compliance, performing repetitive 
fuel control/fuel pump mating spline inspections for engines installed 
on single-engine airplanes used for agricultural operations without 
having to install a modified fuel control.

Costs of Compliance

    We estimate this proposed AD would affect 3,250 engines installed 
on airplanes of U.S. registry. We also estimate it would take about one 
work hour per engine to replace the fuel control assembly during a 
normal scheduled overhaul. We also estimate it would take about three 
work hours to perform a dimensional inspection of the fuel control/fuel 
pump mating splines. The average labor rate is $65 per work hour. A 
replacement fuel control assembly would cost about $9,700 per engine. 
We estimate that on each engine one fuel control inspection would be 
performed, and each engine would have the fuel control replaced. Based 
on these figures, we estimate the total cost of the proposed AD to U.S. 
operators to be $32,370,000.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD 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.
    For the reasons discussed above, I certify that the proposed 
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. Would 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 regulatory evaluation of the estimated costs to 
comply with this proposed AD. See the ADDRESSES section for a location 
to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Under the authority delegated to me by the Administrator, the 
Federal Aviation Administration proposes to amend 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. The FAA amends Sec.  39.13 by adding the following new 
airworthiness directive:

Honeywell International Inc. (formerly AlliedSignal Inc., Garrett 
Engine

[[Page 11548]]

Division; Garrett Turbine Engine Company; and AiResearch 
Manufacturing Company of Arizona): Docket No. FAA-2006-23706; 
Directorate Identifier 2006-NE-03-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this airworthiness directive (AD) action by May 8, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Honeywell International Inc. TPE331-1, -
2, -2UA, -3U, -3UW, -5, -5A, -5AB, -5B, -6, -6A, -10, -10AV, -10GP, 
-10GT, -10P, -10R, -10T, -10U, -10UA, -10UF, -10UG, -10UGR, -10UR, -
11U, -12JR, -12UA, -12UAR, and -12UHR turboprop engines with the 
part numbers (P/Ns) of Woodward fuel control assemblies listed in 
this AD, installed. These engines are installed on, but not limited 
to, the following airplanes:

------------------------------------------------------------------------
              Manufacturer                            Model
------------------------------------------------------------------------
AERO PLANES, LLC (formerly McKinnon      G-21G.
 Enterprises).
ALLIED AG CAT PRODUCTIONS (formerly      G-164 SERIES.
 Schweizer).
AYRES..................................  S-2R SERIES.
BRITISH AEROSPACE LTD (formerly          3101 AND 3201 SERIES, AND
 Jetstream).                              HP.137 JETSTREAM MK.1.
CONSTRUCCIONES AERONAUTICAS, S.A.        C-212 SERIES.
 (CASA).
DEHAVILLAND............................  DH104 SERIES 7AXC (DOVE).
DORNIER................................  228 SERIES.
FAIRCHILD..............................  SA226 AND SA227 SERIES
                                          (SWEARINGEN MERLIN AND METRO
                                          SERIES).
GRUMMAN AMERICAN.......................  G-164 SERIES.
MITSUBISHI.............................  MU-2B SERIES (MU-2 SERIES).
PILATUS................................  PC-6 SERIES (FAIRCHILD PORTER
                                          AND PEACEMAKER).
POLSKIE ZAKLADY LOTNICZE SPOLKA          PZL M18, PZL M18A, PZL M18B.
 (formerly Wytwornia Sprzetu
 Komunikacyjnego).
PROP-JETS, INC.........................  400.
RAYTHEON AIRCRAFT (formerly Beech).....  C45G, TC-45G, C-45H, TC-45H, Tc-
                                          45J. G18S, E18S-9700, D18S,
                                          D18C, H18, RC-45J, JRB-6, UC-
                                          45J, 3N, 3NM, 3TM, B100, C90
                                          AND E90.
SHORTS BROTHERS AND HARLAND, LTD.......  SC7 (SKYVAN) SERIES.
THRUSH (ROCKWELL COMMANDER)............  S-2R.
TWIN COMMANDER (JETPROP COMMAMDER).....  680, 690 AND 695 SERIES.
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD results from reports of loss of the drive between 
the fuel pump and fuel control, leading to engine overspeed, 
overtorque, overtemperature, uncontained rotor failure, and 
asymmetric thrust in multi-engine airplanes. We are issuing this AD 
to prevent rapid, uncommanded, uncontrolled increase in fuel flow to 
the engine, asymmetric thrust, uncontained rotor failure, and damage 
to the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified unless the 
actions have already been done.

Initial Inspection

    (f) At the next scheduled inspection of the fuel control 
assembly and fuel pump mating splines, but within 1,000 hours-in-
service after the effective date of this AD:
    (1) Perform an initial dimensional inspection of the splines 
between the fuel pump and fuel control, for wear or damage. 
Information on spline inspection can be found in Section 72-00-00 of 
the applicable maintenance manuals.
    (2) Repair or replace the fuel control assembly if the splines 
fail the dimensional inspection, with any serviceable fuel control 
assembly.

Repetitive Inspections

    (g) Thereafter, within 1,000 hours since-last-inspection:
    (1) Perform repetitive dimensional inspections of the splines 
between the fuel pump and fuel control, for wear or damage. 
Information on spline inspection can be found in Section 72-00-00 of 
the applicable maintenance manuals.
    (2) Repair or replace the fuel control assembly if the splines 
fail the dimensional inspection, with any serviceable fuel control 
assembly.

TPE331-1, -2, and -2UA Series Engines

    (h) For TPE331-1, -2, and -2UA series engines, replace Woodward 
fuel control assemblies, P/Ns 869199-13/ -20/ -21/ -22/ -23/ -24/ -
25/ -26/ -27/ -28/ -29/ -31/ -32/ -33/ -34 and -35, with a 
serviceable, modified fuel control assembly the next time the fuel 
control assembly is removed for cause that requires return, or when 
the fuel control assembly requires overhaul, but not later than 
December 31, 2012. Information on replacement fuel control assembly 
P/Ns, configuration management, rework, and replacement information, 
can be found in Honeywell Alert Service Bulletin (ASB) No. TPE331-
A73-0271, Revision 1, dated January 25, 2006.

TPE331-3U, -3UW, -5, -5A, -5AB, -5B, -6, -6A, -10AV, -10GP, -10GT, -
10P, and -10T Series Engines

    (i) For TPE331-3U, -3UW, -5, -5A, -5AB, -5B, -6, -6A, -10AV, -
10GP, -10GT, -10P, and -10T series engines, replace Woodward fuel 
control assemblies, P/Ns 893561-7/ -8/ -9/ -10/ -11/ -14/ -15/ -16/ 
-20/ -26/ -27 and -29, and P/Ns 897770-1/ -3/ -7/ -9/ -10/ -11/ -12/ 
-14/ -15/ -16/ -25/ -26 and -28, with a serviceable, modified fuel 
control assembly the next time the fuel control assembly is removed 
for cause that requires return, or when the fuel control assembly 
requires overhaul, but not later than December 31, 2012. Information 
on replacement fuel control assembly P/Ns, configuration management, 
rework, and replacement information, can be found in Honeywell ASB 
No. TPE331-A73-0262, Revision 2, dated June 17, 2005.

TPE331-10, -10R, -10U, -10UA, -10UF, -10UG, -10UGR, -10UR, -11U, -12JR, 
-12UA, -12UAR, and -12UHR Series Engines

    (j) For TPE331-10, -10R, -10U, -10UA, -10UF, -10UG, -10UGR, -
10UR, -11U, -12JR, -12UA, -12UAR, and -12UHR series engines, replace 
Woodward fuel control assemblies, P/Ns 897375-2/ -3/ -4/ -5/ -8/ -9/ 
-10/ -11/ -12/ -13/ -14/ -15/ -16/ -17/ -19/ -21/ -24/ -25/ -26 and 
-27, and P/Ns 897780-1/ -2/ -3/ -4/ -5/ -6/ -7/ -8/ -9/ -10/ -11/ -
14/ -15/ -16/ -17/ -18/ -19/ -20/ -21/ -22/ -23/ -24/ -25/ -26/ -27/ 
-30/ -32/ -34/ -36/ -37 and -38, and P/Ns 893561-17/ -18 and -19, 
with a serviceable, modified fuel control assembly the next time the 
fuel control assembly is removed for cause that requires return, or 
when the fuel control assembly requires overhaul, but not later than 
December 31, 2012. Information on replacement fuel control assembly 
P/Ns, configuration management, rework, and replacement information, 
can be found in Honeywell ASB TPE331-A73-0254, Revision 2, dated 
June 17, 2005.

Definitions

    (k) For the purposes of this AD:
    (1) A serviceable, modified fuel control assembly for engines 
affected by paragraph (h), (i), or (j) of this AD, is a fuel control 
assembly with a P/N not listed in this AD.
    (2) A removal for cause that requires return, for engines 
affected by paragraph (h),

[[Page 11549]]

(i), or (j) of this AD, is a fuel control assembly that has 
displayed an unserviceable or unacceptable operating condition 
requiring the fuel control to be removed and sent to a repair or 
overhaul shop.

Optional Method of Compliance for TPE331 Series Engines Installed On 
Single-Engine Airplanes Used for Agricultural Operations

    (l) As an optional method of compliance to paragraph (h), (i), 
or (j), for TPE331 series engines installed on single-engine 
airplanes used for agricultural operations, having an affected 
Woodward fuel control assembly:
    (1) Continue repetitive dimensional inspections of the splines 
between the fuel pump and fuel control, for wear or damage as 
specified in paragraph (g) of this AD.
    (2) Repair or replace the fuel control assembly if the splines 
fail the dimensional inspection, with any serviceable fuel control 
assembly.
    (3) Installation of a serviceable, modified fuel control 
assembly is not required.

Terminating Action

    (m) Performing a fuel control assembly replacement as specified 
in paragraph (h), (i), or (j) of this AD, is terminating action for 
the initial and repetitive inspections required by this AD.

Alternative Methods of Compliance

    (n) The Manager, Los Angeles Aircraft Certification Office, has 
the authority to approve alternative methods of compliance for this 
AD if requested using the procedures found in 14 CFR 39.19.

Related Information

    (o) None.

    Issued in Burlington, Massachusetts, on March 2, 2006.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E6-3260 Filed 3-7-06; 8:45 am]
BILLING CODE 4910-13-P