
[Federal Register Volume 79, Number 91 (Monday, May 12, 2014)]
[Proposed Rules]
[Pages 26906-26909]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-10783]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0913; Directorate Identifier 2012-NE-23-AD]
RIN 2120-AA64


Airworthiness Directives; Honeywell International Inc. Turboprop 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Honeywell International Inc. TPE331-5, -5A, -5AB, -5B, -10, -
10R, -10U, -10UF, -10UG, -10UGR, and -10UR model turboprop engines. 
This proposed AD was prompted by engine propeller shaft coupling 
failures, leading to unexpected propeller pitch changes resulting in 
high aerodynamic and asymmetric drag on the airplanes using these 
engines. This proposed AD would require removing certain part number 
(P/N) propeller shaft couplings from service. This proposed AD would 
also require inserting a copy of Honeywell International Inc. Operating

[[Page 26907]]

Information Letter OI331-26, dated March 2, 2010, into the applicable 
Airplane Flight Manuals. We are proposing this AD to prevent loss of 
airplane control, leading to an accident.

DATES: We must receive comments on this proposed AD by July 11, 2014.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Honeywell International Inc., 111 S. 34th Street, Phoenix, AZ 85034-
2802; phone: 800-601-3099; Web site: http://portal.honeywell.com. You 
may view this service information at the FAA, Engine & Propeller 
Directorate, 12 New England Executive Park, Burlington, MA. For 
information on the availability of this material at the FAA, call 781-
238-7125.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2012-
0913; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will 
be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Joseph Costa, Aerospace Engineer, Los 
Angeles Aircraft Certification Office, FAA, Transport Airplane 
Directorate, 3960 Paramount Blvd., Lakewood, CA 90712-4137; phone: 562-
627-5246; fax: 562-627-5210; email: joseph.costa@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2012-0913; 
Directorate Identifier 2012-NE-23-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We have received numerous reports of propeller shaft couplings, P/
Ns 3107065-1 and 865888-3, failing. These propeller shaft couplings 
experience fatigue cracks at the corners of the lubrication slots that 
may result in separation and fragmentation of the propeller shaft 
coupling. That separation causes a sudden loss of drive torque from the 
engine's power section to the propeller shaft (called drivetrain 
uncoupling). After a drivetrain uncoupling, the engine's fuel pump 
continues to provide fuel to the power section, and with no propeller 
load and no engine control changes by the pilot, the engine power 
section will accelerate to the fuel control's overspeed governor set 
point. Even though the propeller drive is uncoupled, the propeller 
blade pitch is still controlled by the propeller governor. During this 
overspeed condition, the propeller governor is designed to move the 
propeller blades toward higher pitch until full feather is reached with 
the propeller not rotating or rotating very slowly. Under certain 
conditions the power section will remain at about 104% RPM with the 
propeller blades in feather position and the propeller not rotating or 
rotating very slowly, until the engine is shut down by the pilot.

Potential Unsafe Failure Scenarios

    After a propeller shaft drivetrain uncoupling, the speed of the 
engine's power section may be reduced: (1) From full power, by the 
pilot retarding the power lever to flight idle, which reduces fuel to 
the power section; (2) at flight idle, because the fuel control reduces 
the fuel supply to the power section and/or; (3) by fragmentation of 
the propeller shaft coupling and secondary damage to the gears in the 
gearbox. If the resulting speed of the power section falls below the 
propeller governor set point (set by the pilot-controlled condition 
lever), the propeller governor will move the propeller out of feather 
to a low-pitch, high-drag position.
    Also, after a propeller shaft drivetrain uncoupling, a pilot 
reacting to the overspeed of the power section may inadvertently retard 
the power lever to flight idle. Doing so will cause the propeller 
governor to move the feathered propeller to a low-pitch, high-drag 
condition.
    Several reports during maintenance test flights and in-service 
operations of twin-engine airplanes have shown that inadvertent 
movement of the propeller blade pitch to a low blade angle create a 
high aerodynamic and asymmetric drag with resultant uncommanded yaw and 
roll response on the airplane. Following this unexpected yaw and roll 
response, stabilization and control of the airplane may range from 
unusually difficult to catastrophic, and pilots may lack sufficient 
time to properly assess the engine problem, initiate an engine 
emergency shutdown, and activate the feather valve.
    The drivetrain uncoupling events described previously lead to loss 
of thrust, cause the propeller blade pitch to go to a low-blade angle, 
and create a high aerodynamic and asymmetric drag on the airplane. The 
low-blade angle may result in loss of airplane control, leading to an 
accident. After a review of about 40 years of National Transportation 
Safety Board fatal accident reports of multi-engine airplanes with 
TPE331 engines, we determined that certain airplanes are more at risk 
by engine-failure events than others. Therefore, we are proposing 
compliance times in this AD that address the risk by airplane after a 
propeller shaft coupling failure.

Relevant Service Information

    Allied-Signal Aerospace Company, Garrett Engine Division Service 
Bulletin No. TPE331-72-0873, Revision 1, dated May 20, 1993, describes 
procedures for replacing the affected P/Ns of propeller shaft couplings 
with a defined redesigned propeller shaft coupling.
    Honeywell International Inc. Operating Information Letter OI331-26, 
dated March 2, 2010, describes emergency procedures for aircrew if a 
propeller shaft coupling fails.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

[[Page 26908]]

Proposed AD Requirements

    This proposed AD would require removing propeller shaft couplings, 
P/Ns 3107065-1, 865888-3, 865888-6, and 865888-8, from service.
    This proposed AD would also require inserting a copy of Honeywell 
International Inc. Operating Information Letter OI331-26, dated March 
2, 2010, into the applicable Airplane Flight Manual, Pilot Operating 
Handbook, or Manufacturer's Operating Manual.

Costs of Compliance

    We estimate that this proposed AD would affect 485 engines 
installed on airplanes of U.S. registry. We also estimate that it would 
take about one hour per engine to perform the actions required by this 
proposed AD, if done at next turbine hot section scheduled inspection, 
and 40 hours per engine if done at an unscheduled access of the 
propeller shaft coupling. We also estimate that 400 engines would have 
the replacement actions done at a scheduled time of next turbine hot 
section inspection, and 85 engines would have the replacement actions 
done at an unscheduled access of the propeller shaft coupling. We also 
estimate that the average labor rate is $85 per hour. Required parts 
would cost about $12,000 per engine. Based on these figures, we 
estimate the total cost of the proposed AD to U.S. operators to be 
$6,143,000.

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 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 this 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),
    (3) Will not affect intrastate aviation in Alaska to the extent 
that it justifies making a regulatory distinction, and
    (4) 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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 (AD):

Honeywell International Inc. (Type Certificate Previously Held by 
AlliedSignal Inc., Garrett Engine Division; Garrett Turbine Engine 
Company; and AiResearch Manufacturing Company of Arizona): Docket 
No. FAA-2012-0913; Directorate Identifier 2012-NE-23-AD.

(a) Comments Due Date

    We must receive comments by July 11, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Honeywell International Inc. TPE331-5, -5A, -
5AB, -5B, -10, -10R, -10U, -10UF, -10UG, -10UGR, and -10UR model 
turboprop engines, with a propeller shaft coupling, part number (P/
N) 3107065-1, 865888-3, 865888-6, or 865888-8, installed.

(d) Unsafe Condition

    This AD was prompted by engine propeller shaft coupling failures 
leading to unexpected propeller pitch changes resulting in high 
aerodynamic and asymmetric drag on the airplanes using these 
engines. We are issuing this AD to prevent loss of airplane control, 
leading to an accident.

(e) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) Engines Installed In Mitsubishi MU-2B Series (MU-2 Series) 
Airplanes: Remove from service the affected propeller shaft coupling 
at the earliest of the following:
    (i) Next piece-part exposure; or
    (ii) Next turbine (hot) section inspection (HSI); or
    (iii) Before accumulating an additional 1,200 cycles after the 
effective date of this AD.
    (2) Engines Installed In Construcciones Aeronauticas, S.A. 
(CASA) C-212 Series, and Twin Commander 690 and 695 Series (Jetprop 
Commander) Airplanes: Remove from service the affected propeller 
shaft coupling at the earliest of the following:
    (i) Next piece-part exposure; or
    (ii) Next turbine HSI; or
    (iii) Before accumulating an additional 2,400 cycles after the 
effective date of this AD.
    (3) Engines Installed In British Aerospace Jetstream 3101 
Series, Dornier Luftfahrt Dornier 228 Series, and M7 (formerly 
Fairchild, Swearingen) SA226 and SA227 Series Airplanes, and All 
Other Airplanes Not Listed in this AD Using Affected Engines: Remove 
from service the affected propeller shaft coupling at the earliest 
of the following:
    (i) Next piece-part exposure; or
    (ii) Next turbine HSI; or
    (iii) Before accumulating an additional 3,600 cycles after the 
effective date of this AD.
    (4) Inserting a Copy of Honeywell International Inc. Operating 
Information Letter into the FAA-Approved Flight Manual:
    Within 60 days after the effective date of this AD, for 
airplanes with engine propeller shaft coupling, P/N 3107065-1, 
865888-3, 865888-6, or 865888-8, installed, insert a copy of 
Honeywell International Inc. Operating Information Letter OI331-26, 
dated March 2, 2010, into the Emergency Procedures Section of the 
applicable Airplane Flight Manual, Pilot Operating Handbook, or 
Manufacturer's Operating Manual.

(f) Definition

    For the purpose of this AD, next piece-part exposure is when the 
nose cone assembly is removed from the engine.

(g) Installation Prohibition

    After the effective date of this AD, do not install any 
propeller shaft coupling, P/N 3107065-1, 865888-3, 865888-6, or 
865888-8, into any engine.

(h) Alternative Methods of Compliance (AMOCs)

    The Manager, Los Angeles Aircraft Certification Office, FAA, may 
approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 
to make your request.

[[Page 26909]]

(i) Related Information

    (1) For more information about this AD, contact Joseph Costa, 
Aerospace Engineer, Los Angeles Aircraft Certification Office, FAA, 
Transport Airplane Directorate, 3960 Paramount Blvd., Lakewood, CA 
90712-4137; phone: 562-627-5246; fax: 562-627-5210; email: 
joseph.costa@faa.gov.
    (2) Allied-Signal Aerospace Company Service Bulletin No. TPE331-
72-0873, Revision 1, dated May 20, 1993, addresses acceptable 
replacement parts, and other information pertaining to the subject 
of this AD.
    (3) For service information identified in this AD, contact 
Honeywell International Inc., 111 S. 34th Street, Phoenix, AZ 85034-
2802; phone: 800-601-3099; Web site: http://portal.honeywell.com.
    (4) You may view this service information at the FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, 
MA. For information on the availability of this material at the FAA, 
call 781-238-7125.

    Issued in Burlington, Massachusetts, on May 6, 2014.
Colleen M. D'Alessandro,
Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2014-10783 Filed 5-9-14; 8:45 am]
BILLING CODE 4910-13-P


