[4910-13-P] 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

rDocket No. FAA-2012-0913; Directorate Identifier 2012-NE-23-AD; Amendment 

39-18261; AD 2015-18-03] 

RIN 2120-AA64 

Ainvorthiness Directives; Honeywell International Inc. Turboprop Engines (Type 

Certificate previously held by AlliedSignal Inc., Garrett Engine Division; Garrett 

Turbine Engine Company; and AiRcsearch Manufacturing Company of Arizona) 

AGENCY: Federal Aviation Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new airworthiness directive (AD) for certai n Honeywell 

International Inc. TPE331 -5, -SA, -5AB, -5B, -10, -lOR, -IOU, -IOUF, - IOUG, -IOUGR, 

and -1 OUR model turboprop engines. This AD was prompted by engine propeller shaft 

coupling fai lures, leading to unexpected propeller pitch changes resulting in high 

aerodynamic and asymmetric drag on the airplanes using these engines. This AD requires 

removing certain part number (PIN) propeller shaft couplings from service. This AD also 

requires inserting a copy ofi-Ioneywelllnternationallnc. Operating Information Letter 

01331-26, dated March 2, 2010, into the applicable Airplane Flight Manuals. We are 

issuing this AD to prevent loss of airplane control, leading to an accident. 

DATES: This AD is effective [INSERT DATE 35 DAYS AFTER DATE OF 

PUBLICATION IN THE FEDERAL REGISTER]. 

ADDRESSES: For service information identified in this AD, contact Honeywell 

Intemational Inc., Ill S. 341

h Street, Phoenix, AZ 85034-2802; phone: 800-601-3099; 

Internet: 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 ava ilability of this material at the FAA, call 781-238-7 125. 

Examining the AD Docket 

You may examine the AD docket on the Internet at http://vvvvw.regulations.gov by 

searching for and locating Docket No. F AA-20 12-0913; 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 AD, the regulatory evaluation, any comments 

received, and other information. The address for the Docket Office (phone: 

800-647-5527) is Document Management Facility, U.S. Department ofTransportation, 

Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 

Jersey Avenue SE., Washington, DC 20590. 

FOR FU RTHER INFORMATION CONTACT: .Joseph Costa, Aerospace Engineer, 

Los Angeles Ai1·craft Certification Office, FAA, Transport Airplane Directorate, 3960 

Paramount Blvd., Lakewood, CA 90712-4137; phone: 562-627-5246; fax: 562-627-521 0; 

email: joseph.costa@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by 

adding an AD that would apply to cet1ain Honeywell International Inc. TPE33 1-5, -SA, 

-5AB, -5B, -10, -lOR, -IOU, -lOUF, -IOUG, -IOUGR, and -l OUR model turboprop 

engines. The NPRM published in the Federal Register on May 12, 2014 (79 FR 26906). 

The NPRM 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. The NPRM proposed to require removing certain 

PIN propeller shaft couplings from service and inserti ng a copy ofFioneywell 

International Inc. Operating Information Letter 0 133 1-26, elated March 2, 2010, into the 

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applicable Airplane Flight Manuals. We are issuing this AD to prevent loss of airplane 

control, leading to an accident. 

Comments 

We gave the publi c the opportunity to participate in developing this AD. The 

following presents the comment received on the NPRM (79 FR 26906, May 12, 20 14) 

and the FAA's response to the comment. 

Request to Change Compliance Time Basis 

Honeywell International questioned whether compliance time should be stated in 

flight hours as opposed to flight cycles as used in the NPRM (79 FR 26906, May 12, 

20 14). Major periodic inspections are based on hours and not cycles. 

We do not agree. The FAA practice of stating compliance time is based on the 

component's mode of failure. In this case the failure mode was fatigue; therefore, a 

compliance time in flight cycles is appropriate. We did not change this AD. 

Conclusion 

We reviewed the relevant data, considered the comment received, and determined 

that air safety and the public interest require adopting this AD as proposed. 

Costs of Compliance 

We estimate that this AD will affect 485 engines installed on airplanes of U.S. 

registry. We also estimate that it will take about one hour per engine to perform the 

actions required by this AD, if done at next scheduled tu rbine hot section inspection 

(HSI), and 40 hours per engine if done at an unscheduled access of the propeller shaft 

coupling. We also estimate that 400 engines will have the replacement actions done at a 

scheduled time of next turbine HSI, and 85 engines will have the replacement actions 

done at an unscheduled access of the propeller shaft coupling. The average labor rate is 

$85 per hour. Required parts will cost about $ 12,000 per engine. Based on these figures, 

we estimate the total cost of this AD to U.S. operators to be $6,143,000. 

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Authority for this Rulemaking 

Title 49 of the United States Code specifies the F J\A '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 deta il the scope of the Agency's 

authority. 

We are issui ng this rulemaking under the authority described in Subtitle Vll, 

Part A, Subpart III, Section 44701: "General requirements." Under that section, Congress 

charges the FAA with promoting sa(e night 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 li kely to exist or develop on products 

identified in this rulemaking action. 

Regulatory Findings 

This AD will not have fede ralism implications under Executive Order 13132. This 

AD wil l 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 this AD: 

(1) Is not a "significant regulatory action" under Executive Order 12866, 

(2) Is not a "significant rule'· under DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation in Alaska to the extent that it j ustifies 

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. 

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List of Subjects in 14 CFR Part 39 

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

Adoption of the Amendment 

Accordingly, under the authority delegated to me by the Administrator, the FAA 

amends 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. 

§ 39.13 [Amended! 

2. The FAA amends§ 39.1 3 by adding the following new airworthiness directive 

(AD): 

2015-18-03 Honeywell Interna tional Inc. (Type Certificate previously held by 

AlliedSignal Inc., Ga rrett Engine Division; Garrett Turbine Engine Company; and 

AiResearch Manufacturing Company of Arizona): Amendment 39-18261; Docket No. 

FAA-2012-0913 ; Directorate Identifier 2012-NE-23-AD. 

(a) Effective Date 

This AD is effective [INSERT DATE 35 DAYS AFTER DATE OF 

PUBLICATION rN THE FEDERAL REGISTER]. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Honeywell International Inc. TPE331-5, -SA, -SAB, -SB, -I 0, 

-l OR, -IOU, -JOUF, -IOUG, -lOUGR, and -JOUR model turboprop engines, with a 

propeller shaft coup I ing, part number (P/N) 3107065-1 , 865888-3, 865888-6, or 

865888-8, installed. 

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(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-pat1 exposure; or 

(ii) Next turbine (hot) section inspection (T-TSl); or 

(ii i) Before accumulating an additional I ,200 cycles after the effective date of this 

AD. 

(2) Engines Installed In Construeciones Aeronauticas, S.A. (CASA) C-212 Series, 

and Twin Commander 690 and 695 Series (J etprop Commander) Airplanes: 

Remove from service the affected propeller shaft coupling at the earliest of the 

following: 

AD. 

(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 

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(3) Engines Installed In British Aerospace J etstream 3101 Series, Dornier Luftfahrt 

Dornicr 228 Series, and M7 (formedy 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, PIN 3107065-1, 865888-3, 865888-6, or 865888-8, installed, 

insert a copy of Honeywell International Inc. Operating Information Letter 0133 1-26, 

dated March 2, 20 I 0, 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, PIN 

3107065-1 , 865888-3, 865888-6, or 865888-8, into any engine. 

(h) Alternative Methods of Compliance (AMOCs) 

The Manager, Los Angeles Aircraft Certification Onice, FAA, may approve 

AMOCs for this AD. Use the procedures found in 14 CFR 39. 19 to make your request. 

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(i) Related Information 

(I) 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 907 12-4137; phone: 562-627-5246; 

fax: 562-627-521 0; email: joseph.costa@faa.gov. 

(2) Allied-Signal Aerospace Company Service Bulletin No. TPE331 -72-0873, 

Revision 1, dated May 20, 1993, whi ch is not incorporated by reference in this AD, can 

be obtained from Honeywell International, using the contact information in paragraph 

(i)(3) of this AD. 

(3) For service infonnation identified in this AD, contact Honeywell International 

Inc., I I I S. 34111 Street, Phoenix, AZ 85034-2802; phone: 800-601 -3099; Internet: 

http:/ /portal.honeywel !.com. 

(4) You may view this service information at the FAA, Engine & Propeller 

Directorate, 12 New England Executive Park, Burli ngton, MA. For information on the 

avail ability ofthis material at the FAA, call 781-238-7 125. 

(j) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on August 27, 2014. 

Ann C. Mollica, 

Acting Assistant Directorate Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

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