DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[4910-13-Pl 

[Docket No. F AA-2006-23706; Directorate Identifier 2006-NE-03-AD; Amendment 

39-18177; AD 2015-12-04] 

RIN 2120-AA64 

Ainvorthiness Directives; Honeywell International Inc. Turboprop Engines 

AGENCY: Federal Aviation Administration (FAA), DOT. 

ACTION: Final rule; correction. 

SUMMARY: The FAA is correcting an airworthiness directive (AD) that published in 

the f ederal Register. That AD applies to all Honeywell International Inc. TPE331-1 , -2, 

-2UA, -3U, -3UW, -5, -SA, -SAB, -SB, -6, -6A, -1 0, -IOAV, -lOGP, - lOOT, -lOP, - lOR, 

- lOT, -lOU, -IOUA, -IOUF, -IOUG, - IOUGR, -lOUR, -llU, -12JR, -12UA, -12UAR, and 

-12U HR turboprop engines with certain Honeywell part numbers (PINs) of Woodward 

fuel control unit (FCU) assemblies, installed. The AD number in the Agency 

Identification Numbers of the preamble is incorrect. Additionally, the Amendment 

number in the regulatory text is incorrect. This document corrects these two errors. In all 

other respects, the original document remains the same. 

DATES: This final rule is effective on July 22, 20 15. The effective date of AD 2015-12-

04, Amendment 39- 18177 (80 FR 34534, June 17, 2015) remains July 22,2015. 

ADDRESSES: You may examine the AD docket on the Internet at 

http://www.regu1ations.gov; 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 of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room Wl2-140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: Joseph Costa, Aerospace Engineer, 

Los Angeles Aircraft Certification Office, r: AA, 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: AD 2015-12-04, Amendment 39-18177, 80 

FR 34534, June 17, 20 15), requires initial and repetitive dimensional inspections of the 

affected fuel control drives and insertion of certain airplane operating procedures into the 

applicable flight manuals. 

As published, the AD number in the Agency Identification Numbers of the 

preamble is incorrect. Additionally, the Amendment number in the regulatory text of AD 

2015-12-04 is incorrect. 

No other part of the preamble or regulatory information has been changed. 

The effective date of AD 2015-1 2-04 remains July 22, 20 15. 

Correction of Non-Regulatory Text 

In the Federal Register of June 17, 2015, AD 20 15-12-04; Amendment 39-18177 

is corrected as follows: 

On page 34534, in the 2"d column, on line 6, change "2014-12-04" to "2015-12-

04". 

Correction of Regulatory Text 

§ 39.13 [Corrected] 

2. The FAA amends§ 39.1 3 by removing airworthiness directive (AD) 2006-15-

08, Amendment 39-1 4688 (71 FR 41 12 1, .July 20, 2006), and adding the following new 

AD: 

2015-12-04 Honeywell International Inc.: Amendment 39-18177; Docket 

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No. F AA-2006-23706; Directorate Identifier 2006-NE-03-AD. 

(a) Effective Date 

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

PUBLICATION IN THE FEDERAL REGISTER]. 

(b) Affected ADs 

This AD replaces AD 2006- 15-08, Amendment 39-1 4688 (71 FR 41121, July 20, 

2006). 

(c) Applicability 

This AD applies to all Honeywell International inc. TPE33 1-I , -2, -2UA, -3U, 

-3UW, -5, -SA, -5AB, -58, -6, -6A, -10, -lOA V, -1 OGP, -I OGT, -1 OP, - 1 OR, -1 OT, -1 OU, 

-IOUA, -10UF, -IOUG, - 10UGR, -lOUR, -II U, -1 2JR, -12UA, -1 2UAR, and -12UI-IR 

turboprop engines with Honeywell part numbers (PINs) for Woodward fuel control unit 

(FCU) assemblies listed in Table 1 to paragraph (c) ofthis AD, installed. 

Table 1 to Paragraph (c) - Affected FCU Assembly P/Ns 

Group# Engine 

2* 

3 

4* 

TPE331-I , -2, and -2UA 

TPE33 1-1, -2, and -2UA 

TP£331-3U, -3UW, -5, -SA, 

-5AB, -58, -6, -6A, -lOA V, 

-10GP, -10GT, -lOP, and -lOT 

TP£331-3U, -3UW, -5, -58, -6, 

-6A, and -1 OT 

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FCU Assembly PINs 

PIN 869199-13, -20, -2 1, -22, -23, -24, -25, 

-26, -27, -28, -29, -31 , -32, -33, -34, and 

-35 

PIN 869 199-9, -10, -11 , -12,-14,-16,-17, 

and -18 

PIN 893561-7, -8,-9, -10, -11 , -14,-15, 

-1 6, -20, -26, -27, and -29; or 

PIN 897770-1 , -3,-7, -9,-10, -11, -12, -14, 

-15, -16, -25, -26, and -28 

PIN 893561 -4, -5, -12, and - 13 or PIN 

897770-5, -8, and -1 3 
5 TP£331 -1 0, -lOR, -1 OU, -1 OUA, 

-10UF, - 10UG, -1 0UGR, 

- lOUR, -IIU, -12JR, - 12UA, 

-12UAR, and -12UHR 

* New/added FCU assembly PINs 

(d) Unsafe Condition 

PIN 897375-2, -3, -4,-5, -8,-9, -10,-11 , 

-12, -13,-14, -15, -16, -17, -19, -21 ,-24, 

-25, -26, and -27; or 

PIN 897780- 1, -2, -3, -4, -5, -6, -7, -8, -9, 

-10,-11,-14, -15,-16,-17, -18, -19, -20, 

-2 1, -22, -23,-24, -25,-26, -27, -30,-32, 

-34, -36, -37, and -38; or 

PIN 893561-17,-18, and -19 

We are issuing this AD to prevent failure of the fuel control drive that could result 

in damage to the engine and airplane. 

(e) Compliance 

Comply with this AD within the compliance times specified, unless already done. 

( 1) Inspection of Engines with FCU Assembly P/Ns in Groups 2 and 4 

For FCU assembly PINs in Groups 2 and 4 listed in Table 1 to paragraph (c) of 

this AD: 

(i) At the next scheduled inspection of the fuel control drive, or within 500 hoursin-service (HIS) after the effective date of this AD, whichever occurs first, inspect the 

fuel control drive for wear. 

(ii) Thereafter, re-inspect the fuel control drive within every I ,000 HIS since-lastinspection (SLI). 

(2) Inspection of Engines with FCU Assembly P/Ns in Groups 1, 3, and 5 

For FCU assembly PINs in Groups 1, 3, or 5 listed in Table 1 to paragraph (c) of 

this AD: 

(i) If on the effective date of this AD the FCU assembly has 950 or more HIS SLl, 

inspect the fuel control drive for wear within 50 HIS from the effective date of this AD. 

(ii) If on the effective date of this AD the FCU assembly has fewer than 950 HIS 

SLI, inspect the fuel control drive for wear before reaching I ,000 HlS. 

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(iii) Thereafter, re-inspect the fuel control drive for wear within every 1,000 HIS 

SLI. 

(3) Airplane Operating Procedures 

Within 60 days after the effective date of thjs AD, insert the information in Figure 

1 to paragraph (e) of this AD, into the Emergency Procedures Section of the Airplane 

Flight Manual (AFM), Pilot Operating Handbook (POH), and the Manufacturer's 

Operating Manual (MOM). 

Figure 1 to Paragraph (e)- Airplane Operating Procedures 

NOTE 

Procedures in dotted line boxes are immediate action items to be 

performed by the pilot I flight crew. 

RAPID, UN COMMANDED ACCELERATION DURING 

ENGINE START (Propeller ON Start Locks) 

• Engine Start- Abort Immediately - Move condition lever to 

EMERGENCY STOP. ·--------------------------------------------------------------

WARNING 

Do not attempt to re-start engine. Report to maintenance. 

I 

ON GROUND or IN FLIGHT: 

-------------------------------------------------------------, RAPID, UNCOMMANDED INCREASE IN RPM, TORQUE, 

FUEL FLOW AND/OR TURBINE TEMPERATURE 

(Propeller OFF Start Locks) 

• Identify Malfunctioning Engine (multi-engine airplane) -

Cross check for rugh torque, RPM, fuel flow, and turbine 

temperatures. 

• Engine shut down- Move condition lever to EMERGENCY 

STOP. 

L- ------------------------------------------------------------• 

WARNING 

Never retard the power levers aft of flight idle in flight or on the ground. 

WARNING 

Do not attempt an engine re-start. Report to maintenance. 

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(f) Optional Terminating Action 

Replacing the affected FCU assembly with an FAA-approved fCU assembly PIN 

not listed in this AD is terminating action for the initial and repetitive inspections 

required by this AD, and for inserting the information in Figure 1 to paragraph (e) of this 

AD into the AFM, POH, and MOM. 

(g) Definitions 

For the purposes of this AD: 

( l) The " fuel control drive" is a series of mating splines located between the fuel 

pump and fuel control governor. 

(2) The fuel control drive consists of four drive splines: the fuel pump internal 

spline, the fuel control external "quill shaft" spline, and the stub shaft internal and 

external splines. 

(h) Alternative Methods of Compliance (AMOCs) 

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

AMOCs for thjs AD. Use the procedures found in 14 CFR 39.19 to make your request. 

(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 90712-4137; phone: 562-627-5246; 

fax: 562-627-5210; emai l: joseph.costa@faa.gov. 

(2) Information pertaining to operating recommendations for affected engines 

after a fuel control drive failure is contained in Honeywell International Inc., Operating 

Information Letter (OIL) 01331-l2R6, dated May 26, 2009, for multi-engine airplanes; 

and in OIL 01331-18R4, dated May 26, 2009, for single-engine airplanes. Information on 

fuel control drive inspection can be found in Section 72-00-00 of the applicable TPE331 

maintenance manuals. These Honeywell International Inc., OILs and the TPE331 

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maintenance manuals, which are not incorporated by reference in this AD, can be 

obtained from Honeywell International Inc., using the contact information in paragraph 

(i)(3) of this AD. 

(3) f-or service information identified in this AD, contact Honeywell International 

Inc., 111 S. 34th Street, Phoenix, AZ 85034-2802; Internet: 

https:/ /myaerospace. honeywell.com/wps/portal/! ut; phone: 800-60 1-3099. 

(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. 

U) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on June 26, 20 15. 

Ann C. Moll ica, 

Acting Directorate Manager, Engine and Propeller Directorate, 

Aircraft Certification Service. 

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