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

RIN 2120-AA64 

Airworthiness Directives; Honeywell International Inc. Turboprop Engines 

AGENCY: Federal Aviation Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking (NPRM). 

SUMMARY: We propose to supersede airworthiness directive (AD) 2015w12-04, which 

applies to all Honeywell International Inc. (Honeywell) TPE331-l, -2, -2UA, -3U, -3UW, 

-5, -SA, -SAB, -SB, -6, -6A, -10, -IOAV, -IOGP, -IOGT, -lOP, -lOR, -lOT, -IOU, -IOUA, 

-IOUF, -IOUG, -IOUGR, -lOUR, -11 U, -12JR, -12UA, -12UAR, and -12UHR turboprop 

engines with certain Woodward fuel control Wlit (FCU) assemblies, installed. AD 2015-

12-04 currently requires initial and repetitive dimensional inspections of the affected fuel 

control drives and insertion of certain airplane operating procedures into the applicable 

flight manuals. This proposed AD would correct compliance requirements and relax the 

inspection interval. We are proposing this AD to prevent failure of the fuel control drive, 

damage to the engine, and damage to the airplane. 

DATES: We must receive comments on this proposed AD by [INSERT DATE 60 

DAYS AFTER DATE OF PUBLICATION IN THE FEDERAL REGISTER]. 

ADDRESSES: You may send comments, using the procedures fmmd in 14 CFR 11.43 

and 11.45, by any ofthe following methods: 

• Federal eRulernaking Portal: Go to http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202-493-2251. 
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: 800-60 1-3099; 

Intemet: https://myaerospace.honeywell.com/wps/portal. You may view this service 

information at the FAA, Engine & Propeller Directorate, 1200 District A venue, 

Burlington, MA. For information on the availability of this material at the FAA, call 781-

238-7125. It is also available on the Internet at http://www .regulations.gov by searching 

for and locating Docket No. F AA-2006-23706. 

Examining the AD Docket 

You may examine the AD docket on the Intemet at http://www.regulations.gov by 

searching for and locating Docket No. F AA-2006-23706; 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 

Parammmt Blvd., Lakewood, CA 90712-4137; phone: 562-627-5246; fax: 562-627-5210; 

email: joseph.costa@faa.gov. 

2 
Include "Docket No. FAA-2006-23706; Directorate Identifier 2006-NE-03-AD" at the 

beginning of your comments. We specifically invite comments on the overall regulatory, 

economic, enviromnental, and energy aspects of this NPRM. We will consider all 

comments received by the closing date and may amend this NPRM 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 

NPRM. 

Discussion 

On June 5, 2015, we issued AD 2015-12-04, Amendment 39-18177, (80 FR 

34534, June 17, 2015) ("AD 2015-12-04"), for all Honeywell Internationallnc. TPE331-

l, -2, -2UA, -3U, -3UW, -5, -SA, -SAB, -SB, -6, -6A, -10, -lOAV, -lOOP, -lOOT, -lOP, 

-lOR, -lOT, -lOU, -lOU A, -lOUF, -lOUG, -lOUGR, -lOUR, -llU, -12JR, -12UA, 

-12UAR, and -12UHR turboprop engines with certain Woodward FCU assemblies, 

installed. AD 2015-12-04 requires initial and repetitive dimensional inspections of the 

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

applicable flight manuals. AD 2015-12-04 resulted from reports of loss of the fuel control 

drive, leading to engine overspeed, overtorque, overtemperature, tmcontained rotor 

failure, and asymmetric thrust in multi-engine airplanes. We issued AD 2015-12-04 to 

prevent failure of the fuel control drive, damage to the engine, and damage to the 

airplane. 

3 
inspection was small, changing the compliance time to 100 hours would not add 

additional risk of fuel control drive failure and, therefore, is appropriate. 

We also received reports that some airplanes do not use the condition lever to shut 

down the engine, and so could not comply with the AD. We concluded that references to 

a condition lever were inappropriate. This proposed AD eliminates references to a 

condition lever. 

Related Service Information 

We reviewed Honeywell Operating Information Letter (OIL) 01331-12R6, dated 

May 26, 2009, for multi-engine airplanes; and OIL 01331-18R4, dated May 26, 2009, for 

single-engine airplanes and Honeywell TPE331 maintenance manuals. The service 

information describes procedures for conducting fuel control drive inspections and engine 

shutdown. 

FAA's Determination 

We are proposing this NPRM because we information evaluated all the relevant 

and determined the unsafe condition described previously is likely to exist or develop in 

other products of the same type design. 

Proposed AD Requirements 

This NPRM would increase the inspection time limits for the FCU assembly from 

50 to 100 hours-in-service in Compliance paragraph (e)(2) of this AD. This NPRM would 

also delete reference to the condition lever. 

4 
affected engines will require FCU assembly stub shaft replacement and fuel pump or fuel 

control repair. We also estimate that repairs will cost about $10,000 per engine. Based on 

these figures, we estimate the cost of this AD on U.S. operators to be $525,587 per year. 

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: 

5 
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 

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§ 39.13 by removing airworthiness directive (AD) 2015-12-

04, Amendment 39-18177 (80 FR 34534, Jtme 17, 2015) ("AD 2015-12-04"), and adding 

the following new AD: 

Honeywell International Inc.: Docket No. FAA-2006-23706; Directorate 

Identifier 2006-NE-03-AD. 

(a) Comments Due Date 

The FAA must receive comments on this AD action by [INSERT DATE 60 

DAYS AFTER DATE OF PUBLICATION IN THE FEDERAL REGISTER]. 

(b) Affected ADs 

This AD replaces AD 2015-12-04. 

6 
-12UHR turboprop engines with Woodward fuel control unit (FCU) assemblies with 

Honeywell part numbers (PINs) as listed in Table 1 to paragraph (c) of this AD, installed. 

Table 1 to Paragraph (c)- Affected FCU Assembly PINs 

Group# 

I 

2 

3 

4 

s 

Engine 

TPE331-l, -2, and -2UA 

TPE331-1, -2, and -2UA 

TPE331-3U, -3UW, -S, -SA, 

-SAB, -SB, -6, -6A, -IOAV, 

-lOGP, -IOGT, -lOP, and -lOT 

TPE331-3U, -3UW, -S, -SB, -6, 

-6A, and -I OT 

TPE331-10, -lOR, -lOU, -IOUA, 

-lOUF, -lOUG, -IOUGR, 

-lOUR, -l!U, -12JR, -12UA, 

-12UAR, and -12UHR 

(d) Unsafe Condition 

FCU Assembly PINs 

PIN 869199-13, -20,-21,-22,-23,-24, -2S, 

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

-3S 

PIN869199-9,-10, -11,-12,-14,-16,-17, 

and -18 

PIN 893S61-7, -8, -9,-10,-11,-14, -IS, 

-16,-20,-26, -27, -29; and 

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

-IS, -16, -2S, -26, and -28 

PIN 893S61-4, -S, -12, -13; and PIN 897770-S, -8, and -13 PIN 89737S-2, -3, -4, -5, -8, -9,-10,-11, 

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

-25, -26, -27; and 

PIN897780-1,-2, -3,-4,-S,-6,-7,-8,-9, 

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

-21,-22,-23,-24, -2S, -26, -27,-30,-32, 

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

PIN 893S61-17, -18, and -19 

This AD was prompted by reports ofloss of the fuel control drive, leading to 

engine overspeed and engine failure. We are issuing this AD to prevent failure of the fuel 

control drive, damage to the engine, and damage to the airplane. 

(e) Compliance 

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

7 
in-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 1,000 HIS since-lastinspection (SLI). 

(2) Inspection of Engines with FCU PINs in Groups 1, 3, or 5 

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

this AD: 

(i) If on the effective date of this AD the FCU assembly has 900 or more HIS SLI, 

inspect the fuel control drive for wear within I 00 HIS after the effective date of this AD. 

(ii) If on the effective date of this AD the FCU assembly has fewer than 900 HIS 

SLI, inspect the fuel control drive for wear within 1,000 HIS. 

(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 this AD, insert the infonnation in Figure 

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

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

Operating Manual (MOM). 

8 
 ' ' ' ' ' ' 

, 

ENGINE START (Propeller ON Start Locks) 

: • Engine Start- Abort Immediately- Shut Down Affected ' : Engine in accordance with Emergency Procedures. L--------------------------------------------------------------' 

WARNING 

Do not attempt to re-start engine. Rep01t to maintenance. 

ON GROUND or IN FLIGHT: 

-------------------------------------------------------------, 

RAPID, UN COMMANDED INCREASE IN RPM, TORQUE, 

FUEL FLOW AND/OR TURBINE TEMPERATURE 

(Propeller OFF Start Locks) 

• Identify Malfunctioning Engine (multi-engine airplanes)-

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

temperatures. 

,• 

' 

Shut Down Affected Engine in accordance with Emergency 

Procedures. ' ' 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. 

(1) Optional Terminating Action 

Replacing the affected FCU assembly with an FAA-approved FCU assembly not 

listed in this AD by PIN 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: 

9 
external splines. 

(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. 

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

(2) Information pertaining to operating recommendations for affected engines 

after a fuel control drive failure is contained in Honeywell Operating Information Letter 

(OIL) 01331-12R6, dated May 26, 2009, for multi-engine airplanes; and 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 OILs and the TPE331 maintenance manuals can be obtained 

from Honeywell using the contact information in paragraph (i)(3) of this proposed AD. 

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

Inc., Ill S. 34th Street, Phoenix, AZ 85034-2802; phone: 800-601-3099; Internet: 

https://myaerospace.honeywell.com/wps/portal. 

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

Directorate, 1200 District Avenue, Burlington, MA. For information on the availability of 

this material at the FAA, call 781-238-7125. 

10 
, 

Acting Manager, Engine and Propeller Directorate, 

Aircraft Certification Service. 

11