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**DEPARTMENT OF TRANSPORTATION Federal Aviation Administration**  **14 CFR Part 39 [** **Docket No. FAA -** **2006 -**  **23706 ; Directorate Identifier**  **2006 -** **NE -**  **03 -** **AD ; Amendment**  **39 -**  **18 177**  **; AD 2014**  **- 12**  **- 04**  **] RIN 2120**  **- AA64**  **Airworthiness Directives; Honeywell International In**  **c. Turboprop Engines AGENCY:**  Federal Aviation Administration (FAA), DOT. **ACTION:** Final rule. **SUMMARY:** We are superseding airworthiness directive (AD) 2006 - 15 - 08 for all Honey well 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 certain Honey

well part numbers (P/Ns) of Woodward fuel control unit (FCU) assemblies, installed. AD 2006 - 1 5 - 08 required initial and repetitive dimensional inspections of the fuel control drive s for wear, and replacement of the FCU and fuel pump. This new AD requires initial and repetitive dimensional inspections of the affected fuel control drive s and insertion of certain airplane operating procedures into the applicable flight manuals. This AD was prompted by reports of loss of the fuel control drive, leading to engine overspeed, overtorque, overtemperature, uncontained rotor failure, and asymmetric thrust in multi - engine airplanes. We are issuing this AD to prevent failure of the fuel control drive that could result in damage to the engine and airplane. **DATES:** This AD is effective [ IN SERT DATE 35 DAYS AFTER DATE OF PUBLICATION IN THE FEDERAL REGISTER]. **ADDRESS ES:**  For service information identified in this AD, contact Honey well2

International Inc., 111 S 34 th Street, Phoenix, AZ 85034 - 2802; phone: 800 - 601 - 3099; Internet: https://myaerospace.honey well.com/wps/portal/!ut/ . 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 - 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 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 W12 - 140, 1200 New Jersey Avenue SE., Washington, DC 20590 . **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: Discussion**  We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2006 - 15 - 08 , Amendment 39 - 14688 (71 FR 41121, July 20, 2006) , (“AD 2006 - 15 - 08 ”) . AD 2006 - 15 - 08 applie d to all Honey well 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 certain Honey well part numbers (P/Ns) of Woodward3

FCU assemblies, installed . The NPRM published in the Federal Register on March 19, 2014 ( 79 FR 15261 ). The NPRM was prompted by reports of loss of the fuel control drive, leading to engine overspeed, overtorque , overtemperature, uncontained rotor failure, and as ymmetric thrust in multi - engine airplanes. The NPRM proposed to continue to require initial and repetitive dimensional inspections of the affected fuel control drives but would no longer require the installation of a modified FCU. The NPRM also proposed to require insertion of certain airplane operating procedures into the applicable flight manuals. We are issuing this AD to prevent failure of the fuel control drive that could result in damage to the engin e and airplane. **Comments** We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (79 FR 15261, March 19, 2014) and the FAA’s response to each comment. **Disagreement with**  **the Eliminati on of**  **Requ irement to Install**  **a Modified FCU**  Honey well International Inc. (Honey well) and an individual commenter indicated that the NPRM should mandate the installation of the FCU because of the benefits it provide s . In addition, both commenters disagreed with the FAA that the modified FCU contributed to the rate of in- flight shutdowns (IFSDs) and that the inherent risk of repetitive inspections does not support the elimination of the overspeed governor (OSG) modification requirement of AD 2006 - 15 - 08. We di s agree. We eliminated the mandatory installation of recently

certified, modified FCUs due to the numerous reports of unscheduled removals and the IFSDs caused b y the recent design changes incorporated in the modified FCU. We did not change this AD.4

**Request Change to Costs of Compliance**  Honey well indicated that the cost for repetitive inspections is not accurate. Honey well estimates that, without a change in design, a limitless number of inspections would be needed over the life of the engine. We agree. Numerous fuel control drive inspections could be needed over the life of the engine. The Costs of Compliance paragraph was changed to reflect an annual cost of compliance which was based on the fleet costs as reflected in the NPRM. **Request to Change the Applic ability**  Honey well requested that engines in Group # 4 reflect the engines associated with FCU assembl y P/Ns being added to the Applicability paragraph for added clarity. We agree . We changed Table 1 to paragraph (c) of this AD to clarify the Group # 4 engine models as follows: “ Group # 4 TPE331 - 3U, - 3UW, - 5, - 5B, - 6, - 6A, and

- 10T ” . **Request to Change the Applicability** Honey well requested that clarification be provided for FCU P/Ns of Woodward fuel control units . The Applicability paragraph refers to P/Ns as Woodward P/Ns when the listed P/Ns are Honeywell P/Ns for Woodward FCUs. We agree. We changed paragraph (c) of this AD to read, “... turboprop engines with Honey

well part numbers (P/Ns) for Woodward fuel control unit (FCU) assemblies listed in Table 1 to p aragraph (c) of this AD, installed. ” **Request Redundant Term be Removed from the Compliance**  Honey well requested that “spline” be removed from the fuel control drive inspection as stated in the Compliance paragraph. This change is consistent with the Compliance and the Definitions paragraphs in AD 2006 - 15 - 08 . We agree. We changed paragraph s (e)(1)(i) and (e)(2)(ii) to read: “Inspect the fuel control drive for wear.”5

**Request to Change Related Information** Honey well requested that the publications listed in Related Information, paragraph (i)(2), be referred to as airplane publications and not as obtainable from Honey well International. The reason for this request is that the Airplane Flight Manual (AFM), the Pilot Operating Handbook (POH), and the Manufacturer’s Operating Manual (MOM) are airplane publications and cannot be obtained from Honey well. We agree that the AFM, POH, and the MOM are airplane manuals. As a result of reviewing this comment, we decided that mentioning all applicable owners of airplane manual s is unnecessary

in the related information section of this AD. **Request to Change Airplane Operating Procedures** Honey well requested that reference to the “Loss of Fuel Control Drive” be changed to “Loss of the drive between the engine driven fuel pump and the fuel control governor.” This change would eliminate confusion between the loss of the accessory drive gearing to the fuel pump with the loss of the fuel control drive. We agree that the term “fuel control drive” is not a term used in airplane operating procedures. W e removed the term “fuel control drive” from the Airplane Operating Procedures in this AD and made other changes to simplify and clarify Figure 1 to paragraph (e) of this AD . **Request to Change Airplane Operating Procedures** One commenter reque sted a revision of the Operating Procedure “W arning s” in the NPRM to clearly

address overspeed during start and immediately after start before the propeller has been removed from the start locks. This change would provide clarification and enhance safety. We dis agree. The Loss of Fuel Control Drive causing rapid, uncommanded acceleration during engine star t is as unsafe as the Loss of Fuel Control Drive immediately

after start when the engine is stable before the propeller is removed from the6

start locks. H owever, s ince the observed effects for these two conditions are the same, we combine d both instances as “Rapid, Uncommanded Acceleration During Engine Start” . **Request to Change Airplane Operating Procedures** The commenter requested changing the operating procedures for when the propeller is off the start locks to address the rapid uncommanded, uncontrolled increase in revolutions -per-minute (RPM) . The commenter believes that if the fuel control drive fails when the propeller is off the start l o cks the engine ’s propeller governor will control and stabilize the engine RPM. We disagree with the commenter’s justification because test data has shown that the engine propeller governor will not control and stabilize the engine RPM if the fuel control drive fails when the propeller is off the start locks. A rapid, uncommanded, uncontrolled increase in RPM is most evident during partial or full reverse. W e simplif ied the operating procedure by removing the statement “ Power - Move power lever to or toward flight idle as required to maintain engine limits” with the propeller off the start locks as proposed in the NPRM . We changed Figure 1 to paragraph (e) of this AD by adding the following: “ Engine shut down - Move condition lever to EMERGENCY STOP”. **C onclusion**  We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes:  Are cons istent with the intent that was proposed in the NPRM for correcting the unsafe condition; and  Do not add any additional burden upon the public than was already proposed in the NPRM.7 We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. **Costs of Compliance** We estimate that this AD will affect 2,250 engines installed on airplanes of U.S. registry . We estimate that it will take 8 hours per engine to perform an FCU inspection . The average labor rate is $85 per hour. Due to the more frequent inspections proposed by this AD, we estimate 10 % of affected engines will require FCU assembl y stub shaft replacement, and fuel pump or fuel control repair. We also estimate that repairs will not exceed $10,000 per engine . Based on these figures, we estimate the cost o f 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. Subtitl e 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 s afety 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 AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on8

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 F R 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. **Adoption of the Amendment** Accordingl y, 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 § 39.13 by removing airworthiness directive (AD) 2006 - 15 - 08, Amendment 39 - 14688 (71 FR 41121, July 20, 2006), and adding the following new AD: **201 5**  **- 12**  **- 04**  **Honeywell International Inc.** : Amendment 39 - 18 177 454851 ; Docket No. FAA - 2006 - 23706; Directorate Identifier 2006 -NE - 03 -AD.9

**(a )**  **Effective Date** This AD is effective [ IN SERT DATE 35 DAYS AFTER DATE OF PUBLICATION IN THE FEDERAL REGISTER] . **(b) Affected ADs** This AD replac es AD 2006 - 15 - 08, Amendment 39 - 14688 (71 FR 41121, July 20, 2006). **(c) Applicability** This AD applies to all Honey w ell 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 Honey well part numbers (P/Ns) for Woodward fuel control unit (FCU) assemblies listed in Table 1 to paragraph (c) of this AD, installed.

**Table 1 to Paragraph (c) –**  **Affected FCU Assembly P/Ns Group #**  **Engine FCU Assembly P/Ns**  1 TPE331 - 1, - 2, and - 2UA P/N 869199 **-** 13, - 20, - 21, - 22, - 23, - 24, - 25,

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

- 35 2* TPE331 - 1, - 2, and - 2UA P/N 869199 - 9, - 10, - 11, - 12, - 14, - 16, - 17, and - 18 3 TPE331 - 3U, - 3UW, - 5, - 5A,

- 5AB, - 5B, - 6, - 6A, - l0AV,

- 10GP, - 10GT, - l0P, and - l0T P/N 893561 - 7, - 8, - 9, - 10, - 11 , - 14, - 15,

- 16, - 20, - 26, - 27, and - 29; or P/N 897770 - 1, - 3, - 7, - 9, - 10, - 11, - 12, - 14,

- 15, - 16, - 25, - 26, and - 28 4* TPE331 - 3U, - 3UW, - 5, - 5B, - 6,

- 6A, and - 10T P/N 893561 - 4, - 5, - 12, and - 13 or P/N 897770 **-** 5, - 8, and - 1310

5 TPE331 - 10, - l0R, - 10U, - 10UA,

- 10UF, - 10UG, - 10UGR,

- 10UR, - 11U, - 12JR, - 12UA,

- 12UAR, and - 12UHR P/N 897375 - 2, - 3, - 4, - 5, - 8, - 9, - 10, - 11,

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

- 25, - 26, and - 27; or P/N 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; or P/N 893561 - 17, - 18, and - 19 * New/added FCU assembly P/Ns **(d) Unsafe Condition** 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 assembl y P/Ns 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 hours 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 Assembly P/Ns in Groups 1, 3, and 5** For FCU assembl y P/Ns in Groups 1, 3, or 5 listed in Table 1 to paragraph (c) of this AD: (i) If on the e ffective date of this AD the FCU assembly has 950 or more HIS SLI, 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 HI S SLI, inspect the f

uel control drive for wear before reaching 1,000 HI S.11 (i i i) Thereafter, re - inspect the fuel control drive for wear within every 1,000 HI S SLI. **(3) Airplane Operating Procedures** Within 60 days after the effective date of this AD, insert the information in F igure 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 Oper**  **ating Procedures**

NOTE Procedures in dotted line boxes are immediate action items to be performed b y the pilot / flight crew.

WARNI NG D o not attempt to re - start engine. Report to maintenance. ON GROUND or IN FLIGHT : 

WARNI NG Never retard the power levers aft of flight idle in flight or on the ground. WARNI NG Do not attempt an engine re - start. Report to maintenance. RAPID, UNCOMMANDED ACCELERATION DURING ENGINE START (Propeller ON Start Locks)  Engine Start

– Abort Immediately

– Move condition lever to EMERGENCY STOP .

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 high torque, RPM, fuel flow , and turbine temperatures.  Engine shut down - Move condition lever to EMERGENCY STOP.12

**(f) Optional Terminating Action** Replacing the affected FCU assembly with an FAA - approved FCU assembly P/N not listed in this AD i s terminating action for the initial and repetitive inspections required b y 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: (1) 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 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 - 5210; email: joseph. costa@faa.gov . (2 ) Information pertaining to operating recommendations for affected engines after a fuel control drive failure is contained in Honey well International Inc., Operating In formation Letter (OIL) OI331 - 12R6, dated May 26, 2009, for multi - engine airplanes; and in OIL OI331 - 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 Honey well International Inc., OILs and the TPE33113

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

well International Inc., using the contact information in paragraph (i )( 3 ) of this AD. ( 3 ) For service information identified in this AD, contact Honey well International Inc., 111 S. 34th Street, Phoenix, AZ 85034 - 2802; Internet: https://myaerospace.honey well.com/wps/portal/!ut ; phone: 800 - 601 - 3099. (4 ) You may

view this service information at the FAA, Engine & Propeller Directorate, 12 New England Exe cutive Park, Burlington, MA. For information on the availability

of this material at the FAA, call 781 - 238 - 7125 . **( j**  **) Material Incorporated by Reference** None. Issued in Burlington, Massachusetts , on June 5 , 201 5 . Ann C. Mollica, Acting Directorate Manager, Engine & Propeller Directorate, Aircraft Certification Service.