(a) EFFECTIVE DATE

    This AD is effective November 28, 2016.

(b) AFFECTED ADS

    This AD replaces AD 2015-12-04, Amendment 39-18177, (80 FR 34534, June
    17, 2015).

(c) APPLICABILITY

    This  AD  applies  to  all  Honeywell  International  Inc. (Honeywell)
    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  Woodward  fuel  control  unit  (FCU)  assemblies   with
    Honeywell part numbers (P/Ns) as 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,        P/N 893561-7, -8, -9,
                    -5A, -5AB, -5B, -6,        -10, -11, -14, -15, -16,
                    -6A, -10AV, -10GP,         -20, -26, -27, -29; and
                    -10GT, -10P, and -10T      P/N 897770-1, -3, -7, -9,
                                               -10, -11, -12, -14, -15,
                                               -16, -25, -26, and -28

       4           TPE331-3U, -3UW, -5,        P/N 893561-4, -5, -12,
                    -5B, -6, -6A, and          -13; and
                    -10T                       P/N 897770-5, -8, and -13

       5           TPE331-10, -10R,            P/N 897375-2, -3, -4, -5,
                    -10U, -10UA, -10UF,        -8, -9, -10, -11, -12,
                    -10UG, -10UGR, -10UR,      -13, -14, -15, -16, -17,
                    -11U, -12JR, -12UA,        -19, -21, -24, -25, -26,
                    -12UAR, and -12UHR         -27; and
                                               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,
                                               -38; and
                                               P/N 893561-17, -18, and -19
    ______________________________________________________________________

(d) UNSAFE CONDITION

    This AD was  prompted by reports  of loss  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 al-
    ready done.

(1) INSPECTION OF ENGINES WITH FCU ASSEMBLY P/NS IN GROUPS 2 OR 4

    For  FCU assembly P/Ns in Groups 2 or 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, which-
    ever occurs first, inspect the fuel control drive for wear.

(ii) Thereafter,  reinspect  the fuel control drive within every 1,000 HIS
     since-last-inspection (SLI).

(2) INSPECTION OF ENGINES WITH FCU ASSEMBLY P/NS IN GROUPS 1, 3, OR 5

    For  FCU assembly P/Ns in Groups 1, 3, or 5 listed in Table 1 to para-
    graph (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 100 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,  reinspect  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 infor-
    mation  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).

          FIGURE 1 TO PARAGRAPH (E) – AIRPLANE OPERATING PROCEDURES
    ______________________________________________________________________
                                     NOTE
    Procedures in dotted line boxes are immediate action items to be per-
    formed by the pilot / flight crew.
    ----------------------------------------------------------------------
    RAPID UNCOMMANDED ACCELERATION DURING ENGINE START (Propeller ON Start
    Locks)
    - Engine Start – Abort Immediately – Shut Down Affected Engine in
      accordance with Emergency Procedures.
    ----------------------------------------------------------------------
    
                                   WARNING
    Do not attempt to re-start engine. Report to maintenance.
    
    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 airplanes)– Cross check
      for high torque, RPM, fuel flow, and turbine temperatures.
    - Shut Down Affected Engine in accordance with Emergency Procedures.
    ----------------------------------------------------------------------
                                  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.
    ______________________________________________________________________


(f) OPTIONAL TERMINATING ACTION

    Replacing the affected FCU assembly with an FAA-approved FCU  assembly
    not listed in this AD by P/N 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:

(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  Honeywell
    Operating Information Letter (OIL) OI331-12R6, dated May 26, 2009, for
    multi-engine airplanes; and  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 Honeywell OILs  and the TPE331 maintenance  manuals can
    be obtained from Honeywell using the contact information in  paragraph
    (i)(3) 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; Internet: https://myaerospace.honeywell.com/wps/portal.

(4) You  may  view  this  service information  at  FAA, Engine & Propeller
    Directorate, 1200 District Avenue, Burlington, MA.  For information on
    the availability of this material at the FAA, call 781-238-7125.

Issued  in  Burlington, Massachusetts,  on  October 14,  2016.  Colleen M.
D'Alessandro,   Manager,   Engine   &   Propeller   Directorate,  Aircraft
Certification Service.

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.