DATE: 12/4/15 Engine Last Overhauled @ CURRENT ENGINE TIME AND CYCLES Airframe Total Time (TAT) Aircraft Landings (TAC). TSN 4504.2 Engine TSN 4987.2 Engine CSN 6450 4987.2 6449 CSN 6025 Engine TSO 483.1 Engine CSO 422 Engine PN 3102050-5 SN P-35090 Recurring Interval Part Serial Number Engine CSN at Next Due Cycles Maint Item Number Wheel CSN at installation installation CSN Remaining First Stage Not Recorded 896223-1 Compressor 10yr/5400Cyc 896223-2 Impeller from 12-14-2001 896223-3 X 8-03501-16726 Remove P/N 896223-1,-2,-3,-7 or 896223-7 6025 CSN 6025 24734 18284 P/N 3107109-1,-2,-4 with less than 19K cycles remove before 25K CSN on 896233-1, -2, -3, 7 and 25K CTC on 3107109-1, -2, -4 For all P/Ns over 19,600 CSN/ CTC remove within 5400 cycles after effective date of Rev 1 which was 12-14-2001 SB TPE331 72-0019 and SB TPE331-A72-0971 4800 cycles 3107109-1 3107109-2 3107109-4 9600 cycles 3107110-1/-2 3107110-4/-5 3107110-6 30000 cycles 3108182-2 First Stage 10000 cycles 3101520-1 T-Wheel 3101520-2 20000 cycles 3101520-3 9-03501-6370 3107079-1 X 7438 CSN 6025 20000 13550 Second 4800 cycles 3102106-1 Stage 3102106-6 T-Wheel 3102106-8 9600 cycles 3102106-7 3107077-1 15000 cycles 3102106-9 96-01345-00269 3102106-10 X 1183 CSN 6025 14734 8284 Third 4800 cycles 3102655-1 Stage T-Wheel 3107078-1 6000 cycles 3102655-2 X 12-156101-03928 0 CSN 6025 12025 5575 3107078-2 Seal 20000 cycles 3101519-4 X 8-03501-15813 Plate 6025 CSN 6025 20000 13550 3102483-1
Recurring Interval Engine ETSN Next Hours Maintenance (Hours) TSO at due engine Remaining Item at compliance install TSN Engine Overhaul / Cam 5000 Part Number 0 4504.2 9504.2 4517.0 Hot Section Inspection 2500 Gear Box Inspection 2500 0 4504.2 7004.2 2017.0 0 4504.2 7004.2 2017.0 Engine Oil Change 900 0 4504.2 5404.2 417.0 Engine SOAP 100 Sample 483.1 4987.2 5087.2 100.0 Torque Load Arm Inspection 1000 FCU/Pump Spline Inspection 3700 SB72-0605 N/A by C/W SB 72-0818 N/A IAW SB73-0126 N/A by P/N 897801 FCU N/A N/A BY MODEL 0 4504.2 8204.2 3217.0 Engine Fuel 350 4904.7 5254.7 267.5 Nozzles and Combustion Case Inspection m Tach/Generator Lubrication 400 4904.7 5304.7 317.5 N/A if SB 72-0486 has been complied with PART NUMBER DESCRIPTION SERIAL NUMBER PART TSO INSTALL DATE/TAT NEXT DUE TAT HOURS REMAINING 895481-20 P-3214C 0 4504.2 9904.2 4917.0 Propeller Pitch Control 897410-16 2129645 0 4504.2 9904.2 4917.0 Propeller Governor 394230-9-1 11431 0 4504.2 9904.2 4917.0 Fuel Shutoff Valve 897801-9 2137476 0 4504.2 9904.2 4917.0 Fuel Control Unit 897400-5 P-1216 0 4504.2 9904.2 4917.0 Fuel Pump 895380-4 0-08265-279 0 4504.2 9904.2 4917.0 Torque Limiter AD NUMBER REVISION DESCRIPTION DATE/HOUR CW NEXT DUE TSN NOTES/HOURS REMAINING 84-10-06 R1 To prevent possible engine failure 4/1/95 n/a by p/n series 3 pump PCW SB73-0121 88-12-10 To prevent an uncontained engine 9/1/97 n/a by p/n -7 or -9 rotor
failure-second stage rotor PCW SB 72-0571 89-07-07 R1 To prevent turbine failure-oil 4/1/95 Supersedes AD 86-12-02 scavenge pump PCW SB 72-0533 93-02-01 To prevent fuel spraying on hot 9/1/97 Supersedes AD 92-02-19 turbine components which can result PCW SB A73-0198 in an engine fire 93-15-11 To prevent sudden loss of propeller 4/1/95 Supersedes AD 92-26-07 control that may cause asymmetrical PCW A72-0792 thrust and loss of aircraft control-ppc 94-26-07 To prevent failure of FCU governor N/A BY P/N Only applies to P/N 897780 drive splines-inspect at 100,150,300, of FCU Installed -0.0027778 500,750,1000 and 2000 hours or P/N 897880-X 95-16-08 To prevent uncontained failure of 9/1/97 Work performed by Fliteline turbine rotors, fire, or loss of PCW Mx Eugene E. Shanks aircraft control or Mr. Carl Ramirez 97-15-10 To prevent a non-responsive power 9/1/97 SB 73-0235 lever and lack of control of engine PCW power 98-12-09 To prevent fuel leakage of the fuel 4/18/01 Hose unlimited manifold check PN 3102469-1 or -2 NA per fuel manifold manuf P/N 3102469-1/-2 and Hoses Unlimited Inc name y 2002-25-02 To remove weld repair first stage N/A BY S/N See notes and S/N in SB and cycles TPE331 -A72-2083 impellers P/N 896223-1/-2/-3 & -7 INSTALLED noted to the right and 3107109-2. Remove per S/Ns in May-03 SB A72-2083 table 1 & 2. Remove impellers with no record or cycles since weld repair W/I 3600 cycles in service or at next overhaul or CAM. Remove impellers with more than 8900 cycles since weld repair within 3600 CIS or at next overhaul or CAM. After effective date of 1-21-03 AD2004-09-29 P/N first stage turbine disc 3101520-1 See notes and S/N in SB and cycles TPE331 -A72-2102 Effective June 15, 2004 For disc with 4100 CSN OR less inspect noted to the right at next access but no later than 4500 CSN 8/3/04 If more than 4100 CSN inspect within N/A BY S/N next 400 CIS after effective date of AD. If disc pass FPI it must still have eddy current inspection (ECI) before return to service. P/N 3107079-1 do not require initial insp as they received initial at time of conversion. SB TPE331-A72-2102
AD 2006-14-03 To prevent uncontained failure of the See notes and S/N in SB and cycles TPE331-A72-2130, Effective August 9, 2006 turbine rotor due to low-cycle-fatigue noted to the right TPE331-72-0180 Rev 31 (LCF), and damage to the aircraft. f) For turbine rotors installed before the effective date of this AD, and currently or C/W April 2008 previously used in special-use operations 1) Within 100 major cycles-in-service after the effective date of this AD, or upon removal of the turbine rotor(s) from this engine, whichever occurs first. i) Determine the equivalent cycles accrued for turbine rotors. Use para 2.A. of ASB TPE331-A72-2130 ASB Table 1. ii) If unable to determine equivalent cycles use onetime ratio of six takeoffs and landings per major cycle to estimate prior special-use equivalent cycles for each turbine rotor. iii) For each rotor affected on the Life Limited Part Log Card, record total equivalent cycles accrued using recording requirements of TPE331-72-0180, Rev 31. 2) Remove from service turbine rotors affected using ASB TPE331-72-2130, or within 9 months after effective date this AD. g) For used turbine rotors installed on or after the effective date of this AD, and currently or previously used in special-use operations: Before further flight, determine and record total equivalent cycles using (f)(1)(i) through (f)(1)(iii) and remove from service rotors affected. h) For all new (zero cycle) turbine rotors installed on or after the effective date of this AD used in special-use operations: Use the new counting method by counting and recording minor and major cycles when accrued, and determine equivalent cycles by (f)(1)(i) through (f)(1)(iii). Using the ratio of six takeoff and landing per major cycle for unknown cycle history is not permitted. AD 2006-15-08 To prevent destructive overspeed that TPE-331-A72-0254 Rev 2 Effective August 24, 2006 could result in uncontained rotor failure, dated June 17, 2005 and damage to the airplane. Repair or replace Fuel Pump and/or FCU if the splines fail the dimensional inspection CW 4110.6 IAW Maintenance Manual Section 72-00-00 SB A72-0254 Replace Woodward FCU P/Ns 897375-2/ / -3 / -4 / -5 / -8 / -9 / -10 /- 11 / -12 / -13 / -14 / -15 / -16 / -17 / -19 / -21 / -24 / -25 / -26 and -27 and P/Ns 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 and P/Ns 893561-17 / -18 and -19 with modified FCU PNs found in Honeywell ASB.
AD NUMBER REVISION DESCRIPTION DATE/HOUR CW NEXT DUE TSN Notes/Hours Remaining AD 2009-17-05 To prevent uncontained failure of the Effective September 1, 2009 first stage turbine disk and damage to the airplane. Honeywell International Inc. TPE331-10 and TPE331-11 series N/A per SN turboprop engines. Within 25 hours or 25 cycles in service after the effective date of this AD, whichever occurrs first, remove from service first stage disks P/N 3101520-1 or 3107079-1, S/N 2-03501-2299, 2-03501-2300, 2-03501-2301 2-03501-2302 and 2-03501-2304. After effective date of this AD, do not install first stage turbine disk same P/Ns and S/Ns into any engine. AD 2011-18-51 R1 Applies to all Honeywell International, Inc. Logbook Entry NFS Effective upon receipt model turboprop engines with a Dixie August 17, 2011 Aerospace, LLC main shaft bearing, P/N N/A per Bearing PN 3108098-1WD, installed, where the engine Installed was overhauled or replaced since February 1, 2010. Within 10 operating hours, inspect the airplane records to determine if a main shaft bearing is installed in engine, remove from service before further flight. AD2012-02-06 To prevent failure of first stage turbine N/A by S/N Logbook Entry NFS 3/15/12 AD2015-12-04 Effective July 22, 2015 Supercedes AD2006-15-08 AD2015-18-03 Effective November 13, 2015 disk and damage to airplane. Woodward Fuel Control N/A Due To PN installed This AD was prompted by engine propeller shaft coupling failures. This AD requires removing certain Part Number (P/N) engine propeller shaft couplings from service. NOT DUE YET ( Due by Next HSI or 3,600 Cycles after November 13, 2015)