SA226 Series Engine AD and Time Compliance Sheet TPE U-521G TAT: TAC: Engine Last CURRENT ENGINE TIME AND CYCLES

Transcription

1 DATE: 12/4/15 Engine Last CURRENT ENGINE TIME AND CYCLES Airframe Total Time (TAT) Aircraft Landings (TAC). TSN Engine TSN Engine CSN CSN 6025 Engine TSO Engine CSO 422 Engine PN SN P 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 Compressor 10yr/5400Cyc Impeller from X Remove P/N ,-2,-3,-7 or CSN P/N ,-2,-4 with less than 19K cycles remove before 25K CSN on , -2, -3, 7 and 25K CTC on , -2, -4 For all P/Ns over 19,600 CSN/ CTC remove within 5400 cycles after effective date of Rev 1 which was SB TPE and SB TPE331-A cycles cycles / / cycles First Stage cycles T-Wheel cycles X 7438 CSN Second 4800 cycles Stage T-Wheel cycles cycles X 1183 CSN Third 4800 cycles Stage T-Wheel cycles X CSN Seal cycles X Plate 6025 CSN

2 Recurring Interval Engine ETSN Next Hours Maintenance (Hours) TSO at due engine Remaining Item at compliance install TSN Engine Overhaul / Cam 5000 Part Number Hot Section Inspection 2500 Gear Box Inspection Engine Oil Change Engine SOAP 100 Sample Torque Load Arm Inspection 1000 FCU/Pump Spline Inspection 3700 SB N/A by C/W SB N/A IAW SB N/A by P/N FCU N/A N/A BY MODEL Engine Fuel Nozzles and Combustion Case Inspection m Tach/Generator Lubrication N/A if SB has been complied with PART NUMBER DESCRIPTION SERIAL NUMBER PART TSO INSTALL DATE/TAT NEXT DUE TAT HOURS REMAINING P-3214C Propeller Pitch Control Propeller Governor Fuel Shutoff Valve Fuel Control Unit P Fuel Pump Torque Limiter AD NUMBER REVISION DESCRIPTION DATE/HOUR CW NEXT DUE TSN NOTES/HOURS REMAINING R1 To prevent possible engine failure 4/1/95 n/a by p/n series 3 pump PCW SB To prevent an uncontained engine 9/1/97 n/a by p/n -7 or -9 rotor

3 failure-second stage rotor PCW SB R1 To prevent turbine failure-oil 4/1/95 Supersedes AD scavenge pump PCW SB To prevent fuel spraying on hot 9/1/97 Supersedes AD turbine components which can result PCW SB A in an engine fire To prevent sudden loss of propeller 4/1/95 Supersedes AD control that may cause asymmetrical PCW A thrust and loss of aircraft control-ppc To prevent failure of FCU governor N/A BY P/N Only applies to P/N drive splines-inspect at 100,150,300, of FCU Installed ,750,1000 and 2000 hours or P/N X 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 To prevent a non-responsive power 9/1/97 SB lever and lack of control of engine PCW power To prevent fuel leakage of the fuel 4/18/01 Hose unlimited manifold check PN or -2 NA per fuel manifold manuf P/N /-2 and Hoses Unlimited Inc name y To remove weld repair first stage N/A BY S/N See notes and S/N in SB and cycles TPE331 -A impellers P/N /-2/-3 & -7 INSTALLED noted to the right and Remove per S/Ns in May-03 SB A 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 AD P/N first stage turbine disc See notes and S/N in SB and cycles TPE331 -A 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 do not require initial insp as they received initial at time of conversion. SB TPE331-A

4 AD To prevent uncontained failure of the See notes and S/N in SB and cycles TPE331-A , Effective August 9, 2006 turbine rotor due to low-cycle-fatigue noted to the right TPE 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-A 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 TPE , Rev 31. 2) Remove from service turbine rotors affected using ASB TPE , 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 To prevent destructive overspeed that TPE-331-A 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 IAW Maintenance Manual Section SB A Replace Woodward FCU P/Ns / / -3 / -4 / -5 / -8 / -9 / -10 /- 11 / -12 / -13 / -14 / -15 / -16 / -17 / -19 / -21 / -24 / -25 / -26 and -27 and P/Ns / -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 / -18 and -19 with modified FCU PNs found in Honeywell ASB.

5 AD NUMBER REVISION DESCRIPTION DATE/HOUR CW NEXT DUE TSN Notes/Hours Remaining AD To prevent uncontained failure of the Effective September 1, 2009 first stage turbine disk and damage to the airplane. Honeywell International Inc. TPE and TPE 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 or , S/N , , and After effective date of this AD, do not install first stage turbine disk same P/Ns and S/Ns into any engine. AD 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 WD, installed, where the engine Installed was overhauled or replaced since February 1, 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. AD To prevent failure of first stage turbine N/A by S/N Logbook Entry NFS 3/15/12 AD Effective July 22, 2015 Supercedes AD AD 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)