MINI PACK ENGINE Model: BUILD SPEC. 885 ESN: PW150A FA0278 TSN: 15,012.30 CSN: 15,815 TSO: N/A CSO: N/A TSHSI: 2,056.00 CSHSI: 2,373 RGB SN. FA0278 TSN: 15,012.30 CSN: 15,815 TSO: 3,596.40 CSO: 3,863 CONTENTS: TMM Cert RGB Cert TMM Maintenance Log TMM Logbook Entries Test Data Data Plate Information Sheet Accessory Inventory T6 Thermocouple Log Fuel Nozzle Log Engine Check List LLP Shop Visit Summary List of Replaced Parts AD Status SB Status RGB Maintenance Log RGB Logbook Entries BSI Report
PRATT & WHITNEY CANADA ENGINE MODEL: PW150A ENGINE BORESCOPE REPORT CUSTOMER: Willis Lease Finance Corp. SERIAL NUMBER: PCE- FA0278
EXPORT CONTROL CLASSIFICATION 2 of 34
HISTORICAL FACTS: SALES ORDER: 192734 ENGINE MODEL: TURBOMACHINERY S/N: REDUCTION GEARBOX S/N: CUSTOMER: PW150A FA0278 FA0278 Willis Lease Finance Corp. PREVIOUS SHOP VISIT: September 10, 2014 DATE OF ENGINE REMOVAL: May 1, 2016 DATE OF REVIEW: August 25, 2016 TIME SINCE NEW (TM): 15012.0 TIME SINCE NEW (GB): 15012.0 TIME SINCE O/H (TM): N/A TIME SINCE O/H (GB): 3596.0 HOURS HOURS TIME SINCE H.S.I: N/A HOURS TIME SINCE REPAIR 2055.7 TIME SINCE REPAIR 2055.7 HOURS BY: Jean-Yves Picard PURPOSE: This borescope report is based on a review performed after engine test. REASON FOR REMOVAL: This engine was sent to PWC ST-Hubert service centre due to HP impeller replacement. FINDINGS AT INCOMING INSPECTION: Free rotating of LP, HP impeller and PT rotors. Both chip detectors: Both oil filters: Nothing to report. Nothing to report. 3 of 34
ENGINE TEARDOWN REPORT RECOMMENDED WORKSCOPE: Repair turbomachinery in accordance with PW150A engine manual and CIR (cleaning inspection and repair) manual. Inspect turbomachinery in accordance with S.I. P&WC: 38-2015 for HP impeller replacement. Repair reduction gearbox in accordance with PW150A engine manual and CIR (cleaning inspection and repair) manual. Visually inspect reduction gearbox and engine accessories in accordance with SI PWC: 57-2007 Rev.2. CONCLUSION: During borescope engine review after test, the following conditions were observed: - The reduction gearbox module components showed no obvious damages. - The inner liner floating collars exhibit fretting wear. - The hot section components displayed cracks and / or heat erosion. - The first and second stage PT blades showed corrosion attack. All damages observed found acceptable per PW150A engine manual borescope limits without additional monitoring other than the regular maintenance. Conclusion as to possible causes of the observed problem will be considered as opinion only. PREPARED BY: DATE ISSUED: August 29, 2016 4 of 34
FIRST STAGE HELICAL RIGHT The reduction gearbox module showed: No obvious damages. 5 of 34
FIRST STAGE INPUT SHAFT The reduction gearbox module showed: No obvious damages. 6 of 34
FIRST STAGE HELICAL LEFT The propeller shaft and oil seal runner showed: No obvious damages. 7 of 34
SECOND STAGE PINION LEFT The 1st stage input shaft showed: No obvious damages. 8 of 34
SECOND STAGE BULL GEAR The 1st stage helical gears showed: No obvious damages. 9 of 34
SECOND STAGE PINION RIGHT The 2nd stage bull gear showed: No obvious damages. 10 of 34
1st STAGE COMPRESSOR ROTOR The 1st stage compressor rotor showed: No obvious damage. 11 of 34
1st STAGE COMPRESSOR STATOR ASSY The 1st stage compressor stator assy showed: No obvious damage. 12 of 34
2nd STAGE COMPRESSOR ROTOR The 2nd stage compressor rotor showed: Minor dent at one leading edge. (Within limits). 13 of 34
LP COMPRESSOR STATOR ASSY The low pressure compressor stator assy showed: Dirty condition. 14 of 34
3rd STAGE COMPRESSOR ROTOR The 3rd stage compressor rotor showed: No obvious damage. 15 of 34
LP COMPRESSOR STATOR SET The low pressure compressor stator set showed: No obvious damages. 16 of 34
HP IMPELLER The high pressure impeller showed: No obvious damage. 17 of 34
DIFFUSER EXIT DUCT ASSY The diffuser exit duct assy showed: No obvious damage. 18 of 34
FLOATING COLLARS The fuel nozzles showed: Fretting wear at fuel nozzle bosses floating collars. 19 of 34
COMBUSTION CHAMBER OUTER LINER The combustion chamber outer liner showed: No obvious damage. 20 of 34
COMBUSTION CHAMBER INNER LINER The combustion chamber inner liner showed: Crack and heat erosion at panel sections. Heat erosion at fuel nozzle bosses. 21 of 34
COMBUSTION CHAMBER SMALL EXIT DUCT The combustion chamber small exit duct showed: No obvious damage. 22 of 34
HP TURBINE VANE SEGMENTS The high pressure turbine vane segments showed: Hairline cracks on the airfoil surfaces. Cracks and heat erosion at the trailing edges outer shroud lip. 23 of 34
HP TURBINE BLADES The high pressure turbine blades showed: Rubbing at the airfoil tip. Reddish deposits on airfoil surfaces. 24 of 34
HP TURBINE SHROUD SEGMENTS The high pressure turbine shroud segments showed: Rubbing. 25 of 34
LP TURBINE VANE SEGMENTS The low pressure turbine vane segments showed: Small cracks on the airfoil surfaces. 26 of 34
LP TURBINE BLADES The low pressure turbine blades showed: Light erosion at airfoil tip. 27 of 34
LP TURBINE SHROUD SEGMENTS The low pressure turbine shroud segments showed: No obvious damage. 28 of 34
INTERSTAGE TURBINE VANE RING ASSY The interstage turbine vane ring assy showed: Blueish discoloration. 29 of 34
POWER TURBINE VANE RING ASSY The power turbine vane ring assy showed: Discolored airfoils. 30 of 34
1st STAGE POWER TURBINE BLADES The 1st stage power turbine blades showed: Discolored airfoil. Corrosion attack and numerous pits. 31 of 34
2nd STAGE POWER TURBINE BLADES The 2nd stage power turbine blades showed: Corrosion attack and numerous pits. 32 of 34
NO 5 BEARING AREA No obvious leakage observed. 33 of 34
NO 5 BEARING AREA No obvious leakage observed. 34 of 34