MINI PACK N/A N/A N/A N/A FA0995 N/A
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1 MINI PACK ENGINE MODEL: PW150 BUILD SPEC: 885 TM SN: FA0995 TSN: 4, CSN: 4,194 TSO: CSO: TSHSI: CSHSI: N/A N/A N/A N/A RGB SN: FA0995 TSN: 4, CSN: 5,194 TSO: N/A CSO: N/A CONTENTS: - TMM Transport Canada Form One - Dual EASA Release - RGB Transport Canada Form One - Dual EASA Release - LLP Status - Accessory Inventory - Post Rental Inspection - Logbook Entries - Borescope Report
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9 921 Michelin Laval, Quebec H7L 5B6 AMO No Borescope Inspection Report Engine PCE-FA0995 1
10 BORESCOPE INSPECTION REPORT ENGINE MODEL: ENGINE S/N: TIME HISTORY: CUSTOMER: PW 150A PCE-FA0995 TSN: 4327,6 hrs, CSN: 4194 / TSO: N/A, CSO: N/A Willis INSPECTION DATE: June 7, 2016 PREPARED BY: Nicolas Bazinet, aircraft maintenance engineer Background: This report covers Koptair s interpretation of the borescope inspection findings on the RGB gear train and cold/hot sections gas path components. The engine was borescope inspected in the facility of Koptair at Laval, Quebec on May 30, The inspection was requested by Willis Lease Finance Corporation This inspection was performed in accordance with the Bombardier maintenance manual PSM chapter 72, section instructions and borescope inspection criteria Note that in addition to the pictorial references inserted in this report, the borescope inspection has been recorded on videos. Video files will be sent to Willis representative attention You can refer to the conclusion section at the end of this report for a complete assessment describing the condition of the RGB gear train and TM cold/hot sections gas path components. The results of the borescope inspection and subsequent performed actions described in this report are aimed as an aid to help determine engine condition as viewed by Koptair s engineer a the time of the inspection 2
11 Borescope inspection findings: Reduction Gearbox First stage reduction: input shaft and helical gears There was no signs of corrosion, frosting or spalling on the input shaft gear teeth There was no signs of corrosion, frosting or spalling on the L/H and R/H helical gears Input shaft L/H and R/H helical gears (typical) Second stage reduction: pinion gears and bullgear There was no signs of corrosion, frosting or spalling on the pinion gears There was no signs of corrosion, frosting or spalling on the bull gear L/H and R/H pinions gears (typical) Bull gear 3
12 Borescope inspection findings: 1 st stage LP Compressor Rotor There was no evidence of erosion or FOD at airfoils edge 2 nd stage LP Compressor Rotor There was no evidence of erosion or FOD at airfoils leading edge 4
13 Borescope inspection findings: 3 rd stage LP Compressor Rotor There was no evidence of erosion or FOD at airfoils leading edge 2 nd stage Stator Grommets The grommets were found in good condition 5
14 Borescope inspection findings: HP Compressor Impeller There was no evidence of erosion or FOD at full and splitter vanes airfoils leading edge 6
15 Borescope inspection findings: Small Exit Duct and Combustion Inner Liner The inner liner wall and louvers were found in good condition. The fuel nozzle cups were also found in good condition There was no signs of burnt or hot streak on the small exit duct heat shield Inner liner Small exit duct 7
16 Borescope inspection findings: Combustion Outer Liner The outer liner panels at area B were found with multiple axial and radial cracks less than 2.00 in., converging cracks with no evidence that material could break away and 3 holes with a total surface area less than 1.00 in². The worst condition observed was the presence of an axial crack propagating from panel F to panel e measuring approximately 3.00 in long Hole Converging cracks Crack 8
17 Borescope inspection findings: HP vane ring assembly and HP turbine blades The HP blades were found in good condition. However, there was a significant accumulation of reddish deposit on the airfoil surface The HP shroud segments were found in good condition The HP vane airfoils leading and trailing edges were found in good condition. Reddish deposit HP blades leading edge HP shrouds HP vanes edge 9
18 Borescope inspection findings: LP Turbine blades The LP blades were found in good condition, there was no erosion at blades leading edge Trailing edge Leading edge LP Turbine Vane The LP vane airfoils leading and trailing edges were found in good condition Airfoils leading edge Airfoils trailing edge 10
19 Borescope inspection findings: 1 st and 2 nd stage PT blades The 1 st and 2 nd stages PT blades airfoil were found in good condition 1st stage PT blades leading edge 2nd stage PT blades trailing edge 11
20 Conclusion: BORESCOPE INSPECTION REPORT REDUCTION GEARBOX: The detailed borescope inspection of the reduction gearbox 1 st and 2 nd stages gear train revealed no deviation on the gear teeth COLD SECTION: The LP compressor rotors as well as the 2 nd stage stator grommets were found in good condition. There was no deviation observed on the HP impeller full and splitter vane airfoils HOT SECTION: The outer liner panels at area B were found with multiple axial and radial cracks less than 2.00 in., converging cracks with no evidence that material could break away and 3 holes with a total surface area less than 1.00 in². The worst condition observed was the presence of an axial crack propagating from panel F to panel e measuring approximately 3.00 in long The remainder hot section hardware was found in good condition OBESERVATION: The overall condition of the reduction gearbox, cold and hot sections hardware was found acceptable with no requirement for additional borescope monitoring, except for the combustor panels at area B that is subject to a subsequent borescope inspection monitoring at an interval not to exceed 600 hrs due to axial crack propagating from panel F to panel e measuring approximately 3.00 in long. Refer to Bombardier aircraft maintenance manual section , sub task for combustion chamber liner inspection limits reference table 12
MINI PACK BUILD SPEC. 885 ESN: FA0278 TSN: 15, CSN: 15,815 TSO: N/A CSO: N/A TSHSI: 2, CSHSI: 2,373 RGB SN. FA0278
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