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CFM56-3_BALANCING_NEW

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CFM56-3_BALANCING_NEW

  1. 1. # Blade SN Blade MW Balance Screw PN (PXX) # Blade SN Blade MW Balance Screw PN (PXX) 1 20 2 21 3 22 4 23 5 24 6 25 7 26 8 27 9 28 10 29 11 30 12 31 13 32 14 33 15 34 16 35 17 36 18 37 19 38 Damaged blades positions #: MW Date Engine SN : Notes: 1. Write each blade SN, MW (from blade root). Mark damaged blades. 2. Write each balance screw PN except for balance screws with PN …P07 or …P14 3. Write replacement blades SN, MW 4. Send filled and signed list to CFM56-3 FAN BLADES DATA VERIFICATION LIST Performed by name, sign (stamp) Customer : Aircraft reg # : Engine position : New blades SN
  2. 2. Report # Date Airline WP # Aircraft Engine Remarks Slot # Blade MW Balance screw MW Pair blade # Pair diff 1 3 5 6 7 1 32050 0,00 20 7 2 29334 0,00 21 15 3 31119 88,19 22 148 4 29941 0,00 23 33 5 31072 0,00 24 2 6 30057 0,00 25 9 7 31043 0,00 26 7 8 30136 0,00 27 5 9 31035 0,00 28 52 10 31146 0,00 29 18 11 30967 0,00 30 33 12 30276 137,80 31 65 13 30924 0,00 32 24 14 30362 0,00 33 11 15 30886 0,00 34 69 16 30478 0,00 35 145 17 30779 0,00 36 14 18 30661 0,00 37 46 19 30762 0,00 38 28 20 32057 0,00 1 21 29349 0,00 2 22 31267 0,00 3 23 29908 0,00 4 24 31070 0,00 5 25 30048 0,00 6 26 31036 0,00 7 27 30131 0,00 8 28 30983 0,00 9 29 31164 0,00 10 30 30934 0,00 11 31 30341 0,00 12 32 30900 0,00 13 33 30373 0,00 14 34 30817 0,00 15 35 30623 0,00 16 36 30765 0,00 17 37 30707 0,00 18 38 30734 0,00 19 U= 120,95 Phase A= 100,72 33-SNE26994 37-MAA25288 38-SNE18268 Total unbalance MW (gr x in) 9111M35P07 (14) 9111M35P07 (14) 32-SNE42099 9111M35P07 (14) 9111M35P07 (14) 209 Fan blades distribution after blades #10 and #29 replacement due to damage. Bal weights #3 P03, #12 P05. Ref to report #208, unballance reduced by 40 units. TVP-001616-14Transaero 2014.08.29 Engine CFM56-3 fan blades distribution and ballancing report *209/TVP-001616-14* 27-SNE40433 28-MAA99634 9111M35P07 (14) 9111M35P07 (14) 9111M35P07 (14) 9111M35P07 (14) 9111M35P07 (14) 36-SNE18237 31-SNU54970 34-SNE39213 35-SNE18338 9111M35P07 (14) 02-KGAT5416 30-MAA72046 29N-MAA95049 21-SNE13132 26-MAA57452 13-MAA21337 14-SNE41996 15-SNE39151 18-MAA44800 24-MAAA0261 25-SNE41089 19-SNE41174 20-MAA25026 22-SNU65345 23-SNE40420 10N-MAA92044 12-SNE18709 9111M35P05 (12) 9111M35P07 (14) 9111M35P07 (14) 06-SNE40415 07-SNE41855 08-SNE40437 09-MAA10212 17-SNE16510 9111M35P07 (14) 9111M35P07 (14) Balance screw PN 9111M35P07 (14) 4 EI-DTW Blade SN 2 01-MAA16479 RH 726454 03-MAAA0420 04-SNE37890 05-MAAB5266 11-SNE41332 16-SNE18235 9111M35P07 (14) 9111M35P07 (14) 9111M35P03 (10) 9111M35P07 (14) 9111M35P07 (14) 9111M35P07 (14) 9111M35P07 (14) 9111M35P07 (14) 9111M35P07 (14) 9111M35P07 (14) 9111M35P07 (14) 9111M35P07 (14) 9111M35P07 (14) 9111M35P07 (14) 9111M35P07 (14) 9111M35P07 (14) 9111M35P07 (14) 9111M35P07 (14) 9111M35P07 (14) 9111M35P07 (14) 9111M35P07 (14) 9111M35P07 (14) SAMPLE
  3. 3. Report # Date Airline WP # Aircraft Engine 209 TVP-001616-14Transaero 2014.08.29 Engine CFM56-3 fan blades distribution and ballancing report *209/TVP-001616-14* EI-DTW RH 726454 2. Install all blades in slots in sequence from 1 to 38. Blade for slot #1 is in row #1 and so on. 3. Install balance screws PN as marked in column #4. Fan blades installation instructions 1. "Slot #" blade slot number from reference point. "Blade SN" XXN-ABC12345 (XX blade "old" position, N-new blade, D-damaged blade, ABC12345-blade Serial Number. "Blade MW" all blades moment weight ir gr x in. "Balance screw MW". "Pair blade" each blade opposite blade slot number. "Pair diff" all pair of blades MW difference. 5. After all blades installation Vibration survey (Test #7) IAW AMM 710000 is mandatory. 4. Installer is responsible for all blades SN and MW and balance weights PN and MW rechecking according to this report and installation on the fan disk according to this report. 6. Please send Test #7 results in format %N1/%N2/VIB to andrius.gudelis@fltechnics.com 7. If Test #7 results are not satisfactory contact to andrius.gudelis@fltechnics.com 8. THIS REPORT IS NOT RELEASE TO SERVICE Engine run IAW CFM56-3 AMM 71-00-00 Test #7 result:Performed by To be reported after engines run Test #7. 2014.08.29 A. Gudelis LT-TI-016 Report calculated and prepared with software Results sample: 45.5/87.7/3.6 SAMPLE

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