2. # 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

3. 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

4. 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