TASK 71-00-00-700-009 Test No. 9 - Low Pressure (LP) Compressor (Fan) Trim Balancing (Trial Weight Method), Testing-009

DMC:V2500-A0-71-00-0000-00A-709A-B|Issue No:001.00|Issue Date:2013-11-01

Export Control

EAR Export Classification: Not subject to the EAR per 15 C.F.R. Chapter 1, Part 734.3(b)(3), except for the following Service Bulletins which are currently published as EAR Export Classification 9E991: SBE70-0992, SBE72-0483, SBE72-0580, SBE72-0588, SBE72-0640, SBE73-0209, SBE80-0024 and SBE80-0025.

Copyright

© IAE International Aero Engines AG (2001, 2014 - 2021) The information contained in this document is the property of © IAE International Aero Engines AG and may not be copied or used for any purpose other than that for which it is supplied without the express written authority of © IAE International Aero Engines AG. (This does not preclude use by engine and aircraft operators for normal instructional, maintenance or overhaul purposes.).

Applicability

All

Common Information

TASK 71-00-00-700-009 Test No. 9 - Low Pressure (LP) Compressor (Fan) Trim Balancing (Trial Weight Method), Testing-009

General

This TASK gives the trim balance procedure for the LP compressor (fan) rotor.

This procedure uses three trial balance weights (dummy weights). It makes you compare the actual unbalance vibration indication with the unbalance indication with the three trial trim balance weights installed at the consecutive positions (bolt holes).

The data is vectorially plotted to find the phase angle and the vibration amount necessary for the final trim balance.

This procedure requires three trial trim balance weights (dummy weights). Use the actual trim balance weights, Item No.14, Identification No. 5A0014, as the trial trim balance weights (dummy weights). Refer to Table 4, Figure.

This procedure requires graphical vectorial analysis. Prepare and use a polar graph sheet.

Instructions to operate the engine, engine safety precautions, and other general information are found in Engine Safety Precautions and Engine Operation Limits, Guidelines, and Special Precautions. Refer to TASK 71-00-00-700-050-A00 (TESTING-000, CONFIG-001), TASK 71-00-00-700-050-B00 (TESTING-000, CONFIG-002),TASK 71-00-00-700-051-A00 (TESTING-000, CONFIG-001), and TASK 71-00-00-700-051-B00 (TESTING-000, CONFIG-002).

When you measure the vibration amount and angle, you must use the same vibration channel throughout this TASK.

When you measure the vibration angle you must measure it in a clockwise direction when you look from the engine front.

Angular directions (clockwise/counterclockwise) in this TASK are identified as the directions when you look from the engine front.

NOTE

To identify the consumable materials refer to the PCI.

NOTE

Continue Test No.8 until you finish measuring the vibration at the vibration check points.

NOTE

When you measure the vibration you must take the measurement points going down through the speed range.

NOTE

The angles AD1, AD2 and AD3 are phase lag of the peak point of LP order vibration after pulse signal from the trim balance probe.

NOTE

It is recommended that you install the trial trim balance weights near the angular position AD1 because it is considered that the angular position AD1 is the unbalance position (lightest amount).

NOTE

The trial trim balance weight cannot be installed on the bolts which attach the inlet cone fairing because the trim balance weights can cause to touch the inlet cone fairing.

NOTE

The trial trim balance weight cannot be installed at the position where the existing trim balance weights are already installed.

NOTE

  1. Do not install the washer Inlet Cone Assembly And Inlet Cone Fairing (72-38-11, 01-215) at the bolt hole where the trim balance weight is installed.

  2. The trial trim balance weight is the same as the trim balance weight Item No.14, Identification No.5A0014. See Table 4, Figure.

NOTE

The washer must be installed at the bolt hole where a trim balance weight is not installed.

NOTE

AC1 is the direction from the arrow head of AV1 to the arrow head of AV4. Angle AB1 is the clockwise angle from AC1 to AV1.

NOTE

Get AC2 and angle AB2 with the same method as AC1 and angle AB1.

NOTE

Get AC3 and angle AB3 with the same method as AC1 and angle AB1.

NOTE

Radius of the pitch circle of 24 bolts holes in the inlet cone flange is 7.913in. (201 mm).

NOTE

The inlet cone fairing was removed in step 8.

NOTE

Where the trim balance weight was already installed at the found positions in step 10.B, find the replacement trim balance weight. The value of the replacement weight must be the same as the sum of the values of the existing trim balance weight and the additional value found in step 10.B.

NOTE

The trial trim balance weight cannot be installed on the bolts which attach the inlet cone fairing because the trim balance weights can cause to touch the inlet cone faring.

NOTE

The bolt holes A are the holes where the bolts, which attach the inlet cone fairing, are installed.

NOTE

Do not install the washer Inlet Cone Assembly And Inlet Cone Fairing (72-38-11, 01-215) at the bolt hole where the trim balance weight is installed.

NOTE

The inlet cone fairing was removed in step 8.

NOTE

Use a marker to make temporary marks of positions of these that follow on the front retaining ring:
- the inlet cone
- the trim balance weights if they are initially installed

NOTE

6.540in. is the radius of the pitch circle of the 36 bolt holes in the front retaining ring flange.

NOTE

The first element of HXX-XX on Table 8 shows the bolt hole No. The second element shows the Item No. of trim balance weight, Figure.
H21-4, for example, shows bolt hole No.21 and the Weight Item No.4 (25 gm), Figure.

NOTE

If another trim balance weight (Item No. 1, 2, 3 and/or 4) was already installed at the same position where you require to install the trim balance weight, add the weight value to the value found in step 13.C.(3). Install a trim balance weight of a value equal to the sum.

NOTE

Do not install more than one trim balance weight at one position.

NOTE

Install the washer Inlet Cone Assembly And Inlet Cone Fairing(72-38-11,01-215) at the bolt hole where a trim balance weight is not installed. Do not install the washer at the bolt hole where the trim balance weight is installed.

Preliminary Requirements

Pre-Conditions

NONE

Support Equipment

NameManufacturerPart Number / IdentificationQuantityRemark
OscilloscopeLOCALOscilloscope

Consumables, Materials and Expendables

NameManufacturerPart Number / IdentificationQuantityRemark
CoMat 06-069 MARKERIE207CoMat 06-069

Spares

NONE

Safety Requirements

NONE

Procedure

    1. Do a Vibration Survey

      1. Do a vibration survey by the Test No.8 - Vibration Survey. Refer to TASK 71-00-00-700-008-A00 (TESTING-008, CONFIG-001) and TASK 71-00-00-700-008-B00 (TESTING-008, CONFIG-002). Measure and record the following data:

      1. N1/N2 vibration peaks.

      2. N1/N2 speeds at which vibration peaks occurred.

    2. Examine the Vibration Amount at the Speed Where the Vibration Peak Occurs, Fig. 71-00-00-990-124

      1. Examine the following vibration peaks which are measured and recorded in step 3.A. For the limits, refer to TASK 71-00-00-700-051-A00 (TESTING-000, CONFIG-001) and TASK 71-00-00-700-051-B00 (TESTING-000, CONFIG-002), Engine Operation Limits, Guidelines and Special Procedures; Vibration Limits.

      1. N1/N2 vibration peaks.

      2. N1/N2 speeds at which vibration peaks occurred.

    3. Measure the Vibration at the Vibration Check Points Without the Trial Trim Balance Weights

    1. Slowly increase the engine speed to takeoff power. Refer to TASK 71-00-00-700-008-A00 (TESTING-008, CONFIG-001) and TASK 71-00-00-700-008-B00 (TESTING-008, CONFIG-002).

    2. Slowly decrease the engine speed to the vibration check points which are shown in TABLE 3, Figure.

    3. After the engine speed gets to a vibration check point, keep the speed for one minute before you measure the vibration.

      4. Measure the engine speeds (AS1, AS2, AS3), vibration amounts (AV1, AV2, AV3) and the angles (AD1, AD2, AD3) in N1 order at the three vibration check points and write on TABLE 3, Figure.

      1. Measure the angles AD1, AD2 and AD3 with an oscilloscope or an equivalent.

    5. Go back to MIN IDLE for six minutes.

    6. Do a shutdown by the Discontinued Start and Shutdown Procedure. Refer to TASK 71-00-00-700-054-A00 (TESTING-000, CONFIG-001) and TASK 71-00-00-700-054-B00 (TESTING-000, CONFIG-002).

    4. Install the Trial Trim Balance Weights to the Inlet Cone Flange, Fig. 71-00-00-990-123-001 and Fig. 71-00-00-990-123-002

      1. Remove the inlet cone fairing

      1. Make temporary marks on the front blade retaining ring with CoMat 06-069 MARKER to identify the position of the inlet cone fairing.

      2. Remove the six bolts and the inlet cone fairing from the inlet cone. Refer to TASK 72-38-11-020-001

      2. Find the position at which you install the three trial trim balance weights

      1. Make sure of the angular position AD1 which was measured in step 5.D.

        The angular position AD1 was recorded on Table 3, Figure.

      2. Find three consecutive bolts which are near the angular position AD1.

      3. Install the three trial trim balance weights on to the inlet cone flange

      1. Remove the three bolts and washers from the found bolt holes B.

      2. Install the three trial trim balance weights Inlet Cone Assembly And Inlet Cone Fairing (72-38-11, 01-460) to the bolt holes B with the bolts Inlet Cone Assembly And Inlet Cone Fairing (72-38-11, 01-220).

      3. Torque the bolts to 180 to 220 lbfin (20.00 to 25.00 Nm).

    4. Measure the angle ADo clockwise from the timing mark to the center of the three trial trim balance weights.

    5. Write the angular position ADo on TABLE 7A, Figure.

    6. Install the inlet cone fairing and the six bolts Inlet Cone Assembly And Inlet Cone Fairing (72-38-11, 01-130) to the initial position and torque the bolts to 180 to 220 lbfin (20.00 to 25.00 Nm). Refer toTASK 72-38-11-420-001.

    5. Measure the Vibration at the Vibration Check Points in the TABLE 5, Fig. 71-00-00-990-125

    1. Do Test No.8. Refer to TASK 71-00-00-700-008-A00 (TESTING-008, CONFIG-001) and TASK 71-00-00-700-008-B00 (TESTING-008, CONFIG-002).

    2. Measure and write the vibration at the vibration check points. Write the data on Table 5.

    3. Go back to MIN IDLE for six minutes.

    4. Do a shutdown by the Discontinued Start, Restart and Shutdown Procedures. Refer to TASK 71-00-00-700-054-A00 (TESTING-000, CONFIG-001) and TASK 71-00-00-700-054-B00 (TESTING-000, CONFIG-002).

    6. Remove the Trial Trim Balance Weights, Fig. 71-00-00-990-123-001

      1. Remove the inlet cone fairing

      1. Make temporary marks on the front blade retaining ring with CoMat 06-069 MARKER to identify the position of the inlet cone fairing.

      2. Remove the six bolts and the inlet cone fairing from the inlet cone. Refer to TASK 72-38-11-020-001 (REMOVAL).

      2. Remove the trial trim balance weights and install the washer.

      1. Remove the three bolts which attach the trial trim balance weights to the inlet cone.

      2. Replace each trial balance weight with the washer Inlet Cone Assembly And Inlet Cone Fairing (72-38-11, 01-215).

      3. Install the washers with the bolts Inlet Cone Assembly And Inlet Cone Fairing (72-38-11, 01-220). Torque the bolts to 180 to 220 lbfin (20.00 to 25.00 Nm).

    7. Calculate the Trim Balance Effect Vectors at the Three Speeds, Fig. 71-00-00-990-126

    1. Write the vector AV1 and AV4 on a polar coordinates, DIAGRAM 1.

    2. Write the vector AV2 and AV5 on a polar coordinates, DIAGRAM 2.

    3. Write the vector AV3 and AV6 on a polar coordinates, DIAGRAM 3.

    4. Get the vector AC1 and the angle AB1 on the polar coordinates, DIAGRAM 1.

    5. Get the vector AC2 and the angle AB2 on the polar coordinates, DIAGRAM 2.

    6. Get the vector AC3 and the angle AB3 on the polar coordinates, DIAGRAM 3.

      7. Calculate the required balance effect vectors AW1, AW2 and AW3. They are calculated with the following equations:

        Total amount TM0 = Moment effect of three trial trim

        balance weights (Item No.14, 5A0014)

        = 6.546 oz.in (4714 gm mm)

        Amount AW1 = TM0 (6.546 oz.in) x

        LENGTH AV1

        LENGTH AC1

        Amount AW2 = TM0 (6.546 oz.in) x

        LENGTH AV2

        LENGTH AC2

        Amount AW3 = TM0 (6.546 oz.in) x

        LENGTH AV3

        LENGTH AC3

      1. The direction of the vectors AW1, AW2 and AW3 are found as follows (DIAGRAM 4):

        Direction AW1: Clockwise turned from the

        trial trim weight direction by

        angle AB1 that is the

        clockwise angle from AC1 to AV1

        Direction AW2: Clockwise turned from the

        trial trim weight direction by

        angle AB2 that is the

        clockwise angle from AC2 to AV2

        Direction AW3: Clockwise turned from the

        trial trim weight direction by

        angle AB3 that is the

        clockwise angle from AC3 to AV3

    8. Calculate the Vector Average of Vectors AW1, AW2 and AW3 to Get the Required Trim Balance Weight

      1. Calculate vector sum of vectors AW1, AW2 and AW3

      1. Make lines of vectors AW1, AW2 and AW3 on DIAGRAM 4 as following sequence, Figure.

        AW1 has not got a start point but has a direction Clockwise angle AB1 from datum.

        AW2 has a start point at the end of AW1 and a direction clockwise angle AB2 from the datum.

        AW3 has a start point at the end of AW2 and a direction clockwise angle AB3 from the datum.

      2. Get vector sum AW4 and angle AB4. Vector AW4 starts at the root of AW1 and stops at the tip of AW3. AB4 is the clockwise angle from the datum line to vector AW4.

    2. Calculate the required trim balance weight W to correct the unbalance

      W oz =

      AW4 length

      X

      1

      3

      7.913

      W gm =

      AW4 length

      X

      1

      3

      201,00

    3. Get the required trim phase angle AK in the clockwise direction from the timing mark on the front retaining ring, Figure.

      AK = ADo (clockwise angle from the timing mark

      to the trial trim balance weight position)

      +

      AB4 (clockwise angle from the datum line

      to the vector AW4)

    9. Find the Flange at which the Required Trim Balance Weight (Unbalance Amplitude W) is to be Installed

    1. If the required trim balance weight W is not more than 1 oz (28 gm), trim the LP compressor balance with the trim balance weights on the inlet cone flange. Go to step 12.

    2. If the required trim balance weight W is more than 1 oz (28 gm), trim the LP compressor balance with the trim balance weights on the retaining ring flange. Go to step 13.

    10. Install the Trim Balance Weights to the Inlet Cone Flange (24 Bolt Flange)

    1. Make sure that the inlet cone fairing is not installed on the inlet cone.

      2. Find the trim balance weights and positions

      1. Find the trim balance weight and positions with W, FA and Table 7, Figure.

      2. Find the trim balance weights with the result of step 10.B. and Table 4, Figure.

      3. An example follows:

      1. Suppose that the required trim balance weight W calculated in step 10.B. is 12.7 gm and that the necessary trim angular position (phase angle) AK is 398 degrees.

      2. Suppose that bolt holes A are 15, 75, 135, 195, 255 and 315 degrees clockwise apart from the timing mark, Figure.nd Figure.

      3. Calculate the unbalance phase angle FB.

        FB = AK - 180

        = 398 - 180

        = 218 degrees

      4. Find the bolt hole A near to the unbalance phase, in a clockwise direction looking from the engine front.

        The bolt hole A which is 195 degrees apart from the timing mark is selected, Figure.

      5. Give the numbers N1 to N24 to the bolt holes. N1 must be given to the hole A found in step (4). The remaining numbers must be identified in clockwise direction when you look from the engine front.

      6. Calculate the unbalance phase angle FA.

        FA = FB - 195

        = 218 - 195

        = 23 degrees

      7. Find the nearest unbalance amplitude on Table 7 to the W (12.7 gm).

        The nearest unbalance amplitude = 15 gm.

      8. Find the nearest unbalance phase angle FA on Table 7 to the FA (36 degrees) found in step (6).

        The nearest unbalance phase angle = 25 degrees.

      9. Find the trim balance weights and positions from Table 7 Sheet 4 with 15 gm and 25 degrees, Figure.

        The following data are found

        N2-11

        N14-14

        N15-14

        N24-11

      10. The found trim balance weights and positions are shown on Figure.

      4. Install the trim balance weights to the found positions which are found in step B., Figure.

      1. To find the positions where you require to install the trim balance weights, count the hole numbers. Start at bolt hole No.N1 which is near to the unbalance phase and go clockwise when you look from the engine front.

      2. Make a mark on the front blade retaining ring with CoMat 06-069 MARKER to identify the position of the trim balance weights.

      3. Remove the bolts and the washers from the found positions and remove the trim balance weights, if they were already installed at the positions. Refer to the NOTE in step 12.B.(2).

      4. Make sure of the identification mark and the weight value identified on each trim balance weight, Figure.

      6. Torque the bolts to 180 to 220 lbfin (20.00 to 25.00 Nm).

    5. Install the inlet cone fairing and the six bolts Inlet Cone Assembly And Inlet Cone Fairing (72-38-11, 01-130) to the initial position. Refer to TASK 72-38-11-420-001 (INSTALLATION).

    6. Go to step 14.

    11. Install the Trim Balance Weights to the Front Blade Retaining Ring

    1. Make sure that the inlet cone fairing is not installed on the inlet cone.

    2. Remove the inlet cone. Refer to TASK 72-38-11-020-001.

      3. Find the trim balance weights and positions

      1. Calculate the required trim balance weight (unbalance amplitude) WF on the front retaining ring flange with the following formula.

        WF = W x

        7.913

        6.540

        = W x 1.210

      2. Calculate the unbalance phase angle FB

        FB (degrees) = AK - 180

      3. Find the bolt hole numbers and Fig Item numbers of the trim balance weights with WF, FB and Table 8, Figure.

      4. Find the trim balance weights with the result of step 13.C.(1) and Table 6, Figure.

      4. An example follows:

      1. Suppose that the required trim balance weight W is 28.4 gm and the trim phase angle AK (clockwise) is 241 degrees.

      2. Calculate the required trim balance weight (unbalance amplitude) WF on the retaining ring flange.

        WF = W x 1.210

        = 28.4 x 1.210

        = 34.4 gm

      3. Calculate the unbalance phase angle FB.

        FB = AK - 180

        = 241 - 180

        = 61 degrees

      4. Find the nearest unbalance amplitude on Table 8 to the WF (34.4 gm).

        The nearest unbalance amplitude = 30 gm

      5. Find the nearest unbalance phase angle FB on Table 8 to FB (61 degrees) found in step (3).

        The nearest unbalance phase angle FB = 60 degrees

      6. Find the trim balance weights and positions from Table 8 Sheet 18 with 30 gm and 60 degrees, Figure.

        The following data are found

        H24-2

        H25-4

        H28-1

      7. The found trim balance weights and positions are shown on Figure.

      5. Install the trim balance weights at the positions, Figure.

      1. To find the positions where you require to install the trim balance weights, count holes counterclockwise from the timing mark on the front blade retaining ring, Figure.

      2. Remove the bolts at the found position. Remove the trim balance weight if it was already installed at the found position.

      3. Make sure of the identification mark and the weight value of each trim balance weight, Figure.

      4. Install the trim balance weights ENGINE-LP COMPRESSOR (FAN) MODULE (72-31-00, 01-164 , ENGINE-LP COMPRESSOR (FAN) MODULE 01-165, ENGINE-LP COMPRESSOR (FAN) MODULE 01-166 and ENGINE-LP COMPRESSOR (FAN) MODULE 01-167) to the front blade retaining ring with bolts ENGINE-LP COMPRESSOR (FAN) MODULE (72-31-00, 01-120).

      5. Torque the bolts to 180 to 220 lbfin (22.00 to 25.00 Nm).

    6. Install the inlet cone, the trim balance weights Inlet Cone Assembly And Inlet Cone Fairing (72-38-11, 01-440 , Inlet Cone Assembly And Inlet Cone Fairing 01-445, Inlet Cone Assembly And Inlet Cone Fairing 01-450, Inlet Cone Assembly And Inlet Cone Fairing 01-455 and Inlet Cone Assembly And Inlet Cone Fairing 01-460), the washers Inlet Cone Assembly And Inlet Cone Fairing (72-38-11, 01-215) and the 18 bolts Inlet Cone Assembly And Inlet Cone Fairing (72-38-11, 01-220) to the initial positions, Figure and Figure. Refer to TASK 72-38-11-420-001.

    7. Install the inlet cone fairing and the six bolts Inlet Cone Assembly And Inlet Cone Fairing (72-38-11, 01-130) to the initial position. Refer to TASK 72-38-11-420-001.

    12. Do a Vibrational Survey

    1. Do a vibration survey by the Test No.8 - Vibration Survey. Refer to TASK 71-00-00-700-008-A00 (TESTING-008, CONFIG-001) and TASK 71-00-00-700-008-B00 (TESTING-008, CONFIG-002).

    2. Make sure that the vibration is in the limits listed in TASK 71-00-00-700-051-A00 (TESTING-000, CONFIG-001) and TASK 71-00-00-700-051-B00 (TESTING-000, CONFIG-002), Engine Operation Limits, Guidelines and Special Procedures; Vibration Limits.

    13. Figure: Trim balance weight installation position

    Trim balance weight installation position

    Figure: Trim balance weight installation position

    Trim balance weight installation position

    Figure: Vibration limits and vibration record sheets

    Vibration limits and vibration record sheets

    Figure: Trim Balance Weights and vibration record sheets

    Trim Balance Weights and vibration record sheets

    Figure: Vector diagram to calculate trim amount

    Vector diagram to calculate trim amount

    Figure: Table 7 Sheet 1 Trim balance weight and bolt hole No. (Inlet cone flange)

    Table 7 Sheet 1 Trim balance weight and bolt hole No. (Inlet cone flange)

    Figure: Table 7 Sheet 2 Trim balance weight and bolt hole No. (Inlet cone flange)

    Table 7 Sheet 2 Trim balance weight and bolt hole No. (Inlet cone flange)

    Figure: Table 7 Sheet 3 Trim balance weight and bolt hole No. (Inlet cone flange)

    Table 7 Sheet 3 Trim balance weight and bolt hole No. (Inlet cone flange)

    Figure: Table 7 Sheet 4 Trim balance weight and bolt hole No. (Inlet cone flange)

    Table 7 Sheet 4 Trim balance weight and bolt hole No. (Inlet cone flange)

    Figure: Example of trim balance weights on inlet cone flange

    Example of trim balance weights on inlet cone flange

    Figure: Table 8 Sheet 1 Trim balance weights and bolt hole No. (Retaining ring flange)

    Table 8 Sheet 1 Trim balance weights and bolt hole No. (Retaining ring flange)

    Figure: Table 8 Sheet 2 Trim balance weights and bolt hole No. (Retaining ring flange)

    Table 8 Sheet 2 Trim balance weights and bolt hole No. (Retaining ring flange)

    Figure: Table 8 Sheet 3 Trim balance weights and bolt hole No. (Retaining ring flange)

    Table 8 Sheet 3 Trim balance weights and bolt hole No. (Retaining ring flange)

    Figure: Table 8 Sheet 4 Trim balance weights and bolt hole No. (Retaining ring flange)

    Table 8 Sheet 4 Trim balance weights and bolt hole No. (Retaining ring flange)

    Figure: Table 8 Sheet 5 Trim balance weights and bolt hole No. (Retaining ring flange)

    Table 8 Sheet 5 Trim balance weights and bolt hole No. (Retaining ring flange)

    Figure: Table 8 Sheet 6 Trim balance weights and bolt hole No. (Retaining ring flange)

    Table 8 Sheet 6 Trim balance weights and bolt hole No. (Retaining ring flange)

    Figure: Table 8 Sheet 7 Trim balance weights and bolt hole No. (Retaining ring flange)

    Table 8 Sheet 7 Trim balance weights and bolt hole No. (Retaining ring flange)

    Figure: Table 8 Sheet 8 Trim balance weights and bolt hole No. (Retaining ring flange)

    Table 8 Sheet 8 Trim balance weights and bolt hole No. (Retaining ring flange)

    Figure: Table 8 Sheet 9 Trim balance weights and bolt hole No. (Retaining ring flange)

    Table 8 Sheet 9 Trim balance weights and bolt hole No. (Retaining ring flange)

    Figure: Table 8 Sheet 10 Trim balance weights and bolt hole No. (Retaining ring flange)

    Table 8 Sheet 10 Trim balance weights and bolt hole No. (Retaining ring flange)

    Figure: Table 8 Sheet 11 Trim balance weights and bolt hole No. (Retaining ring flange)

    Table 8 Sheet 11 Trim balance weights and bolt hole No. (Retaining ring flange)

    Figure: Table 8 Sheet 12 Trim balance weights and bolt hole No. (Retaining ring flange)

    Table 8 Sheet 12 Trim balance weights and bolt hole No. (Retaining ring flange)

    Figure: Table 8 Sheet 13 Trim balance weights and bolt hole No. (Retaining ring flange)

    Table 8 Sheet 13 Trim balance weights and bolt hole No. (Retaining ring flange)

    Figure: Table 8 Sheet 14 Trim balance weights and bolt hole No. (Retaining ring flange)

    Table 8 Sheet 14 Trim balance weights and bolt hole No. (Retaining ring flange)

    Figure: Table 8 Sheet 15 Trim balance weights and bolt hole No. (Retaining ring flange)

    Table 8 Sheet 15 Trim balance weights and bolt hole No. (Retaining ring flange)

    Figure: Table 8 Sheet 16 Trim balance weights and bolt hole No. (Retaining ring flange)

    Table 8 Sheet 16 Trim balance weights and bolt hole No. (Retaining ring flange)

    Figure: Table 8 Sheet 17 Trim balance weights and bolt hole No. (Retaining ring flange)

    Table 8 Sheet 17 Trim balance weights and bolt hole No. (Retaining ring flange)

    Figure: Table 8 Sheet 18 Trim balance weights and bolt hole No. (Retaining ring flange)

    Table 8 Sheet 18 Trim balance weights and bolt hole No. (Retaining ring flange)

    Figure: Table 8 Sheet 19 Trim balance weights and bolt hole No. (Retaining ring flange)

    Table 8 Sheet 19 Trim balance weights and bolt hole No. (Retaining ring flange)

    Figure: Table 8 Sheet 20 Trim balance weights and bolt hole No. (Retaining ring flange)

    Table 8 Sheet 20 Trim balance weights and bolt hole No. (Retaining ring flange)

    Figure: Table 8 Sheet 21 Trim balance weights and bolt hole No. (Retaining ring flange)

    Table 8 Sheet 21 Trim balance weights and bolt hole No. (Retaining ring flange)

    Figure: Table 8 Sheet 22 Trim balance weights and bolt hole No. (Retaining ring flange)

    Table 8 Sheet 22 Trim balance weights and bolt hole No. (Retaining ring flange)

    Figure: Table 8 Sheet 23 Trim balance weights and bolt hole No. (Retaining ring flange)

    Table 8 Sheet 23 Trim balance weights and bolt hole No. (Retaining ring flange)

    Figure: Table 8 Sheet 24 Trim balance weights and bolt hole No. (Retaining ring flange)

    Table 8 Sheet 24 Trim balance weights and bolt hole No. (Retaining ring flange)

    Figure: Example of trim balance weights on retaining ring flange

    Example of trim balance weights on retaining ring flange

    Figure: Identification mark on trim balance weight

    Identification mark on trim balance weight

Requirements After Job Completion

Follow-On Conditions

NONE
Manufacturer Code:IE207
Enterprise Name:DELETED, REFER TO 16956
Manufacturer Code:LOCAL
Enterprise Name:LOCALLY SUPPLIED
Manufacturer Code:IE207
Supply Number:CoMat 06-069
Type:sp01
Supply Short Name:CoMat 06-069 MARKER
Supply Name:CoMat 06-069 MARKER
Specification Groups:
Doc NumberType
OMAT:262TMARKS-A-LOT
JCR-085MARKS-A-LOT
Suppliers:
ManufacturerRemarks
IE207
Manufacturer Code:LOCAL
Tool Number:Oscilloscope
Tool Name:Oscilloscope