TASK 72-41-00-440-003-A00 HPC Assembly - Replace The HPC Stage 3, 4, 5 And 6 Blades - (HPC Surgical Strike Procedure), Special Procedure-003

DMC:V2500-A1-72-41-0001-01A-710A-B|Issue No:005.00|Issue Date:2019-05-01

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

V2500-A1

Common Information

TASK 72-41-00-440-003-A00 HPC Assembly - Replace The HPC Stage 3, 4, 5 And 6 Blades - (HPC Surgical Strike Procedure), Special Procedure-003

General

This TASK gives the procedure to replace the HP compressor stage 4, 5 and 6 blades as part of the Surgical Strike workscope for -A1 series engines.

This TASK details the replacement of rotor blades by matching the residual out of balance of the replacement blades with that of the existing blades.

Fig/item numbers in parentheses in the procedure agree with those used in the IPC. Only the primary Fig/item numbers are used. For the service bulletin alpha variants refer to the IPC.

For all parts identified in a different Chapter/Section/Subject, the applicable Chapter/Section/Subject comes before the Fig/item numbers.

Overhaul processes referred to in the procedure by the TASK/SUBTASK number are in SPM.

For standard torque data and procedure refer to SPM TASK 70-41-00-400-501, SPM TASK 70-41-01-400-501 and SPM TASK 70-41-02-400-501.

Special torque data is identified with the symbol * after the torque value.

Special assembly tolerances are included in this procedure.

Lubricate all threads and mating faces of nuts and bolts with CoMat 10-077 APPROVED ENGINE OILS, unless other lubricants are referred to in the procedure.

All the curvic teeth and mating faces must be cleaned with CoMat 01-001 SOLVENT, DELETED or CoMat 01-002 SOLVENT, DELETED. before assembly. Refer to SPM TASK 70-11-01-300-503. They must also be dry assembled unless told differently in the procedure.

All of the temporary marks made in this procedure must be removed after completion of this task.

The minimum necessary equipment and requirements.

The recommended method of achieving acceptable rotor blade tip grinding using a dummy HPC rotor.

The normal overhaul Engine Manual limits apply to the tip grinding dimensions. It is necessary to make an inspection record of the final assembly tip dimensions and clearances achieved during this procedure.

Replacement blades can be tip ground in the dummy rotor before the pattern of unbalance procedure is done for the blade stage needing replacement.

The recommended type weighing machine for blade weight measurement.

The weighing machine used in this procedure must be capable of a minimum weighing accuracy of between 0.0018 oz to 0.0053 oz (0.05 g to 0.15 g).

The recommended method to balance pattern a set of rotor blades.

The blade distribution computer program VX45 or alternative program IAE 1R19842 Blade distribution computer program X45 must be used. The program will be able to match (within a tolerance) the residual out of balance left by the removal of an existing blade set with the new set.

The program will also account for fixed blade positions, such as, the locking blades and the segments between the locking blades. An example of this is seen during the platform gap setting of the stage 6 blades.

NOTE

To identify the consumable materials refer to the PCI.

NOTE

The tools specified are the minimum standard for this TASK. For subsequent standards of tools refer to the Illustrated Tools and Equipment Manual (ITEM).

NOTE

  1. Refer to TASK 72-41-00-040-000 (DISASSEMBLY-000, Pageblock-501) for the other related Surgical Strike TASKS and engine series.

  2. Refer to TASK 72-41-00-440-000 (ASSEMBLY-000, Pageblock-1001) for the other related Surgical Strike TASKS and engine series.

NOTE

VX45 is a MS DOS based program and IAE 1R19842 Blade distribution computer program X45 is a MS Windows based program.

Preliminary Requirements

Pre-Conditions

NONE

Support Equipment

NameManufacturerPart Number / IdentificationQuantityRemark
Dummy stageLOCAL

3 to 8 HP compressor

Dummy retaining platesLOCAL

stages 3, 4 and 5

Dummy lock platesLOCAL

stages 3, 4 and 5

Dummy set, nut and screw lock assemblyLOCAL

stage 6 (jacking screw and locknut assembly)

Moment weighing machineLOCAL

with V2500 stage 3 blade moment weight fixtures

Weighing machineLOCAL
WM00 (80MM INTERFACE)LOCALSCHENCK WM0

(80MM INTERFACE)

WM00 (80MM INTERFACE)LOCALSCHENCK WM0

(100MM INTERFACE) and REUTLINGER THB3 (100 mm) interface

IAE 1R18069 Rear anvil0AM53IAE 1R180691
IAE 1R18070 Front anvil0AM53IAE 1R180701
IAE 1R18071 Rear anvil0AM53IAE 1R180711
IAE 1R18072 Front anvil0AM53IAE 1R180721
IAE 1R18073 Rear anvil0AM53IAE 1R180731
IAE 1R18074 Front anvil0AM53IAE 1R180741
IAE 1R18076 Slave lock plates0AM53IAE 1R180761
IAE 1R18079 Drift0AM53IAE 1R18079
IAE 1R18080 Drift0AM53IAE 1R180801
IAE 1R18082 Pliers0AM53IAE 1R180821
IAE 1R18083 Hydraulic tool0AM53IAE 1R180831
IAE 1R18084 Pliers0AM53IAE 1R180841
IAE 1R18097 Drift0AM53IAE 1R180971
IAE 1R18245 Adapter0AM53IAE 1R182451
IAE 1R18590 Socket end0AM53IAE 1R185901
IAE 1R18683 Caliper adapter0AM53IAE 1R186831
IAE 1R18911 Drill0AM53IAE 1R189111
IAE 1R18914 Setting gage0AM53IAE 1R189141
IAE 1R19767 Fixture0AM53IAE 1R197671
IAE 1R19768 20mm Spacer0AM53IAE 1R197681
IAE 1R19811 Filing fixture0AM53IAE 1R198111
IAE 1R19812 Filing fixture0AM53IAE 1R19812
IAE 1R19813 Filing fixture0AM53IAE 1R19813
IAE 1R19842 Blade distribution computer program X450AM53IAE 1R19842

Consumables, Materials and Expendables

NameManufacturerPart Number / IdentificationQuantityRemark
CoMat 01-001 SOLVENT, DELETEDX111XCoMat 01-001
CoMat 01-002 SOLVENT, DELETED.X111XCoMat 01-002
CoMat 02-121 TEMPORARY MARKER PENCIL/CRAYONIE304CoMat 02-121
CoMat 02-122 TEMPORARY MARKER PENCIL/CRAYONK6835CoMat 02-122
CoMat 03-398 METAL SPRAYING STOPPING-OFFCOMPOUNDLOCALCoMat 03-398
CoMat 07-075 HIGH-HEAT RESISTING STOVING ENAMELk3504CoMat 07-075
CoMat 10-070 ANTI-SEIZE COMPOUNDLOCALCoMat 10-070
CoMat 10-077 APPROVED ENGINE OILSX333XCoMat 10-077

Spares

NameManufacturerPart Number / IdentificationQuantityRemark
PLATE - LOCKING0AM536A10299

(stage 3)

PLATE - LOCKING0AM536A10343

(stage 4)

PLATE - LOCKING0AM536A10393

(stage 5)

Safety Requirements

NONE

Procedure

    1. SUBTASK 72-41-00-040-208 Remove the Stage 3 HP Compressor Blades

      1. Correlate the stage 3 blades.

      1. NOTE

        Start from this No. 1 blade slot and number the blades in a clockwise direction when you look from the rear.
        It is recommended that the same direction is used throughout all procedures.

        Use CoMat 02-121 TEMPORARY MARKER PENCIL/CRAYON or CoMat 02-122 TEMPORARY MARKER PENCIL/CRAYON to temporarily mark the stage 3 disk rim and adjacent blade. Use this correlation mark as a start point and mark each of the stage 3 blades with a number from 1 to 31.

      2. Remove the blades from the stage 3 disk.

      1. NOTE

        This is to make sure that the light-heavy-light sequence is retained for the retaining plates.

        Correlate the sequence and positions of the retaining plates relative to the No. 1 slot.

      2. With an applicable tool remove the lockplates from the front of the stage 3 disk.

      3. With IAE 1R18079 Drift 1 off move the retaining plates around the disk to close up the space between them. This will give sufficient space to remove one blade, forwards, from the disk.

      4. Continue to move the retaining plates around the disk until sufficient blades have been removed to let you remove one of the retaining plates.

      5. Move the retaining plates, in turn, around the disk until they have all been removed.

      6. Remove the remaining blades from the stage 3 disk.

      7. Correlate balance weights and Silcoset from any balance weight holes relative to the No. 1 slot.

    2. SUBTASK 72-41-00-220-199 Inspect the Stage 3 Blade Retaining Plates

      1. Inspect the removed stage 3 retaining plates.

      2. If it is necessary to discard a stage 3 retaining plate then the replacement plate must be matched weighed and correlated with the unsatisfactory plate. Refer to SUBTASK 72-41-00-440-220.

    3. SUBTASK 72-41-00-440-227 Moment Weigh the Removed Stage 3 Blades and Weigh the Retaining Plate(s)

      1. Moment weigh the stage 3 compressor blades ENGINE-HP COMPRESSOR BLADES (72-41-15,01-200).

      1. CAUTION

        DAMAGE TO THE BLADES CAN OCCUR IF YOU DO NOT MAKE SURE THAT THE CORRECT MIXTURE OF BLADES ARE INSTALLED. REFER TO THE APPLICABLE SERVICE BULLETINS.

        Moment weigh each of the compressor blades in turn and keep a record of the weight against each blade identification number.

      2. NOTE

        You only need to match weigh the retaining plate(s) if it requires replacement.

        Weigh the stage 3 retaining plate(s).

      1. Weigh each of the particular retaining plate(s) to the nearest 0.0035 oz (0.100 g). Refer to TASK 72-41-10-440-003-B00, SUBTASK 72-41-10-440-160.

    4. SUBTASK 72-41-00-440-221 Determine the Residual Unbalance of the Stage 3 Blades

    1. Refer to Figure.

      2. Determine the residual unbalance, distance A.

      1. Put the resulting pattern of the stage 3 moment weights in to the blade distribution program VX45 or alternative method IAE 1R19842 Blade distribution computer program X45. The resultant residual unbalance will be a measurement in gmm at an angle from the correlation datum point.

      2. CAUTION

        MAKE SURE YOU USE THE CORRECT METHOD TO DETERMINE THE RESIDUAL UNBALANCE AND PREVENT DAMAGE TO ENGINE COMPONENTS. IT IS VERY IMPORTANT TO KNOW THAT THE BLADE SETS VECTOR IS IN THE OPPOSITE SENSE TO THE RESIDUAL UNBALANCE IN THE HP COMPRESSOR ROTOR.

        Record the residual unbalance, vector B. You must try to match the new set of blades with this target vector figure, refer to Step.

    5. SUBTASK 72-41-00-440-222 Install the Replacement Stage 3 Blades in the Dummy Rotor

    1. Refer to Figure, Figure, Figure and Figure.

      2. Install the stage 3 compressor blades.

      1. Correlate the dummy rotor for the No. 1 position and the No. 1 blade.

      2. Start from this No. 1 blade slot and install the blades from the front of the disk in a clockwise direction when you look from the rear.

      3. NOTE

        Install dummy retaining plates into the grooves of the disk and blades.
        It is not necessary to apply high heat resisting enamel to the mating surfaces of the plates during this part of the procedure.

        Install the stage 3 retaining plates.

      1. Move all of the stage 3 blades forward in the blade slots.

      2. Move rearward the blade at the No. 1 blade position until the groove in the disk and the groove in the blade are aligned.

      3. Install one of the plates ENGINE-HP COMPRESSOR BLADES (72-41-15,01-050) into the two grooves.

      4. Align the groove of the next blade clockwise with the groove of the disk.

      5. Use IAE 1R18079 Drift 1 off to move the retaining plate around the disk in to the next blade groove.

      6. Do steps C.(4) and C.(5) until the plate is fully in to the grooves of the disk and blades.

      7. Do steps C.(3) thru C.(6) to install the remaining plates in to the blade and disk grooves.

      4. Install (IAE 1R18076 Slave lock plates) slave lockplates9 off in to the grooves of the blades and the disk.

      1. Install the slave lockplates in position between the retaining plates at equal distances around the disk. Refer to Figure for an example of the slave lockplates positions.

    6. SUBTASK 72-41-00-040-209 Grind the Tips of the Replacement Stage 3 Blades

    1. Use a brush to apply CoMat 03-398 METAL SPRAYING STOPPING-OFFCOMPOUND to protect the stage 3 rotor airfoils. Apply the material to approximately two thirds of the blade airfoil length when measured from the blade tips.

      2. Remove the temporary surface protection from the rotor blade airfoils.

      1. Position cloth between each stage of rotor blades.

      2. NOTE

        The de-mineralized water must have a conductivity of 20 micro siemens.

        Use de-mineralized water and a cloth or brush to remove CoMat 03-398 METAL SPRAYING STOPPING-OFFCOMPOUND from the blade airfoils.

      3. Clean the blades with new de-mineralized water.

      4. Dry the blades with clean cloth or compressed air.

    3. Remove the stage 3 blades from the dummy rotor, refer to the procedure in Step.

    4. Make sure that the new blades are marked with their positions 1 to 31 in the disk.

    7. SUBTASK 72-41-00-440-223 Weigh the Removed Stage 3 Blades

      1. Weigh and record the moment weight of each blade in its sequence in the stage.

      1. Put the blades on a suitable work surface in a light to heavy sequence.

      2. NOTE

        This will allow the program to produce an acceptable pattern satisfactorily.

        Use CoMat 02-121 TEMPORARY MARKER PENCIL/CRAYON or CoMat 02-122 TEMPORARY MARKER PENCIL/CRAYON to identify the blades in an initial light-heavy-light sequence ready for assembly. Refer to Figure for an example of a light-heavy-light sequence.

    8. SUBTASK 72-41-00-440-224 Do a Balance Patternation for the Replacement Stage 3 Blades

    1. Refer to Figure.

      2. Record the results.

      1. Record the results of the initial sequence from Step in the blade distribution program VX45 or alternative method IAE 1R19842 Blade distribution computer program X45 to calculate vector C.

      2. Record the results of vector B in the blade distribution program VX45 or alternative method IAE 1R19842 Blade distribution computer program X45, refer to Step.

    3. Do a balance patternation to match vector B. The static unbalance must be within 40 gmm of vector B, this is seen as distance D.

      4. Correlate the stage 3 blades.

      1. Use CoMat 02-121 TEMPORARY MARKER PENCIL/CRAYON or CoMat 02-122 TEMPORARY MARKER PENCIL/CRAYON to identify the blades in the new sequence determined in step C.

    9. SUBTASK 72-41-00-440-225 Install the Replacement Stage 3 Blades in the HP Compressor Rotor

    1. Refer to Figure, Figure, Figure and Figure.

      2. Install the stage 3 compressor blades.

      1. NOTE

        The lockplates must be in line with a blade root.

        Install the balance weights and Silcoset in original circumferential correlated positions.

      2. Find the correlation marks on the rotor for the No. 1 position and the No. 1 blade.

      3. Start from this No. 1 blade slot and install the blades from the front of the disc in a clockwise direction when you look from the rear.

      3. Install the stage 3 retaining plates using previously correlated sequence.

      1. Move all of the stage 3 blades forwards in the blade slots.

      2. Move rearward the blade at the No. 1 blade position until the groove in the disc and the groove in the blade are aligned.

      3. Apply CoMat 07-075 HIGH-HEAT RESISTING STOVING ENAMEL to the mating surfaces of the retaining plates.

      4. Install one of the plates into the two grooves.

        NOTE

        You must ensure that if Repair, VRS6630 TASK 72-41-11-300-023 (REPAIR-023) has been carried out, the retaining plate is fitted centrally over any area(s) of material removed.

      5. Align the groove of the next blade clockwise with the groove of the disc.

      6. Use IAE 1R18079 Drift 9 drift 1 off to move the retaining plate around the disc into the next blade groove.

      7. Do Step and Step until the plate is fully into the grooves of the disc and blades.

      8. Do Step thru Step to install the remaining plates into the blade and disc grooves. The plates must be installed in the sequence identified in Step.

      4. Examine the Clapper Abutment Faces.

      1. Refer to Zone A Figure.

        2. Make sure the clapper abutment face aligns with the adjacent clapper face.

          1. 50 percent of clapper abutment faces aligned.

          1. Accept.

          2. Less than 50 percent of clapper abutment faces aligned.

          1. Reject

      5. Install (440-114) stage 3 lockplates 9 off into the grooves of the blades and the disc.

      1. NOTE

        If the last lockplate overlaps a retaining plate go to Step.

        Install the nine stage 3 lockplates in position between the retaining plates. Use IAE 1R18079 Drift to move the lockplates and retaining plates around the disc until they touch. The lock plates must line up with a blade root. Measure the total clearance (dimension X) between a lockplate and a retaining plate.

      2. Use feeler gauges to measure the total clearance (dimension X). The total clearance (dimension X) must not exceed 0.010 in. (0.25 mm).

        3. If it is necessary to remove metal from a lockplate to get the correct plate clearance do the steps that follow:

        1. Remove the lockplates.

        2. Install a lockplate into IAE 1R19811 Filing fixture 1 off and use a file to remove metal. The minimum permitted width (dimension Y) of the stage 3 lockplate after filing is 0.315 in. (8.00 mm).

          NOTE

          Remove metal from the minimum number of lockplates.
          Remove metal from the edge opposite the extraction slot.

        3. Remove the lockplate from the filing fixture.

        4. Do Step thru Step again.

      4. Remove all of the lockplates.

      5. Apply CoMat 07-075 HIGH-HEAT RESISTING STOVING ENAMEL to the mating surfaces of the disc and the lockplates.

      6. NOTE

        The lockplates must be in line with a blade root.
        You must ensure that if Repair, VRS6630 TASK 72-41-11-300-023 (REPAIR-023) has been carried out, the lockplate is fitted centrally over any area(s) of material removed.

        Install the lockplates in position.

      6. Lock the stage 3 lockplates in position.

      1. CAUTION

        YOU MUST USE THE CORRECT ANVILS AND PLIERS FOR EACH STAGE WHEN LOCKING THE LOCKPLATES.

        CAUTION

        LOCKPLATES THAT ARE DAMAGED IN ANY WAY DURING INSTALLATION, FOR EXAMPLE: OVER BENT, TWISTED OR NICKED SHOULD BE REPLACED WITH NEW PARTS. CORRECT ENGAGEMENT OF THE LOCKPLATES IS ESSENTIAL.

      2. Connect the air supply to the hydraulic tool and then connect the hose from the pressure control valve to the pliers.

      3. Adjust the control valve until a sufficient pressure is shown on the pressure gauge when the foot pedal is pushed in.

      4. Engage the pliers in the position identified 'BEND'.

      5. Install the pliers so that the front anvil is located against the lockplates.

      6. Push in the foot pedal until the pliers are in the locked position.

      7. Release the air pressure to the pliers.

      8. Engage the pliers in the position identified 'NIP'.

      9. Install the pliers so that the front anvil is located against the lockplate.

      10. Push in the foot pedal until the pliers are in a locked position.

      11. Release the air pressure to the pliers.

      12. Do Step thru Step to lock the remaining lock plates in position.

      13. Use a cloth to remove the unwanted high heat resisting stoving enamel.

    10. SUBTASK 72-41-00-040-182 Remove the Stage 4 HP Compressor Blades

      1. Correlate the stage 4 blades.

      1. NOTE

        Start from this No. 1 blade slot and number the blades in a clockwise direction when you look from the rear.
        It is recommended that the same direction is used throughout all procedures.

        Use CoMat 02-121 TEMPORARY MARKER PENCIL/CRAYON or CoMat 02-122 TEMPORARY MARKER PENCIL/CRAYON to temporarily mark the stage 4 disk rim and adjacent blade. Use this correlation mark as a start point and mark each of the stage 4 blades with a number from 1 to 38.

      2. Remove the blades from the stage 4 disk.

      1. NOTE

        This is to make sure that the light-heavy-light sequence is retained for the retaining plates.

        Correlate the sequence and positions of the retaining plates relative to the No. 1 slot.

      2. With an approved tool remove the lockplates from the front of the stage 4 disk.

      3. With IAE 1R18080 Drift 1 off move the retaining plates around the disk to close up the space between them. This will give sufficient space to remove one blade, forwards, from the disk.

      4. Continue to move the retaining plates around the disk until sufficient blades have been removed to let you remove one of the retaining plates.

      5. Move the retaining plates, in turn, around the disk until they have all been removed.

      6. Remove the remaining blades from the stage 4 disk.

    11. SUBTASK 72-41-00-220-189 Inspect the Stage 4 Blade Retaining Plates

      1. Inspect the removed stage 4 retaining plates ENGINE-HP COMPRESSOR BLADES (72-41-15,01-350).

      2. If it is necessary to discard a stage 4 retaining plate then the replacement plate must be matched weighed and correlated with the unsatisfactory plate. Refer to Step.

    12. SUBTASK 72-41-00-440-176 Weigh the Removed Stage 4 Blades and Retaining Plates

      1. Weigh the stage 4 compressor blades ENGINE-HP COMPRESSOR BLADES (72-41-15, 01-500).

      1. Weigh each of the compressor blades in turn and keep a record of the mass weight against each blade identification number.

      2. NOTE

        You only need to match weigh the retaining plate(s) if it requires replacement.

        Weigh the stage 4 retaining plate(s) ENGINE-HP COMPRESSOR BLADES (72-41-15, 01-350).

      1. Weigh each of the particular retaining plate(s) to the nearest 0.0035 oz (0.10 g).

    13. SUBTASK 72-41-00-440-177 Determine the Residual Unbalance of the Stage 4 Blades

    1. Refer to Figure.

      2. Determine the residual unbalance, distance A.

      1. Put the resulting pattern of the stage 4 mass weights in to the blade distribution program VX45 or alternative method IAE 1R19842 Blade distribution computer program X45. The resultant residual unbalance will be a measurement in grams at an angle from the correlation datum point.

      2. CAUTION

        MAKE SURE YOU USE THE CORRECT METHOD TO DETERMINE THE RESIDUAL UNBALANCE AND PREVENT DAMAGE TO ENGINE COMPONENTS. IT IS VERY IMPORTANT TO KNOW THAT THE BLADE SETS VECTOR IS IN THE OPPOSITE SENSE TO THE RESIDUAL UNBALANCE IN THE HP COMPRESSOR ROTOR.

        Record the residual unbalance, vector B. You must try to match the new set of blades with this target vector figure, refer to Step.

    14. SUBTASK 72-41-00-440-178 Install the Replacement Stage 4 Blades in the Dummy Rotor

    1. Refer to Figure, Figure and Figure

      2. Install the stage 4 compressor blades.

      1. Correlate the dummy rotor for the No. 1 position and the No. 1 blade.

      2. Start from this No. 1 blade slot and install the blades from the front of the disk in a clockwise direction when you look from the rear.

      3. NOTE

        It is recommended that a dummy set of retaining plates and lockplates are used for this part of the procedure and that these parts are not re-used during subsequent compressor build operations.
        It is not necessary to apply high heat resisting enamel to the mating surfaces of the plates during this part of the procedure.

        Install the stage 4 retaining plates.

      1. Move all of the stage 4 blades rearwards in the blade slots.

      2. Move forward the blade at the No. 1 blade position until the groove in the disk and the groove in the blade are aligned.

      3. Install one of the plates into the two grooves.

        NOTE

        You must ensure that if Repair, VRS6630 TASK 72-41-11-300-023 (REPAIR-023) has been carried out, the retaining plate is fitted centrally over any area(s) of material removed.

      4. Align the groove of the next blade clockwise with the groove of the disk.

      5. Use IAE 1R18080 Drift 1 off to move the retaining plate around the disk in to the next blade groove.

      6. Do Step and Step until the plate is fully in to the grooves of the disk and blades.

      7. Do Step thru Step to install the remaining plates in to the blade and disk grooves.

      4. Install ENGINE-HP COMPRESSOR BLADES (72-41-15, 01-425) stage 4 lockplates 3 off in to the grooves of the blades and the disk.

      1. NOTE

        If the last lockplate overlaps a retaining plate go to Step.

        Install the three stage 4 lockplates in position between the retaining plates. Use IAE 1R18080 Drift to move the lockplates and retaining plates around the disk until they touch. Measure the total clearance (dimension X) between a lockplate and a retaining plate, refer to Figure.

      2. Use feeler gauges to measure the total clearance (dimension X). The total clearance (dimension X) must not exceed 0.010 in. (0.25 mm).

        3. If it is necessary to remove metal from a lockplate to get the correct plate clearance do the steps that follow:

        1. Remove the lockplates.

        2. Install a lockplate in to IAE 1R19812 Filing fixture filing fixture 1 off and use a file to remove metal. The minimum permitted width (dimension Y) of the stage 4 lockplate after filing is 0.402 in. (10.20 mm).

          NOTE

          Remove metal from the minimum number of lockplates.
          Remove metal from the edge opposite the extraction slot.

        3. Remove the lockplate from the filing fixture.

        4. Do Step thru Step again.

      4. NOTE

        The lockplates must be in line with a blade root.
        You must ensure that if Repair, VRS6630 TASK 72-41-11-300-023 (REPAIR-023) has been carried out, the lockplate is fitted centrally over any area(s) of material removed.

        Install the lockplates in position.

      5. Lock the stage 4 lockplates in position.

      1. CAUTION

        YOU MUST USE THE CORRECT ANVILS AND PLIERS FOR EACH STAGE WHEN LOCKING THE LOCKPLATES.

        CAUTION

        LOCKPLATES THAT ARE DAMAGED IN ANY WAY DURING INSTALLATION, FOR EXAMPLE: OVER BENT, TWISTED OR NICKED SHOULD BE REPLACED WITH NEW PARTS. CORRECT ENGAGEMENT OF THE LOCKPLATES IS ESSENTIAL.

      2. Connect the air supply to the hydraulic tool and then connect the hose from the pressure control valve to the pliers.

      3. Adjust the control valve until a sufficient pressure is shown on the pressure gauge when the foot pedal is pushed in.

      4. Engage the pliers in the position identified 'BEND'.

      5. Install the pliers so that the front anvil is located against the lockplates.

      6. Push in the foot pedal until the pliers are in the locked position.

      7. Release the air pressure to the pliers.

      8. Engage the pliers in the position identified 'NIP'.

      9. Install the pliers so that the front anvil is located against the lockplate.

      10. Push in the foot pedal until the pliers are in a locked position.

      11. Release the air pressure to the pliers.

      12. Do Step thru Step to lock the remaining lock plates in position.

    15. SUBTASK 72-41-00-324-003 Grind the Tips of the Replacement Stage 4 Blades (SBE 72-0370)

      SBE 72-0370: HP compressor blades - introduction of increased stage 4 rotor blade tip clearance

    1. Use a brush to apply CoMat 03-398 METAL SPRAYING STOPPING-OFFCOMPOUND to protect the stage 4 rotor airfoils. Apply the material to approximately two thirds of the blade airfoil length when measured from the blade tips.

    2. Deleted.

    3. SBE 72-0370 : Grind the tips of the replacement stage 4 blades installed in the dummy HP compressor rotor using the procedures given in TASK 72-41-10-440-004-A00.

      4. Remove the temporary surface protection from the rotor blade airfoils.

      1. Position cloth between each stage of rotor blades.

      2. NOTE

        The de-mineralized water must have a conductivity of 20 micro siemens.

        Use de-mineralized water and a cloth or brush to remove CoMat 03-398 METAL SPRAYING STOPPING-OFFCOMPOUND from the blade airfoils.

      3. Clean the blades with new de-mineralized water.

      4. Dry the blades with clean cloth or compressed air.

    5. Remove the stage 4 blades from the dummy rotor, refer to the procedure in Step.

    6. Make sure that the new blades are marked with their positions 1 to 38 in the disk.

    16. SUBTASK 72-41-00-440-179 Weigh the Removed Stage 4 Blades

      1. Weigh and record the mass of each blade in its sequence in the stage. Refer to Step.

      1. Put the blades on a suitable work surface in a light to heavy sequence.

      2. NOTE

        This will allow the program to produce an acceptable pattern satisfactorily.

        Use CoMat 02-121 TEMPORARY MARKER PENCIL/CRAYON or CoMat 02-122 TEMPORARY MARKER PENCIL/CRAYON to identify the blades in an initial light-heavy-light sequence ready for assembly. Refer to Figure for an example of a light-heavy-light sequence.

    17. SUBTASK 72-41-00-440-180 Do a Balance Patternation for the Replacement Stage 4 Blades

    1. Refer to Figure.

      2. Record the results.

      1. Record the results of the initial sequence from Step in the blade distribution program VX45 or alternative method IAE 1R19842 Blade distribution computer program X45 to calculate vector C.

      2. Record the results of vector B in the blade distribution program VX45 or alternative method IAE 1R19842 Blade distribution computer program X45, refer to Step.

    3. Do a balance patternation to match vector B. The static unbalance must be within 1.5 grams of vector B, this is seen as distance D.

      4. Correlate the stage 4 blades.

      1. Use CoMat 02-121 TEMPORARY MARKER PENCIL/CRAYON or CoMat 02-122 TEMPORARY MARKER PENCIL/CRAYON to identify the blades in the new sequence determined in step C.

    18. SUBTASK 72-41-00-440-181 Install the Replacement Stage 4 Blades in the HP Compressor Rotor

    1. Refer to Figure, Figure and Figure.

      2. NOTE

        Because the blades are axially rooted it is not necessary to check the platform gaps as there are no locking blades for stage 4.

        Install the stage 4 compressor blades.

      1. Find the correlation marks on the rotor for the No. 1 position and the No. 1 blade.

      2. Start from this No. 1 blade slot and install the blades from the front of the disk in a clockwise direction when you look from the rear.

      3. Install the stage 4 retaining plates.

      1. Move all of the stage 4 blades rearwards in the blade slots.

      2. Move forward the blade at the No. 1 blade position until the groove in the disk and the groove in the blade are aligned.

      3. Apply CoMat 07-075 HIGH-HEAT RESISTING STOVING ENAMEL to the mating surfaces of the retaining plates.

      4. Install one of the plates into the two grooves.

        NOTE

        You must ensure that if Repair, VRS6630 TASK 72-41-11-300-023 (REPAIR-023) has been carried out, the retaining plate is fitted centrally over any area(s) of material removed.

      5. Align the groove of the next blade clockwise with the groove of the disk.

      6. Use IAE 1R18080 Drift 1 off to move the retaining plate around the disk in to the next blade groove.

      7. Do Step and Step until the plate is fully in to the grooves of the disk and blades.

      8. Do Step thru Step to install the remaining plates in to the blade and disk grooves. The plates must be installed in the sequence identified in Step.

      4. Install ENGINE-HP COMPRESSOR BLADES (72-41-15, 01-425) stage 4 lockplates 3 off in to the grooves of the blades and the disk.

      1. NOTE

        If the last lockplate overlaps a retaining plate go to Step.

        Install the three stage 4 lockplates in position between the retaining plates. Use IAE 1R18080 Drift to move the lockplates and retaining plates around the disk until they touch. Measure the total clearance (dimension X) between a lockplate and a retaining plate, refer to Figure.

      2. Use feeler gauges to measure the total clearance (dimension X). The total clearance (dimension X) must not exceed 0.010 in. (0.25 mm).

        3. If it is necessary to remove metal from a lockplate to get the correct plate clearance do the steps that follow:

        1. Remove the lockplates.

        2. Install a lockplate in to IAE 1R19812 Filing fixture 1 off and use a file to remove metal. The minimum permitted width (dimension Y) of the stage 4 lockplate after filing is 0.402 in. (10.20 mm).

          NOTE

          Remove metal from the minimum number of lockplates.
          Remove metal from the edge opposite the extraction slot.

        3. Remove the lockplate from the filing fixture.

        4. Do Step thru Step again.

      4. Remove all of the lockplates.

      5. Apply CoMat 07-075 HIGH-HEAT RESISTING STOVING ENAMEL to the mating surfaces of the disk and the lockplates.

      6. NOTE

        The lockplates must be in line with a blade root.
        You must ensure that if Repair, VRS6630 TASK 72-41-11-300-023 (REPAIR-023) has been carried out, the lockplate is fitted centrally over any area(s) of material removed.

        Install the lockplates in position.

      5. Lock the stage 4 lockplates in position.

      1. CAUTION

        YOU MUST USE THE CORRECT ANVILS AND PLIERS FOR EACH STAGE WHEN LOCKING THE LOCKPLATES.

        CAUTION

        LOCKPLATES THAT ARE DAMAGED IN ANY WAY DURING INSTALLATION, FOR EXAMPLE: OVER BENT, TWISTED OR NICKED SHOULD BE REPLACED WITH NEW PARTS. CORRECT ENGAGEMENT OF THE LOCKPLATES IS ESSENTIAL.

      2. Connect the air supply to the hydraulic tool and then connect the hose from the pressure control valve to the pliers.

      3. Adjust the control valve until a sufficient pressure is shown on the pressure gauge when the foot pedal is pushed in.

      4. Engage the pliers in the position identified 'BEND'.

      5. Install the pliers so that the front anvil is located against the lockplates.

      6. Push in the foot pedal until the pliers are in the locked position.

      7. Release the air pressure to the pliers.

      8. Engage the pliers in the position identified 'NIP'.

      9. Install the pliers so that the front anvil is located against the lockplate.

      10. Push in the foot pedal until the pliers are in a locked position.

      11. Release the air pressure to the pliers.

      12. Do Step thru Step to lock the remaining lock plates in position.

      13. Use a cloth to remove the unwanted high heat resisting stoving enamel.

    19. SUBTASK 72-41-00-040-183 Remove the Stage 5 HP Compressor Blades

      1. Correlate the stage 5 blades.

      1. NOTE

        Start from this No. 1 blade slot and number the blades in a clockwise direction when you look from the rear.
        It is recommended that the same direction is used throughout all procedures.

        Use CoMat 02-121 TEMPORARY MARKER PENCIL/CRAYON or CoMat 02-122 TEMPORARY MARKER PENCIL/CRAYON to temporarily mark the stage 5 disk rim and adjacent blade. Use this correlation mark as a start point and mark each of the stage 5 blades with a number from 1 to 64.

      2. Remove the blades from the stage 5 disk.

      1. NOTE

        This is to make sure that the light-heavy-light sequence is retained for the retaining plates.

        Correlate the sequence and positions of the retaining plates relative to the No. 1 slot.

      2. With an approved tool remove the lockplates from the front of the stage 5 disk.

      3. With IAE 1R18080 Drift 1 off move the retaining plates around the disk to close up the space between them. This will give sufficient space to remove one blade, forwards, from the disk.

      4. Continue to move the retaining plates around the disk until sufficient blades have been removed to let you remove one of the retaining plates.

      5. Move the retaining plates, in turn, around the disk until they have all been removed.

      6. Remove the remaining blades from the stage 5 disk.

    20. SUBTASK 72-41-00-220-190 Inspect the Stage 5 Blade Retaining Plates

      1. Inspect the removed stage 5 retaining plates ENGINE-HP COMPRESSOR BLADES (72-41-15,01-650).

      2. If it is necessary to discard a stage 5 retaining plate then the replacement plate must be matched weighed and correlated with the unsatisfactory plate. Refer to Step.

    21. SUBTASK 72-41-00-440-182 Weigh the Removed Stage 5 Blades and Retaining Plates

      1. Weigh the stage 5 compressor blades ENGINE-HP COMPRESSOR BLADES (72-41-15, 01-800).

      1. Weigh each of the compressor blades in turn and keep a record of the mass weight and the blade identification number.

      2. NOTE

        You only need to match weigh the retaining plate(s) if it requires replacement.

        Weigh the stage 5 retaining plate(s) ENGINE-HP COMPRESSOR BLADES (72-41-15, 01-650).

      1. Weigh each of the particular retaining plate(s) to the nearest 0.0035 oz (0.10 g).

    22. SUBTASK 72-41-00-440-183 Determine the Residual Unbalance of the Stage 5 Blades

    1. Refer to Figure.

      2. Determine the residual unbalance, distance A.

      1. Put the resulting pattern of the stage 5 mass weights in to the blade distribution program VX45 or alternative method IAE 1R19842 Blade distribution computer program X45. The resultant residual unbalance will be a measurement in grams at an angle from the correlation datum point.

      2. CAUTION

        MAKE SURE YOU USE THE CORRECT METHOD TO DETERMINE THE RESIDUAL UNBALANCE AND PREVENT DAMAGE TO ENGINE COMPONENTS. IT IS VERY IMPORTANT TO KNOW THAT THE BLADE SETS VECTOR IS IN THE OPPOSITE SENSE TO THE RESIDUAL UNBALANCE IN THE HP COMPRESSOR ROTOR.

        Record the residual unbalance, vector B. You must try to match the new set of blades with this target vector figure, refer to Step.

    23. SUBTASK 72-41-00-440-184 Install the Replacement Stage 5 Blades in the Dummy Rotor

    1. Refer to Figure, Figure and Figure

      2. Install the stage 5 compressor blades.

      1. Correlate the dummy rotor for the No. 1 position and the No. 1 blade.

      2. Start from this No. 1 blade slot and install the blades from the front of the disk in a clockwise direction when you look from the rear.

      3. NOTE

        It is recommended that a dummy set of retaining plates and lockplates are used for this part of the procedure and that these parts are not re-used during subsequent compressor build operations.
        It is not necessary to apply high heat resisting enamel to the mating surfaces of the plates during this part of the procedure.

        Install the stage 5 retaining plates.

      1. Move all of the stage 5 blades rearwards in the blade slots.

      2. Move forward the blade at the No. 1 blade position until the groove in the disk and the groove in the blade are aligned.

      3. Install one of the plates into the two grooves.

        NOTE

        You must ensure that if Repair, VRS6630 TASK 72-41-11-300-023 (REPAIR-023) has been carried out, the retaining plate is fitted centrally over any area(s) of material removed.

      4. Align the groove of the next blade clockwise with the groove of the disk.

      5. Use IAE 1R18080 Drift 1 off to move the retaining plate around the disk in to the next blade groove.

      6. Do Step and Step until the plate is fully in to the grooves of the disk and blades.

      7. Do Step thru Step to install the remaining plates in to the blade and disk grooves.

      4. Install ENGINE-HP COMPRESSOR BLADES (72-41-15, 01-725) stage 5 lockplates3 off in to the grooves of the blades and the disk.

      1. NOTE

        If the last lockplate overlaps a retaining plate go to Step.

        Install the three stage 5 lockplates in position between the retaining plates. Use IAE 1R18080 Drift to move the lockplates and retaining plates around the disk until they touch. Measure the total clearance (dimension X) between a lockplate and a retaining plate, refer to Figure.

      2. Use feeler gauges to measure the total clearance (dimension X). The total clearance (dimension X) must not exceed 0.010 in. (0.25 mm).

        3. If it is necessary to remove metal from a lockplate to get the correct plate clearance do the steps that follow:

        1. Remove the lockplates.

        2. Install a lockplate in to IAE 1R19813 Filing fixture 1 off and use a file to remove metal. The minimum permitted width (dimension Y) of the stage 5 lockplate after filing is 0.297 in. (7.64 mm).

          NOTE

          Remove metal from the minimum number of lockplates.
          Remove metal from the edge opposite the extraction slot.

        3. Remove the lockplate from the filing fixture.

        4. Do Step thru Step again.

      4. NOTE

        The lockplates must be in line with a blade root.
        You must ensure that if Repair, VRS6630 TASK 72-41-11-300-023 (REPAIR-023) has been carried out, the lockplate is fitted centrally over any area(s) of material removed.

        Install the lockplates in position.

      5. Lock the stage 5 lockplates in position.

      1. CAUTION

        YOU MUST USE THE CORRECT ANVILS AND PLIERS FOR EACH STAGE WHEN LOCKING THE LOCKPLATES.

        CAUTION

        LOCKPLATES THAT ARE DAMAGED IN ANY WAY DURING INSTALLATION, FOR EXAMPLE: OVER BENT, TWISTED OR NICKED SHOULD BE REPLACED WITH NEW PARTS. CORRECT ENGAGEMENT OF THE LOCKPLATES IS ESSENTIAL.

      2. Install IAE 1R18245 Adapter 1 off between the pressure control valve and IAE 1R18083 Hydraulic tool 1 off.

      3. Connect the air supply to the hydraulic tool and then connect the hose from the pressure control valve to the pliers.

      4. Adjust the control valve until a sufficient pressure is shown on the pressure gauge when the foot pedal is pushed in.

      5. Engage the pliers in the position identified 'BEND'.

      6. Install the pliers so that the front anvil is located against the lockplates.

      7. Push in the foot pedal until the pliers are in the locked position.

      8. Release the air pressure to the pliers.

      9. Engage the pliers in the position identified 'NIP'.

      10. Install the pliers so that the front anvil is located against the lockplate.

      11. Push in the foot pedal until the pliers are in a locked position.

      12. Release the air pressure to the pliers.

      13. Do Step thru Step to lock the remaining lock plates in position.

    24. SUBTASK 72-41-00-324-004 Grind the Tips of the Replacement Stage 5 Blades

    1. Use a brush to apply CoMat 03-398 METAL SPRAYING STOPPING-OFFCOMPOUND to protect the stage 5 rotor airfoils. Apply the material to approximately two thirds of the blade airfoil length when measured from the blade tips.

    2. Grind the tips of the replacement stage 5 blades installed in the dummy HP compressor rotor using the procedures given in TASK 72-41-10-440-004-A00.

      3. Remove the temporary surface protection from the rotor blade airfoils.

      1. Position cloth between each stage of rotor blades.

      2. NOTE

        The de-mineralized water must have a conductivity of 20 micro siemens.

        Use de-mineralized water and a cloth or brush to remove CoMat 03-398 METAL SPRAYING STOPPING-OFFCOMPOUND from the blade airfoils.

      3. Clean the blades with new de-mineralized water.

      4. Dry the blades with clean cloth or compressed air.

    4. Remove the stage 5 blades from the dummy rotor, refer to the procedure in Step.

    5. Make sure that the new blades are marked with their positions 1 to 64 in the disk.

    25. SUBTASK 72-41-00-440-185 Weigh the Removed Stage 5 Blades

      1. Weigh and record the mass of each blade in its sequence in the stage. Refer to Step.

      1. Put the blades on a suitable work surface in a light to heavy sequence.

      2. NOTE

        This will allow the program to produce an acceptable pattern satisfactorily.

        Use CoMat 02-121 TEMPORARY MARKER PENCIL/CRAYON or CoMat 02-122 TEMPORARY MARKER PENCIL/CRAYON to identify the blades in an initial light-heavy-light sequence ready for assembly. Refer to Figurefor an example of a light-heavy-light sequence.

    26. SUBTASK 72-41-00-440-186 Do a Balance Patternation for the Replacement Stage 5 Blades

    1. Refer to Figure.

      2. Record the results.

      1. Record the results of the initial sequence from Step in the blade distribution program VX45 or alternative method IAE 1R19842 Blade distribution computer program X45 to calculate vector C.

      2. Record the results of vector B in the blade distribution program VX45 or alternative method IAE 1R19842 Blade distribution computer program X45, refer to Step.

    3. Do a balance patternation to match vector B. The static unbalance must be within 1.5 grams of vector B, this is seen as distance D.

      4. Correlate the stage 5 blades.

      1. Use CoMat 02-121 TEMPORARY MARKER PENCIL/CRAYON temporary marker or CoMat 02-122 TEMPORARY MARKER PENCIL/CRAYON temporary marker to identify the blades in the new sequence determined in step C.

    27. SUBTASK 72-41-00-440-187 Install the Replacement Stage 5 Blades in the HP Compressor Rotor

    1. Refer to Figure, Figure and Figure

      2. NOTE

        Because the blades are axially rooted it is not necessary to check the platform gaps as there are no locking blades for stage 5.

        Install the stage 5 compressor blades.

      1. Find the correlation marks on the rotor for the No. 1 position and the No. 1 blade.

      2. Start from this No. 1 blade slot and install the blades from the front of the disk in a clockwise direction when you look from the rear.

      3. Install the stage 5 retaining plates.

      1. Move all of the stage 5 blades rearwards in the blade slots.

      2. Move forward the blade at the No. 1 blade position until the groove in the disk and the groove in the blade are aligned.

      3. Apply CoMat 07-075 HIGH-HEAT RESISTING STOVING ENAMEL to the mating surfaces of the retaining plates.

      4. Install one of the plates into the two grooves.

        NOTE

        You must ensure that if Repair, VRS6630 TASK 72-41-11-300-023 (REPAIR-023) has been carried out, the retaining plate is fitted centrally over any area(s) of material removed.

      5. Align the groove of the next blade clockwise with the groove of the disk.

      6. Use IAE 1R18080 Drift 1 off to move the retaining plate around the disk in to the next blade groove.

      7. Do Step and Step until the plate is fully in to the grooves of the disk and blades.

      8. Do Step thru Step to install the remaining plates in to the blade and disk grooves. The plates must be installed in the sequence identified in Step.

      4. Install ENGINE-HP COMPRESSOR BLADES (72-41-15, 01-725) stage 5 lockplates 3 off in to the grooves of the blades and the disk.

      1. NOTE

        If the last lockplate overlaps a retaining plate go to Step.

        Install the three stage 5 lockplates in position between the retaining plates. Use IAE 1R18080 Drift to move the lockplates and retaining plates around the disk until they touch. Measure the total clearance (dimension X) between a lockplate and a retaining plate, refer to Figure.

      2. Use feeler gauges to measure the total clearance (dimension X). The total clearance (dimension X) must not exceed 0.010 in. (0.25 mm).

        3. If it is necessary to remove metal from a lockplate to get the correct plate clearance do the steps that follow:

        1. Remove the lockplates.

        2. Install a lockplate in to IAE 1R19813 Filing fixture 1 off and use a file to remove metal. The minimum permitted width (dimension Y) of the stage 5 lockplate after filing is 0.297 in. (7.64 mm).

          NOTE

          Remove metal from the minimum number of lockplates.
          Remove metal from the edge opposite the extraction slot.

        3. Remove the lockplate from the filing fixture.

        4. Do Step thru Step again.

      4. Remove all of the lockplates.

      5. Apply CoMat 07-075 HIGH-HEAT RESISTING STOVING ENAMEL to the mating surfaces of the disk and the lockplates.

      6. NOTE

        The lockplates must be in line with a blade root.
        You must ensure that if Repair, VRS6630 TASK 72-41-11-300-023 (REPAIR-023) has been carried out, the lockplate is fitted centrally over any area(s) of material removed.

        Install the lockplates in position.

      5. Lock the stage 5 lockplates in position.

      1. CAUTION

        YOU MUST USE THE CORRECT ANVILS AND PLIERS FOR EACH STAGE WHEN LOCKING THE LOCKPLATES.

        CAUTION

        LOCKPLATES THAT ARE DAMAGED IN ANY WAY DURING INSTALLATION, FOR EXAMPLE: OVER BENT, TWISTED OR NICKED SHOULD BE REPLACED WITH NEW PARTS. CORRECT ENGAGEMENT OF THE LOCKPLATES IS ESSENTIAL.

      2. Install IAE 1R18245 Adapter 1 off between the pressure control valve and IAE 1R18083 Hydraulic tool 1 off.

      3. Connect the air supply to the hydraulic tool and then connect the hose from the pressure control valve to the pliers.

      4. Adjust the control valve until a sufficient pressure is shown on the pressure gauge when the foot pedal is pushed in.

      5. Engage the pliers in the position identified 'BEND'.

      6. Install the pliers so that the front anvil is located against the lockplates.

      7. Push in the foot pedal until the pliers are in the locked position.

      8. Release the air pressure to the pliers.

      9. Engage the pliers in the position identified 'NIP'.

      10. Install the pliers so that the front anvil is located against the lockplate.

      11. Push in the foot pedal until the pliers are in a locked position.

      12. Release the air pressure to the pliers.

      13. Do Step thru Step to lock the remaining lock plates in position.

      14. Use a cloth to remove the unwanted high heat resisting stoving enamel.

    28. SUBTASK 72-41-00-040-184 Correlate the Stage 6 HP Compressor Blades

      1. Correlate the stage 6 blades.

      1. NOTE

        It is recommended that one of the locking blades is used as the correlation position as a start point for the No. 1 position.
        Start from this No. 1 blade slot and number the blades in a clockwise or counter-clockwise direction when you look from the rear. Keep the same direction for numbering the blades through this procedure.
        It is recommended that the same direction is used throughout all procedures.

        Use CoMat 02-121 TEMPORARY MARKER PENCIL/CRAYON or CoMat 02-122 TEMPORARY MARKER PENCIL/CRAYON to temporarily mark the stage 6 disk rim and adjacent blade. Use this correlation mark as a start point and mark each of the stage 6 blades with a number from 1 to 79.

    29. SUBTASK 72-41-00-040-185 Remove the Stage 6 HP Compressor Blades

      1. NOTE

        To drill out seized blade locknuts use the following tools: IAE 1R18911 Drill 1 off and IAE 1R18914 Setting gage 1 off.
        Each nut and screw lock assembly must be kept as a set.
        Correlate the nut and screw lock assemblies to their removed positions.

        Remove the blades from the stage 6 disk.

      1. With IAE 1R18590 Socket end 1 off release the two nut and screw lock assemblies.

      2. With IAE 1R18097 Drift 1 off move the blades around the disk until a blade can be removed through the loading slot.

      3. Do step (2) again, to remove each blade and the two nut and screw lock assemblies, until all the blades have been removed.

      4. Remove the damping wires from the disks.

    30. SUBTASK 72-41-00-220-191 Inspect the Stage 6 Nut and Screw lock assemblies

      1. Inspect the removed stage 6 nut and screw lock assemblies ENGINE-HP COMPRESSOR BLADES (72-41-15,02-165).

      2. If it is necessary to discard a stage 6 nut and screw lock assembly then the replacement assembly must be matched weighed and correlated with the unsatisfactory assembly. Refer to Step.

    31. SUBTASK 72-41-00-440-188 Weigh the Removed Stage 6 Blades and Nut and Screw Lock Assemblies

      1. Weigh the stage 6 compressor blades ENGINE-HP COMPRESSOR BLADES (72-41-15, 02-170 , 02-185, 02-200, 02-215 and 02-217).

      1. Weigh each of the compressor blades in turn and keep a record of the mass weight and the blade identification number.

      2. NOTE

        You only need to match weigh the assemblies(s) if it requires replacement.

        Weigh the stage 6 nut and screw lock assembly ENGINE-HP COMPRESSOR BLADES (72-41-15, 02-165).

      1. Weigh each of the particular nut and screw lock assemblies to the nearest 0.0035 oz (0.10 g).

    32. SUBTASK 72-41-00-440-189 Determine the Residual Unbalance of the Stage 6 Blades

    1. Refer to Figure.

      2. Determine the residual unbalance, distance A.

      1. Put the resulting pattern of the stage 6 mass weights in to the blade distribution program VX45 or alternative method IAE 1R19842 Blade distribution computer program X45. The resultant residual unbalance will be a measurement in grams at an angle from the correlation datum point.

      2. CAUTION

        MAKE SURE YOU USE THE CORRECT METHOD TO DETERMINE THE RESIDUAL UNBALANCE AND PREVENT DAMAGE TO ENGINE COMPONENTS. IT IS VERY IMPORTANT TO KNOW THAT THE BLADE SETS VECTOR IS IN THE OPPOSITE SENSE TO THE RESIDUAL UNBALANCE IN THE HP COMPRESSOR ROTOR.

        Record the residual unbalance, vector B. You must try to match the new set of blades with this target vector figure, refer to Step.

    33. SUBTASK 72-41-00-440-190-A00 Find the Correct Selection of Stage 6 Blades (Pre SBE 72-0161)

      NOTE

      1. This method is used if the compressor disks have four locking slots for the nut and screw lock assemblies. Refer to Figure Inset 2.

      2. Make sure each nut and screw lock assembly is kept as a set.

      3. CoMat 02-122 TEMPORARY MARKER PENCIL/CRAYON to make a mark on the nut and screw lock assembly and on the stage 6 thru 12 compressor disks so that they can be installed in the same positions.

      1. NOTE

        1. A selection of the 25 standard and the 25 undersize blades is used to get the correct platform build clearance.

        2. A maximum of 25 undersize blades is permitted.

        Find the correct selection of stage 6 compressor blades.

        A full set of stage 6 compressor blades includes the IPC Fig/item numbers that follow:

        2 LH locking blades ENGINE-HP COMPRESSOR BLADES (72-41-15, 02-170).

        2 RH locking blades ENGINE-HP COMPRESSOR BLADES (72-41-15, 02-185).

        60 Standard blades ENGINE-HP COMPRESSOR BLADES (72-41-15, 02-200).

        25 Standard blades ENGINE-HP COMPRESSOR BLADES (72-41-15, 02-215).

        25 Undersize blades ENGINE-HP COMPRESSOR BLADES (72-41-15, 02-217).

        1. CAUTION

          YOU MUST NOT USE THE DRIFT ON THE AIRFOIL SURFACES.

          Install the blades in to the stage 6 disk slot of the dummy rotor.

        1. Install all but two of the standard blades in to the disk through the blade loading slot. Use IAE 1R18097 Drift 1off positioned against the blade roots to move them around the disk in a counterclockwise direction when you look from the rear.

        2. Install one LH and then one RH locking blade in to the disk and move them counterclockwise.

        3. Install the two remaining standard size blades in to the disk and move them counterclockwise.

        4. NOTE

          Two standard size blades must be installed between the two pairs of locking blades.

          Install the second LH and then the second RH locking blade in to the disk and move them counterclockwise.

        2. Measure the platform build clearance, dimension A. Refer to Figure.

        1. Use the drift against the blade roots to make sure all of the blade platforms touch.

        2. Use feeler gauges to measure dimension A. The feeler gauges must go through the full axial length X of both platforms and must span the full radial height Y of both platforms.

        3. Write a record of the platform build clearance.

      3. The platform build clearance (dimension A) must be 0.010 to 0.040in. (0.25 to 1.02 mm). Try to get a nominal clearance of 0.018 in. (0.45mm).

      4. NOTE

        One undersize blade will give an increase in the platform build clearance of 0.016in. (0.40 mm).
        Undersize blades must not be installed adjacent to each other on assembly.

        Calculate the number of undersize blades that are required to make the correct platform build clearance.

      5. Remove the necessary number of standard blades and install the undersize blades.

      6. Do steps B.(2) and B.(3) again to make sure the platform build clearance is correct.

      7. Use CoMat 02-121 TEMPORARY MARKER PENCIL/CRAYON or CoMat 02-122 TEMPORARY MARKER PENCIL/CRAYON to identify the two standard blades which are installed between the two pairs of locking blades.

      8. Temporarily mark the blade positions on all the stage 6 blades.

      9. Remove all of the blades from the disk.

    34. SUBTASK 72-41-00-440-190-B00 Find the Correct Selection of Stages 6 Compressor Blades (SBE 72-0161)

      NOTE

      1. This method is used if the compressor disks have only two locking slots for the nut and screw lock assemblies. Refer to FigureInset 1.

      2. Make sure each nut and screw lock assembly is kept as a set.

      3. CoMat 02-122 TEMPORARY MARKER PENCIL/CRAYONto make a mark on the nut and screw lock assembly and on the stage 6 thru 12 compressor disks so that they can be installed in the same positions.

      SBE 72-0161: HP disks and blades - Stages 7 and 8 rotor blades with damping wires and stages 6, 7 and 8 blades with anti-fret coating.

      1. NOTE

        1. A selection of the 26 standard and the 26 undersize blades is used to get the correct platform build clearance.

        2. A maximum of 26 undersize blades is permitted.

        Find the correct selection of stage 6 compressor blades.

        A full set of stage 6 compressor blades includes the IPC Fig/item numbers that follow:

        2 LH locking blades ENGINE-HP COMPRESSOR BLADES (72-41-15, 02-170).

        2 RH locking blades ENGINE-HP COMPRESSOR BLADES (72-41-15, 02-185).

        59 Standard blades ENGINE-HP COMPRESSOR BLADES (72-41-15, 02-200).

        26 Standard blades ENGINE-HP COMPRESSOR BLADES (72-41-15, 02-215).

        26 Undersize blades ENGINE-HP COMPRESSOR BLADES (72-41-15, 02-217).

        1. CAUTION

          YOU MUST NOT USE THE DRIFT ON THE AIRFOIL SURFACES.

          Install the blades in to the stage 6 disk slot of the dummy rotor.

        1. Install all of the standard blades in to the disk through the blade loading slot. Use IAE 1R18097 Drift 1 off positioned against the blade roots to move them around the disk in a counterclockwise direction when you look from the rear.

        2. Install one LH and then one RH locking blade in to the disk and move them counterclockwise.

        3. NOTE

          Two standard size blades must be installed between the two pairs of locking blades.

          Install the second LH and then the second RH locking blade in to the disk and move them counterclockwise.

        2. Measure the platform build clearance, dimension A. Refer to Figure.

        1. Use the drift against the blade roots to make sure all of the blade platforms touch.

        2. Use feeler gauges to measure dimension A. The feeler gauges must go through the full axial length X of both platforms and must span the full radial height Y of both platforms.

        3. Write a record of the platform build clearance.

      3. The platform build clearance (dimension A) must be 0.010 to 0.040in. (0.25 mm to 1.02 mm). Try and get a nominal clearance of 0.018 in. (0.45mm).

      4. NOTE

        One undersize blade will give an increase in the platform build clearance of 0.016in. (0.40 mm).
        Undersize blades must not be installed adjacent to each other on assembly.

        Calculate the number of undersize blades that are required to get the correct platform build clearance.

      5. Remove the necessary number of standard blades and install the undersize blades.

      6. Do steps B.(2) and B.(3) again to make sure that the platform build clearance is correct.

      7. Use CoMat 02-121 TEMPORARY MARKER PENCIL/CRAYON or CoMat 02-122 TEMPORARY MARKER PENCIL/CRAYON to identify all the stage 6 blades with their positions.

      8. Remove all of the blades from the disk.

    35. SUBTASK 72-41-00-440-191 Install the Stage 6 Disk Sealing Wires

    1. Refer to Figure

    2. CAUTION

      WHEN INSTALLING THE DAMPER WIRES, POSITION THE DAMPER WIRE SO THAT THE SPLIT LINE IS AS FAR AWAY AS POSSIBLE FROM BOTH THE BLADE LOADING SLOT AND THE LOCATION OF THE MAXIMUM LOCAL WEAR TO THE DAMPER WIRE GROOVE.

      NOTE

      It is recommended that a dummy set of stage 6 front and rear sealing wires are used for this part of the procedure and that these parts are not re-used during subsequent compressor build operations.

      Install the stage 6 front sealing wire ENGINE-HP COMPRESSOR DISCS (STAGES 3-8) (72-41-11, 01-386) in to the stage 6 disk front groove of the dummy rotor.

    3. Push the sealing wire in to the bottom of the groove around the disk and measure the overlap (dimension B). Make sure that dimension B is a minimum of 0.236 in. (6.00 mm).

    4. Install the stage 6 rear sealing wire ENGINE-HP COMPRESSOR DISCS (STAGES 3-8) (72-41-11, 01-388) in to the stage 6 disk rear groove. The front and rear sealing wire joints must be 180 degrees apart.

    5. Do step B. again for the rear sealing wire.

    36. SUBTASK 72-41-00-440-192-001 Install the Correct Selection of Replacement Stage 6 Blades for Grinding Operations

      NOTE

      This method is used if the compressor disk has four locking slots for the nut and screw lock assemblies. Refer to Figure Inset 2.

    1. Refer to Figure, Figure and Figure.

    2. CAUTION

      YOU MUST NOT USE THE DRIFT ON THE AIRFOIL SURFACES.

      NOTE

      Do not install the two standard size blades which must be installed between the locking blades.

      Correlate the dummy rotor for the No. 1 position and the No. 1 blade.

      Start from this No. 1 slot and Install the stage 6 standard and undersize blades which were selected in Step in to the disk in the identified sequence. Use IAE 1R18097 Drift 1 off to move the blades around the disk in a counterclockwise direction when you look from the rear.

      3. Prepare the jacking screw and locknut assemblies.

      1. NOTE

        Each nut and screw lock assembly must be kept as a set.
        It is recommended that a dummy set of nut and screw lock assemblies are used for this part of the procedure and that these parts are not re-used during subsequent compressor build operations.
        It is not necessary to apply high temperature anti-seize compound to the threads of the nut and screw lock assemblies during this part of the procedure.

        Make sure that there is no grit or unwanted material on the threads and surfaces and then assemble the jacking screw and locknut assemblies. Make sure the bottom end of the screws are below the surface of nuts.

      2. Install the jacking screws in to the locknuts. Make sure the bottom end of the jacking screws are below the surface of the locknuts.

      4. Install the LH and RH locking blades, jacking screw and locknut assemblies and the two remaining standard blades. Refer to Figure.

      1. Install one of the LH locking blades in to the blade loading slot and use the drift to move it counterclockwise when you look from the rear.

      2. Install one jacking screw and locknut assembly in to the blade loading slot and move it counterclockwise when you look from the rear.

      3. Install one of the RH locking blades in to the blade loading slot and use the drift to move it counterclockwise when you look from the rear.

      4. Install the two standard blades in to the blade loading slot and use the drift to move them counterclockwise when you look from the rear.

      5. Install the second RH locking blade in to the blade loading slot and use the drift to move it clockwise when you look from the rear.

      6. Install the second jacking screw and locknut assembly in to the blade loading slot and move it clockwise when you look from the rear.

        7. Install the second LH locking blade in to the blade loading slot and use the drift to move it clockwise when you look from the rear. If it is not easy to install the final blade then do the steps that follow:

        1. Remove one of the two standard blades installed between the two pairs of locking blades and replace it with an undersize blade.

        2. Install the second LH locking blade in to the blade loading slot and move it clockwise when viewed from the rear of the disk.

      8. NOTE

        The jacking screw and locknut assemblies must be installed in the outer pair of locking slots in the disk.

        Continue to move the blades clockwise until the nut and screw lock assemblies are in their correct position. Refer to Figure.

      9. Use IAE 1R18590 Socket end 1 off to torque the screws to between 4 and 5 lbfin (0.45 to 0.56 Nm) above the applicable locking torque.

        10. use IAE IAE 1R18683 Caliper adapter 1 off to make sure that the jacking screws are correctly installed.

        1. The jacking screws must not be more than 0.0137in. (0.35 mm) above the top of the locknut and not more than 0.0787in. (2.00 mm) below the top of the locknut. Get the dimension at the position of the locknut that points to the front of the engine.

        11. If an undersize blade was installed in step C.(7)(a) do the steps that follow.

        1. Make sure the blades are installed against the jacking screw and locknut assemblies.

        2. Measure the clearance (dimension C) between the platforms of the standard size blade and the undersize blade. Refer to Figure.

        3. NOTE

          This clearance is in addition to the platform build clearance measured in Step.

          Make sure dimension C is not more than 0.018 in. (0.45 mm).

    37. SUBTASK 72-41-00-440-192-002 Install the Correct Selection of Stage 6 Blades for Grinding Operations, Fig Install the Correct Selection of Replacement Stage 6 Blades for Grinding Operations

      NOTE

      This method is used if the compressor disk has only two locking slots for the nut and screw lock assembly. Refer to Figure Inset 1.

    1. Refer to Figure, Figure and Figure

    2. CAUTION

      YOU MUST NOT USE THE DRIFT ON THE AIRFOIL SURFACES.

      Correlate the dummy rotor for the No. 1 position and the No. 1 blade.

      Start from the No. 1 blade and install the stage 6 standard and undersize blades which were selected in Step in to the disk in the identified sequence. Use IAE 1R18097 Drift 1 off to move the blades around the disk in a counterclockwise direction when you look from the rear.

      3. Prepare the jacking screw and locknut assemblies.

      1. NOTE

        Each nut and screw lock assembly must be kept as a set.
        It is recommended that a dummy set of nut and screw lock assemblies are used for this part of the procedure and that these parts are not re-used during subsequent compressor build operations.
        It is not necessary to apply high temperature anti-seize compound to the threads of the nut and screw lock assemblies during this part of the procedure.

        Make sure that there is no grit or unwanted material on the threads and surfaces and then assemble the jacking screw and locknut assemblies. Make sure the bottom end of the screws are below the surface of nuts.

      2. Install the jacking screws in to the locknuts. Make sure the bottom end of the jacking screws are below the surface of the locknuts.

      4. Install the LH and RH locking blades and jacking screw and locknut assemblies.

      1. Install one of the LH locking blades in to the blade loading slot and use the drift to move it counterclockwise when you look from the rear.

      2. Install one jacking screws and locknut assembly in to the blade loading slot and move it counterclockwise when you look from the rear.

      3. Install one of the RH locking blades in to the blade loading slot and use the drift to move it counterclockwise when you look from the rear.

      4. Install the second RH locking blade in to the blade loading slot and use the drift to move it clockwise when you look from the rear.

      5. Install the second jacking screw and locknut assembly in to the blade loading slot and move it clockwise when you look from the rear.

      6. Install the second LH locking blade in to the blade loading slot and use the drift to move it clockwise when you look from the rear.

      7. NOTE

        A blade platform joint will be in line with the center of the blade loading slot.

        Continue to move the blades in a clockwise direction until the jacking screw and locknut assemblies are in their correct positions. Refer to Figure.

      8. Use IAE 1R18590 Socket end 1 off to torque the screws to between 4 and 5 lbfin (0.45 and 0.56 Nm) above the applicable locking torque.

        9. Use IAE IAE 1R18683 Caliper adapter 1 off to make sure that the jacking screws are correctly installed.

        1. The jacking screws must not be more than 0.0137 in. (0.35 mm) above the top of the locknut and not more than 0.0787 in. (2.00 mm) below the top of the locknut. Get the dimension at the position that points to the front of the engine.

    38. SUBTASK 72-41-00-324-005 Grind the Tips of the Replacement Stage 6 Blades

    1. Use a brush to apply CoMat 03-398 METAL SPRAYING STOPPING-OFFCOMPOUND to protect the stage 6 rotor airfoils. Apply the material to approximately two thirds of the blade airfoil length when measured from the blade tips.

    2. Grind the tips of the replacement stage 6 blades installed in the dummy HP compressor rotor using the procedures given in TASK 72-41-10-440-004-A00.

      3. Remove the temporary surface protection from the rotor blade airfoils.

      1. Position cloth between each stage of rotor blades.

      2. NOTE

        The de-mineralized water must have a conductivity of 20 micro siemens.

        Use de-mineralized water and a cloth or brush to remove CoMat 03-398 METAL SPRAYING STOPPING-OFFCOMPOUND from the blade airfoils.

      3. Clean the blades with new de-mineralized water.

      4. Dry the blades with clean cloth or compressed air.

    4. Remove the stage 6 blades from the dummy rotor, refer to the procedure in Step.

    5. Make sure that the new blades are marked with their positions 1 to 79 in the disk.

    39. SUBTASK 72-41-00-440-193 Weigh the Removed Stage 6 Blades

    1. Weigh and record the mass each of the standard and undersize blades in its sequence in the stage. Keep a record of the weight and the blade identification number.

    2. Put the selection of standard, undersize blades and LH and RH locking blades on a suitable work surface in a light to heavy sequence. This sequence will determine the position of the locking blades. Refer to Figure.

    3. NOTE

      Undersize blades must not be installed adjacent to each other on assembly.
      Blades must be evenly distributed around the disk.

    40. SUBTASK 72-41-00-440-194 Do a Balance Patternation for the Replacement Stage 6 Blades

    1. Refer to Figure.

      2. Record the results.

      1. Record the results of the initial sequence (from Step) in the blade distribution program VX45 or alternative method IAE 1R19842 Blade distribution computer program X45 to calculate vector C.

      2. Record the results of vector B in the blade distribution program VX45 or alternative method IAE 1R19842 Blade distribution computer program X45, refer to Step. Make sure that the position of the locking blades are fixed in the patternation sequence.

    3. NOTE

      Undersize blades must not be installed adjacent to each other on assembly.
      Blades must be evenly distributed around the disk.

      Do a balance patternation to match vector B. The static unbalance must be within 1.5 grams of vector B, this is seen as distance D.

      4. If the undersize blades cannot be distributed evenly then do the following procedure.

      1. Choose applicable nominal and undersize blades and change their positions to get a more even distribution between the two segments. It could be necessary to fix a small segment of eight blades and let the program work with a larger segment.

        If it is necessary to change the positions of the blades then make sure that the platform build clearance (dimension A) and when applicable, the clearance (dimension C), refer to Step, are satisfactory and are within acceptable limits.

      2. Do a balance patternation to match vector B. The static unbalance must be within 1.5 grams of vector B, this is seen as distance D.

    41. SUBTASK 72-41-00-440-195 Install the Stage 6 Disk Sealing Wires

    1. Refer to Figure

    2. CAUTION

      WHEN INSTALLING THE DAMPER WIRES, POSITION THE DAMPER WIRE SO THAT THE SPLIT LINE IS AS FAR AWAY AS POSSIBLE FROM BOTH THE BLADE LOADING SLOT AND THE LOCATION OF THE MAXIMUM LOCAL WEAR TO THE DAMPER WIRE GROOVE.

      Install the stage 6 front sealing wire ENGINE-HP COMPRESSOR DISCS (STAGES 3-8) (72-41-11, 01-386) in to the stage 6 disk front groove of the dummy rotor.

    3. Push the sealing wire in to the bottom of the groove around the disk and measure the overlap (dimension B). Make sure that dimension B is a minimum of 0.236 in. (6.00 mm).

    4. Install the stage 6 rear sealing wire ENGINE-HP COMPRESSOR DISCS (STAGES 3-8) (72-41-11, 01-388) in to the stage 6 disk rear groove. The front and rear sealing wire joints must be 180 degrees apart.

    5. Do step B. again for the rear sealing wire.

    42. SUBTASK 72-41-00-440-196-001 Install the Correct Selection of Stage 6 Blades

      NOTE

      This method is used if the compressor disk has four locking slots for the nut and screw lock assemblies. Refer to Figure Inset 2.

    1. Refer to Figure, Figure and Figure

    2. CAUTION

      YOU MUST NOT USE THE DRIFT ON THE AIRFOIL SURFACES.

      NOTE

      Do not install the two standard size blades which must be installed between the locking blades.

      Install the stage 6 standard and undersize blades which were selected in Step in to the disk in the identified sequence. Use IAE 1R18097 Drift 1 off to move the blades around the disk in a counterclockwise direction when you look from the rear.

      3. Prepare the jacking screw and locknut assemblies.

      1. WARNING

        WHEN YOU USE CoMat 01-001 SOLVENT, DELETED OR CoMat 01-002 SOLVENT, DELETED. YOU MUST USE THE NECESSARY PROTECTIVE CLOTHING. DO NOT GET THE SOLVENT ON YOUR SKIN OR IN YOUR EYES. YOU MUST NOT SMOKE WHEN YOU USE THE SOLVENT AS THE VAPOR CHANGES AND BECOMES TOXIC.

        Use CoMat 01-001 SOLVENT, DELETED or CoMat 01-002 SOLVENT, DELETED. and a cloth to clean the threads of the jacking screw and locknut assemblies.

      2. Use a brush to apply CoMat 10-070 ANTI-SEIZE COMPOUND to the threads of the stage 6 jacking screw and locknut assemblies.

      3. Install the jacking screws in to the locknuts. Make sure the bottom end of the jacking screws are below the surface of the locknuts.

      4. NOTE

        The jacking screw and locknut assemblies must be installed in the positions they were removed from. Refer to Step.

        Install the LH and RH locking blades, jacking screw and locknut assemblies and the two remaining standard blades.

      1. Install one of the LH locking blades in to the blade loading slot and use the drift to move it counterclockwise when you look from the rear.

      2. Install one jacking screw and locknut assembly in to the blade loading slot and move it counterclockwise when you look from the rear.

      3. Install one of the RH locking blades in to the blade loading slot and use the drift to move it counterclockwise when you look from the rear.

      4. Install the two standard blades in to the blade loading slot and use the drift to move them counterclockwise when you look from the rear.

      5. Install the second RH locking blade in to the blade loading slot and use the drift to move it clockwise when you look from the rear.

      6. Install the second jacking screw and locknut assembly in to the blade loading slot and move it clockwise when you look from the rear.

        7. Install the second LH locking blade in to the blade loading slot and use the drift to move it clockwise when you look from the rear.

        1. Remove one of the two standard blades installed between the two pairs of locking blades and replace it with an undersize blade.

        2. Install the second LH locking blade in to the blade loading slot and move it clockwise when viewed from the rear of the disk.

      8. NOTE

        The jacking screw and locknut assemblies must be installed in the outer pair of locking slots in the disk.

        Continue to move the blades clockwise until the nut and screw lock assemblies are in their correct position. Refer to Figure.

      9. Use IAE 1R18590 Socket end 1 off to torque the screws to between 4 and 5 lbfin (0.45 to 0.56 Nm) above the applicable locking torque.

        10. use IAE IAE 1R18683 Caliper adapter 1 off to make sure that the jacking screws are correctly installed.

        1. The jacking screws must not be more than 0.0137in. (0.35 mm) above the top of the locknut and not more than 0.0787in. (2.00 mm) below the top of the locknut. Get the dimension at the position of the locknut that points to the front of the engine.

        11. If an undersize blade was installed in step C.(7)(a) do the steps that follow.

        1. Make sure the blades are installed against the jacking screw and locknut assemblies.

        2. Measure the clearance (dimension C) between the platforms of the standard size blade and the undersize blade. Refer to Figure.

        3. NOTE

          This clearance is in addition to the platform build clearance measured in Step.

          Make sure dimension C is not more than 0.018in. (0.45 mm).

    43. SUBTASK 72-41-00-440-196-002 Install the Correct Selection of Stage 6 Blades

      NOTE

      This method is used if the compressor disk has two locking slots for the nut and screw lock assembly. Refer to Figure Inset 1.

    1. Refer to Figure and Figure

    2. CAUTION

      YOU MUST NOT USE THE DRIFT ON THE AIRFOIL SURFACES.

      Install the stage 6 standard and undersize blades which were selected in Step in to the disk in the identified light-heavy-light sequence. Use IAE 1R18097 Drift 1 off to move the blades around the disk in a counterclockwise direction when you look from the rear.

      3. Prepare the jacking screw and locknut assemblies.

      1. WARNING

        WHEN YOU USE CoMat 01-001 SOLVENT, DELETED OR CoMat 01-002 SOLVENT, DELETED. YOU MUST USE THE NECESSARY PROTECTIVE CLOTHING. DO NOT GET THE SOLVENT ON YOUR SKIN OR IN YOUR EYES. YOU MUST NOT SMOKE WHEN YOU USE THE SOLVENT AS THE VAPOR CHANGES AND BECOMES TOXIC.

        Use CoMat 01-001 SOLVENT, DELETED or CoMat 01-002 SOLVENT, DELETED. and a cloth to clean the threads of the jacking screw and locknut assemblies.

      2. Use a brush to apply CoMat 10-070 ANTI-SEIZE COMPOUND to the threads of the stage 6 jacking screw and locknut lock assemblies.

      3. Install the jacking screws in to the locknuts. Make sure the bottom end of the jacking screws are below the surface of the locknuts.

      4. NOTE

        The jacking screws and locknuts assemblies must be installed in the positions they were removed from. Refer to Step.

        Install the LH and RH locking blades and jacking screw and locknut assemblies.

      1. Install one of the LH locking blades in to the blade loading slot and use the drift to move it counterclockwise when you look from the rear.

      2. Install one jacking screws and locknut assembly in to the blade loading slot and move it counterclockwise when you look from the rear.

      3. Install one of the RH locking blades in to the blade loading slot and use the drift to move it counterclockwise when you look from the rear.

      4. Install the second RH locking blade in to the blade loading slot and use the drift to move it clockwise when you look from the rear.

      5. Install the second jacking screw and locknut assembly in to the blade loading slot and move it clockwise when you look from the rear.

      6. Install the second LH locking blade in to the blade loading slot and use the drift to move it clockwise when you look from the rear.

      7. NOTE

        A blade platform joint will be in line with the center of the blade loading slot.

        Continue to move the blades in a clockwise direction until the jacking screw and locknut assemblies are in their correct positions. Refer to Figure.

      8. Use IAE 1R18590 Socket end 1 off to torque the screws to between 4 and 5 lbfin (0.45 and 0.56 Nm) above the applicable locking torque.

        9. Use IAE IAE 1R18683 Caliper adapter 1 off to make sure that the jacking screws are correctly installed.

        1. The jacking screws must not be more than 0.0137in. (0.35 mm) above the top of the locknut and not more than 0.0787in. (2.00 mm) below the top of the locknut. Get the dimension at the position that points to the front of the engine.

    44. Figure: Measure Blade Lockplate Clearance

    Sheet 1

    Legend
    Measure Blade Lockplate Clearance

    Sheet 1

    Close

    Figure: Install the stage 3 retaining plates and lockplates

    Sheet 2

    Legend
    Install the stage 3 retaining plates and lockplates

    Sheet 2

    Close

    Figure: Examine the Clapper Abutment Faces

    Sheet 3

    Legend
    Examine the Clapper Abutment Faces

    Sheet 3

    Close

    Figure: Install the stages 4 and 5 retaining plates and lockplates

    Install the stages 4 and 5 retaining plates and lockplates

    Figure: Position of retaining plates following dressing repair

    Position of retaining plates following dressing repair

    Figure: Lock the lockplates in position

    Lock the lockplates in position

    Figure: Example of a light-heavy-light sequence

    Example of a light-heavy-light sequence

    Figure: Calculate the static unbalance

    Calculate the static unbalance

    Figure: Example of stage 6 blade loading slot and locknut slots

    Example of stage 6 blade loading slot and locknut slots

    Figure: Measure the stage 6 platform build clearance

    Measure the stage 6 platform build clearance

    Figure: Measure the clearance (dimension C) between the undersize blade and the standard blade

    Measure the clearance (dimension C) between the undersize blade and the standard blade

    Figure: Measure the stage 6 sealing wires overlap

    Measure the stage 6 sealing wires overlap

    Figure: Install the nut and screw lock assemblies in to the stage 6 disk

    Install the nut and screw lock assemblies in to the stage 6 disk

Requirements After Job Completion

Follow-On Conditions

NONE
Change Type:

Revised the temporary mark procedure. (18VG365))

Manufacturer Code:0AM53
Enterprise Name:IAE INTERNATIONAL AERO ENGINES AG
BU Name:NULL
Building:SUITE 400
Street:628 HEBRON AVENUE
City:GLASTONBURY
State:CT
Zip Code:06033
Country:USA
Manufacturer Code:IE304
Enterprise Name:DELETED
BU Name:DELETED,SEE CAGE CODE 0V6W9
Manufacturer Code:K6835
Enterprise Name:MED-LAB LTD
BU Name:MED-LAB LTD
Street:COPELAND ST
City:DERBY
Zip Code:DE1 2PU
Country:GREAT BRITAIN
Phone Number:44-1332-349094
Fax Number:44-1332-371237
Email:sales@med-lab.co.uk
Internet:www.med-lab.co.uk
Manufacturer Code:LOCAL
Enterprise Name:LOCALLY SUPPLIED
Manufacturer Code:X111X
Enterprise Name:N/A – DELETED CONSUMABLE MATERIAL
Manufacturer Code:X333X
Enterprise Name:REFER TO V2500 SB ENG-79-0108
Link not Found
Part Number:6A1029
Part Name:PLATE - LOCKING
Manufacturer Code:0AM53
Part Number:6A1034
Part Name:PLATE - LOCKING
Manufacturer Code:0AM53
Part Number:6A1039
Part Name:PLATE - LOCKING
Manufacturer Code:0AM53
Manufacturer Code:X111X
Supply Number:CoMat 01-001
Type:sp01
Supply Short Name:CoMat 01-001 SOLVENT, DELETED
Supply Name:CoMat 01-001 SOLVENT, DELETED
Specification Groups:
Doc NumberType
wiring harnesses. Where CoMat 01‐001 is specified to clean mechanical components, use one or more of the solvents that SPM TASK 70‐11‐26‐300‐503 specifies as applicable.DELETED. Where CoMat 01‐001 is specified to clean electrical contacts or wiring harnesses, use one or more of the solvents that SPM TASK 70‐11‐57‐110‐501 specifies to clean electrical contacts or
Suppliers:
ManufacturerRemarks
X111X
Manufacturer Code:X111X
Supply Number:CoMat 01-002
Type:sp01
Supply Short Name:CoMat 01-002 SOLVENT, DELETED.
Supply Name:CoMat 01-002 SOLVENT, DELETED.
Specification Groups:
Doc NumberType
wiring harnesses. Where CoMat 01‐002 is specified to clean mechanical components, use one or more of the solvents that SPM TASK 70‐11‐26‐300‐503 specifies as applicable.DELETED. Where CoMat 01‐002 is specified to clean electrical contacts or wiring harnesses, use one or more of the solvents that SPM TASK 70‐11‐57‐110‐501 specifies to clean electrical contacts or
Suppliers:
ManufacturerRemarks
X111X
Manufacturer Code:IE304
Supply Number:CoMat 02-121
Type:sp01
Supply Short Name:CoMat 02-121 TEMPORARY MARKER PENCIL/CRAYON
Supply Name:CoMat 02-121 TEMPORARY MARKER PENCIL/CRAYON
Specification Groups:
Doc NumberType
OMAT: 261BEROL VERITHIN (HARD TYPE)
Suppliers:
ManufacturerRemarks
IE304
K5720
K6835
LOCAL
Manufacturer Code:K6835
Supply Number:CoMat 02-122
Type:sp01
Supply Short Name:CoMat 02-122 TEMPORARY MARKER PENCIL/CRAYON
Supply Name:CoMat 02-122 TEMPORARY MARKER PENCIL/CRAYON
Specification Groups:
Doc NumberType
DELETED
Suppliers:
ManufacturerRemarks
K6835
IE133
Manufacturer Code:LOCAL
Supply Number:CoMat 03-398
Type:sp01
Supply Short Name:CoMat 03-398 METAL SPRAYING STOPPING-OFFCOMPOUND
Supply Name:CoMat 03-398 METAL SPRAYING STOPPING-OFFCOMPOUND
Specification Groups:
Doc NumberType
OMAT:3/37AMETCO ANTI-BOND
Suppliers:
ManufacturerRemarks
LOCAL
39918
IE103
IE195
K1030
K6835
IE200
Manufacturer Code:X222X
Supply Number:CoMat 07-075
Type:sp01
Supply Short Name:CoMat 07-075 HIGH-HEAT RESISTING STOVING ENAMEL
Supply Name:CoMat 07-075 HIGH-HEAT RESISTING STOVING ENAMEL
Specification Groups:
Doc NumberType
Deleted. Use one of the CoMat 07-075 letter suffix materials.
Suppliers:
ManufacturerRemarks
X222X
Manufacturer Code:X222X
Supply Number:CoMat 10-070
Type:sp01
Supply Short Name:CoMat 10-070 ANTI-SEIZE COMPOUND
Supply Name:CoMat 10-070 ANTI-SEIZE COMPOUND
Specification Groups:
Doc NumberType
DELETED. USE COMAT 10-070A
Suppliers:
ManufacturerRemarks
X222X
Manufacturer Code:X333X
Supply Number:CoMat 10-077
Type:sp01
Supply Short Name:CoMat 10-077 APPROVED ENGINE OILS
Supply Name:CoMat 10-077 APPROVED ENGINE OILS
Specification Groups:
Doc NumberType
For V2500-A1/A5/D5 models - Refer to V2500 Service Bulletin ENG-79-0108
For V2500-E5 model - Refer to Service Bulletin E5-79-0001
Suppliers:
ManufacturerRemarks
X333X
Manufacturer Code:0AM53
Tool Number:IAE 1R18069
Tool Name:IAE 1R18069 Rear anvil
Manufacturer Code:0AM53
Tool Number:IAE 1R18070
Tool Name:IAE 1R18070 Front anvil
Manufacturer Code:0AM53
Tool Number:IAE 1R18071
Tool Name:IAE 1R18071 Rear anvil
Manufacturer Code:0AM53
Tool Number:IAE 1R18072
Tool Name:IAE 1R18072 Front anvil
Manufacturer Code:0AM53
Tool Number:IAE 1R18073
Tool Name:IAE 1R18073 Rear anvil
Manufacturer Code:0AM53
Tool Number:IAE 1R18074
Tool Name:IAE 1R18074 Front anvil
Manufacturer Code:0AM53
Tool Number:IAE 1R18076
Tool Name:IAE 1R18076 Slave lock plates
Manufacturer Code:0AM53
Tool Number:IAE 1R18079
Tool Name:IAE 1R18079 Drift
Manufacturer Code:0AM53
Tool Number:IAE 1R18080
Tool Name:IAE 1R18080 Drift
Manufacturer Code:0AM53
Tool Number:IAE 1R18082
Tool Name:IAE 1R18082 Pliers
Manufacturer Code:0AM53
Tool Number:IAE 1R18083
Tool Name:IAE 1R18083 Hydraulic tool
Manufacturer Code:0AM53
Tool Number:IAE 1R18084
Tool Name:IAE 1R18084 Pliers
Manufacturer Code:0AM53
Tool Number:IAE 1R18097
Tool Name:IAE 1R18097 Drift
Manufacturer Code:0AM53
Tool Number:IAE 1R18245
Tool Name:IAE 1R18245 Adapter
Manufacturer Code:0AM53
Tool Number:IAE 1R18590
Tool Name:IAE 1R18590 Socket end
Manufacturer Code:0AM53
Tool Number:IAE 1R18683
Tool Name:IAE 1R18683 Caliper adapter
Manufacturer Code:0AM53
Tool Number:IAE 1R18911
Tool Name:IAE 1R18911 Drill
Manufacturer Code:0AM53
Tool Number:IAE 1R18914
Tool Name:IAE 1R18914 Setting gage
Manufacturer Code:0AM53
Tool Number:IAE 1R19767
Tool Name:IAE 1R19767 Fixture
Manufacturer Code:0AM53
Tool Number:IAE 1R19768
Tool Name:IAE 1R19768 20mm Spacer
Manufacturer Code:0AM53
Tool Number:IAE 1R19811
Tool Name:IAE 1R19811 Filing fixture
Manufacturer Code:0AM53
Tool Number:IAE 1R19812
Tool Name:IAE 1R19812 Filing fixture
Manufacturer Code:0AM53
Tool Number:IAE 1R19813
Tool Name:IAE 1R19813 Filing fixture
Manufacturer Code:0AM53
Tool Number:IAE 1R19842
Tool Name:IAE 1R19842 Blade distribution computer program X45
Manufacturer Code:LOCAL
Tool Number:SCHENCK WM0
Tool Name:WM00 (80MM INTERFACE)
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