TASK 72-32-00-430-014-A00 LPC/Intermediate Case Module - Install The Front Fairings, No. 1 And No. 6 Strut Fairing Panels, Fan Exit Pressure Boss, And Block, Assembly-014

DMC:V2500-A1-72-32-0000-14A-710A-B|Issue No:002.00|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

V2500-A1

Common Information

TASK 72-32-00-430-014-A00 LPC/Intermediate Case Module - Install The Front Fairings, No. 1 And No. 6 Strut Fairing Panels, Fan Exit Pressure Boss, And Block, Assembly-014

General

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 number.

For standard torque data and procedures, refer to the SPM TASK 70-41-00-400-501 and SPM TASK 70-41-02-410-501 .

Special torque data and assembly tolerances are included in the procedure.

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

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

To install lockwire, refer to the SPM TASK 70-42-05-400-501.

The abbreviation Intf shows an interference or tight fit. This causes REJECT IF MORE THAN to become REJECT IF LESS THAN. The abbreviation Clear shows a clearance fit.

The number for each radial location must be identified in a clockwise direction. These start at the engine top position when you look from the rear of the engine, unless stated differently in the procedure.

The No.1 strut, which is the top position strut of the fan frame assembly, is identified by the five pressure tubes on the No. 1 strut leading edge.

This TASK gives the procedure to install the front fairings, the No. 1 and No. 6 strut fairing panels, the fan exit pressure boss and the block. For the other parts of the LP compressor/intermediate case module, refer to TASK 72-32-00-430-000 (ASSEMBLY-000).

NOTE

To identify the consumable materials refer to the PCI.

NOTE

Special tools are identified in the procedure by the tool primary number.

Preliminary Requirements

Pre-Conditions

NONE

Support Equipment

NameManufacturerPart Number / IdentificationQuantityRemark
Sealant dispenserLOCALSealant dispenser
IAE 1J12508 Measuring stretch0AM53IAE 1J125081

Consumables, Materials and Expendables

NameManufacturerPart Number / IdentificationQuantityRemark
CoMat 01-124 ISOPROPYL ALCOHOLLOCALCoMat 01-124
CoMat 01-031 ACETONE (CH3)2COLOCALCoMat 01-031
CoMat 02-119 LOCKWIRELOCALCoMat 02-119
CoMat 04-004 JOINTING COMPOUND, LIGHT GRADELOCALCoMat 04-004
CoMat 08-014 PRIMER, SILICONE ADHESIVE/SEALANT0AM53CoMat 08-014
CoMat 08-045 SILICONE RUBBER COMPOUNDLOCALCoMat 08-045
CoMat 10-077 APPROVED ENGINE OILSLOCALCoMat 10-077

Spares

NONE

Safety Requirements

NONE

Procedure

    1. SUBTASK 72-32-00-430-170 Apply the Jointing Compound to the Mating Faces on the Brackets

    1. Refer to Figure.

    2. Make sure that the fan frame and fan case assembly is installed horizontally on the turnover stand. Refer to TASK 72-32-00-430-013-A00 (ASSEMBLY-013, CONFIG-001).

    3. Make sure that the work mat is in position in the fan case. Refer to TASK 72-32-00-430-012-A00 (ASSEMBLY-012, CONFIG-001).

    4. Make a clean cloth moist with CoMat 01-124 ISOPROPYL ALCOHOL to clean the mating faces on the 16 brackets.

    5. NOTE

      1. Do not get the jointing compound into the threaded holes of the clinch nuts on the brackets.

      2. Install the front fairings on the brackets before the jointing compound becomes dry.

      Apply CoMat 04-004 JOINTING COMPOUND, LIGHT GRADE with a stiff brush to the mating faces on the brackets.

    2. SUBTASK 72-32-00-430-171-A00 Install the Front Fairings on the Brackets (Pre SBE 72-0136)

    1. Refer to Figure.

    2. Attach the four front fairings V2500-A5-72-32-93-01A-941A-D (72-32-93, 01-200) to the 16 brackets with the 40 screws (01-210) and dimpled washers (01-208). Tighten the screws lightly.

    3. Make sure that there are correct circumferential clearances between the front fairings. The clearances must be less than 0.039 in. (1.0 mm). Adjust the position of each front fairing to get the correct clearance if necessary.

    4. Make sure that there are correct axial clearances between the front fairing and the splitter fairing of the fan outlet inner vane assembly. The clearances must be 0.004 to 0.019 in. (0.1 to 0.5 mm). Adjust the position of each front fairing to get the correct clearance if necessary.

    5. Torque the 40 screws to 65 to 75* lbfin (7.48 to 8.62 Nm).

    3. SUBTASK 72-32-00-430-171-B00 Install the Front Fairing onto the Brackets (SBE 72-0136)

      SBE 72-0136: Deletion of polyurethane coating of front fairing assembly

    1. Refer to Figure and Figure.

    2. Attach the four front fairings V2500-A5-72-32-93-01A-941A-D (72-32-93, 01-200) to the 16 brackets with the 40 screws (01-210). Tighten the screws lightly.

    3. Make sure that there are correct circumferential clearances between the front fairings. The clearances must be less than 0.039 in. (1.0 mm). Adjust the position of each front fairing to get the correct clearance if necessary.

    4. Make sure that there are correct axial clearances between the front fairing and the splitter fairing of the fan outlet inner vane assembly. The clearances must be 0.004 to 0.019 in. (0.1 to 0.5 mm). Adjust the position of each front fairing to get the correct clearance if necessary.

    5. Torque the 40 screws to 65 to 75* lbfin (7.34 to 8.47* Nm).

    4. SUBTASK 72-32-00-430-173-A00 Measure the Module Interface Dimension for the Installation of the HP System Module (Pre SBE 72-0391)

    1. Refer to Figure.

    2. Read the tool dimension L marked on IAE 1J12508 Measuring stretch 1 off.

      3. Install the measuring stretch on the fan frame assembly.

      1. Put the two blocks (part of the measuring stretch) on the fan frame rear flange at 12 and 6 o'clock positions.

      2. Put the measuring stretch on the blocks.

      3. Install the two wing bolts, two nuts and the four washers which attach the measuring stretch to the fan frame rear flange. Tighten the wing bolts.

    4. Measure the dimensions L1 at 12 and 6 o'clock positions with the depth micrometer.

      5. Measure the dimension J1 at 12 and 6 o' clock positions.

      1. Apply force of 33lbs (15 Kg) or more to push LP stub shaft rearward by hand until its movements stops. Continue pushing to keep the LP stub shaft in the position until Step is completed.

      2. NOTE

        No. 1 bearing axial play causes the LP stub shaft to be moveable if the module is horizontal. The LP stub shaft must be at the rear position in the movement range for correct measurement of J1. The LP stub shaft moves correctly to the rear end position if you push it with sufficient force.

        Measure the dimension J1 with a depth micrometer.

    6. Use the following formulas to calculate the dimensions AB and AD at the two positions.

      AB = J1 - L.

      AD = L1 - L.

    7. Make sure that the dimensions AB are 6.4767 to 6.4951 in. (164.506 to 164.97 mm).

    8. Make sure that the dimensions AD are 0.9410 to 0.9606 in. (23.900 to 24.400 mm).

      9. Remove the measuring stretch from the fan frame rear flange.

      1. Remove the two wing bolts, two nuts and the four washers which attach the measuring stretch and the two blocks to the fan frame rear flange.

      2. Remove the measuring stretch and blocks from the flange.

      10. Measure the dimensions J1 and L1 and make sure of the dimensions AB and AD at 3 and 9 o'clock positions.

      1. Do step C. to install the blocks and the measuring stretch at 3 and 9 o'clock positions.

      2. Do steps D. to I. to measure the dimensions J1 and L1 and make sure of the dimensions AB and AD at 3 and 9 o'clock positions.

    5. SUBTASK 72-32-00-430-173-B00 Measure the Module Interface Dimension for the Installation of the HP System Module (SBE 72-0391)

      SBE 72-0391: New separate type No. 1 bearing support asembly

    1. Refer to Figure.

    2. Read the tool dimension L marked on IAE 1J12508 Measuring stretch 1 off.

      3. Install the measuring stretch on the fan frame assembly.

      1. Put the two blocks (part of the measuring stretch) on the fan frame rear flange at 12 and 6 o'clock positions.

      2. Put the measuring stretch on the blocks.

      3. Install the two wing bolts, two nuts and the four washers which attach the measuring stretch to the fan frame rear flange. Tighten the wing bolts.

    4. Measure the dimensions L1 at 12 and 6 o'clock positions with the depth micrometer.

      5. Measure the dimension J1 at 12 and 6 o' clock positions.

      1. Apply force of 33lbs (15 Kg) or more to push LP stub shaft rearward by hand until its movements stops. Continue pushing to keep the LP stub shaft in the position until Step is completed.

      2. NOTE

        No. 1 bearing axial play causes the LP stub shaft to be moveable if the module is horizontal. The LP stub shaft must be at the rear position in the movement range for correct measurement of J1. The LP stub shaft moves correctly to the rear end position if you push it with sufficient force.

        Measure the dimension J1 with a depth micrometer.

    6. Use the following formulas to calculate the dimensions AB and AD at the two positions.

      AB = J1 - L.

      AD = L1 - L.

    7. Make sure that the dimensions AB are 6.4582 to 6.4766 in. (164.036 to 164.508 mm).

    8. Make sure that the dimensions AD are 0.9410 to 0.9606 in. (23.900 to 24.400 mm).

      9. Remove the measuring stretch from the fan frame rear flange.

      1. Remove the two wing bolts, two nuts and the four washers which attach the measuring stretch and the two blocks to the fan frame rear flange.

      2. Remove the measuring stretch and blocks from the flange.

      10. Measure the dimensions J1 and L1 and make sure of the dimensions AB and AD at 3 and 9 o'clock positions.

      1. Do Step to install the blocks and the measuring stretch at 3 and 9 o'clock positions.

      2. Do steps Step to Step to measure the dimensions J1 and L1 and make sure of the dimensions AB and AD at 3 and 9 o'clock positions.

    6. SUBTASK 72-32-00-430-317-A00 Install the Fan Exit Pressure Boss onto the Fan Case (Pre SBE 75-0010)

    1. Refer to Figure.

    2. Attach the pressure boss ENGINE-FAN CASE (72-32-85, 02-100) to the fan case at the 12 o'clock position wth the three bolts ENGINE-FAN CASE (72-32-85, 02-110).

    3. Torque the bolts to 36 to 45 lbfin (4.00 to 5.00 Nm).

    7. SUBTASK 72-32-00-430-317-B00 Install the Fan Exit Pressure Boss onto the Fan Case (SBE 75-0010)

      SBE 75-0010: Cooling air supply to dedicated alternator.

    1. Refer to Figure.

    2. Attach the pressure boss (03-200) to the fan case at the 12 o'clock position with the three bolts (03-210).

    3. Torque the bolts to 36 to 45 lbfin (4.00 to 5.00 Nm).

    8. SUBTASK 72-32-00-430-318 Install the Block onto the Fan Case

    1. Refer to Figure and Figure.

    2. Align the holes in the block ENGINE-FAN CASE (72-32-85, 02-330) with the holes in the two flanges on the fan case.

    3. Install the pin ENGINE-FAN CASE (72-32-85, 02-320) into the aligned holes and safety with the stopper ENGINE-FAN CASE (72-32-85, 02-300).

    9. SUBTASK 72-32-00-430-287-A00 Install the Fire Shields to the No.1 Strut Fairing Panel (Pre SBE 72-0216)

    1. Refer to Figure.

      2. Install the two shields on the No.1 strut fairing panel.

      1. Install the shield ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-400) on the No. 1 strut fairing panel ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-300) with the two screws ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-410), washers ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-407) and nuts ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-405).

      2. Torque the nuts to 6.00 to 8.00 lbfin (0.68 to 0.90 Nm).

      3. Install the shield ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-420) on the No. 1 strut fairing panel ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-300) with the two screws ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-430), washers ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-427) and nuts ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-425).

      4. Torque the nuts to 6.00 to 8.00 lbfin (0.68 to 0.90 Nm).

    10. SUBTASK 72-32-00-430-287-B00 Install the Fire Shields to the No. 1 Strut Fairing Panel (SBE 72-0216 and Pre SBE 72-0230)

      SBE 72-0216: Additional plate nut on the No.1 strut fairing panel

    1. Refer to Figure.

      2. Install the two shields on the No.1 strut fairing panel.

      1. Install the shield ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-400) on the no. 1 strut fairing panel ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-300) with the two screws ENGINE-INTERMEDIATE STRUCTURE (72-32- 03,02-410).

      2. Torque the screws to 6.00 to 8.00 lbfin (0.68 to 0.90 Nm).

      3. Install the shield ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-420) on to the No. 1 strut fairing panel ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-300) with the two screws ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-430).

      4. Torque the screws to 6.00 to 8.00 lbfin (0.68 to 0.90 Nm).

    11. SUBTASK 72-32-00-430-319 Apply Jointing Compound to the Mating Faces on the Panel Supporting Brackets

    1. Refer to Figure.

    2. Make a clean cloth moist with CoMat 01-124 ISOPROPYL ALCOHOL to clean the mating faces on the two panel supporting brackets ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-500 and ENGINE-INTERMEDIATE STRUCTURE 02-550).

    3. NOTE

      Install the panel supporting brackets onto the fan case before the jointing compound becomes dry.

      Apply CoMat 04-004 JOINTING COMPOUND, LIGHT GRADE with a stiff brush to the mating faces.

    12. SUBTASK 72-32-00-430-175-A00 Install the No. 1 Strut Fairing Panel onto the Fan Frame and the Fan Case (Pre SBE 72-0051)

    1. Refer to Figure.

      2. Attach the panel supporting brackets to the fan case.

      1. Attach the panel supporting bracket ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-550) to the fan case at the 12 o'clock position with the two washers ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-570), bolts ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-560) and nuts ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-580).

      2. Torque the bolts to 85 to 105 lbfin (10.00 to 12.00 Nm).

      3. Attach the No. 1 strut fairing panel ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-300) to the fan frame and the bracket.

      1. Put the panel on the fan frame and the bracket.

      2. Install the three washers ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-315), bolts ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-310), washers ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-307) and nuts ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-305) which attach the panel to the bracket. Tighten the bolts lightly.

      3. Install the four washers ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-320) and bolts ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-330) which attach the panel to the fan frame. Tighten the bolts lightly.

      4. Torque the bolts ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-310) to 85 to 105 lbfin (10.00 to 12.00 Nm).

      5. Torque the bolts ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-330) to 36 to 45 lbfin (4.00 to 5.00 Nm).

    13. SUBTASK 72-32-00-430-175-B00 Install the No. 1 Strut Fairing Panel onto the Fan Frame and the Fan Case (SBE 72-0051)

      SBE 72-0051: Incorporating a fuel drain tube in the fan frame assembly

    1. Refer to Figure.

      2. Attach the panel supporting brackets to the fan case.

      1. Attach the panel supporting bracket ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-550) to the fan case at the 12 o'clock position with the two washers ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-570), bolts ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-560) and nuts ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-580).

      2. Torque the bolts to 85 to 105 lbfin (10.00 to 12.00 Nm).

      3. Attach the No.1 strut fairing panel ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-300) to the fan frame and the bracket.

      1. Put the panel on the fan frame and the bracket.

      2. Install the three washers ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-315), bolts ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-310), washers ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-307) and nuts ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-305) which attach the panel to the bracket. Tighten the bolts lightly.

      3. Install the four washers ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-320) and bolts ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-330) which attach the panel to the fan frame. Tighten the bolts lightly.

      4. Torque the bolts ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-310) to 85 to 105 lbfin (10.00 to 12.00 Nm).

      5. Torque the bolts ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-330) to 36 to 45 lbfin (4.00 to 5.00 Nm).

      6. Safety the bolts ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-330) with CoMat 02-119 LOCKWIRE.

    14. SUBTASK 72-32-00-430-320-A00 Install the No. 6 Strut Fairing Panel onto the Fan Frame Assembly and the Fan Case (Pre SBE 72-0051, SBE 72-0175 and SBE 72-0435)

      SBE 72-0175: Provide longer attaching bolts for the open latch indicator bracket

      SBE 72-0435: Fan case panel and bracket scalloped for No.4 scavenge tube reroute

    1. Refer to Figure and Figure.

      2. Attach the panel supporting bracket to the fan case.

      1. Put the panel supporting bracket ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-500) onto the fan case at the 6 o'clock position.

        2. Safety with the two washers ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-530), bolts ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-520) and nuts ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-510).

        1. Torque the bolts to 85 to 105 lbfin (10.00 to 12.00 Nm).

      3. Attach the No.6 strut fairing panel ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-100) to the fan frame and the panel supporting bracket.

      1. Put the panel onto the fan frame assembly and the bracket.

      2. Install the two bolts ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-132), washers ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-120) and nuts ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-110) which attach the panel to the bracket. Tighten the bolts lightly.

      3. Install the four washers ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-140) and bolts ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-150) which attach the panel to the fan frame assembly. Tighten the bolts lightly.

      4. Torque the bolts ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-132) to 85 to 105 lbfin (10.00 to 12.00 Nm).

      5. Torque the bolts ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-150) to 85 to 105 lbfin (10.00 to 12.00 Nm).

    15. SUBTASK 72-32-00-430-320-B00 Install the No. 6 Strut Fairing Panel onto the Fan Frame Assembly and the Fan Case (SBE 72-0051, SBE 72-0175 and SBE 72-0435)

      SBE 72-0051: Incorporate a fuel drain tube in the fan frame assembly.

      SBE 72-0175: Provide longer attaching bolts for the open latch indicator bracket.

      SBE 72-0435: Fan case, panel and bracket scalloped for No. 4 scavenge tube reroute

    1. Refer to Figure and Figure.

      2. Attach the panel supporting bracket to the fan case.

      1. Put the panel supporting bracket ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-500) onto the fan case at the 6 o'clock position.

      2. Safety with the two washers ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-530), bolts ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-520) and nuts ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-510).

      3. Torque the bolts to 85 to 105 lbfin (10.00 to 12.00 Nm).

      3. Attach the No.6 strut fairing panel ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-100) to the fan frame and the panel supporting bracket.

      1. Put the panel onto the fan frame assembly and the bracket.

      2. Install the two bolts ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-132), washers ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-120) and nuts ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-110) which attach the panel to the bracket. Tighten the bolts lightly.

      3. Install the drain pipe ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-080), the four washers ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-140) and bolts ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-150) which attach the panel to the fan frame assembly. Tighten the bolts lightly.

      4. Torque the two bolts ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-132) to 85 to 105 lbfin (10.00 to 12.00 Nm).

      5. Torque the bolts ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-150) to 85 to 105 lbfin (10.00 to 12.00) Nm).

      6. Safety the bolts ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-150) with CoMat 02-119 LOCKWIRE.

    16. SUBTASK 72-32-00-430-224 Install the Stopper on the Fan Frame Assembly (SBE 72-0150)

      SBE 72-0150: Provide a new weight reduced fan frame assembly and associated details.

    1. Refer to Figure.

    2. Install the stopper ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-450) with the two screws ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-454) and nuts ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-451).

    3. Torque the two nuts to 36 to 45 lbfin (4.00 to 5.00 Nm).

    17. SUBTASK 72-32-00-430-176 Apply Sealant to the Mating Faces on the Corner Fillers

    1. Refer to Figure.

      2. Make a clean cloth or a soft brush moist with CoMat 01-031 ACETONE (CH3)2CO or CoMat 01-124 ISOPROPYL ALCOHOL.

      1. the LH corner strut filler ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 01-700).

      2. the RH corner strut filler ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 01-750).

      3. the LH corner strut filler ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 01-850).

      4. the RH corner strut filler ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 01-800).

    3. NOTE

      Apply the primer in less than eight hours after the mating faces are cleaned.

      Apply a thin layer of CoMat 08-014 PRIMER, SILICONE ADHESIVE/SEALANT with a soft brush to the mating faces. Air dry for 30 minutes minimum.

    4. Apply CoMat 08-045 SILICONE RUBBER COMPOUND from the nozzle of the sealant tube to the mating faces.

    5. Press the silicone rubber compound into position with a spatula.

    18. SUBTASK 72-32-00-430-177 Install the Corner Strut Fillers and the Panel Corner Fillers on to the Struts and the Strut Fairing Panels

    1. Refer to Figure.

      2. Install the LH corner strut filler ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 01-300) and the RH corner strut filler ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 01-400) on to the No. 1 strut.

      1. Attach the fillers to the No. 1 strut.

      2. Attach the LH corner strut filler with the screw ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 01-340), the washer ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 01-320) and the nut ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 01-310). Torque the nut to 36 to 45 lbfin (4.00 to 5.00 Nm).

      3. Attach the RH corner strut filler with the screw ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 01-440), the washer ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 01-420) and the nut ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 01-410). Torque the nut to 36 to 45 lbfin (4.00 to 5.00 Nm).

      3. Install the LH corner strut filler ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 02-200) and the RH corner strut filler ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 01-100) on the No. 6 strut.

      1. Attach the fillers to the No. 6 strut.

      2. Attach the LH corner strut filler with the screw ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 01-240), the washer ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 01-220) and nut ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 01-210). Torque the nut to 36 to 45 lbfin (4.00 to 5.00 Nm).

      3. Attach the RH Corner strut filler with the screw ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 01-140), the washer ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 01-120) and nut ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 01-110). Torque the nut to 36 to 45 lbfin (4.00 to 5.00 Nm).

      4. Install the LH panel corner filler ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 01-700) and the RH panel corner filler ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 01-750) on the No. 1 strut fairing panel.

      1. Attach the fillers to the No. 1 strut fairing panel.

      2. Attach the LH panel corner filler with the two washers ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 01-704 and ENGINE-INTERMEDIATE STRUCTURE 01-708) and bolts ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 01-702 and ENGINE-INTERMEDIATE STRUCTURE 01-706). Torque the bolts to 36 to 45 lbfin (4.00 to 5.00 Nm).

      3. Attach the RH panel corner filler with the two washers ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 01-754 and ENGINE-INTERMEDIATE STRUCTURE01-758) and bolts ENGINE-INTERMEDIATE STRUCTURE(72-32-03, 01-752 and ENGINE-INTERMEDIATE STRUCTURE01-756). Torque the bolts to 36 to 45 lbfin (4.00 to 5.00 Nm).

      5. Install the LH panel corner filler ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 01-850) and the RH panel corner filler ENGINE-INTERMEDIATE STRUCTURE(72-32-03,01-800) on the No. 6 strut fairing panel.

      1. Attach the fillers to the No. 6 strut fairing panel.

      2. Attach the LH panel corner filler with the two washers ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 01-854 and ENGINE-INTERMEDIATE STRUCTURE 01-858) and bolts ENGINE-INTERMEDIATE STRUCTURE(72-32-03, 01-852 and ENGINE-INTERMEDIATE STRUCTURE 01-856). Torque the bolts to 36 to 45 lbfin (4.00 to 5.00 Nm).

      3. Attach the RH panel corner filler with the two washers ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 01-804 and ENGINE-INTERMEDIATE STRUCTURE 01-808) and bolts ENGINE-INTERMEDIATE STRUCTURE (72-32-03, 01-802 and ENGINE-INTERMEDIATE STRUCTURE 01-806). Torque the bolts to 36 to 45 lbfin (4.00 to 5.00 Nm).

    19. SUBTASK 72-32-00-430-178 Fill the Recesses in the Corner Strut Fillers with Sealant

    1. Refer to Figure.

    3. NOTE

      Apply the primer in less than eight hours after the cleaning of the mating faces.

      Apply thin layer of CoMat 08-014 PRIMER, SILICONE ADHESIVE/SEALANT with a soft brush to the surfaces of the recesses. Air dry for 30 minutes minimum.

    4. Fill CoMat 08-045 SILICONE RUBBER COMPOUND from the nozzle of the sealant tube into the recesses.

    5. Press the silicone rubber compound into position with a spatula.

    20. SUBTASK 72-32-00-430-180 Turn the LP Compressor/Intermediate Case Module Vertical with the Rear End Up

    1. Refer to Figure.

      2. Release the fan case front flange from the stopper base and stopper assembly (part of the turnover stand).

      1. Loosen the two knobs (part of the turnover stand) to release the fan case front flange from the stopper.

      2. Loosen the set screw (part of the turnover stand) so that you can turn the adjuster (part of the turnover stand).

      3. Turn the adjuster counterclockwise to lower the stopper until it is clear of the fan case front flange.

      4. Remove the stopper base and stopper assembly from the turnover stand.

    3. Release the lock pin from the holes in the handle and the support C of the turnover stand.

    4. Turn the handle to set the module vertical with the rear end up.

    5. NOTE

      Make sure that the hole in the support C and one of eight holes in the handle are aligned. If necessary, turn the handle to align the two holes.

      Install the lock pin into position to lock the handle.

    21. SUBTASK 72-32-00-430-181 Install the Six Bolts into the Threaded Holes in the No.5 and No.7 Struts

    1. Refer to Figure.

    2. NOTE

      The bolts are tightened to the specified torque value after the installation of the brackets in TASK 71-00-21-400-001 (INSTALLATION).

      Install the six bolts (01-540) through the fan case holes into the six threaded holes in the No.5 and No.7 struts. Tighten the bolts lightly.

    22. Figure: Apply Jointing Compound to the Mating Faces on the Brackets

    Apply Jointing Compound to the Mating Faces on the Brackets

    Figure: Install the Front Fairings on to the Brackets

    Sheet 1

    Legend
    Install the Front Fairings on to the Brackets

    Sheet 1

    Close

    Figure: Install the Front Fairings on to the Brackets

    Sheet 2

    Legend
    Install the Front Fairings on to the Brackets

    Sheet 2

    Close

    Figure: Clean the Surfaces of the Corners F around the Dimpled Washers and Apply Primer

    Clean the Surfaces of the Corners F around the Dimpled Washers and Apply Primer

    Figure: Fill Silicone Compound in to the Corners F and Press it into Position

    Fill Silicone Compound in to the Corners F and Press it into Position

    Figure: Measure the Module Interface Dimensions for the Installation of the HP System Module

    Measure the Module Interface Dimensions for the Installation of the HP System Module

    Figure: Apply Jointing Compound to the Panel Supporting Brackets

    Apply Jointing Compound to the Panel Supporting Brackets

    Figure: Install the No.1 Strut Fairing Panel on the Fan Frame Assembly and the Fan Case

    Install the No.1 Strut Fairing Panel on the Fan Frame Assembly and the Fan Case

    Figure: Pre SBE 72-0175: Install the No.6 Strut Fairing Panel on the Fan Case

    Sheet 1

    Legend
    Pre SBE 72-0175: Install the No.6 Strut Fairing Panel on the Fan Case

    Sheet 1

    Close

    Figure: SBE 72-0175 and SBE 72-0435: Install the No.6 Strut Fairing Panel on the Fan Case

    Sheet 2

    Legend
    SBE 72-0175 and SBE 72-0435: Install the No.6 Strut Fairing Panel on the Fan Case

    Sheet 2

    Close

    Figure: Install the No.6 Strut Fairing Panel on the Fan Frame Assembly

    Install the No.6 Strut Fairing Panel on the Fan Frame Assembly

    Figure: SBE 72-0150: Install the Stopper on the Fan Frame Assembly

    SBE 72-0150: Install the Stopper on the Fan Frame Assembly

    Figure: Apply Silicone Rubber Compound to the Corner Strut Fillers and the Panel Corner Fillers

    Apply Silicone Rubber Compound to the Corner Strut Fillers and the Panel Corner Fillers

    Figure: Install the Panel Corner Fillers and the Corner Strut Fillers on the Fan Frame Assembly

    Sheet 1

    Legend
    Install the Panel Corner Fillers and the Corner Strut Fillers on the Fan Frame Assembly

    Sheet 1

    Close

    Figure: Install the Panel Corner Fillers and the Corner Strut Fillers on the Fan Frame Assembly

    Sheet 2

    Legend
    Install the Panel Corner Fillers and the Corner Strut Fillers on the Fan Frame Assembly

    Sheet 2

    Close

    Figure: Pre SBE 75-0010: Install the Fan Exit Pressure Boss and the Block on the Fan Case

    Sheet 1

    Legend
    Pre SBE 75-0010: Install the Fan Exit Pressure Boss and the Block on the Fan Case

    Sheet 1

    Close

    Figure: SBE 75-0010: Install the Fan Exit Pressure Boss and the Block on the Fan Case

    Sheet 2

    Legend
    SBE 75-0010: Install the Fan Exit Pressure Boss and the Block on the Fan Case

    Sheet 2

    Close

    Figure: Remove the Stopper and Release the Lock Pin to turn the Fan Frame and Fan Case Assembly from Horizontal to Vertical

    Remove the Stopper and Release the Lock Pin to turn the Fan Frame and Fan Case Assembly from Horizontal to Vertical

    Figure: Install the Six Bolts into the Threaded Holes in the No.5 and No.7 Struts

    Install the Six Bolts into the Threaded Holes in the No.5 and No.7 Struts

    Figure: Pre SBE 72-0216: Install the Shields on the No.1 Strut Fairing Panel

    Sheet 1

    Legend
    Pre SBE 72-0216: Install the Shields on the No.1 Strut Fairing Panel

    Sheet 1

    Close

    Figure: SBE 72-0216 and Pre SBE 72-0230: Install the Shields on the No.1 Strut Fairing Panel

    Sheet 2

    Legend
    SBE 72-0216 and Pre SBE 72-0230: Install the Shields on the No.1 Strut Fairing Panel

    Sheet 2

    Close

Requirements After Job Completion

Follow-On Conditions

NONE
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:LOCAL
Enterprise Name:LOCALLY SUPPLIED
Manufacturer Code:LOCAL
Supply Number:CoMat 01-031
Type:sp01
Supply Short Name:CoMat 01-031 ACETONE (CH3)2CO
Supply Name:CoMat 01-031 ACETONE (CH3)2CO
Specification Groups:
Doc NumberType
OMAT: 150 (RR REF)COMMERCIAL GRADE O-A-51
PMC 9008 (PW REF)COMMERCIAL GRADE O-A-51
JCR-041 (JAEC REF)COMMERCIAL GRADE O-A-51
MTH 169 (98%) (MTU REF)COMMERCIAL GRADE O-A-51
Suppliers:
ManufacturerRemarks
LOCAL
K6835
81348
K3504
U1185
24853
70657
Manufacturer Code:LOCAL
Supply Number:CoMat 01-124
Type:sp01
Supply Short Name:CoMat 01-124 ISOPROPYL ALCOHOL
Supply Name:CoMat 01-124 ISOPROPYL ALCOHOL
Specification Groups:
Doc NumberType
OMAT:1/40GPR TECHNICAL GRADE
PMC 9094GPR TECHNICAL GRADE
JCR-011GPR TECHNICAL GRADE
Suppliers:
ManufacturerRemarks
LOCAL
U1185
24853
K6835
Manufacturer Code:LOCAL
Supply Number:CoMat 02-119
Type:sp01
Supply Short Name:CoMat 02-119 LOCKWIRE
Supply Name:CoMat 02-119 LOCKWIRE
Specification Groups:
Doc NumberType
SAE AS9226 Part Number MS-9226-04 (0.032 IN DIA.)
Suppliers:
ManufacturerRemarks
LOCAL
51563
81343
V508V
Manufacturer Code:LOCAL
Supply Number:CoMat 04-004
Type:sp01
Supply Short Name:CoMat 04-004 JOINTING COMPOUND, LIGHT GRADE
Supply Name:CoMat 04-004 JOINTING COMPOUND, LIGHT GRADE
Specification Groups:
Doc NumberType
OMAT: 4/46 (REF RR)HYLOMAR AEROGRADE (PL32), LIGHT GRADE
JCR-025 (JAEC REF)HYLOMAR AEROGRADE (PL32), LIGHT GRADE
MSRR 9055 (RR REF)HYLOMAR AEROGRADE (PL32), LIGHT GRADE
Suppliers:
ManufacturerRemarks
LOCAL
460Y4
CJ731
K3237
Manufacturer Code:X222X
Supply Number:CoMat 08-014
Type:sp01
Supply Short Name:CoMat 08-014 PRIMER, SILICONE ADHESIVE/SEALANT
Supply Name:CoMat 08-014 PRIMER, SILICONE ADHESIVE/SEALANT
Specification Groups:
Doc NumberType
Use the applicable letter suffix material. Refer to SPM TASK 70-36-02-360-501.
Suppliers:
ManufacturerRemarks
X222X
Manufacturer Code:LOCAL
Supply Number:CoMat 08-045
Type:sp01
Supply Short Name:CoMat 08-045 SILICONE RUBBER COMPOUND
Supply Name:CoMat 08-045 SILICONE RUBBER COMPOUND
Specification Groups:
Doc NumberType
RTV-103 (BLACK) JCR-246
RTV-103 (BLACK) JS-3019
Suppliers:
ManufacturerRemarks
LOCAL
U4065
K6835
IE146
IE505
IE521
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 1J12508
Tool Name:IAE 1J12508 Measuring stretch
Manufacturer Code:LOCAL
Tool Number:Sealant dispenser
Tool Name:Sealant dispenser