DMC:V2500-A5-72-00-0000-04A-664A-B|Issue No:001|Issue Date:2021-08-01

Export Control

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

Copyright

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

Applicability

All

Common Information

TASK 72-00-00-300-015 HPT Hubs Inspection - Project Visit Maintenance, Repair-015 (VRS3863)

General

This EA provides workscope requirements for conducting High Pressure Turbine (HPT) Hub inspections, removal, and installation at a shop to implement V2500 Service Bulletin 72-0713. These requirements are in addition to, or instead of, those provided in disassembly and re-assembly procedure in the Engine Manual (EM).

This maintenance action is considered a Project Visit and does not zero time any hardware relative to maintenance requirements - including BSI inspection, and no Maintenance Planning Document (MPD) tasks are necessary. Any scheduled or planned maintenance activity must be done by the operator’s approved Aircraft Maintenance Program (AMP).

This EA mandates the use of a Visual Check as defined in the Standard Practices Manual, for continued serviceability assessment for all parts, subassemblies and modules that are removed or exposed solely to gain access to the HPT module and HPT hubs. The minimum inspection requirement to return a part, subassembly or module to service is to do a Visual Check to detect obvious damage, failure, or irregularity outside of normal in-service wear to make sure that the item is approved for continued in-service use. A Visual Check is made without magnification and does not require dimensional measurements. Please refer to Standard Practices Manual TASK 70-20-00-200-501 Inspection - General Information.

NOTE

The Follow-On Condition SI 43F-21 uses aircraft display with Flight Warning Computer (FWC) standard H2F8 or later.

If during Project Visit there is a finding that needs additional actions, contact CTS for further instructions.

Preliminary Requirements

Pre-Conditions

Action/Condition	Data Module/Technical Publication
For the engine selection process, the pre-requisites listed below are for internal use by International Aero Engines (IAE), AG to define candidate engines for this procedure:
1. Engine must not have had any major event on wing.
2. Service Bulletin 72-0642 - Engine - High Pressure (HP) Compressor - Stage 3 to 8 Compressor Drum - Introduction of Damper Wires for Stages 6 to 8.
3. Service Bulletin 72-0673 - NMSB - Replacement of No. 3 Bearings from Suspect Population (LOT A).
Pre-Conditions (checklist):
The preconditions listed below are for internal use by IAE-AG to define candidate engines for this procedure:
1. Engine must be serviceable when removed or can be returned to serviceability through implementation of this EA or any other AMM task.
2. The engine must be preserved by the six month requirement in AMM TASK 71-00-00-550-010-A.
3. The engine must have more than 30% of hot section interval remaining.
4. The engine must have more than 20% LLP life remaining.
5. The engine must obey to the N1 and N2 vibration conditions below:
- N1 vibration, monitored at cruise conditions before 30 days of operation, is no higher than 1.5 aircraft units and has no upward step more than 1.0 aircraft unit.
- N2 vibration data, monitored at cruise conditions before 30 days of operation, is no higher than 1.2 aircraft units.
6. The engine must have an EGT margin at takeoff conditions (realistic worst case EGT margin) more than the limit of 20°C (68°F).
7. The engine must have Diffuser M-Flange with less than 19,000 cycles since new.
Preservation Notes:
A. The effective date of preservation will be the date the operator preserved the engine. If the six month preservation period will expire during the shop visit/shipment of the engine back to the customer, IAE will authorize a period of 15 days upon receipt of the engine by the customer to re-preserve or return the engine to service by applicable AMM procedures.
B. If work scope expands more than typical quick turn procedure, please contact CTS for Engine Preservation requirements.

Support Equipment

NONE

Consumables, Materials and Expendables

NONE

Spares

NONE

Safety Requirements

NONE

Procedure

The proprietary nature of this repair requires that any facility not authorized to accomplish this repair must contact IAE Repair Development Group to determine if a qualification program can be initiated at their facility.
IAE International Aero Engines AG
400 Main Street
Mail Stop 121-10
East Hartford CT 06118
USA
Email: gpiaerepaircouncil@iaev2500.com
ATTN: IAE Repair Council
1. 1. Do a Visual Check TASK 70-20-00-200-501 Step (3) (b) of the engine assembly for foreign objects, damage, and correct assembly. Photograph front, rear, left side, right side, top, and bottom of the engine to record the full inspection. Contact CTS with any damage that is considered to be abnormal.
  2. NOTE
    Borescope of the engine gas path is not necessary. Engine was removed serviceable or could be made serviceable by incorporation of the SB’s listed in this procedure. Any scheduled or planned maintenance activity will occur as planned before.
    Disassemble to remove LPT/TEC and HPT modules to expose the HPT hubs:
    Do a Visual Check of the Fan Inlet Cone, Inlet Cone Fairing, and Fan Front Retaining Ring for obvious damage.
    Examine the TEC No. 4 weep tube exit location in the TEC.
    Before you do LPT/TEC removal, carry out No. 5 Compartment Vacuum check and record results, refer to TASK 72-00-50-420-001-C00.
    Before you do LPT/TEC removal, correlate the position of the LPT Shaft relative to the LPC Drive Shaft. Identify shaft positions with suitable marker.
    Remove the LPT/TEC Module from the Engine by TASK 72-00-50-020-002.
  3. NOTE
    It is permitted to leave the fan rotor assembly installed in the fan case after removal of LPT/TEC.
    After LPT/TEC module removal, do not do EM inspections of exposed interfaces of LPT and TEC. Do instead:
    A Visual Check of the LPT/TEC module by TASK 70-20-00-200-501 Step (3) (b).
    Photograph any findings considered to be unusual wear or damage and give to CTS.
    No further action is necessary.
  4. Remove HPT module by TASK 72-00-45-020-001-B01 or TASK 72-00-45-020-001-B02.
  5. Examine the HPT module by Project Visit Maintenance TASK 72-00-45-200-003.
  6. Disassemble HPT module by Project Visit maintenance TASK 72-00-45-200-004. Route HPT hubs to approved source for inspection by SB 72-0713.
  7. After you remove HPT module, do not do engine manual inspections for the interfaces of the HPC rear shaft, diffuser, and stage 1 nozzle assemble that you can see but do the procedure that follows:
    Do a Visual Check by SPM TASK 70-20-00-200-501 of the interfaces and hardware that follows:
    Rear of stage 1 Nozzle group.
    Rear of No. 4 Bearing Compartment.
    Section of HPC rear shaft that you can see.
    Photograph any findings considered to be unusual wear or damage and give to CTS.
2. 1. Install again the HPT module (TASK 72-00-45-420-000 HPT Assembly - Install The HPT Assembly, Installation-000):
    Fits need not be measured, if you install again the same HPT module that was orginal to the engine.
    Location #2225 is not necessary for this Project Visit only.
    Location #2246 is not necessary for this Project Visit if the HPC Rear Shaft is used again.
  2. Install again the LPT/TEC module (TASK 72-00-50-420-000 LPT Module - Install The LPT Module, Installation-000):
    Fits need not be measured, if you install again the same LPT/TEC module that was original to the engine and the HPT hardware at LPT interface locations 5623 and 5624 is original to the engine.
    Install the LPT shaft, use the correlation marks with LPC stub shaft that were applied before you remove LPT/TEC module. The adjustment ring for the axial setting of the LPT module stays the same only if the identical hardware will be assembled again.
  3. Complete the installation procedure again for the external hardware removed to enable HPT disassembly.

Requirements After Job Completion

Follow-On Conditions

Action/Condition	Data Module/Technical Publication
NOTE: The Follow-On Condition SI 43F-21 requires aircraft display with Flight Warning Computer (FWC) standard H2F8 or later.
1. Preservation: The effective date of preservation will be the date the operator preserved the engine. If the 6-month preservation period will expire during the shop visit/shipment of the engine back to the customer, IAE will authorize a period of 15 days upon receipt of the engine by the customer to re-preserve or return the engine to service by applicable AMM procedures.
2. Install again the engine on the aircraft and carry out Special Instruction 43F-21 to return the engine to service. This SI requires engine testing by AMM Chapter 71 including monitoring of the No. 4 Bearing Compartment Scavenge Pressure (parameter PSB) during the Vibration Survey.