mini pack - willis lease - mini pack... · pw124b/pw127/pw127e ... at the fuel nozzle tip and on...

MINI PACK

ENGINE Model: PW127M

BUILD SPEC. 1237

ESN: 127077

TSN: 34,083.80

CSN: 34,597

TSO: 3,985.40

CSO: 4,457

TSHSI: 3,985.40

CSHSI: 4,457

RGB SN. 127077

TSN: 34,083.80

CSN: 34,597

TSO: 3,985.40

CSO: 4,457

CONTENTS:

127077 –Dual Release Form One

LLP

HP Blade Listing

Accessory Inventory

AD Status

BSI

Part Certs

Kranenberg 2 5047 TR Tilburg

PO Box 4197 5004 JD Tilburg

The Netherlands Phone: +31-(0)13 572 8572

Fax: +31-(0)13 572 8500 www.standardaero.com

PW100 Borescope Inspection Report

Task Control Number: WT338208 Shop Order: Q46YF Purchase Order: 753825

Borescope Inspection

Of

Complete Engine

PCE 127077 PW127M (BS1237) RGB 127077

Prepared for: StandardAero Limited

Attn: Mrs. Lisa Munoz

Prepared by:

Almer Schoutens Field Service Representative

Reviewed by:

Corstiaan van Alphen Customer Service Representative Date: 17 February 2016

CONTENT IS CONFIDENTIAL AND PROPRIETARY TO STANDARD AERO. INFORMATION SHALL NOT BE DISCLOSED TO THIRD PARTIES WITHOUT THE WRITTEN CONSENT OF STANDARD AERO.

Document Identifier : SABV TPAF F 7.5.2-1-3 Page 2 of 15 Revision level : 4.0 Owner approval: Hans van Uden Issue date : 09-Jul-2015 Quality approval: Sander Coomans

Borescope Inspection Report WT338208

StandardAero Limited PCE 127077 / RGB 127077

Distribution List

Name Company

Mrs. Lisa Munoz StandardAero Limited

Mr. Corstiaan van Alphen StandardAero B.V. Customer Service Representative

Mr. Almer Schoutens StandardAero B.V. Field Service Representative

Table of Contents

1. Introduction

2. Engine History

3. Borescope Inspection Findings

3.1 Turbomachinery Module

3.2 Reduction Gearbox Module

3.3 Accessory Gearbox

4. Conclusion

5. Pictures





1. Introduction

The Borescope Inspection was carried out in accordance with the:

PW124B/PW127/PW127E/PW127F/PW127M/PW127N Maintenance Manual

P/N: 3037332, Rev. 51.1, OCT 07/2015

ATA 72-00-00 ENGINE-INSPECTION/CHECK-1, Paragraph 9.

The results of this Borescope Inspection and subsequent performed actions are described in this report. Borescope Inspection performed at the facility of StandardAero B.V. European Service Center, Tilburg, The Netherlands commissioned by StandardAero Limited (Purchase Order No. : 753825) on 16 February 2016.

2. Engine History

Turbomachinery s/n: PCE 127077 Reduction Gearbox s/n: RGB 127077

TSN: 34083.8 TSN: 34083.8

CSN: 34597 CSN: 34597

TSO: 3985.4 TSO: 3985.4

CSO: 4457 CSO: 4457

TSHSI: N/A

CSHSI: N/A

Aircraft Registration: Removed from XY-AIS (MSN 626)

Engine Position: RH (No. 2 Engine)





3. Borescope Inspection Findings

3.1 Turbomachinery Module

Low Pressure Impeller:

Found 2 nicks on Area Cb of the Low Pressure Impeller with a length of more than 0.060" (see picture 1 and 2). Blend repair nicks more than 0.030" (0.76 mm) deep and 0.060" (1.52 mm) long, to a maximum depth 0.250" (6.35 mm). Observed several smaller nicks are also found on Area Cb which are within serviceable limits.

Note: Serviceable and blend repaired nicks or dents must be monitored, by visual inspection or with a borescope for the presence of or beginning of a crack (Ref. 05-20-00, SCHEDULED INSPECTIONS/MAINTENANCE INTERVALS). Cracks are not acceptable.

High Pressure Impeller:

No findings and/or observations.

Intercompressor Case Air Plenum:

Observed oil wetness at the bottom of the Intercompressor Case Air Plenum (see picture 3). Because there is no oil accumulation this is a serviceable condition, no further action required.

Combustion Chamber Outer Liner:


Combustion Chamber Inner Liner:

Observed cracks, coating loss and missing material at the cooling ring of the Combustion Chamber Inner Liner (see picture 4). Cooling rings eroded and/or cracked and/or having material missing due to metal break away are acceptable. Plasma top coating (ceramic) loss on inner and outer liner assemblies is acceptable. The engine may continue in service with subsequent inspections carried out as defined in the regular maintenance program.

Note: Cooling rings having material missing may change air flow which could accelerate combustion chamber deterioration.

Note: Carbon formation (black soot) at the fuel nozzle tip and on the combustion chamber liners may appear and disappear depending of the engine operating condition and fuel quality and does not affect the engine serviceability.

Small Exit Duct:

Observed coating loss on several areas of the Small Exit Duct (see picture 5). Plasma top coating (ceramic) loss is acceptable. The engine may continue in service with subsequent inspections carried out as defined in the regular maintenance program.

HP Turbine Vane Ring Segments:

Found 1 HP Turbine Vane Ring Segments with material missing at the leading edge (1 segment with 2 damaged airfoils), exposing the inside of the vane (see picture 6 and 7). This damage is categorized as Category 4 damage (Non-repairable damage requiring more frequent monitoring. Serviceable condition with subsequent borescope inspection interval: 400 hours Max.).

Found 1 HP Turbine Vane Ring Segment with material missing at the leading edge, not exposing the inside of the vane (see picture 8). This damage is categorized as Category 3 damage (Minor





non-repairable damage. Serviceable condition with subsequent borescope inspection interval: For engine on ECTM: 1500 hours, for engine not on ECTM: 1000 hours Max.

Found 1 HP Turbine Vane Ring Segment with material missing at the trailing edge of the outer platform (see picture 9). This damage is categorized as Category 3 damage (Minor non-repairable damage. Serviceable condition with subsequent borescope inspection interval: For engine on ECTM: 1500 hours, for engine not on ECTM: 1000 hours Max.

Observed several other Vane Ring Segments with hairline cracks on the trailing edge (see picture 10 for an example). This damage is categorized as Category 2 damage (Minor repairable damage. Serviceable condition with subsequent borescope inspection interval: For engine on ECTM: 1500 hours, for engine not on ECTM: 1000 hours Max.

Note: Visual access is limited, therefore segments cannot be completely inspected.

HP Turbine Blades:

Observed minor coating loss on the leading edges of the HP Turbine Blades (see picture 11). Coating loss is covering less than 40% of the leading edge surface, acceptable condition.

HP Turbine Shroud Segments:

Observed minor rubbing marks and/or discoloration on several HP Turbine Shroud Segments (see picture 12). Inspection shows silver-grey heat discoloration, with no axial cracks. 21 Shroud Segment Configuration: No additional maintenance action required.

LP Turbine Stator:

Found at least 1 vane of the LP Turbine Stator partially burnt through (see picture 13). If one or more vane is partially burnt through, a borescope inspection interval of 500 FH is recommended.

Observed several other vanes with hairline cracks (< 0.500" length) at the leading edges (see picture 14). Airfoil leading edge with multiple hairline, non-converging hairline cracks less than 0.500" (12.700 mm) long are acceptable.

LP Turbine Blades:


LP Turbine Shroud Segments:

Found most of the LP Turbine Shroud Segments burnt (LP Turbine Blades have not rubbed) (see picture 15). Cracking, burning and curling is acceptable provided no rubbing occurs with the LPT blade and the curled shroud. Subsequent inspections must be carried out at intervals not more than 600 flight hours.

First and Second Stage Power Turbine Stator:


First and Second Stage Power Turbine Blades:






No. 6 and 7 Bearing Vent Transfer Tube:

Observed carbon deposit covering almost 25% of the tube cross section of the No. 6 and 7 Bearing Vent Transfer Tube (see picture 16). A carbon deposit covering a maximum of approximately 25% of the tube cross section is acceptable but it is recommended to clean the Transfer Tube now the engine is in an engine shop.

Turbomachinery Module Chip Detector:

Not inspected.

3.2 Reduction Gearbox Module

RGB First-stage Gears (Helical and Input Shaft Gears):


RGB Second-stage Gears (Bull Gear and Layshaft Pinions):


Reduction Gearbox Module Chip Detector:

Not inspected.

3.3 Accessory Gearbox

Fuel Pump and Oil Pump Drive Bevel Gears:


Starter-generator Drive Gear:


Accessory Drive Bevel Gears (Towershaft):






4. Conclusion

The engine may continue in service with subsequent inspections carried out as defined in the regular maintenance program provided that the following parts/assemblies are inspected with specific subsequent intervals:

- Low Pressure Impeller: 2 nicks on area Cb which have to be blend repaired;

- HP Turbine Vane Ring Segments: 1 Vane Segment with Category 4 damage, BSI interval of 400 hours max. 2 Vane Segments with Category 3 damage, BSI interval of 1500 hours (engine on ECTM) or 1000 hours (engine not on ECTM). Several segments with Category 2 damage BSI interval of 1500 hours (engine on ECTM) or 1000 hours (engine not on ECTM).

- LP Turbine Stator: 1 vane partially burnt through, BSI interval of 500 hours max.

- LP Turbine Shroud Segments: Burnt, BSI interval of 600 hours max.

- No. 6 and 7 Bearing Vent Transfer Tube: Carbon deposit covering almost 25% of tube cross section, recommended to clean.





5. Pictures

Picture 1:

Low Pressure Impeller: Nick >0.060” in length, must be blend repaired.

Picture 2:

Low Pressure Impeller: Nick >0.060” in length, must be blend repaired.





Picture 3:

Intercompressor Case Air Plenum: Oil wetness at bottom, serviceable condition.

Picture 4:

Combustion Chamber Inner Liner: Cracks, coating loss and missing material at

cooling ring, acceptable condition.





Picture 5:

Small Exit Duct: Plasma top coating loss, acceptable condition.

Picture 6:

HP Turbine Vane Ring Segment: Category 4 damage, BSI interval 400 hours.





Picture 7:

HP Turbine Vane Ring Segment: Category 4 damage, BSI interval 400 hours.

Picture 8:

HP Turbine Vane Ring Segment: Category 3 damage, BSI interval 1500 hours

(engine on ECTM) or 1000 hours (engine not on ECTM).





Picture 9:



Picture 10:







Picture 11:

HP Turbine Blades: Coating loss leading edge (<40%), acceptable condition.

Picture 12:

HP Turbine Shroud Segment: Rubbing marks / discoloration, acceptable

condition.





Picture 13:

LP Turbine Stator: Vane partially burnt through, BSI interval 500 hours

recommended.

Picture 14:

LP Turbine Stator: Hairline cracks at leading edge, acceptable condition.





Picture 15:

LP Turbine Shroud Segments: Burning on segments, BSI interval not more than

600 flight hours.

Picture 16:

No. 6 and 7 Bearing Vent Transfer Tube: Carbon deposit covering almost 25% of

tube cross section, recommended to clean.

mini pack - willis lease - mini pack... · pw124b/pw127/pw127e ... at the fuel nozzle tip and on...

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