724108 - TES Engine Datapack (April 10)(1)

ESN724108 PW4060-1C

Lease Data Pack January 2010

Table of Contents

1. Engine Specification Summary

2. LLP Status

3. Key SB & AD Status

4. Shop Visit History & Modular Workscope Summary

5. QEC/Accessory Status

6. Performance/ECM Summary/MPA Run

7. Latest EASA Form 1/FAA 8130-3

8. Borescope Inspection Summary

a) Last BSI Report

b) Last Full Front to Back BSI Report If not covered in (8a)

9. Preservation Details

10. Non Incident / Accident Statement

Lease Engine Data pack ESN 724108

1. Engine Specification Summary

TES EngineSpecification Sheet

Status Date 13-Aug-2009 Thrust 58,000 lbs

Engine Standard Phase I LLP Limit (Fan) 4,191

TSN 65,644 LLP Limiter (Fan) Hub Front Compressor

CSN 10,809 LLP Limit (Core) 4,191

TSO 9257 LLP Limiter (Core) Hub HPC Front Rotor

CSO 1266 RCC Status (Ad 2003-19-15) RCC Compliant

HPT 2 Blades CSN 1,737 (post SB 72-716) Latest EGTM 52 degrees

HPT 2 Blades PN 54L232 Date of last BSI 20-Aug-2009

Available For Sale Lease or Exchange Date Available Immediately

Certification FAA / EASA Form 1 Engine Stand Available Yes

PW4060-1C

ESN 724108

Engine Details

Date 30 Nov 2006

Shop SRT

TSN 56,387

CSN 9,543

Exhaust Sleeve

CHM + RCC

Starter Control Valve AVM

Inlet Cowl

Last SV Details

Workscope Summary

Serviceable with no repeat inspections

High Pressure Pilot Controller TAI Valve

Starter Ducts

Exhaust Centre Body

Pressure Controller

Anti Ice Duct

Current Condition

QEC Configuration

Items not included:

IDG Hydraulic Pump

Starter

TES Aviation Ltd - Lease Engine Specification Page 1 of 2 09/11/2009


2. LLP Status

LLP Parts ESN 724108

TSN 65,644 CSN Date 04-Nov-09

Part Serial 4060 / 4060A / 4060 / 4060A / 4060 / 4060A /

Number Number 4060C Cycles Data 4060C Cycles Limit4060C Cyc Remaining

LPC Module Hub Front Compressor 50B321 R48533 10809 15000 4191

Disk Drum Rotor Stages 1.6-4 50B422 R38203 10809 15000 4191

Disk Stage 1.6 0 0 - - -

Disk Stage 2 Unknown Unknown - - -



LPC/LPT Coupling Turbine Shaft (LPC/LPT) Coupling 50A281 P49488 10809 30000 19191

HPC Module Hub HPC Front Rotor 51H572 N71530 10809 15000 4191

Disk Stage 5 51H005 N71364 10809 15000 4191

Disk Drum Rotor Stages 6-12 52H926-01 R34932 10809 15000 4191

Disk Drum Rotor Stg 13-15 and HPC Drive Shaft 50H936 R31946 10809 15000 4191

Disk Drum Rotor Stages 13-15 - - - - -

10,809

Module Name Part Name

Disk Drum Rotor Stages 13-15 - - - - -

HPC Inlet Airseal 56H279 P49292 10809 15000 4191

Diffuser Airseal 50H218 RY7574 10809 15000 4191

HPT Module Hub Turbine Stage 1 51L201 S80290 10338 15000 4662

Hub Turbine Stage 2 52L002 S59952 10338 15000 4662

HPT Stage 1 Outer Rotating Air Seal 50L485 UD8771 10338 15000 4662

Plate HPT Stage 2 Blade Retaining 50L242 TR4624 10338 15000 4662

HPT Stage 1 Inner Rotating Air Seal 50L659 C331AA0534 9642 15000 5358

HPT Stage 2 Rotating Air Seal 53L030 CKLBD25578 5407 15000 9593

HPT Stage 1 Ring - - - - -

LPT Module LPT Disk Stage 3 50N003 R58379 10809 15000 4191

LPT Disk Stage 4 50N024 R32180 10809 15000 4191

Hub Rear Turbine Stage 5 50N405 R34499 10809 15000 4191

LPT Disk Stage 6 50N486-01 R32107 10809 15000 4191

LPT Stage 3 Outer Air Seal 50N008 RG6182 10809 15000 4191

LPT Stage 3 Inner Air Seal 50N007 RY8003 10809 15000 4191

LPT Stage 4 Air Seal 50N346 TE1080 10809 15000 4191

LPT Stage 5 Air Seal 50N347 UF7427 10809 15000 4191

Front Compressor Drive Turbine (LPT) Shaft 50A077 S76017 9085 30000 20915

TES Aviation Ltd - Lease Engine Specification 04-Nov-2009

PW4000 Limit Set created from Engine Manual Revision 090 Dated 01 Sep 09

TES Aviation Ltd - Lease Engine Specification Page 2 of 2 04-Nov-2009


3. Key SB & AD Status

EASA No. DGAC CN

FAA /CAA AD

Amdt N R

D

TITLE

METHOD OF COMPLIANCE / REMARKS

COMPLIANCE LAST NEXT REMARKS

DATE HRS CYC DATE HRS CYC

PW4000 Master Airworthiness Directive List

ESN: 724108

Date: 09 Feb 2010

MSN / Pos: n/a Engine TSN: 65634 Latest FAA AD issue date: 01/02/10 Engine Type: PW4000 Engine CSN: 10807 Latest EASA AD issue date: 09/02/10 Compilation Date: 09 Feb 2010 Compilation Issue: 2

F-1990- 228-IMP

(B)

90-22-02 39-6783

N

LPT SHAFT INSPECTION.

(ATA 72)

To prevent a LPT Shaft Break, perform an Eddy Current Inspection I.A.W. SB PW4ENG A72-328, before 01-Jan-1991 (For DGAC CN) or 31-Oct-

1990 (For FAA AD).

Inspection performed at manufacture byP&W.

Verified by P&W statement.

Concerns P&W Types 4050,4052,4056,4060,40

60A, 4152, 4156,4158 and 4460

installed on B747, B767, A300 and A310 Series.

Template Issue 16 Page 1 of 13 Template Issue Date: 22/12/2008

EASA No. DGAC CN

FAA /CAA AD

Amdt N R

D

TITLE





ESN: 724108

Date: 09 Feb 2010


-

91-09-15

N

PREVENT FALSE OIL

FILTER BYPASS INDICATION OR

LOSS OF OIL QUANTITY FROM

FAILED PRESSURE SWITCHES

Within 60 days after 28-May-1991 or prior to

accumulating 10,000 total service hours, whichever occurs later, and thereafter at intervals not to exceed 10,000 total service hours replace the engine oil filter differential pressure switches

as follows: -

1 – For Pratt & Whitney Engines: - Replace P/N S332T004-23 with a new -23 Switch

2 – For Pratt & Whitney JT9D-7R4 Engines: -

Replace P/N S332T004-25, -25 or -29 with a new -29 Switch. If a -2 or -25 Switch currently installed, modification in accordance with Boeing SB 767-

79-0008 is required in order to install a -29 switch configuration

Pressure switches removed following the

accumulation of 10,000 total service hours shall not be re-installed on any airplane

N/A by P/N

Concerns Model 767 series airplanes

equipped with engine oil filter differential pressure switched on JT9D-7R4 and PW4000 engines


EASA No. DGAC CN

FAA /CAA AD

Amdt N R

D

TITLE





ESN: 724108

Date: 09 Feb 2010


F-1993- 130-IMP

(B)

93-08-16 39-8564

N

HPC FAILURECAUSED BY

AIRSEAL INTERFERENCE.

(ATA 73)

Apply "Boeing" ASB's 747-73A2055 and 767-

73A0033.

N/A by P/N Concerns P&W Types

4050, 4052, 4056, 4060 and 4060A turbofan

engines only.


EASA No. DGAC CN

FAA /CAA AD

Amdt N R

D

TITLE





ESN: 724108

Date: 09 Feb 2010

MSN / Pos: n/a Engine TSN: 65634 Latest FAA AD issue date: 26/10/09 Engine Type: Engine CSN: 10807 Latest EASA AD issue date: 03/11/09 Compilation Date: 09Feb 2010 Compilation Issue: 2

F-1998- 423-IMP

(B)

98-19-03 39-10746

N

SECOND STAGE HPT ROTATING AIRSEALS P/N's

50L156 or 50L195. (ATA 72)

To prevent Rotating airseal cracking, at the next HSI

(Any time HPT Module is disassembled) and subsequently each HSI, apply ASB PW4ENG 72-

628 R1.

Within 6 Years after 09-Nov-1998, modify Second Stage Ring Segments and Vane Clusters and install modified Rotating Airseals I.A.W. SB PW4ENG 72-

636 and 72-637 constitutes T/A.

Terminating action embodied. SB72-

636 - Nov 1997 - Eng CSN 5402 SB72-637 - Nov 1997 - Eng CSN 5402

Concerns P&W Model 4052,4056,4060,4062,4

152,4156A, 4158,4460,4462,4164 & 4168 turbofan engine, with 2nd stage high

pressure turbine (HPT) rotating airseals, P/N's

50L156 or 50L195 installed, fitted to A300,

A310, A330, B747, B767 & MD11.


EASA No. DGAC CN

FAA /CAA AD

Amdt N R

D

TITLE





ESN: 724108

Date: 09 Feb 2010


F-1999- 030-IMP

(B)

98-23-08 39-10873

N

HIGH PRESSURE COMPRESSOR (HPC) SURGE.

(ATA 72)

Within 1,400 CIS after 12-Jan-1999, or prior to 30- Jun-1999, whichever occurs first, perform the

following modifications:

1. Incorporate Stage 9 through 12 aluminium oxide blade tips and grind HPC blade tips at the rotor assembly I.A.W. P&W SB PW4ENG-72- 484 R3.

th th

2. Modify HPC 8 - 14 stage stators I.A.W. SB PW4ENG-72-486 R1.

3. Modify 1st stage HPT cooling duct (TOBI Duct), install metering plug in N°2 bearing thrust balance vent tube and incorporate 1st stage HPT vanes with increased airflow area I.A.W. SB PW4ENG-72-514 R1.

4. Incorporate HPC 13th - 15th stage zirconium oxide blade tips I.A.W. SB PW4ENG-72-575 R1.

N/A by SB status

SB72-484 – Apr 1995 – Eng CSN 3371 SB72-486 – Apr 1995 – Eng CSN 3371 SB72-514 – Nov 1994 – Eng CSN 3218 SB72-575 – Nov 1997 – Eng CSN 5402

Concerns only P&W Model

4050,4052,4056,4060/A /C,

4062,4152,4156,4156A, 4158,4160,4256,4460,4

462,4650 turbofan engine, not

incorporating at least one of the modifications described in SB's listed in items 1) through 6),

excluding those engines having a (-3) identifier next to the Eng. Model

Number. 1) PW4ENG 72-484 R3,

72-486 R1. 2) PW4ENG 72-484 R3,

72-575 R1,


EASA No. DGAC CN

FAA /CAA AD

Amdt N R

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TITLE





ESN: 724108

Date: 09 Feb 2010


F-2000- 047-IMP

(B)

99-26-09

N

PREVENT POSSIBLE

SEPARATION OF THE ENGINE FROM THE AIRPLANE IN THE EVENT OF A

PRIMARY THRUST LINKAGE FAILURE

Initial and repetitive inspections: For group 1 & 2 airplanes:

1. Within 500 flight hours of 300 flight cycles after24-Jan-2000, whichever occurs later,

accomplish work package 1 (a detailed visual inspection of the forward engine mount to

ensure that the thrust link, evener bar, associated lugs, and attaching hardware are

firmly attached). Thereafter repeat work package 1at the intervals specified in the Alert Service Bulletin until the requirements of the

AD are accomplished. 2. Prior to the accumulation of 16000 total flight

cycles on any engine or within 500 flight hoursof 300 flight cycles after 24-Jan-2000,

whichever occurs later, accomplish work package 2 non-destructive test inspection if the

forward engine mount to ensure the proper condition if the engine thrust link components).

Thereafter repeat work package 2 on that engine at the intervals specified in the ASB.

Replacement and terminating action:

Within 3 years after 24-Jan-2000, accomplish work package 3 (end cap bolt replacement of the forward

engine mount). For group 2 airplanes:

Within 3 years after 24-Jan-2000, accomplish work package 4 (bolt replacement) in accordance with

ASB 767-71A0087.

Terminating action embodied

Boeing SB71A-0087 Nov 1996 - Eng CSN 4670

Concerns Model 767 series airplanes

powered by P&W PW4000 and JT9D

series engines, as listed in Boeing Alert SB 767-

71A0087


EASA No. DGAC CN

FAA /CAA AD

Amdt N R

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TITLE





ESN: 724108

Date: 09 Feb 2010


F-2001- 113-IMP

(B)

2001-05-07 39-12144

N

LPT 4th STAGE AIR

SEAL FAILURE.(ATA 72)

Replace the 4th stage air seal P/N 50N478 with a

serviceable part P/N's 51N038 or 50N478-001 before the following limits (If limit exceeded, replace

prior further flight): 8.000 CSN for PW4052, 4060,4060A, 4156 & 4158 fewer than 8.000

CSN.8.000 CSN for PW4056, 4152,4156A, and 4460 post SB PW4ENG72-657R1 fewer than 8.000CSN.4.500 CSN for PW4056, 4152,4156A, 4460 preSB PW4ENG72-657R1 fewer than 4.500 CSN.8.000

CSN for PW4056, 4152,4156A, and 4460 not identified in Table 3 of AD and fewer than 8.000 CSN. 7.000 CSN for PW4062 & 4462 fewer than

7.000 CSN.

N/A by P/N

Concerns P&W Model 4052,4056,4060,4060A, 4062,4152,4156,4156A, 4158,4164,4168,4168A, 4460 & 4462 turbofan engine fitted to A300, A310, A330, B747, B767 & MD-11, with

LPT 4th Stage air seal P/N's 50N478 or

50N478-001 installed.CN

SUPERSEDES CN 2001-013-IMP R1AD SUPERSEDES AD

2000-25-06.

N

For PW4164, 4168 & 4168A, replace the 4th stage air seal P/N's 50N478 or 50N478-001 with a

serviceable part P/N's 51N038 before the following limits (If limit exceeded, replace prior further flight):4.500 CSN for those fewer or equal to 3.000 CSN, 1.500 CIS after 29-Dec-2000, for those between

3.000 & 4.500 CSN, 6.000 CSN for those between 4.500 & 6.000 CSN.


EASA No. DGAC CN

FAA /CAA AD

Amdt N R

D

TITLE





ESN: 724108

Date: 09 Feb 2010


F-2002- 394-IMP

(B)

2002-12-15 39-12787

N

DETECTION OF PREMATURE

CRACKING OF THE HPC FRONT DRUM

ROTOR(ATA 72)

1-Perform an initial inspection of HPC front rotors IAW on-wing §1 through 13 of PW ASB PW4ENG

A72-722 or Rev. 1): within 500 CIS after accumulating 1,000 CSN, for HPC front drum rotor less than 1,000 CSN on 31-Jul-2002, or within 500 CIS after 31-Jul-2002, for HPC front drum rotor with

1,000 CSN or more.

18th May 2007 Eng CSN 9,543

Concerns P&W Model

4052, 4056, 4060, 4062, 4152, 4156A, 4158, 4460 & 4462 Turbofan engines. SUPERSEDES CN

2001-514-IMP SUPERSEDES AD

2001-20-13.

N2-If the presence of a crack needs to be confirmed,perform an E/C inspection within 5 cycles after item

1.N/A

N

3-If the presence of a crack needs to be confirmed,and the suspect crack indication extends from the knife-edges to the disk radius directly adjacent to

spacer wall of the sixth or seventh stage, perform an E/C inspection before further flight.

N/A

N4-If the presence of a crack is confirmed, remove

and replace the HPC front drum rotor before further flight.

N/A

N

5-Repeat every 2.200 CSLI, inspection of items 1,

and if necessary items 2, 3 or 4.

th 10 April 2008

Eng CSN 10,184

Sooner of:Next piece part

exposure Or

Eng CSN 12,384


EASA No. DGAC CN

FAA /CAA AD

Amdt N R

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TITLE





ESN: 724108

Date: 09 Feb 2010


F- 2003- 382- IMP

2003-19-15

N

PREVENTION OF ENGINE POWER LOSSES DUE TO HPC SURGE.(ATA

72)

Determine the engine configuration as per table 1 of present AD.

Terminating action embodied. SB 72-755 – May 07 – Eng CSN 9543

Concerns P&W Model 4050, 4052, 4056, 4060,

4060A, 4060C, 4062, 4152, 4156, 4156A, 4158, 4160,

4460, 4462 & 4650 Turbofan engines.THIS CN SUPERSEDESCN 2002- 564-IMP (B) R1THIS AD SUPERSEDES AD 2002-

21-10THIS AD SUPERSEDES AD 2003-

11-18

N

Thereafter, determine the applicable limits depending

on the engine configuration. See AD for details.


EASA No. DGAC CN

FAA /CAA AD

Amdt N R

D

TITLE





ESN: 724108

Date: 09 Feb 2010


2005-25-09

N

PW4000 SERIES TURBOFAN

ENGINES TIME LIMITS SECTION

REVISION

Within the next 60 days after the effective date of this AD, revise the Time

Limits Section (TLS) of the Engine Manuals (EMs), Part Numbers 50A443,

50A605, 50A822, 51A342,51A345, and 51A751, as

applicable Air carriers to revise the

approved continuous airworthiness maintenance

program, by adding the applicable parts of

paragraph (f)(1) of this ADunder the heading:

“MANDATORY INSPECTIONS".

LPC Front Hub - Next piece part

This AD supersedes AD 2002-03-08. AD applies to all PW4000-94"/-100"/-112"

engine Models.

HPC5 Disk - Next piece part HPC Front Drum - Next piece part HPC Rear Drum - Next piece part Hub Turb Front 18 May 2007 Next piece part Hub Turb Rear 18 May 2007 Next piece part Airseal HPT2 18 May 2007 Next piece part

LPT3 Disk - Next piece part LPT4 Disk - Next piece part LPT5 Disk - Next piece part

LPT6 Disk 18 May 2007 Next piece part


EASA No. DGAC CN

FAA /CAA AD

Amdt N R

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TITLE





ESN: 724108

Date: 09 Feb 2010


N-2008-

24-13 (B)

2008-24-13

N

ENGINE FUEL AND

CONTROL

Onetime Visual Inspection and Reporting Requirements

(f) Within 600 operating hours after January 8, 2009 (the effective date of this AD):

(1) Perform a one-time visual inspection of the EEC-131 model EECs to identify, categorize, and mark them as a Group 1, Group 2, Group 3, or Group 4

EEC. (2) Use paragraphs 1 through 7 in the

Accomplishment Instructions of SB PW4000- A73-214 R2 to inspect, categorize, and mark the EECs.

(3) Within 30 calendar days of completing paragraph (f)(1) of this AD, report all inspection findings to

Kevin Dickert, Engine Certification Office, Engine & Propeller Directorate, 12 New England Executive

Park, Burlington, MA 01803. (4) The Office of Management and Budget (OMB)

has approved the reporting requirements and assigned OMB control number 2120-0056.

EEC belongs to Group 2

Remove EEC by the

sooner of: 9 July 2011, Or

Eng CSN 15,647 (engCSN 10647 at 21

Dec 2008 – closest preceding data)

Applicable to PW4052,

PW4056, PW4060, PW4062, PW4152,

PW4156A, PW4158, PW4460, and PW4462

turbofan engines


EASA No. DGAC CN

FAA /CAA AD

Amdt N R

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TITLE





ESN: 724108

Date: 09 Feb 2010


N-2008-

24-13 (B) {Cont’d}

2008-24-13 {CONT’D}

N

ENGINE FUEL AND

CONTROL

Replacement of Group 1 EECs (g) Replace Group 1 EECs with a serviceable EEC before reaching 2,000 cycles-in-service (CIS) after

January 8, 2009, but not later than January 8, 2010.

Replacement of Groups 2, 3, and 4 EECs (h) Replace the following groups of EECs with a

serviceable EEC, or any EEC that does not violate the EEC installation procedure as provided by

paragraphs (k), (l), and (m) of this AD, as follows: (1) Group 2 EECs, before reaching 5,000 CIS after

January 8, 2009, but not later than July 8, 2011. (2) Group 3 EECs, before reaching 13,000 CIS after January 8, 2009, but not later than July 8, 2015. (3)There are no scheduled replacement requirements

for Group 4 EECs.


PW4056, PW4060, PW4062, PW4152,

PW4156A, PW4158, PW4460, and PW4462

turbofan engines


EASA No. DGAC CN

FAA /CAA AD

Amdt N R

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TITLE





ESN: 724108

Date: 03 Nov


N-2008-

24-13 (B) {Cont’d}

2008-24-13 {CONT’D}

N

ENGINE FUEL AND

CONTROL

Definition of Serviceable EECs(i) A serviceable EEC is an EEC that does not

violate the EEC installation procedure as provided by paragraphs (k), (l), and (m) of this AD, or a Group

4 EEC. (j) Information on obtaining a serviceable EEC can

be found in SB PW4000- 73-216.

EEC Installation Prohibition (k) Do not install any Group 1 EEC after January 8,2010 or any Group 1 EEC that has accumulated an

additional 2,000 CIS from January 8, 2009. (l) Do not install any Group 2 EEC after July 8, 2011

or any Group 2 EEC that has accumulated an additional 5,000 CIS from January 8, 2009.

(m) Do not install any Group 3 EEC after July 8,

2015 or any Group 3 EEC that has accumulated an additional 13,000 CIS from January 8, 2009.

Previous Credit (n) Inspecting, categorizing, and marking of EECs

before January 8, 2009 performed using the Accomplishment Instructions of SB PW4000- A73-

214 original issue or Revision 1, satisfy the requirements of paragraph

(f)(1) of this AD.


PW4056, PW4060, PW4062, PW4152,

PW4156A, PW4158, PW4460, and PW4462

turbofan engines

END OF STATUS



4. Shop Visit History & Modular

Workscope Summary

Engine model:

Date of Manufacture:

hours

cycles

hours

cyclesPosition/MSN:

At date: 04/10/2009

Installed 12-Jul-1989 28 26 UNK UNKRemoved 3-Aug-1989 306 53 UNK UNK

Operator

Installed 11-Oct-1989 306 53 UNK UNK

Removed 12-Sep-1990 4334 801 UNK UNK

Operator

Installed 4-Feb-1991 4,334 801 UNK UNK

Removed 25-Sep-1993 15,599 2,372 UNK UNK

Operator

Installed 11-Jan-1994 15,599 2,372 UNK UNK

Removed 20-Oct-1994 19,046 3,218 UNK UNK

Operator

Installed 24-Nov-1994 19,046 3,218 UNK UNK

Removed 28-Jan-1995 19,721 3,371 UNK UNK

Stg 5 Blade found

over limit During BSI

6th HPC Blade L/E

Torn (BMOD) Due.

5th Lock found

Broken

M10 - 1 & 1.5 Brg

CD's, GB Deoiler &

TAT

ESN: 724108

PW 4060-1c

10,809

CSN:

TSLSV:

1 LN RCB

1 OY KDH

2

SAS

Engine History Summary Sheet

TAC

Reason for removal/

additional commentsTSN CSN A/C Rag MSNPos

65,644

TSN:

EC FHA

SAS

CSLSV:In storage

2 SE DOA

SPP

222168:00:00

1,266

SAS

Mod - engine update

(Campaign)

1 EC FCU

Overhaul - Timex HPT

Module

Issue 2

Template issue Date:11/02/05 1 of 2

Removed 28-Jan-1995 19,721 3,371 UNK UNK

Operator

Installed 30-Jun-1995 18,721 3,371 UNK UNK


Operator


Removed 7-Aug-1997 29,301 5,402 UNK UNK

Operator



Operator

CD's, GB Deoiler &

HSG DMG

BSI 6th Stg HPC

blade Crack

High EGT, Eng Mods.

Refurbished &

overhauledSPP

SPP

EC FCU

1 EC FCU

2 EC FHA

LPC Low Stab, Found

HPC Rear Case worn

& 11-14 Stator

Damage

SPP

SPP

2 EC FHA

2

Issue 2


Installed 26-Jan-2001 39,092 7,063 UNK UNK

Removed 13-Apr-2002 49,615 8,448 UNK UNK

Operator

Installed 26-May-2002 49,615 8,448 UNK UNK

Removed 30-Jun-2003 53,911 9,001 UNK UNK

Operator

Installed 26-Mar-2005 53,911 9,001 UNK UNK


Operator

Installed 14-Jun-2007 56,387 9,543 UNK UNK

Removed 16-Apr-2009 65,635 10,807 UNK UNK

Operator

Installed TBC 65,635 10,807 101,915 19,390

Removed 19-Aug-2009 65,644 10,809 101,924 19,392

Operator

Convenience owner

Repos Engine

SPP

2 EC FHA

1 LN RCH

Engine History Summary Sheet

ESN: 724108

1 PH MCIConvenience A/C

Parked

MPH

Convenience

SAS

1 PH MCGFerry flight

MPH

1 PH AHXRemoved for Fuel

Pump. No Further info

Available. SV for O/H

& RCC IncorporationHXL

Issue 2

Template issue Date:11/02/05 2 of 2Issue 2


Modules Status ESN 724108

TSN 65,644 CSN Date 04-Aug-09

Last Shop Visit Heavy Maintenance

Workscope Date

LPC Module 65,644 10,809 CHM + RCC 30-Nov-2006 9,257 1,266 19-Apr-2004 11,733 1,808

LPC/LPT Coupling

HPC Module 65,644 10,809 CHM + RCC 30-Nov-2006 9,257 1,266

HPT Module 62,088 10,338 CHM + RCC 30-Nov-2006 9,257 1,266

Cyc since SV Hrs since SV Cyc since SV

10,809

Module Name Total TSN Total CSN SV Date Hrs since SV

LPT Module 65,644 10,809 CHM + RCC 30-Nov-2006 9,257 1,266

Fan Case 65,644 10,809 CHM + RCC 30-Nov-2006 9,257 1,266

Fan Blade Module

Intermediate Case 65,644 10,809 CHM + RCC 30-Nov-2006 9,257 1,266

Diffuser / Combustion 65,644 10,809 CHM + RCC 30-Nov-2006 9,257 1,266

Turbine Nozzles 65,644 10,809 CHM + RCC 30-Nov-2006 9,257 1,266

Turbine Exhaust Case 65,084 11,480 CHM + RCC 30-Nov-2006 9,257 1,266

Angle Gear Box Assy 65,644 10,809 CHM + RCC 30-Nov-2006 9,257 1,266

Main Gear Box Module 65,644 10,809 CHM + RCC 30-Nov-2006 9,257 1,266

TES Aviation Ltd - Lease Engine Specification 04-Nov-2009


5. QEC/Accessory Status

Engine Model: PW4060 At date: 30/10/2009 Compilation Da te: 30 October 2009

MSN / POS: Storage TSN: 65,644 Compilation Issue: 1

ESN: 724108 CSN: 10,809

1

2

3

4

5

6

7

8

9

10

11

12

13

14

15

16

17

18

19

20

21

22

23

24

25

26

27

28

10-621630-110-621630-1

825501-12

8TJ124GGN3

Part Number - P&W

52A193

LPTCC ValveHPTCC Valve

BSV (Burner Staging Valve) - SAC

StarterStarter Air Valve

VBV Position SensorVBV Motor-Gear HydraulicExciter Ignition Unit (Upper)Exciter Ignition Unit (Lower)

T25 Temperature sensorECU

Stator AlternatorIdentification Plug

AGBTGB

Oil / Fuel Heat ExchangerServo Fuel Heater

Fuel Flow TransmitterDownstream Fuel Filter

HMUT12 Temperature Sensor

Serial Number CommentsPart Name

IDG Oil Cooler

N2 Speed SensorOil Tank

Lubrication UnitFuel Pump

Fuel Return ValveN1 Speed Sensor

1308

PW 4158 QEC Accessory Listing

WH4872

4539

9143346290259493




ESN: 724108 CSN: 10,809

Part Number - P&W Serial Number CommentsPart Name

IDG Oil Cooler


29

30

31

32

33

34

35

36

37

38

39

40

41

42

43

44

45

46

47

48

49

50

51

52

53

54

55

56

51A020

802170-10790270-14

801000-3813520-1

788366-204P23-12

42D395

773289-13

Ignition Cable Upper

HPC Flow Control Valve (RH)HPC Flow Control Valve (LH)

TVBC Valve (RH)TVBC Valve (LH)

Switch TVBC (RH)TCC Shut / Off Valve Phase 3 (RH)

Fuel Bypass ValveVibration Pickup BRG 1

Stator Vane ActuatorFuel Distribution Valve

SOL. 2.9 Bleed Valve (5h)Tachometer N1

QAD AdapterIDG

Nozzle AssemblyCenterbody Assembly

Fuel Differential Pressure SwitchFuel Metering Unit

Nacelle cooling and Air Transient Bleed Bleed Pressure Regulator Valve

IP Check ValveHP Regulator Valve

Hydraulic PumpNose Cowl Anti-Ice Valve

Fuel Manifold Modulating Valve - DACRACC Valve

Air Transient Valve

890915

F18940CSGCB17097

F8072

F18266

881224

1620

A95060051




ESN: 724108 CSN: 10,809


IDG Oil Cooler


57

58

59

60

61

62

63

64

65

66

67

68

69

70

71

72

73

74

75

76

77

78

79

80

81

82

83

84

IDG Air/Oil Overdide Con Switch798850-2

47111-12043830032-105

15622-000788399-5

350880-6430070-1

1502564-0045830201-1111605140-001

791100-6-108

SOL. TVBCA & Heat Air (10h)Pneumatic Relay Valve (5h)

Thermocouple T3.5High Stage Sensor (11h)

Eng. Air/Oil Heat Exchanger (LH)Eng. Air/Oil Heat Exchanger ValveIDG Air/Oil Heat Exchanger (RH)IDG Air/Oil Heat Exchanger Valve

Oil Cooler Bypass ValveFuel/Oil Cooler

Main Oil PumpEEC Generator

2.9 Bleed Valve (RH)2.9 Thermocouple

2.9 Bleed Valve (LH)2.9 Thermocouple

SCUActuator TCC

Cable Actuator TCCActuator 2.5 Bleed ValveSol. IDG A/O Cooling (1h)

Pressure Switch (1h)

Ignition Cable LowerInlet Cone Assy

Cover to Inlet Cone AssyEEC

EEC Programming PlugESF00178

0770A

C905042131

371

MX-275053300

2641F12665

F18220

187TR8099

11968-000




ESN: 724108 CSN: 10,809


IDG Oil Cooler


85

86

87

88

89

90

91

92

93

94

95

96

97

98

99

100

101

102

103

104

105

106

107

108

109

110

111

112

77-109-13

T/R Pneumatic Drive UnitT/R Shut/Off Regulator Valve

Core Compartment Temp BulbBarometric Switch

Vibration Pickup (FC)T/R Splitter Gearbox

T/R Flex ShaftT/R Selector Valve

Oil Low Pressure SwitchOil Differential Pressure Switch

Oil Temp SensorScavenge Oil Temp. ProbeFuel Pressure Transmitter

T/R Ground Valve

Pneumatic Regulating ValveHigh Stage Control ValveCheck Valve 8. STG (LH)Check Valve 8. STG (RH)Oil Quantity TransmitterOil Pressure Transmitter

BRG. 3 Breather ValveHydraulic Pump FWDHydraulic Pump AFTHydraulic Filter FrontHydraulic Filter RearStarter Control Valve

EEC Fuel Temp. ProbeECC Oil Temp. Probe

137



6. Performance/ECM Summary/MPA

Run


7. Latest EASA Form 1/FAA 8130-3


8. Borescope Inspection Summary a) Last BSI Report

b) Last Full Front to Back BSI Report If not covered in (a)


8a) Last BSI Report


8b) Not Applicable


9. Preservation Details

steve.lyons


10. Non Incident / Accident Statement

Date post:	23-Nov-2014
Category:	Documents
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724108 - TES Engine Datapack (April 10)(1)

Documents