Engine Model: PW ESN: Time Since New: 84,463. Cycles Since New: 13,974

Transcription

1 Engine Mini Pack Engine Model: PW ESN: Time Since New: 84,463 Cycles Since New: 13,974 Time Since Last Shop Visit: 9,015 Cycles Since Last Shop Visit: 1,793 Last Shop Visit: Eagle Services May 2011 LLP Limiter: 1,793 Location: UK Available Immediately A J Walter Leasing Limited, Exchange House, Athol Street, Douglas, IM1 1JD, Isle of Man, T: E: alun.roberts@ajw-leasing.com W:

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4 LIFE LIMITED PARTS REPORT ENGINE SERIAL NUMBER MODEL TSN PW CSN TSLSV CSLSV STATUS DATE Dec-16 TOTAL PER CATEGORY LIFE LIMIT REMAINING LIFE DESCRIPTION P/N S/N TSN CSN (CYCLES) (CYCLES) (CYCLES) / 4156 / 4052 / 4460 / / 4156 / 4052 / 4460 / / 4156 / 4052 / 4460 / HUB FRONT COMPRESSOR 50B321 CBDUAN DISK DRUM ROTOR B422 CBDUAN TURBINE SHAFT (LPC-LPT COUPLING) 50A281 P HUB HPC FRONT 51H572 CENCA HPC DISK STAGE 5 56H605 CENCA HPC DISK DRUM ROTOR H CENCAW HPC DISK DRUM ROTOR H CENCBA HPC DRIVE SHAFT 54H767 CENCBG HPC AIRSEAL, DIFFUSER 54H792 CENCA HUB TURBINE FRONT (STAGE 1) 52L301 CKLBFJ HUB TURBINE INTER. REAR (STAGE 2) 52L802 CKLBFD AIRSEAL HPT STAGE 1 (OUTER) 50L879 CKLBE RING HPT STAGE 1 50L664 CKLBFM PLATE HPT STAGE 2 BLADE RETAINING 50L242 CKLBES AIRSEAL HPT STAGE 2 53L030 CKLBFA DISK. LPT STAGE 3 50N003 R DISK. LPT STAGE 4 50N024 P HUB REAR TURBINE STAGE 5 50N405 P DISK. LPT STAGE 6 50N CLDLA AIRSEAL LPT STAGE 3 (OUTER} 50N008 RG AIRSEAL LPT STAGE 3 (INNER} 50N007 RY AIRSEAL LPT STAGE 4 50N009 RG AIRSEAL LPT STAGE 5 50N347 S FRONT COMP. ORNE TURB. (LPT) SHAFT 50A077 P PREPARED BY Cesar Boggian DATE 04-Jan-17 SIGNATURE

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9 Borescope Inspection Report Ref: RB0881_P724307CN_21OCT2016_MART_R1 R1: Hours and cycles added; details for T2 inspection added Engine Type : PW4056 Engine Serial No.: P724307CN Customer: APMS Aviation Ltd Hangar K4, Cotswold Airport, Cirencester, Gloucestershire, GL7 6BA United Kingdom EASA 145 UK FAR 145 Foreign Repair Station O6RY005B (PW in : Iss 2 OCT/14)

10 Ref: RB0881_P724307CN_21OCT2016_MART_R1 Section 1 General Information Section 2 Nose Cone Fan Blades Fan Track OGV s Contents Section 3 LP Compressor Blades C1.6 & C4 Section 4 HP Compressor Blades C5 to C15 Section 5 Combustor HP Nozzle Guide Vanes HP Turbine Blades T1 & &2 Section 6 LP Turbine Nozzle Guide Vanes T3 LP Turbine Blades T3 & T6 Section 7 General Comments & Recommendations The complete video borescope findings are recorded on the DVD which is included with this report. APMS Aviation Ltd Hangar K4, Cotswold Airport, Cirencester, Gloucestershire, GL7 6BA United Kingdom 2

11 Ref: RB0881_P724307CN_21OCT2016_MART_R1 Section 1 General Information Engine Type: PW4000 Aircraft: B Reg/MSN/Position: PH-MPP / unknown / #2 Engine S/N P724307CN Mark / Rating PW TSN TSLSV 9015 CSN CSLSV 1793 Inspection Details: Location : TERUEL (TARMAC) Spain Date : 21-OCT-2016 Reason For Inspection : Pre Sale Borescope Technical Data Used: Boeing B AMM Rev 87 Dated Jul 15, 2016 Borescope Inspection Procedures Contained in ATA Section(s): APMS Aviation Ltd Hangar K4, Cotswold Airport, Cirencester, Gloucestershire, GL7 6BA United Kingdom 3

12 Ref: RB0881_P724307CN_21OCT2016_MART_R1 Section 2 Fan Section Nose cone Fan blades Fan track OGV s *These items are subject only to a general visual inspection only. Inspection Findings: Nose Cone: Minor erosion and minor impacts noted. All satisfactory to AMM limits without reduced inspection interval. Continue-In-Service Limits 1) The FOD visual limits of the external cone surface are given as follows: a) The damage that follows is permitted if it does not cause crazing with the primary path to the inner surface of the cone: <1> Small paint particles <2> Dents <3> Scratches <4> Chipping Fan Blades (38ea): Minor erosion noted. All satisfactory to AMM limits without reduced inspection interval. Fan Track: No defects noted. APMS Aviation Ltd Hangar K4, Cotswold Airport, Cirencester, Gloucestershire, GL7 6BA United Kingdom 4

13 Ref: RB0881_P724307CN_21OCT2016_MART_R1 OGV s: Minor erosion noted. All satisfactory to AMM limits without reduced inspection interval. General Comments Fan: No significant defects noted on module. APMS Aviation Ltd Hangar K4, Cotswold Airport, Cirencester, Gloucestershire, GL7 6BA United Kingdom 5

14 Ref: RB0881_P724307CN_21OCT2016_MART_R1 Section 3 LP Compressor Blades C1.6 & C4 Blades Inspection Findings: C1.6 Blades (94ea): 1 blade has a nick on the L/E (lower half) which requires a blend repair. All other blades are acceptable to AMM limits. 1 blade has a nick/dent in the lower half on the L/E (Area E) AMM Limit SUBTASK N00: Rounded damage at the leading and trailing edges, which you can see on the opposite surface of the blade, are permitted as follows: 1) The damage is on the outer half of the blade. 2) The dent is not more than inch (0.254 mm) in depth. Depth of 0,54 mm is within blend limit (0,813 mm): APMS Aviation Ltd Hangar K4, Cotswold Airport, Cirencester, Gloucestershire, GL7 6BA United Kingdom 6

15 Ref: RB0881_P724307CN_21OCT2016_MART_R1 C4 Blades (66ea): Minor erosion noted. All satisfactory to AMM limits without reduced inspection interval. Pictures added to show the general condition of the blades. General Observations Booster Compressor: 1 LPC 1.6 blade requires a blend repair. APMS Aviation Ltd Hangar K4, Cotswold Airport, Cirencester, Gloucestershire, GL7 6BA United Kingdom 7

16 Ref: RB0881_P724307CN_21OCT2016_MART_R1 Section 4 HP Compressor Blades. C5 C15 Blades. Inspection Findings: C5 Blades (40ea): Minor erosion and minor impacts noted. All satisfactory to AMM limits without reduced inspection interval. 1 blade has a noticeable impact on the L/E (Area C). Nick depth: 0,41 mm (Area C) AMM Limit - Table 609/ N00: Multiple damage on the same blade edge that is not more than inch (0.794 mm) in depth is permitted. There is no separation requirement for damage on the same edge. Measurement APMS Aviation Ltd Hangar K4, Cotswold Airport, Cirencester, Gloucestershire, GL7 6BA United Kingdom 8

17 Ref: RB0881_P724307CN_21OCT2016_MART_R1 C6 Blades (51ea): Minor erosion and minor impacts noted. All satisfactory to AMM limits without reduced inspection interval. 1 blade has a noticeable impact on the L/E (Area E). Nick depth: 0,2 mm AMM Limit - Table 609/ N00: Multiple damage on the same blade edge that is not more than inch (0.397 mm) deep is permitted. There is no separation requirement for damage on the same edge. Measurement C7 Blades (56ea): Minor erosion and minor impacts noted. All satisfactory to AMM limits without reduced inspection interval. Pictures added to show the general condition of the blades. APMS Aviation Ltd Hangar K4, Cotswold Airport, Cirencester, Gloucestershire, GL7 6BA United Kingdom 9

18 Ref: RB0881_P724307CN_21OCT2016_MART_R1 C8 Blades (53ea): Minor erosion noted. All satisfactory to AMM limits without reduced inspection interval. Pictures added to show the general condition of the blades. C9 Blades (66ea): Minor erosion and minor impacts noted. All satisfactory to AMM limits without reduced inspection interval. Pictures added to show the general condition of the blades. C10 Blades (62ea): Minor erosion and minor impacts noted. All satisfactory to AMM limits without reduced inspection interval. Pictures added to show the general condition of the blades. APMS Aviation Ltd Hangar K4, Cotswold Airport, Cirencester, Gloucestershire, GL7 6BA United Kingdom 10

19 Ref: RB0881_P724307CN_21OCT2016_MART_R1 C11 Blades (68ea): Minor erosion and minor impacts noted. All satisfactory to AMM limits without reduced inspection interval. 4 blades have noticeable impacts on the L/E. Deepest impact measured: Nick depth 0,13 mm well within AMM limits AMM Limit - Table 609/ N00: Worst case area E: Stage 9 through 15 Multiple damage on the same blade edge that is not more than inch (0.794 mm) in depth is permitted. APMS Aviation Ltd Hangar K4, Cotswold Airport, Cirencester, Gloucestershire, GL7 6BA United Kingdom 11

20 Ref: RB0881_P724307CN_21OCT2016_MART_R1 C12 Blades (72ea): No defects noted. Pictures added to show the general condition of the blades. C13 Blades (78ea): Minor erosion and minor impacts noted. All satisfactory to AMM limits without reduced inspection interval. Pictures added to show the general condition of the blades. C14 Blades (76ea): Minor erosion and minor impacts noted. All satisfactory to AMM limits without reduced inspection interval. Pictures added to show the general condition of the blades. APMS Aviation Ltd Hangar K4, Cotswold Airport, Cirencester, Gloucestershire, GL7 6BA United Kingdom 12

21 Ref: RB0881_P724307CN_21OCT2016_MART_R1 C15 Blades (70ea): Minor erosion and minor impacts noted. All satisfactory to AMM limits without reduced inspection interval. Pictures added to show the general condition of the blades. General Observations HP Compressor: No significant defects noted on module. Note: All compressor stages show white crystals (salt or deposits) on the blades. APMS Aviation Ltd Hangar K4, Cotswold Airport, Cirencester, Gloucestershire, GL7 6BA United Kingdom 13

22 Ref: RB0881_P724307CN_21OCT2016_MART_R1 Section 5 Combustion & HP Turbine Combustor HP Nozzle Guide Vanes HP Turbine Blades T1 & T2 Inspection Findings: Combustor: Bulkhead: Minor coating loss on fuel nozzle heat shields noted. AMM Limit Any Amount. AMM Table 612/ N00: Heatshield Surface Layer that is missing All quantities. NOTE: When the surface layer is missing, the rate of the Heatshield deterioration will increase. All findings are acceptable to AMM limits and do not require a reduced inspection interval. Inner Liner (Louver): No defects noted. Pictures added for reference only. APMS Aviation Ltd Hangar K4, Cotswold Airport, Cirencester, Gloucestershire, GL7 6BA United Kingdom 14

23 Ref: RB0881_P724307CN_21OCT2016_MART_R1 Outer Liner (Louver): Minor cracks noted. All findings are acceptable to AMM limits and do not require a reduced inspection interval. 3 locations with an axial crack which completely traverses 1 louver. AMM limit for regular inspection interval (Table 611/ N00): Axial Cracks that are only on one Louver All cracks that are not more than 0.75 inch ( mm) in length. Cracks can completely traverse one louver, but must be separated circumferentially by 6.0 inches ( mm) minimum. HPT 1 Nozzle Guide Vanes: Minor coating erosion/ loss. All satisfactory to AMM limits without reduced inspection interval. Pictures added to show the general condition of the Vanes. APMS Aviation Ltd Hangar K4, Cotswold Airport, Cirencester, Gloucestershire, GL7 6BA United Kingdom 15

24 Ref: RB0881_P724307CN_21OCT2016_MART_R1 HP Turbine Blades T1 (60ea): Minor tip rub and minor coating loss noted. All satisfactory to AMM limits without reduced inspection interval. Pictures added to show the general condition of the blades. AMM Limit (Table 615/ N00): Thermal Barrier Coat not on blade A, B and C All quantities of thermal barrier coat are permitted to be not there, chipped, crazed or cracked. All findings are acceptable to AMM limits and do not require a reduced inspection interval. APMS Aviation Ltd Hangar K4, Cotswold Airport, Cirencester, Gloucestershire, GL7 6BA United Kingdom 16

25 Ref: RB0881_P724307CN_21OCT2016_MART_R1 During the HPT1 Blade inspection cracks were noted on HPT2 Guide Vanes. The allowable limit depends on the installed P/N and the status of SB PW4ENG T2 Vane inspection is not part of the regular AMM inspection. Martinair provided the following information: Time since last insp. per SB : 367 H / 70 cycles. Remaining until next insp.: 33 H / 30 C Inspection performed 70 Cycles ago HP Turbine Blades T2 (82ea): No defects noted. Pictures added to show the general condition of the blades. General Observations Combustion / HPT: No significant defects noted. APMS Aviation Ltd Hangar K4, Cotswold Airport, Cirencester, Gloucestershire, GL7 6BA United Kingdom 17

26 Ref: RB0881_P724307CN_21OCT2016_MART_R1 Section 6 Low Pressure Turbine LP Turbine Nozzle Guide Vanes T3 LP Turbine Blades T3 & T6 Inspection Findings: LP Turbine Nozzle Guide Vanes T3: No defects noted. Pictures added to show the general condition of the vanes. LP Turbine Blades T3 (128ea): No defects noted. Pictures added to show the general condition of the blades. APMS Aviation Ltd Hangar K4, Cotswold Airport, Cirencester, Gloucestershire, GL7 6BA United Kingdom 18

27 Ref: RB0881_P724307CN_21OCT2016_MART_R1 LP Turbine Blades T6 (128ea): No defects noted. Pictures added to show the general condition of the blades. General Comments LP Turbine: No defects noted on module. APMS Aviation Ltd Hangar K4, Cotswold Airport, Cirencester, Gloucestershire, GL7 6BA United Kingdom 19

28 Ref: RB0881_P724307CN_21OCT2016_MART_R1 General Comments: Section 7 The condition of LPC 1.6 (1 blade) requires a blend repair. All other stages didn t show any significant defects. Observation: Cracks have been noted on T2 NGV s concave side. T2 NGV s are not part of the AMM borescope inspection. T2 NGV s are covered by PW4ENG Next due in 30 cycles. Recommendations: Deposits (crystals) have been noted on all compressor stages. An engine wash is highly recommended. Inspection Performed and Report Prepared by: Inspectors name: Robert Bauer Signature: Date: Oct. 26 th 2016 IMPORTANT NOTICE The content of this report is based on attentive inspection and review within the capabilities of the inspection equipment used (as recommended by the OEM) and in accordance with documentation and procedures noted in Section 1. It is exclusive of any damage not detectable without removal and disassembly of the unit. It is believed to be a true representation of the engine condition at the specific time of inspection and prior to any further operation. This report is submitted in confidence to the above named client and is without responsibility to others to whom it may be shown. APMS Aviation Ltd Hangar K4, Cotswold Airport, Cirencester, Gloucestershire, GL7 6BA United Kingdom 20

29 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC F IMP (B) N N FUEL METERING UNITS P/N's 51T217 & 53T419. (ATA 73) TO PREVENT ENGINE COMPARTMENT FIRES Replace the Fuel Metering Units I.A.W. SB PW4ENG A73-37 R1 as follows: For FMU more than 140 FH, within 10 FH after 26- Mar-1988 (For DGAC CN) or 01-Sep-1989 (For FAA AD) For FMU less than 140 FH, before 150 FH TSN. Thereafter replace FMU's at interval not to exceed 150 FH. A. Within 30 days after March 30, 1989, inspect the main fuel and vapor recovery hose assembly for fuel leakage and determine the cure date code contained on both the main fuel supply hose and the vapor recovery hose, IAW SB A R1 The affected main fuel supply hoses contain cure date codes of 3Q84 through 2Q87. The affected vapor recovery hoses contain cure date codes of 2Q84 through 3Q87. The affected bulk 601 hose contains a CAGE code of (regardless of cure date code). Not Applicable due to aircraft type Not Applicable due to aircraft type Concerns P&W Type 4152 installed on A Series. AEROQUIP bulk 601 hoses with CAGE code of Fitted on Airbus A310 powered by PW4000 Engines 1. If fuel leakage is detected, prior to further flight, replace the hose(s) with a serviceable hose not containing the cure date codes or CAGE code specified above, IAW the applicable service bulletin identified above. (P.T.O) Template Issue 43 Page 1 of 47 Template Issue Date: 29/04/2016

30 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC (Cont d) N TO PREVENT ENGINE COMPARTMENT FIRES 2. If the affected hoses are installed, but fuel leakage is not detected, repetitively inspect the hoses for evidence of fuel leakage IAW the schedule specified in the applicable service bulletin. After March 30, 1989, bulk 601 hose with CAGE code of shall not be installed on any airplane. C. Replacement of main fuel supply and vapor recovery hoses with serviceable hoses that do not contain the cure date codes or CAGE code specified in paragraph A., above, constitutes terminating action for the requirements of this AD. Not Applicable due to aircraft type AEROQUIP bulk 601 hoses with CAGE code of Fitted on Airbus A310 powered by PW4000 Engines N 8 th STAGE BLEED SYSTEM CHECK VALVE - INSPECTION / REPAIR Within the next 250 FH after 12-Feb-1990 (the effective date of this AD), or prior to accumulating 600 hours TSN on the valve, whichever occurs later, perform the inspections of the 8 th Stage Bleed System Check Valve IAW Boeing SB A0030. Prior to further flight, repair or replace Check Valves which do not pass all required inspections. Installation of a P/N valve in lieu of a P/N or -4 valve constitutes terminating action for the inspection required by this AD. Not Applicable due to aircraft type Concerns model 767 series airplanes equipped with Allied Signal 8 th Stage Bleed System Check Valve, P/N or -4 Template Issue 43 Page 2 of 47 Template Issue Date: 29/04/2016

31 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC N PREVENT INABILITY TO FULLY OPEN AND CLOSE THE OUTBOARD ENGINE FUEL SHUTOFF VALVE Within 30 days from 6-Jun-1990 replace the outboard engine fuel shutoff calve actuator bonding wire in accordance with Boeing ASB A2143 Within 10 days after completion of the modification report all findings of wires longer than six inches to Seattle Manufacturing Inspection District Office. Reports shall include the serial number of the affected airplanes and identify positions of valves found with long straps. Aircraft related. Willis Asset Management has no records to confirm compliance to AD Concerns model series airplanes equipped with PW4000 series engines identified in Boeing ASB A [This AD supersedes AD which superseded AD and AD ] N 8 th STAGE BLEED SYSTEM CHECK VALVE - INSPECTION / REPAIR A. Within the next 500 hours Time-In-Service [TIS] after March 19, 1990 (the effective date of AD ), or prior to the accumulation of 1,200 hours TIS on the valve, or within 30 days after June 18, 1990, whichever occurs later, perform the inspections of the Pneumatic System 8th Stage Bleed Check Valve specified in Hamilton Standard SB R0 or R1. Prior to further flight, repair or replace any Check Valves which do not pass all the required inspections. Thereafter, inspect the check valve poppet at intervals not to exceed 1,200 hours TIS, IAW Hamilton Standard SB R1. B. Used Check Valves must be inspected and repaired, if necessary, IAW Hamilton Standard SB R0 or R1, prior to installation in any Model 767 series airplane. Not Applicable due to aircraft type Concerns model 767 series airplanes equipped with Hamilton Standard Pneumatic System 8th Stage Bleed Check Valve, P/N Template Issue 43 Page 3 of 47 Template Issue Date: 29/04/2016

32 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC 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: N PREVENT FALSE OIL FILTER BYPASS INDICATION OR LOSS OF OIL QUANTITY FROM FAILED PRESSURE SWITCHES 1 For Pratt & Whitney Engines: - Replace P/N S332T 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 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 Not Applicable due to aircraft type Concerns Model 767 series airplanes equipped with engine oil filter differential pressure switched on JT9D-7R4 and PW4000 engines Template Issue 43 Page 4 of 47 Template Issue Date: 29/04/2016

33 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC F (B) R N ENGINE ANTI-ICE OPERATING REQUIREMENT: HPC DAMAGE & SURGE. (ATA 72) Before 09-Sep-1992 (For DGAC CN) or 05-Aug (For FAA AD), install a placard in the flightdeck of A & A310 as per AI SIL Rev. 1 and enter in the AFM the TR's /7 (For A310) and /3 (For A ). Embodiment of AI MOD 8874 (SB's A or A ) covering VSB "P&W" PW4ENG cancels the requirements listed above provided both engine are equipped with FADEC SCN 10E/U or SCN 10F/U installed by VSB "P&W" PW4ENG (SB's A or A ). Not Applicable due to aircraft type Concerns P&W Types 4152,4156 & 4158 equipped with EEC P/N 50D436, 50D791, 50D824, 51D037 & 50D053 fitted to A & A310. F IMP (B) R D ENGINE CONTROL MODIFICATIONS. (ATA 73) See Superseding AD- CN superseded by CN F IMP (B) AD Superseded by AD PW4050, PW4052, PW4056, PW4060, and PW4060A Engines F IMP (B) 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). Shaft inspection performed on 24 th October (as recorded by SIA history sheet) AD Closed. Concerns P&W Types 4050,4052,4056, 4060, 4060A, 4152, 4156,4158 and 4460 installed on B747, B767, A300 and A310 Series. F IMP (B) R1 - D HIGH PRESSURE COMPRESSOR. (ATA 72) - CANCELLED CN Cancelled Template Issue 43 Page 5 of 47 Template Issue Date: 29/04/2016

34 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC F R2 (B) F R2 (B) {Cont d} R {Cont d} R ENGINE MOUNTS LINKS. (ATA 71) L/H FWD MOUNT LINK. R/H FWD MOUNT LINK. L/H OUTBOARD ENGINE MOUNT LINK. R/H OUTBOARDENGINE MOUNT LINK. R/H INBOARD ENGINE MOUNT LINK. AFT BEAM. FWD & AFT mount assemblies: Possible overheat of FWD engine mounts and omission of dip etching of AFT engine mounts during the machining process. P/N , perform visual inspection I.A.W. SB PW4NAC Part 1 (AI SB A or SB A ) and a Nital Etch inspection as per Part 2 of SB at next engine Removal. P/N , perform visual inspection I.A.W. SB PW4NAC Part 1 (AI SB A or SB A ) and a Nital Etch inspection as per Part 2 of SB at next engine Removal. P/N , perform visual inspection I.A.W. SB PW4NAC Part 1 (AI SB A or SB A ) and perform a Dip Etch and FPI as per Part 2 of SB at next engine Removal. P/N , perform visual inspection I.A.W. SB PW4NAC Part 1 (AI SB A or SB A ) and perform a Dip Etch and FPI as per Part 2 of SB at next engine Removal. {P.T.O] P/N , perform visual inspection I.A.W. SB PW4NAC Part 1 (AI SB A or SB A ) and perform a Dip Etch and FPI as per Part 2 of SB at next engine Removal. P/N & P/N , perform visual inspection I.A.W. SB PW4NAC Part 1 (AI SB A or SB A ) and perform a Dip Etch and FPI as per Part 2 of SB at next engine Removal. Not Applicable due to aircraft type Not Applicable due to aircraft type Concerns P&W Types 4152 or 4158 turbofan engines fitted to A300B4-622, -622R and A Concerns P&W Types 4152 or 4158 turbofan engines fitted to A300B4-622, -622R and A Concerns P&W Types 4152 or 4158 turbofan engines fitted to A300B4-622, -622R and A Template Issue 43 Page 6 of 47 Template Issue Date: 29/04/2016

35 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC N N {Cont d} N ENSURES THE INTEGRITY OF THE FAIL SAFE FEATURES OF THE THRUST REVERSER SYSTEM ENSURES THE INTEGRITY OF THE FAIL SAFE FEATURES OF THE THRUST REVERSER SYSTEM ENSURES THE INTEGRITY OF THE FAIL SAFE FEATURES OF THE THRUST REVERSER SYSTEM See AD Compliance Within 90 days after 24-Aug-1994 perform and inspection to detect damage to the bullnose seal on the translating sleeve of the thrust reverser, and perform a test of the lock mechanism of the centre locking actuator in accordance with SB or ASB A2112 R1. Repeat this inspection and test thereafter at intervals not to exceed 1,000 hours, Time-In- Service. {P.T.O] Within 9 months after 24-Aug-1994, perform inspections and functional tests of the thrust reverser control and indication systems in accordance with SB or ASB A2112 R1. Repeat these inspections and functional tests thereafter at intervals not to exceed 18 months Not Applicable due to aircraft type Aircraft related. Willis Asset Management has no records to confirm compliance to AD Aircraft related. Willis Asset Management has no records to confirm compliance to AD Concerns Model 767 series airplanes equipped with P&W PW4000 series engines Concerns model series airplanes equipped with PW4000 series engines. Concerns model series airplanes equipped with PW4000 series engines N PREVENT POSSIBLE DEPLOYMENT OF A THRUST REVERSER IN FLIGHT Within 18 months of 25-Nov-1994, replace the thrust reverser flow restrictor devices with one way valve restrictors in accordance with ASB A2128. Aircraft related. Willis Asset Management has no records to confirm compliance to AD Concerns model series airplanes equipped with PW4000 series engines. Template Issue 43 Page 7 of 47 Template Issue Date: 29/04/2016

36 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC F (B) R R GREEN HYDRAULIC DRAIN SYSTEM INSPECTION AND ENGINE ACCESSORY GEAR BOX SEAL REPLACEMENT AT THE GREEN HYDRAULIC PUMP PAD. (ATA 72) Within 500 flight hours after 07-Nov-1992 (For DGAC CN) or before 23-Dec-1997 (For FAA AD), perform the flow check as per SB's AI A or A , as applicable. Repeat the above test at interval not to exceed 500 flight hours. [P.T.O] Not Applicable due to aircraft type Concerns P&W Types 4152, 4156A & 4158 fitted to A , -325 & A300B4-622, - 622R,all MSN's pre MOD (SB AI A , A , VSB PW4ENG ). F (B) R2 {Cont d} {Cont d} R GREEN HYDRAULIC Terminating Action: DRAIN SYSTEM Before 31-Dec-1993 (For DGAC CN) or 23-Nov- INSPECTION AND 1998 (For FAA AD) ENGINE Incorporate on both engines a spring loaded seal as ACCESSORY GEAR per SB's AI A or A , as BOX SEAL applicable. REPLACEMENT AT Note: For ETOPS configured aircraft this T/A must THE GREEN be accomplished within the next 10 flights. It is HYDRAULIC PUMP recommended to accomplish this modification only PAD. on one engine at a time. (ATA 72) Not Applicable due to aircraft type Concerns P&W Types 4152, 4156A & 4158 fitted to A , -325 & A300B4-622, - 622R,all MSN's pre MOD (SB AI A , A300 F IMP (B) N HPC FAILURE CAUSED BY AIRSEAL INTERFERENCE. (ATA 73) Apply "Boeing" ASB's A2055 and A0033. Aircraft related. Willis Asset Management has no records to confirm compliance to AD Concerns P&W Types 4050, 4052, 4056, 4060 and 4060A turbofan engines only. Template Issue 43 Page 8 of 47 Template Issue Date: 29/04/2016

37 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC F (B) F (B) N N N ENGINE MOUNTS. (ATA 71) AFT FRAME OF P&W ENGINE MOUNT PICK-UP. (ATA 71) PREVENT FRACTURING OF THE COUPLING NUT, WHICH COULD RESULT IN RELEASE OF FUEL ONTO THE ENGINE COWLING AND A SUBSEQUENT FIRE Within 4800 flight cycles or 180 days after 09-Apr (For DGAC CN) or within 120 Days after 08- Jul-1994 (For FAA AD): Identify the links & perform a FPI & ECI on the links as per: Airbus SB A (SB's PW7R & PW4NAC ). Airbus SB's A (SB's APW7R and APW4NAC ) Before accumulation of 500 flight hours after 10- Feb-1996 (for DGAC CN) or 02-Jul-1998 (for FAA AD), perform a visual inspection and replace if necessary I.A.W. Part 1 of SB PW7R4 A or PW4NAC A (Part A of AI SB's A or A ). At the next Engine removal or within 4,000 CY after 10-Feb-1996 (for DGAC CN) or 02-Jul-1998 (for FAA AD), whichever occurs first, perform FPI and ECI, and replace if necessary I.A.W. Part 2 of SB's PW7R4 A or PW4NAC A (Part B of SB's A or A ). Within 24 Months after 23-May-1996: 1. For model Series airplanes identified in SB A2185 R1, replace the strut fuel tubes and couplings on engine numbers 1 and 4 with new redesigned couplings. 2. For model series airplanes having variable numbers RT641 through RT450 inclusive, identified in SB , on engine positions 1 AND 4 install new fuel lines, shrouded fuel lines couplings and drain lines. Not Applicable due to aircraft type Not Applicable due to aircraft type Aircraft related. Willis Asset Management has no records to confirm compliance to AD Concerns P&W engines fitted to A & A310. Concerns P&W turbofan engines Types 4152, 4156A or 4158 fitted to A300B4-622, -622R and A , Concerns Model 747 series airplanes equipped with P&W PW4000 or CF6-80C2 engines as identified in SB A2185 R1, and SB Template Issue 43 Page 9 of 47 Template Issue Date: 29/04/2016

38 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC F IMP (B) N THRUST REVERSERS To prevent AFT Cascade Support Frame Assembly INCORPORATE AFT failure due to cracks, inspect within 250 FH after 03- CASCADE Sep-1996 I.A.W. Part 1 Interim inspection of SB, SUPPORT FRAME thereafter repeat at Int. 450 FH or modify I.A.W. SB SUPPORT PW4NAC R6. ASSEMBLIES,P/N's or (ATA 78) Not Applicable due to aircraft type Concerns P&W Series 4000 turbofan engines, with thrust reverser, STC FAA N SJ514NE, installed on A and A310, STC FAA SE744NE, installed on MD11. F IMP (B) 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 R1. Terminating Action 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 and Not applicable by P/N P/N 53L030 installed AD Closed Concerns P&W Model 4052, 4056, 4060, 4062, 4152, 4156A, 4158, 4460, 4462, 4164 & 4168 turbofan engine, with 2 nd Stage High Pressure Turbine (HPT) rotating airseals, P/N's 50L156 or 50L195 installed, fitted to A300, A310, A330, B747, B767 & MD11. Template Issue 43 Page 10 of 47 Template Issue Date: 29/04/2016

39 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC F IMP (B) F IMP (B) 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 R3. 2. Modify HPC 8 th - 14 th stage stators I.A.W. SB PW4ENG R1. 3. Modify 1 st stage HPT cooling duct (TOBI Duct), install metering plug in N 2 bearing thrust balance vent tube and incorporate 1 st stage HPT vanes with increased airflow area I.A.W. SB PW4ENG R1. 4. Incorporate HPC 13th - 15th stage zirconium oxide blade tips I.A.W. SB PW4ENG R1 Not applicable to phase 3 engines AD Closed Concerns only P&W Model 4050,4052,4056,4060/A /C, 4062,4152,4156,4156A, 4158,4160,4256,4460, 4462,4650 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 R3, R1. 2) PW4ENG R3, R1, F R R DEACTIVATION OF THRUST REVERSERS Deactivate T/Rs unless specific modifications are embodied or specific actions carried out. Not Applicable due to aircraft type Applies to A310 and A A/C fitted with JT9D7R4 or PW4000 engines F IMP D TO PREVENT CRITICALLIFE- Revision of Engine Manufacturer's Time Limits Section (TLS) DGAC AD F IMP R1 (B) is superseded by F IMP (B). See superseding. AD s Template Issue 43 Page 11 of 47 Template Issue Date: 29/04/2016

40 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC R1 (B) F IMP (B) N LIMITED ROTATINGENGINE PART FAILURE.(ATA 05,72) PREVENT POSSIBLE SEPARATION OF THE ENGINE FROM THE AIRPLANE IN THE EVENT OF A PRIMARY THRUST LINKAGE FAILURE See AD Compliance FAA AD is superseded by Aircraft related. Willis Asset Management has no records to confirm compliance to AD Concerns Model series airplanes powered by P&W PW4000 engines as listed in Boeing Alert SB A2283 F IMP (B) N 4 th STAGE LPT DISKS: P/N 50N924. (ATA 72) A - Prior accumulation of CIS, remove the affected 4th stage LPT disks & replace them with new or serviceable parts. B - Restoration of the original life limits on affected disks may be accomplished as follows: B.1) Re-operation performed on the LPT disks installed in PW4164 or PW4168 Model engines IAW "PW" SB PW , prior to CIS to incorporate the slotted cooling air configuration may restore life limit to CIS. P.T.O Not Applicable by P/N P/N 50N024 Installed AD Closed Concerns P&W model 4056, 4152, 4156A, 4164, 4168 & 4460 Turbofan engines with 4 th Stage LPT Disk P/N 50N924, See AD for S/N's listed. Template Issue 43 Page 12 of 47 Template Issue Date: 29/04/2016

41 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC F IMP (B) {Cont d} F IMP R1 (B) {Cont d} N D 4 th STAGE LPT DISKS: P/N 50N924. (ATA 72) HPC SURGE EVENT. (ATA 72) B.2) Re-operation performed on the LPT disks installed in PW4156A or PW4460 Model engines IAW "PW" SB PW4ENG , prior to CIS to incorporate the slotted cooling air configuration may restore life limit to CIS B.3) Re-operation performed on the LPT disks installed in PW4152 or PW4056 Model engines IAW "PW" SB PW4ENG , prior to CIS to incorporate the slotted cooling air configuration may restore life limit to CIS. See Superseding AD s Not Applicable by P/N P/N 50N024 Installed AD Closed DGAC AD F IMP (B is superseded by F IMP (B) FAA AD is superseded by Concerns P&W model 4056, 4152, 4156A, 4164, 4168 & 4460 Turbofan engines with 4 th Stage LPT Disk P/N 50N924, See AD for S/N's listed. F IMP (B) N PREVENT FAILURE OF THE THRUST REVERSER DEACTIVATION PINS Within 24 months after 24-Jan-2000, replace the existing deactivation PIN, PIN bushing in the AFT cascade mountain ring, and insert flange on each thrust reverser half, with new, improved components in accordance with Boeing ASB A2165R1 (Model series airplanes) or Boeing ASB A0080 (for model 767 series airplanes). Aircraft related. Willis Asset Management has no records to confirm compliance to AD series airplanes powered by PW4000 engines as listed in Boeing Alert SB A2165R1, and 767 series airplanes powered by PW4000 series engines as listed in Boeing ASB A0080. Template Issue 43 Page 13 of 47 Template Issue Date: 29/04/2016

42 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC F IMP (B) F IMP (B) N N PREVENT POSSIBLE SEPARATION OF THE ENGINE FROM THE AIRPLANE IN THE EVENT OF A PRIMARY THRUST LINKAGE FAILURE PREVENT A SLIDER DISENGAGING FROM THE AUXILIARY TRACK ASSEMBLY, WHICH COULD LEAD TO SEPARATION OF A PORTION OF THE THRUST REVERSER FROM THE AIRPLANE DURING FLIGHT. See AD Compliance See AD Compliance Not Applicable due to aircraft type Aircraft related. Willis Asset Management has no records to confirm compliance to AD Concerns Model 767 series airplanes powered by P&W PW4000 and JT9D series engines, as listed in Boeing Alert SB A0087 Concerns Model series airplanes powered by P&W PW4000 series engines, line numbers 696 through 1100 inclusive, and model and -300 series airplanes powered by PW4000 line numbers 1 through 646 inclusive. F IMP R1 (B) D REVISION OF ENGINE MANUAL TIME LIMITS SECTION. (ATA 05,72) See Superseding AD s F IMP (B) superseded by F IMP (B) superseded by AD Concerns All PW /-100/-112 Series Engines, Template Issue 43 Page 14 of 47 Template Issue Date: 29/04/2016

43 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC F IMP R1 (B) N PREVENT INADVERTENT DEPLOYMENT OF A THRUST REVERSER DURING FLIGHT. For airplanes identified in Boeing SB R2, Accomplish the requirements of paragraphs (a)(1) and (a)(2) of this AD at the times specified in those paragraphs. Accomplishment of these actions constitutes terminating action for the inspections and tests required by paragraph (a) of AD Within 4,000 hours TIS after accomplishment of paragraph (a) of this AD, or production equivalent; or within 1,000 hours TIS after the effective date of this AD, whichever occurs later: Perform a functional test to detect discrepancies of the additional locking system on each engine thrust reverser, in accordance with Appendix 1 of this AD. Prior to further flight, correct any discrepancy detected and repeat the functional test of that repair, in accordance with the procedures described in the Boeing AMM. Repeat the functional test thereafter at intervals not to exceed 4,000 hours TIS. Aircraft related. Willis Asset Management has no records to confirm compliance to AD Applicable to B747 A/C only F IMP (B) R D LIMITATION OF NUMBER OF "HPC CBS" CONFIG ENGINE INSTALLED ON EACH AIRPLANE. (ATA 72) See Superseding ADs DGAC AD superseded by F IMP. FAA AD superseded by Concerns PW " (B747, B767 & MD-11 applications} which have embodied Cut- Back Stator Vanes as per PW4000 SB R3 or SB Template Issue 43 Page 15 of 47 Template Issue Date: 29/04/2016

44 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC F IMP R1 (B) D LPT 4 th STAGE AIR SEAL FAILURE. (ATA 72) See Superseding ADs F IMP superseded by F IMP (B). AD superseded by Concerns PW Series Turbofan Engines with LPT 4th Stage air seal P/N's 50N478 or 50N installed. F IMP (B) N FOR AIRPLANES THAT HAVE EARLY PRODUCTION FAN BLADES INSTALLED ON ALL ENGINES Correction of Flight Manual performance figures due to reduced thrust from pre mod standard Fan Blades. The actions shall be done IAW Boeing Telex M , including Attachments. Aircraft related. Willis Asset Management has no records to confirm compliance to AD Applicable to B747 & B767 Applications having early-production Fan Blades (Phase 0/1, FB2B or FB2T). F R2 (B) R FOR AIRPLANES THAT HAVE EARLY PRODUCTION FAN BLADES INSTALLED ON BOTH ENGINES The actions shall be done IAW Airbus A310 Flight Manual Temporary Revision /01, dated January 22, 2001; Airbus A310 Flight Manual Temporary Revision /02, dated January 22, 2001; and Airbus A Flight Manual Temporary Revision /01, dated January 22, 2001; as applicable. Not Applicable due to aircraft type Applicable to A , A , and A300 B4-622R series airplanes; with PW4000 series engines, NOT fitted with currentproduction FB2C Fan Blades (Phase 3 Fan Blades) on both engines. Template Issue 43 Page 16 of 47 Template Issue Date: 29/04/2016

45 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC F IMP (B) N LPT 4 th STAGE AIR SEAL FAILURE.(ATA 72) Replace the 4 th Stage Air Seal P/N 50N478 with a serviceable part P/N's 51N038 or 50N before the following limits (If limit exceeded, replace prior to further flight): CSN for PW4052, 4060,4060A, 4156 & 4158 fewer than CSN CSN for PW4056, 4152,4156A, and 4460 post SB PW4ENG72-657R1 fewer than CSN CSN for PW4056, 4152,4156A, 4460 pre SB PW4ENG72-657R1 fewer than CSN CSN for PW4056, 4152,4156A, and 4460 not identified in Table 3 of AD and fewer than CSN CSN for PW4062 & 4462 fewer than CSN. Not applicable by P/N P/N 50N009 Installed AD Closed Concerns PW Series Turbofan Engines with LPT 4th Stage air seal P/N's 50N478 or 50N installed. F IMP (B) R D MULTIPLE ENGINE POWER LOSSES DUE TO HPC SURGE. (ATA 72) See Superseding ADs DGAC AD superseded by F IMP (B). FAA AD superseded by Concerns PW " Series Turbofan Engines Having ESNs Listed in the AD. F (B) - N ENG REV UNLOCK' PROCEDURE Revision of AFM procedure Not Applicable due to aircraft type Applies to A310 and A Aircraft Template Issue 43 Page 17 of 47 Template Issue Date: 29/04/2016

46 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC F IMP (B) R D MULTIPLE ENGINE POWER LOSSES DUE TO HPC SURGE. (ATA 72) See Superseding ADs DGAC AD superseded by F IMP. FAA AD superseded by Concerns PW " Series Turbofan Engines Having Configurations and ESNs Listed in the AD. F (B) N - N ENSURING THAT FLIGHT CREW IS INFORMED OF LIMITATIONS IN AIRPLANE PERFORMANCE FWD ENGINE MOUNT. (ATA 71) AFM Revision: Performance section 4A or 4B. Perform restoration of the leading edge contour every 450 cycles. MAIN BEAM P/N (Assy P/N ): Limit life of Main Beam installed on PW 4156A (A ) to FC. CROSS BEAM P/N (Assy P/N ): Installation restricted to PW 4152 Engines. Not Applicable due to aircraft type Not Applicable due to aircraft type Applicable to MD 11 airplanes with PW4460 or PW4462 engines having FB2B Fan Blades installed: This AD superseded AD Concerns P&W Model 4152, 4156A & 4158 Turbofan engine fitted to A300B4-622, B4-622R, -F4-622R & A , F IMP (B) D MULTIPLE ENGINE POWER LOSSES DUE TO HPC SURGE. (ATA 72) See Superseding ADs DGAC AD superseded by F IMP. FAA AD superseded by Concerns PW " Series Turbofan Engines Having Configurations and ESNs Listed in the AD. Template Issue 43 Page 18 of 47 Template Issue Date: 29/04/2016

47 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC F IMP R D DETECTION OF PREMATURE CRACKING OF THE HPC FRONT DRUM ROTOR (ATA 72) See Superseding ADs Concerns P&W Model DGAC AD is superseded by F IMP 4050, 4052, 4056, (B). 4060, 4062, 4152, FAA AD superseded by A, 4158, 4460 & 4462 Turbofan engines. F R1 - R THRUST REVERSER - IMPLEMENTATION OF THIRD LINE OF DEFENCE Embody S/B A or A Not Applicable due to aircraft type Applies to A310 and A A/C fitted with JT9D7R4 or PW4000 engines Template Issue 43 Page 19 of 47 Template Issue Date: 29/04/2016

48 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC F IMP (B) N N PREVENT THE POTENTIAL FOR DUAL WIRE FAULTS FROM GROUNDED, SEPARATED, OR SHORTED WIRES PREVENT BLOCKAGE OF THE CHECK TEE VALVE AND CRACKS IN THE FIRE EXTINGUISHER DISCHARGE TUBES IN THE ENGINE STRUTS Prior to the accumulation of 10,000 hours TIS or within 180 days after the effective date of this AD, whichever occurs later: Do a one-time detailed visual inspection of the wire bundles located in the aft section of the strut forward fairing panel of both engine struts to detect chafing damage, per Boeing SB A0049, R3, or R4. If any chafing damage of any wire bundle is found, do the actions required by paragraphs (a)(1) and (a)(2) of this AD at the times specified in those paragraphs. For Model and F series airplanes, line numbers 696 through 1061 inclusive equipped with PW4000 engines: Within 30 days after April 25, 2000 (the effective date of AD ), perform a detailed inspection to detect cracking of the fire extinguisher discharge tubes in the number 2 and number 3 engine struts, in accordance with Boeing Alert SB A2266. Not Applicable due to aircraft type Aircraft related. Willis Asset Management has no records to confirm compliance to AD Applicable to B767 A/C only Applicable to B747 A/C only F IMP (B) R D PREVENTION OF ENGINE POWER LOSSES DUE TO HPC SURGE. (ATA 72) See Superseding ADs DGAC AD cancelled, superseded by F IMP (B). FAA AD is superseded by AD Concerns PW40-94 Series0 Turbofan engines. Template Issue 43 Page 20 of 47 Template Issue Date: 29/04/2016

49 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC F IMP (B) D TO PREVENT CRITICAL LIFE-LIMITED ROTATING ENGINE PART FAILURE. (ATA 05) See Superseding ADs DGAC AD is cancelled at Rev 1, due to the issue of FAA AD FAA AD is superseded by Concerns All PW /-100/-112 Series Engines. Template Issue 43 Page 21 of 47 Template Issue Date: 29/04/2016

50 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC HPC 5 th Stg Disk HPC Front Drum HPC Rear Drum Inspected performed on 4 th May 2005 F IMP R1 (B) N R TO PREVENT CRITICAL LIFE-LIMITED ROTATING ENGINE PART FAILURE. (ATA 05, 72) Before 12-Aug-2006, revise the manufacturer's Time Limits Section of the Manufacturer's Engine Manual, P/N's 50A443, 50A605, 50A822, 51A342, 51A345, and 51A751 AND for Air Carrier Operations, revise the Approved Continuous Airworthiness Maintenance Program by adding paragraph (f) (1) of the AD. LPC Front Hub LPT 5 th Disk LPT 6 th Disk LPT 4 th Disk LPT 3 rd Disk Inspected performed on 5 th May 2005 At next piece part level Concerns PW / -100 / -112 Engine Series Hub Turb Front Inspected performed on 16-May-11 Hub Turb Rear 2 nd Template Issue 43 Page 22 of 47 Template Issue Date: 29/04/2016

51 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC F IMP (B) N PREVENTION OF FAILURE OF THE OIL PRESSURE INDICATOR AND LOW-OIL PRESSURE WARNING "Titeflex" OIL CIRCUIT FLEXIBLE HOSE. (ATA 79) Before 31-Dec-2002, replace the flexible hose assembly P/N by a newly certified hard line P/N See also VSB PW4NAC A Within 8 months after the effective date (22 Jan 2004) of this AD, replace the existing flexible hose assembly, P/N with P/N Before further flight after the replacement, perform a test of the engine oil system, per the accomplishment instructions of the service bulletin specified as applicable. Not Applicable due to aircraft type Concerns PW 4000 series fitted to A or A310, PRE AIB MOD (SB A or A ). Template Issue 43 Page 23 of 47 Template Issue Date: 29/04/2016

52 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC F IMP (B) N N N N 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 A 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. 2-If the presence of a crack needs to be confirmed, perform an E/C inspection within 5 cycles after item 1. 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. 4-If the presence of a crack is confirmed, remove and replace the HPC front drum rotor before further flight. 5-Repeat every CSLI, inspection of items 1, and if necessary items 2, 3 or 4. Inspection performed on 28 th May 2011 at CSN: 12,181 (Engine Time) Next Inspection due at CSN: 14,381 (Engine Time) Concerns P&W Model 4052, 4056, 4060, 4062, 4152, 4156A, 4158, 4460 & 4462 Turbofan engines. SUPERSEDES CN IMP SUPERSEDES AD F IMP (B) R D PREVENTION OF ENGINE POWER LOSSES DUE TO HPC SURGE. (ATA 72) See Superseding ADs DGAC AD cancelled, superseded by F IMP. FAA AD is superseded by AD Concerns PW40-94 Series0 Turbofan engines. Template Issue 43 Page 24 of 47 Template Issue Date: 29/04/2016

53 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC F IMP R D PREVENTION OF ENGINE POWER LOSSES DUE TO HPC SURGE. (ATA 72) See Superseding ADs DGAC AD cancelled, superseded by F IMP (B) FAA AD superseded by Concerns P&W Model 4050, 4052, 4056, 4060, 4060A, 4060C, 4062, 4152, 4156, 4156A, 4158, 4160, 4460, 4462 & 4650 Turbofan engines... F IMP N PREVENTION OF ENGINE POWER LOSSES DUE TO HPC SURGE. (ATA 72) Determine the engine configuration as per table 1 of present AD. Thereafter, determine the applicable limits depending on the engine configuration. See AD for details. SB (RCC Mod) performed on 21st May 2005 as terminating action AD Closed Concerns PW " Series Turbofan Engines N PREVENTION OF IN- FLIGHT DEPLOYMENT OF A THRUST REVERSER Within 18 months after the effective date (17 Aug 2004) of this AD, install modifications related to an independent third line of defence on the thrust reversers, in accordance with the applicable SEB listed in table 2 Not Applicable due to aircraft type Applicable to A Series and A310 Series Airplanes; Equipped With JT9D-7R4 or PW4000 Series Engines N TO PREVENT INADVERTENT COMMANDED SHUTDOWN OF THE ENGINE BLEED AIR DISTRIBUTION SYSTEMS DUE TO AN ERRONEOUS ASCTU COMMAND. (a) Within 18 months after the effective date of this AD: Carry out the modifications and functional tests of the wiring of the wire integration unit (WIU) and the ASCTU iaw Boeing SB A2136 R2. Before further flight, carry out the post-installation tests in accordance with the SB. (b) As of the effective date of this AD, no person may install on any airplane an ASCTU with applicable P/N listed in Hamilton Sundstrand SB Aircraft related. Willis Asset Management has no records to confirm compliance to AD Applicable to Boeing , 400D, and 400F series AC as listed in Boeing SB A2136 R2. Template Issue 43 Page 25 of 47 Template Issue Date: 29/04/2016

54 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC F (B) See Entry for AD D CERTIFICATION LIMITATIONS - CERTIFICATION MAINTENANCE REQUIREMENTS (CMR). See Superseding AD DGAC AD F (B) is Cancelled By DGAC AD F R1 (B) Due To The Release of EASA AD A310, A , & A ST Aircraft N TO PREVENT ENGINE FIRE DUE TO OIL LEAKAGE. Within 18 months of the effective date of this AD replace oil tube P/N with P/N Do the replacement with the accomplishment instructions of Boeing Alert SB MD11-79A008 Not Applicable due to aircraft type All PW4000 engines installed on MD-11 or MD-11F Aircraft Template Issue 43 Page 26 of 47 Template Issue Date: 29/04/2016

55 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC 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 AD under the heading: MANDATORY INSPECTIONS". HPC 5 th Stg Disk HPC Front Drum HPC Rear Drum LPC Front Hub LPT 5 th Disk LPT 6 th Disk LPT 4 th Disk LPT 3 rd Disk Hub Turb Front Hub Turb Rear 2 nd Inspected performed on 4 th May 2005 Inspected performed on 5 th May 2005 Inspected performed on 16-May-11 At next piece part level This AD supersedes AD AD applies to all PW "/- 100"/-112" engine Models. Template Issue 43 Page 27 of 47 Template Issue Date: 29/04/2016

56 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC See Entry For F (B) N REVISION OF AIRWORTHINESS LIMITATIONS ITEMS SECTION (1) Not later than 22 November 2007, revise the Airworthiness Limitations section of the Instructions for Continued Airworthiness by incorporating Airbus A CMR AI/ST5/829/85, Issue 12, (for Model A series airplanes); or Airbus A310 CMR AI/ST5/849/85, Issue 12, (for Model A310 series airplanes); as applicable. TES NOTE: Only CMR Task MSI is enginerelated, applicable to PW4000-powered A airplanes. MPD Task P1-1, FADEC Ground and BITE Test, covers this Task at intervals of 1000 FH. (P.T.O) Not Applicable due to aircraft type A , A ST and A310 Airplanes Fitted with CF6-80A, CF6-80C2, JT9D-7R4 & PW4000 Engines Template Issue 43 Page 28 of 47 Template Issue Date: 29/04/2016

57 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC See Entry For F (B) (Cont d) N Accomplish the actions specified in the applicable CMRs at the intervals specified in the applicable CMRs, except as provided by paragraph (2) below. Where the CMRs specify to contact the Direction Générale de l'aviation Civile (DGAC), operators are required to contact the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, for such REVISION OF approvals. The actions must be accomplished in AIRWORTHINESS accordance with the applicable CMRs. (2) For tasks LIMITATIONS ITEMS identified in MSI , "Thrust Reverser SECTION Actuation and Cowling,'' of Section 2, "CMR `Two Star' Tasks,'' of Airbus A CMR AI/ST5/829/85, Issue 12, and Airbus A310 CMR AI/ST5/849/85, Issue 12: The initial compliance time is within 2,000 flight cycles after 22 August 2007 or 22 August 2008, whichever occurs later. Thereafter, actions identified in MSI must be accomplished within the repetitive interval specified in the applicable CMRs Not Applicable due to aircraft type A , A ST and A310 Airplanes Fitted with CF6-80A, CF6-80C2, JT9D-7R4 & PW4000 Engines Template Issue 43 Page 29 of 47 Template Issue Date: 29/04/2016

58 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC N (B) N ENGINE FUEL AND CONTROL One-time 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- A 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 (4) The Office of Management and Budget (OMB) has approved the reporting requirements and assigned OMB control number Group 4 EEC installed with S/N AD Closed Applicable to PW4052, PW4056, PW4060, PW4062, PW4152, PW4156A, PW4158, PW4460, and PW4462 turbofan engines Template Issue 43 Page 30 of 47 Template Issue Date: 29/04/2016

59 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC 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, N (B) {Cont d} {CONT D} N ENGINE FUEL AND CONTROL 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, (2) Group 3 EECs, before reaching 13,000 CIS after January 8, 2009, but not later than July 8, (3) There are no scheduled replacement requirements for Group 4 EECs. Group 4 EEC installed with S/N AD Closed Applicable to PW4052, PW4056, PW4060, PW4062, PW4152, PW4156A, PW4158, PW4460, and PW4462 turbofan engines Template Issue 43 Page 31 of 47 Template Issue Date: 29/04/2016

60 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC 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 PW N (B) {Cont d} {CONT D} N ENGINE FUEL AND CONTROL 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, (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, (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, Previous Credit (n) Inspecting, categorizing, and marking of EECs before January 8, 2009 performed using the Accomplishment Instructions of SB PW4000- A original issue or Revision 1, satisfy the requirements of paragraph (f)(1) of this AD. Group 4 EEC installed with S/N AD Closed Applicable to PW4052, PW4056, PW4060, PW4062, PW4152, PW4156A, PW4158, PW4460, and PW4462 turbofan engines Template Issue 43 Page 32 of 47 Template Issue Date: 29/04/2016

61 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC R R N ENGINE EXHAUST CENTRE LATCH OF THRUST REVERSER DOOR OPENING MECHANISM REPLACEMENT / INSPECTION Airbus SBs A A Pratt & Whitney SBs PW4NAC PW4NAC PW7R PW7R Not Applicable due to aircraft type A & A310 Series Aircraft Equipped with PW4000 Or JT9D-7R4 Series Engines UF R1 (AB) R MAINTENANCE INSTRUCTIONS For aircraft operated in areas suspected of Volcanic Ash contamination, perform the maintenance actions detailed in the AD. Not Applicable due to Dutch registered aircraft. French-Registered Aircraft Operated in Areas Suspected of Volcanic Ash Contamination Template Issue 43 Page 33 of 47 Template Issue Date: 29/04/2016

62 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC N (B) (AMOC) D D ENGINE - HP COMPRESSOR DRUM ROTOR DISK ASSEMBLY - INSPECTIONS Perform a local fluorescent penetrant inspection for cracks in the HPC Drum Rotor Disk Assembly Blade Locking and Loading Slots of the specific stages of the HPC Drum Rotor Disk Assemblies from which any of the blades are removed as specified in Table 1 of the AD. Use the Accomplishment Instructions of SB PW , SB PW4G R1 or SB PW4G R2, as applicable to the engine model. Remove from service any HPC Drum Rotor Disk Assembly found with a crack in the Blade Loading And Locking Slots of the HPC Drum Rotor Disk Assembly. NOTE: FAA AD (AMOC) permits returning the other stages of the Drum Rotor Disk Assembly to service if they are not cracked, and if the cracked stages of the HPC Drum Rotor Disk Assembly are replaced by new disks per the disk replacement repairs in the CIR manual. SUPERSEDED BY FAA AD PW4052, PW4056, PW4060, PW4062, PW4062A, PW4074, PW4077, PW4077D, PW4084D, PW4090, PW4090-3, PW4152, PW4156A, PW4158, PW4164, PW4168, PW4168A, PW4460, and PW4462 turbofan engines Template Issue 43 Page 34 of 47 Template Issue Date: 29/04/2016

63 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC N (B) N NO. 3 BEARING OIL PRESSURE TUBES Compliance is required the next time the No. 3 Bearing Oil Pressure Tube is in the piece-part condition after 28-Dec-10, the effective date of this AD, unless the actions have already been done: f) Perform a one-time visual inspection of the exterior of the No. 3 Bearing Oil Pressure Tube for cracks and evidence of being repaired. (1) Remove the tube from service if any cracks are found. (2) Remove the tube from service if found repaired, or if suspected that the tube was repaired. (g) After 28-Dec-10, do not install any repaired No. 3 Bearing Oil Pressure Tube into any engine. (h) Guidance on the No. 3 bearing oil pressure tube visual inspection can be found in Chapter of the applicable Clean, Inspect, Repair Manual (CIRM) AD performed by installing new Tube. At 16 th May 2011 At Next Piece part condition PW / -100 / -112 Series Turbofan Engines Template Issue 43 Page 35 of 47 Template Issue Date: 29/04/2016

64 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC N (B) (AMOC_Jun-11) N N HP COMPRESSOR STAGE 10 DISK A. PW engines with HPC RCC SBs , , , , and PW4G-100 engines with conversion SB embodied, if equipped with a 9 th stage compressor stator segment assembly with 24 slots: Perform the Initial Inspection within 7,200 cycles-inservice (CIS) since incorporation of the referenced S/Bs or within 1,000 CIS after 21-Jan-2011 (the effective date of this AD), whichever occurs later. Use the Instructions of SB PW R1 or SB PW4G to do the inspections, as applicable to the engine model. B. PW4168A-1D and PW4170 with ESNs P through P Perform the Initial Inspection within 7,200 CSN or within 1,000 CIS after 21-Jan-2011, whichever occurs later. Use the Instructions of SB PW4G to do the Inspections. Inspection performed on 16 th May 2011 at CSN 12,181 (Engine Time) Inspection due at CSN 19,381 (Engine Time) PW / -100 Series Turbofan Engines If a crack is found, remove the HPC drum rotor disk assembly from service. P.T.O Template Issue 43 Page 36 of 47 Template Issue Date: 29/04/2016

65 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC Repetitive Inspections of the AVT Shelf Slots Perform a BSI or FPI for cracks in the AVT shelf slots on the 10 th stage HPC disk of the HPC drum rotor disk assembly within every 7,200 cycles-sincelast-inspection N (B) {Cont d} (AMOC_Jun-11) {Cont d} N N HP COMPRESSOR STAGE 10 DISK Optional Terminating Action (l) As optional terminating action to the repetitive inspection requirements of this AD, install new 9th stage compressor stator segments, part number (P/N) 50S479-01, P/N 50S479-02, P/N 50S479-03, and P/N 50S479-04, and perform one of the following: (1) At the time the new 9 th stage compressor stator segments are installed, replace the HPC drum rotor disk assembly with a new, 0 cycle, HPC drum rotor disk assembly; ; or P.T.O. Inspection performed on 16 th May 2011 at CSN 12,181 (Engine Time) Inspection due at CSN 19,381 (Engine Time) PW / -100 Series Turbofan Engines Template Issue 43 Page 37 of 47 Template Issue Date: 29/04/2016

66 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC N (B) {Cont d} (AMOC_Jun-11) {Cont d} N N HP COMPRESSOR STAGE 10 DISK Optional Terminating Action (Cont d) (2) At the time the new 9th stage compressor stator segments are installed, replace the 10th stage HPC disk with a new, 0 cycle, 10th stage HPC disk; or (3) Perform a one-time BSI or FPI for cracks in the AVT shelf slots on the 10th stage HPC disk of the HPC drum rotor disk assembly between 4,000 and 7,200 cycles-in-service since installation of the new 9th stage compressor stator segments. (i) If a crack is found, remove the HPC drum rotor disk assembly from service. (ii) If no crack is found, then no further inspections are required. (4) Guidance on installation of the new 9th stage compressor stator segments can be found in SB PW R1 or SB PW4G , as applicable to the engine model. Inspection performed on 16 th May 2011 at CSN 12,181 (Engine Time) Inspection due at CSN 19,381 (Engine Time) PW / -100 Series Turbofan Engines N (B) N No later than 15-Jun-2014, modify the Thrust THRUST REVERSER Reverser Control System wiring to the Flap Control CONTROL SYSTEM - Unit (FCU) in the P252 and P253 Thrust Reverser WIRING Relay Panels, in accordance with the MODIFICATION Accomplishment Instructions of Boeing Alert SB A2184 R1. Aircraft related. Willis Asset Management has no records to confirm compliance to AD , D, and F Series Airplanes Equipped With CF6-80C2 or PW4000 Series Engines Template Issue 43 Page 38 of 47 Template Issue Date: 29/04/2016

67 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC N (B) N At the next piece- part exposure after 10-Jan-2012 (the effective date of this AD), or before ENGINE - HPT accumulating the number of cycles listed in the STAGE 1 AND HPT applicable Table; STAGE 2 AIRSEALS Remove P/N 50L879, HPT Stage 1 Airseal, AND HPT STAGE 1 observing Table 1 of the AD; AIRSEAL RINGS - Remove P/N 53L030, HPT Stage 2 Airseal, LIFE LIMITS observing Table 2 of the AD; REDUCTION Remove P/N 50L664, HPT Stage 1 Airseal Rings, observing Table 3 of the AD No piece part opportunity New limits will be applied at next piece part opportunity PW '' (-3), (-3A), or (-3B) Series Engines; PW4164, PW4164C, PW4164C/B, PW4168, and PW4168A Engine Models N (B) {Cont d} N (B) {Cont d} N N ENGINE - HPT Installation Prohibition STAGE 1 AND HPT After 10-Jan-2012, do not install any Stage 1 HPT STAGE 2 AIRSEALS Airseal, P/N 50L879, Stage 2 HPT Airseal, P/N AND HPT STAGE 1 53L030, or Stage 1 HPT Airseal Ring, P/N 50L664, AIRSEAL RINGS - that is at piece-part exposure and exceeds the new LIFE LIMITS life limit listed in Table 1, Table 2, or Table 3 of this REDUCTION AD. CERTAIN FUEL METERING UNITS (FMUS) - REPLACEMENT (f) Replacement of Affected FMUs At the next shop visit after 05-April-2012 (the effective date of this AD), remove FMU P/Ns 53T335 (HS P/N ), 55T423 (HS P/N ), and 50U150 (HS P/N ) and install an FMU that incorporates the modification in paragraphs 3.C through 3.E of the Accomplishment Instructions of Hamilton Sundstrand Alert SB JFC A24 R1. (g) Installation Prohibition After three years from 05-April-2012, do not install or re-install an FMU P/N 53T335 (HS P/N ), 55T423 (HS P/N ) or 50U150 (HS P/N ) onto any engine. No piece part opportunity New limits will be applied at next piece part opportunity FMU installed with S/N F27124 AD Closed PW '' (-3), (-3A), or (-3B) Series Engines; PW4164, PW4164C, PW4164C/B, PW4168, and PW4168A Engine Models PW " Series Engines Fitted With Fuel Metering Units (FMUs) P/Ns 53T335 (HS P/N ); 55T423 (HS P/N ) ; 50U150 (HS P/N ) Template Issue 43 Page 39 of 47 Template Issue Date: 29/04/2016

68 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC N (B) N ENGINE - NO. 4 BEARING COMPARTMENT AND OIL PRESSURE AND SCAVENGE TUBES COKING - INSPECTIONS, CLEANING, AND ENGINE MODIFICATIONS (f) Inspection and Cleaning of No. 4 Bearing Compartment for Coking (1) Within 1,000 Cycles-In-Service (CIS) after 27- April-2012 (the effective date of this AD), inspect and clean the No. 4 bearing compartment. (2) Thereafter, within every additional 1,000 CIS, reinspect and clean the No. 4 bearing compartment. (g) Modification To Stop Build-up of Coking in the No. 4 Bearing Compartment, and Re-routing of the No. 4 Bearing Pressure and Scavenge Tubes At the next engine shop visit, but not to exceed 5 years after 27-April-2012, perform the replacements and modification listed in steps (g)(1) though (g)(9) of the AD. SB Performed on 20 th May 1998 SB Performed on 20 th May 1998 SB N/A due to Post SB and AD Closed All PW " Turbofan Engines, including models with any dash number suffix, which have not incorporated the modifications introduced by SB PW , SB PW and Alert SB PW4000-A Template Issue 43 Page 40 of 47 Template Issue Date: 29/04/2016

69 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC N (B) N ENGINE - CERTAIN HPT STAGE 1 FRONT HUBS - INSPECTION / REMOVAL FROM SERVICE (f) Removal of HPT Stage 1 Front Hubs From Service (1) For HPT Stage1 Front Hubs listed in paragraph (c)(1) of this AD, do the following: (i) If the HPT Stage1 Front Hub has accumulated 17,000 or fewer cycles-since-new (CSN) on 28-Sep (the effective date of this AD), remove the HPT Stage1 Front Hub from service before accumulating 18,000 CSN. (ii) If the HPT Stage1 Front Hub has accumulated more than 17,000 CSN on 28-Sep-2012, remove the HPT Stage1 Front Hub from service before accumulating an additional 1,000 Cycles-in-Service (CIS) or at the next piece-part exposure above 18,000 CSN, whichever occurs first. (2) For HPT Stage1 Front Hubs listed in paragraphs (c)(2) and (c)(3) of this AD, do the following: (i) If the HPT Stage1 Front Hub has accumulated 12,700 or fewer CSN on 28-Sep-2012, remove the HPT Stage1 Front Hub from service before accumulating 13,700 CSN. P.T.O Part S/N (CKLBFJ9008) is recorded in SB so limit can stay at 20,000. AD Closed PW '' and PW '' Turbofan Engines. See AD for details of Models and ESNs. Template Issue 43 Page 41 of 47 Template Issue Date: 29/04/2016

70 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC N (B) {Cont d} {Cont d} N ENGINE - CERTAIN HPT STAGE 1 FRONT HUBS - INSPECTION / REMOVAL FROM SERVICE (ii) If the HPT Stage1 Front Hub has accumulated more than 12,700 CSN on 28-Sep-2012, remove the HPT Stage1 Front Hub from service before accumulating an additional 1,000 CIS or at the next piece-part exposure above 13,700 CSN, whichever occurs first. g) Installation Prohibition After 28-Sep-2012, do not install into any engine any HPT Stage1 Front Hubs listed in paragraph (c)(1) of this AD that are at piece-part exposure and exceed 18,000 CSN, or any HPT Stage1 Front Hubs listed in paragraphs (c)(2) and (c)(3) of this AD that are at piece-part exposure and exceed 13,700 CSN. Part S/N (CKLBFJ9008) is recorded in SB so limit can stay at 20,000. AD Closed PW '' and PW '' Turbofan Engines. See AD for details of Models and ESNs. (k) Material Incorporated by Reference (i) P&W ASB PW4ENG A72-821, dated July 6, (ii) P&W ASB No. PW4G-100-A72-246, dated June 28, Template Issue 43 Page 42 of 47 Template Issue Date: 29/04/2016

71 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC N (AMOC) N N Comply with this AD the next time the HPT module is removed from the engine, unless already done. (1) Remove the Stage 1 HPT Seal Support, P/N 55K601 (contained within assembly P/N 55K602-01) or P/N 50K532 (contained within assembly P/N 50K530-01), from service and replace it with a serviceable Stage 1 HPT Seal Support. (2) Remove the 1 st Stage HPT Air Seal Ring, P/N ENGINE - STAGE 1 50L664 from the engine for an FPI or ECI inspection HPT SEAL SUPPORT for cracks. If found cracked, remove the 1 st Stage HPT Air Seal Ring from service Relevant Service Information The following Service Information describe procedures for replacing the 1st stage HPT Seal Support, P/N 55K601, or P/N 50K532, with a redesigned 1 st Stage HPT Seal Support, /N 50K153. SB PW SB PW4G ENGINE - HP COMPRESSOR DRUM ROTOR DISK See AD Compliance & AD (AMOC) ASSEMBLY - INSPECTIONS AD Open At next HPT module removal. AD Open To perform at next de-blade of 13th, 14th, or 15th stage HP Compressor Drum PW '' and PW '' Turbofan Engines. PW4052, PW4056, PW4060, PW4062, PW4062A, PW4074, PW4077, PW4077D, PW4084D, PW4090, PW4090-3, PW4152, PW4156A, PW4158, PW4164, PW4168, PW4168A, PW4460, and PW4462 turbofan engines Template Issue 43 Page 43 of 47 Template Issue Date: 29/04/2016

72 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC 1. Perform the Compliance Requirements IAW paragraph (e) of the AD N N 3 RD AND 4 TH STAGE LPT VANES - INSPECTION / REMOVAL FROM SERVICE CERTAIN STAGE 3 LP TURBINE DUCT SEGMENTS - REMOVAL FROM SERVICE 2. Installation Prohibition After 07-Nov-2012 (the effective date of this AD), do not install or re-install into any engine any LPT 4th stage vanes with a P/N listed in Table 1 to paragraph (e) of this AD that are at piece-part exposure and have had more than one strip and recoat repair. Comply with this AD within the compliance times specified, unless already done. 3 rd Stage LPT Duct Segments Removal from Service At the next piece-part exposure after19 Dec-2012 (the effective date of this AD), remove from service 3 rd Stage LPT Duct Segments, P/Ns 50N095; 50N ; 50N235; 50N ; 50N494-01; 50N ; 50N495-01; and 50N Installation Prohibition After 19 Dec-2012, do not install into any engine any 3rd Stage LPT Duct Segment, P/N 50N095; 50N ; 50N235; 50N ; 50N494-01; 50N ; 50N495-01; or 50N , that is at piece-part exposure. AD Open At next Piece part opportunity AD Open Next piece part exposure (SB PART-A found previously performed on 21 st May 2011.) PW '' and PW '' Turbofan Engines PW '' Turbofan Engines Fitted With The Affected Parts Relevant Service Information SB PW R3 Template Issue 43 Page 44 of 47 Template Issue Date: 29/04/2016

73 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC FAA AD N D TIME LIMITS AND MAINTENANCE CHECKS - CERTIFICATION MAINTENANCE REQUIREMENTS - ALS PART 3 - AMENDMENT Reports of Latently Failed Fuel Shutoff Valves Discovered During Fuel Filter Replacement See AD Compliance This AD was prompted by reports of latently failed fuel shutoff valves discovered during fuel filter replacement. We are issuing this AD to detect and correct latent failures of the fuel shutoff valve to the engine and auxiliary power unit (APU), which could result in the inability to shut off fuel to the engine and APU and, in case of certain fires, an uncontrollable fire that could lead to structural failure. Within 30 days after the effective date of this AD, revise the maintenance or inspection program, as applicable, to add airworthiness limitation numbers 28-AWL-ENG, 28-AWL-MOV, and 28- AWLAPU, by incorporating the information specified in the AD. The initial compliance time for accomplishing the actions specified is within 10 days after accomplishing the maintenance or inspection program revision as detailed above. Not Applicable due to aircraft type Superseded by FAA AD A310, A and A ST aeroplanes, All MSNs This AD applies to all The Boeing Company Model , -300, - 300F, and -400ER series airplanes Template Issue 43 Page 45 of 47 Template Issue Date: 29/04/2016

74 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC FAA AD N Engine - Removal from Service of LP Turbine 4th Stage Inner Air Seal (IAS), PN 51N038 Comply with this AD within the compliance times specified, unless already done. For the affected engines: (1) At each LPT overhaul after the effective date of this AD, remove from service the LPT 4 th stage IAS, P/N 51N038. (2) At each engine shop visit after the effective date of this AD, remove from service the LPT 4th stage IAS, P/N 51N038, if it has more than 10,900 cycles since new. AD Open At next LPT overhaul All PW4050, PW4052, PW4056, PW4060, PW4060A, PW4060C, PW4062, PW4062A, PW4152, PW4156, PW4156A, PW4158, PW4160, PW4460, PW4462, and PW4650 turbofan engines including models with a ''-3'' suffix with an LPT 4th stage IAS, P/N 51N038, installed are affected by this AD. FAA AD N Reports of Latently Failed Fuel Shutoff Valves Discovered During Fuel Filter Replacement This AD was prompted by reports of latently failed fuel shutoff valves discovered during fuel filter replacement. We are issuing this AD to detect and correct latent failures of the fuel shutoff valve to the engine and auxiliary power unit (APU), which could result in the inability to shut off fuel to the engine and APU and, in case of certain fires, an uncontrollable fire that could lead to structural failure. Not Applicable due to aircraft type This AD applies to all The Boeing Company Model , -300, -300F, and -400ER series airplanes Template Issue 43 Page 46 of 47 Template Issue Date: 29/04/2016

75 PW Master Airworthiness Directive List ESN: Date: 28 th October 2016 MSN / Pos: PH-MPP / #2 Engine TSN: 84,463 Latest FAA AD issue date: 19 th October 2016 Engine Type: PW Engine CSN: 13,974 Latest EASA AD issue date: 24 th October 2016 Compilation Date: 28 th October 2016 Compilation Issue: 4 DGAC Authority Revision: 12 th October 2016 Key Code: N = New; R = Revised; D = Deleted, Superseded or Cancelled EASA No. N COMPLIANCE DGAC CN FAA AD R TITLE METHOD OF COMPLIANCE / REMARKS LAST NEXT REMARKS D DATE HRS CYC DATE HRS CYC FAA AD N Initial/Repetitive Ultrasonic Inspection of the HPC Stage 10 Disk (1) After 01/06/2016, whenever the HPT or LPT is removed from the engine, perform an ultrasonic inspection (USI) of the HPC 10th stage disk for cracks. If the HPC 10th stage disk fails the USI, perform a follow-on eddy current inspection (ECI) or remove the disk from service and replace with a part eligible for installation. (2) After the effective date of this AD, whenever the HPC front drum rotor disk assembly is removed from the engine, perform an ECI of the HPC 10th stage disk for cracks. Remove from service any HPC 10th stage disk that fails inspection and replace with a part eligible for installation. A USI as required by (1) is not required if an ECI is performed. AD Open At next HPT/ LPT removal Effective 1 st June 2016 Applicable to PW4050, PW4052, PW4056, PW4060, PW4060A, PW4060C, PW4062, PW4062A, PW4152, PW4156, PW4156A, PW4158, PW4160, PW4460, PW4462, and PW4650 with affected parts installed. END OF AD STATUS CLICK HERE TO SEE ACTIVE EASA PADs & FAA NPRMs Template Issue 43 Page 47 of 47 Template Issue Date: 29/04/2016

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80 I. Approving National Aviation Form Tracking Number Authority/Country AUTHORISED RELEASE CERTIFICATE FANrC/A2011/237 C F AA/UNl'rED STATES FAA Form , AIRWORTHINESS APPROVAL TAG 4. Organization Name and Address: 5. Work Order/Contract/Invoice Number: EAGLE SERVICES ASIA.. 51 Calshot Road Singapore (E33Y1660) SALES ORDER NO: E Item: 7. Description: 8. Part Number: 9.. Eligibility: * 10. Quantity: II. SeriallBatch Number: 12. StatusIWork 01 PRATT & WHITNEY ENGINE PW4056 (-3) NA 1 P724307CN REPAIRED 13. Remari<s! ENGINE REPAIRED, TESTED AND PRESERVED FOR A PERIOD OF MORE THAN 60 DAYS AS PER METHOD II law. PRATT & WHITNEY ENGINE MANUAL PN: 50A605 REV 95 DATED MAY 01, ALL WORK CONDUCTED law. PW INCH MAINTENANCE PLANNING GUIDE PIN: 51A772 REV DATE: 03/31/11. REFER TO SWA FOR INFORMATION ON LIFE LIMITED PART, SB, len AND AD COMPLIANCE. TSN: 75441: HOURS CSN: 12181CYCLES NOTE: ALL ITEMS LISTED IN GEN/10 MUST BE ACCOMPLISHED PRIOR TO INSTALLATION I OPERATION. "',,"~.,"",. "0"",".,,"'''''' _"".""M""""~ ),9. I2J 14 CFR 43.9 Return to Service D Other regulation specified in B1ocl< 13 D Approved design data and are in a condition for safe condition, Certifies that unless otherwise specified in Block 13, the worl< identified in Block 12 and described in Block 13 was accomplished in accordance with Title 14, Code of Federal Regulations, part 43 and in D Non~approved design data specified in Block 13.. respect to that work, the items are approved for return to service. IS. Authorized Signatures: ~proval/authorization No.: 20. Authorized Signature: /7 21. Approval/Certificate No.: I~ ~~ E33Y Date (m/d/y) 22. Name (Typed o~ Printed): 23. Date (m/d/y): UserlInstaller Responsibilities It is important to :"J:nderstand that the existence of this document alone does not automatically constitute authority tq install the part/component/assembly..' ONG MENG SOON MAY 28,2011 \Vhere the user/installer works in accordance with the national regulations of an airworthiness authority different than the airworthiness authority of the country specified in Block 1, it is essential that the user/installer ensures that his/her airworthiness authority accepts parts/component/assemblies from the airworthiness authority of the country specified in Block 1. Statements in Blocks 14 and 19 do not constitute installation certification. In all cases the aircraft maintenance records must contain an installation certification issued in accordance with the national regulations by the user/installer before the aircraft may be flown ~ -_ J,..r.n~' nr n,",,ro.., \....-.,... ",n..,...,~,..."'...,

81 AUTHORISED RELEASE CERTIFICATE EASA EASA FORM 1 1. Approving Competent Authority/Country Organisation Name and Address: 3, Form Tracking Number EASAffC/A2011n8 5. Work Order/Contract/Invoice SALES ORDER NO: EAGLE SERVICES ASIA 51 Calshot Road Singapore E Item 7. Description 8. Part No. 9. Quantity 10. Serial No. 11. StatusIWork 01 PRATT & WHITNEY ENGINE PW4056 (-3) 1 P724307CN REPAIRED, -. ls 12. Remarks ENGINE REPAIRED, TESTED AND PRESERVED FOR A PERIOD OF MORE THAN 60 DAYS AS PER METHOD lll.a.w. PRATT & WHITNEY ENGINE MANUAL PN: 50A605 REV 95 DATED MAY 01, ALL WORK CONDUCTED law. PW INCH MAINTENANCE PLANNING GUIDE PIN: 51A772 REV DATE: 03/31/11. REFER TO SWA FOR INFORMATION ON LIFE LIMITED PART, SB, len AND AD COMPLIANCE. TSN: HOURS CSN: 12181CYCLES NOTE: ALL ITEMS LISTED IN GENI10 MUST BE ACCOMPLISHED PRIOR TO INSTALLATION I OPERATION. '''o.~"~ '".~".'"~.~.._"._~ D approved design data and are in a condition for safe condition D non-approved design data specified in block b. Authorised Signature ~ ~ USER/INSTALLER RESPONSIBILITIES This certificate does not automatically constitute authority to install the item(s). 14a. t8:l Part-14S.A.SO Release to Service o Other regulation specified in block 12 Certifies that unless othelwise specified in block 12,' the work identified in block 11 and described in block 12 was accomplished in accordance with Part 145 and in respect to that work, the items are considered ready for release to service. ~pproval/authorisation Number 14b. Authorised Signatu~ ~ 14c. Certificate/Approval Ref. No.. -ff':!t /7'!P EASA e. Date (dd mmm yyyy) 14d. Name 14e. Date (dd mmm yyyy) ONG MENG SOON 28 MAY 2011 Where the user/installer performs work in accordance with the regulations of an airworthiness authqrity different from the airworthiness authority specified in block 1, it is essential that the userlinstaller ensures that his/her airworthiness authority accepts items from the airworthiness authority specified in block 1. Statements in block 13a and 14a do not constitute installation certification. In all cases the aircraft maintenance records must contain an installation certification issued in accordance with the national regulations by the user/installer before the aircraft may be flown.. COpy OF ORIGINAL (NOTTO BE USED AS AN ORIGINAL) EASA Form 1 - MF/145 Issue 2 CONSIGNEE'S COPY ESAQ 002 R6 (03/2010)

82 FORM ers SUMMARY OF WORK ACCOMPLISHED EJ.\GLE SER'ViCES A.S/A Model: PW4056 (-3) ESN: P724307CN TSN: CSN: SID: E Customer Order No: R Customer: MARTINAIR 1) HOURS/CYCLES REMAINING FOR LIFE LIMITED PART OR MODULE WITH LOWEST REMAINING LIFE: 2) FPIIAW ASB NOT APPLICABLE TO DIFFUSER CASE PIN: 50J , 3586 CYCLES REMAINING - SEAL-AIR, LPT, 4 STAGE The above engine has been released after Inspection, Repair, Modification, Module Replacement and Testing in accordance with the specifications and recommendations of the Manufacturer and other approved procedures and is passed as serviceable. Detailed records of work carried out are maintained by the Technical Records Section. This document contains: - 1. Summary of Work Accomplished. 2. Engine Life Limited Parts. 3. Modules Status. 4. Engine Components Removed and Installed. 5. Fan Blades Moment Weight Record. 6. Shop Out Modification Status. 7. len Status. 8. Airworthiness Directives Compliance. 9. Recordable Tracked Parts. 10. Engine Test Report. 11. Engine FAA Form Engine EASA Form One. Verified By: /\~~ Approval Ref: AWI/166 Date: 28-May-2011 Date of Revision: - {REV NO: O} Page 1 of 1

83 FORM ers 100-1; SUMMARY OF WORK ACCOMPLISHED Model: PW4056 (-3) TSN: S/O: E Customer Order No: R Eagle Services ASIA ESN: P724307CN CSN: Customer: MARTINAIR Position: Removed At: Reason for Removal: No.2 Ex-Aircraft Regn: D-ACGC Date Removed: UNK Time/Cycles Since Last Visit: 20329/3684 Date of Shop Visit: STAGE 2 NGV DISTRESS 16 Feb Mar2011 THE ENGINE WAS INSPECTED, REPAIRED, REPLACED, MODIFIED AND TESTED IN ACCORDANCE WITH PRATI & WHITNEY ENGINE MANUAL PIN: 50A605 REVISION 95 DATED MAY 01,2011. ALL WORK CONDUCTED law PW INCH MAINTENANCE PLANNING GUIDE PIN: 51A772 REV DATE: 03/31/ THE FOLLOWING MODULES AND ASSEMBLY WERE RE-INSTALLED AFTER HEAVY MAINTENANCE:- a) DIFFUSER CASE b) TURBINE NOZZLE ASSY c) HIGH PRESSURE TURBINE 2. THE FOLLOWING MODULES WERE RE-INSTALLED AFTER CHECK AND REPAIR:- a) LOW PRESSURE COMPRESSOR b) HIGH PRESSURE COMPRESSOR c) LOW PRESSURE TURBINE d) MAIN GEARBOX 3. THE FOLLOWING MODULES WERE MODULE LEVEL INSPECTION:- a) LPCILPT COUPLING b) FAN CASE c) INTERMEDIATE CASE d) ANGLE GEARBOX 4. THE TURBINE EXHAUST CASE WAS REPLACED WITH HEAVY MAINTENANCE. 5. THE BELL-CRANK ASSY WAS VISUAL INSPECTION. 6. MAIN BEARINGS :- a) #1 AND #3 WERE RE-INSTALLED AFTER OVERHAUL. b) #1 AND #1.5 WERE VISUAL INSPECTION. c) #4 WAS REPLACED WITH OVERHAUL. 7. THE FORWARD MOUNT ASSEMBLY WERE RE-INSTALLED AFTER OVERHAUL. Detailed records of work carried out are maintained by the Technical Records Section. Verified By: f& ~ Approval Ref: AWI/166 Date of Original Issue: 28-May-2011 Date of Revision: LEE THIAM YEW QUALITY ENGINEER R501 DEC 2005

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