Turbomeca Turbines - Civil Aviation Authority of New Zealand
Airworthiness Directive Schedule Engines Turbomeca Turbines 29 January 2015 Notes 1. This AD schedule is applicable to Turbomeca turbine engines manufactured under the following Type Certificate Numbers: Helicopter Model: Arriel 1B Arriel 1C Arriel 1D Arriel 1D1 Arriel 2B Arriel 2B1 Arriel 2D Arriel 2E Arrius 1A Arrius 1A1 Astazou III Arrius 2F Artouste IIIB Type Certificate Number: EASA E.073 EASA E.073 EASA E.073 EASA E.073 EASA E.001 EASA E.001 EASA E.001 EASA E.001 EASA E.080 EASA E.080 EASA E.071 DGAC M22 DGAC M12 2. The European Aviation Safety Agency (EASA) is the National Airworthiness Authority (NAA) responsible for the issue of State of Design Airworthiness Directives (ADs) for Turbomeca turbine engines. State of Design ADs applicable to these engines can be obtained directly from the EASA web site. The link to the EASA web site is available on the CAA web site at http://www.caa.govt.nz/Airworthiness_Directives/states_of_design.html 3. The date above indicates the amendment date of this schedule. 4. New or amended ADs are shown with an asterisk * Contents DCA/TUR/1 DCA/TUR/2A DCA/TUR/3 DCA/TUR/4 DCA/TUR/5B DCA/TUR/6A DCA/TUR/7 DCA/TUR/8C DCA/TUR/9B DCA/TUR/10 DCA/TUR/11 DCA/TUR/12 DCA/TUR/13 DCA/TUR/14A DCA/TUR/15A DCA/TUR/16A DCA/TUR/17 DCA/TUR/18 DCA/TUR/19 DCA/TUR/20 Condition Monitoring System - Modification ...................................................................... 4 Electric Fuel Valve - Modification ...................................................................................... 4 Turbine Case - Identification Plate Removal And Modification ......................................... 4 Gas Generator Rear Bearing Oil Pipe - Modification ........................................................ 4 Cancelled – DCA/TUR/82 refers ....................................................................................... 5 Reduction Gear Module - Inspection, Modification and Removal ..................................... 5 Free Wheel Assembly - Modification ................................................................................ 5 Second Stage Nozzle Guide Vanes - Inspection and Modification ................................... 5 Free Power Turbine - Containment Modifications ............................................................. 6 Overspeed Sensor - One Time Inspection ........................................................................ 6 Gas Generator Rear Bearing Chip Detector - Installation ................................................. 7 Cancelled – Purpose Fulfilled ........................................................................................... 7 Power Turbine Nozzle Assembly - Inspection................................................................... 7 Cancelled – DCA/TUR/20 now refers ............................................................................... 7 Cancelled – DCA/TURN/21 now refers ............................................................................. 7 Cancelled – DCA/TUR/86 refers ....................................................................................... 7 Fuel Pump Body - Inspection ............................................................................................ 7 Fuel Control Unit - Modification......................................................................................... 8 Cancelled – Superseded by DCA/TUR/36 ........................................................................ 8 Centrifugal Impeller - Modification .................................................................................... 8 Issued 29 January 2015 Page 1 of 36 CAA of NZ DCA/TUR/21 DCA/TUR/22 DCA/TUR/23 DCA/TUR/24 DCA/TUR/25A DCA/TUR/26B DCA/TUR/27 DCA/TUR/28 DCA/TUR/29 DCA/TUR/30 DCA/TUR/31 DCA/TUR/32 DCA/TUR/33 DCA/TUR/34 DCA/TUR/35 DCA/TUR/36 DCA/TUR/37 DCA/TUR/38 DCA/TUR/39 DCA/TUR/40 DCA/TUR/41 DCA/TUR/42 DCA/TUR/43A DCA/TUR/44 DCA/TUR/45 DCA/TUR/46 DCA/TUR/47 DCA/TUR/48 DCA/TUR/49 DCA/TUR/50A DCA/TUR/51 DCA/TUR/52 DCA/TUR/53 DCA/TUR/54 DCA/TUR/55 DCA/TUR/56A DCA/TUR/57 DCA/TUR/58 DCA/TUR/59 DCA/TUR/60 DCA/TUR/61 DCA/TUR/62 DCA/TUR/63 DCA/TUR/64 DCA/TUR/65A DCA/TUR/66 DCA/TUR/67 DCA/TUR/68A DCA/TUR/69 DCA/TUR/70D DCA/TUR/71 DCA/TUR/72 DCA/TUR/73 DCA/TUR/74 DCA/TUR/75 Centrifugal Impeller - Modification .................................................................................... 9 Second Stage Turbine Blade - Replacement.................................................................... 9 Engine Operation - Limitation ........................................................................................... 9 Fuel Control System – Software Upgrade....................................................................... 10 Cancelled - DCA/TUR/43 refers ...................................................................................... 10 nd Arriel 2 Stage NGV - Inspection ................................................................................... 10 Cancelled - DCA/TUR/44 refers ...................................................................................... 10 High Pressure Turbine – Inspection and Repair ............................................................. 11 Fuel Control Unit Fuel Filter - Inspection ........................................................................ 11 Cancelled – DCA/TUR/39 refers. .................................................................................... 11 Cancelled - DCA/TUR/41 refers ...................................................................................... 11 Cancelled – DCA/TUR/40 refers. .................................................................................... 11 Free Turbine Containment Shield – Inspection and Replacement ................................. 12 Cancelled - DCA/TUR/46 refers ...................................................................................... 12 Cancelled - DCA/TUR/45 refers ...................................................................................... 12 Turbine Shaft Labyrinth – Inspection and Replacement ................................................. 12 Start Electro Fuel Valve Leaks – Inspection and Repair................................................. 13 Flexible Fuel Pipe – Inspection and Replacement .......................................................... 13 Oil Check-valve Piston O-ring – Inspection and Replacement ....................................... 13 Oil Check-valve Piston O-ring – Inspection and Replacement ....................................... 14 Fuel Control Unit Constant Delta Pressure Valve Diaphragm – Modification ................. 14 Cancelled – DCA/TUR/52 refers ..................................................................................... 14 Cancelled – DCA/TUR/68 refers ..................................................................................... 14 Cancelled – DCA/TUR/69 refers ..................................................................................... 14 Engine Fuel Pump Maximum Flow – Inspection and Replacement ................................ 15 Cancelled – EASA AD 2013-170 refers .......................................................................... 16 Engines Returned to Civil Use – Conformity Inspection and Rework ............................. 16 Gas Generator Front Bearing - Modification ................................................................... 16 Cancelled – DCA/TUR/85 refers ..................................................................................... 16 Module 03 Turbine – Inspection and Replacement ........................................................ 17 Engines Returned to Civil Use – Conformity Inspection and Rework ............................. 17 Cancelled – DCA/TUR/64 refers ..................................................................................... 18 Cancelled – DCA/TUR/81 refers ..................................................................................... 18 HMU Low Fuel Pressure Switch – Inspection and Replacement .................................... 18 Balancing Piston – Life Limit Reduction ......................................................................... 19 Cancelled – DCA/TUR/77 refers ..................................................................................... 19 Fuel Injection System – Modification .............................................................................. 19 Fuel Injectors – Replacement ......................................................................................... 19 Turbine Overspeed Protection System – Inspection ....................................................... 20 Lubrication Unit – Modification ........................................................................................ 20 Reduction Gearbox Intermediate Pinion – Modification .................................................. 20 Cancelled – DCA/TUR/65 refers ..................................................................................... 21 Cancelled – DCA/TUR/67 refers ..................................................................................... 21 Cancelled - EASA AD 2013-0171 refers ......................................................................... 21 Module 04 Power Turbine – Life Limitation and Replacement........................................ 21 Cancelled – DCA/TUR/73 refers ..................................................................................... 22 Module M05 Reduction Gearbox – Inspection and Repair ............................................. 22 Cancelled – DCA/TUR/87 refers ..................................................................................... 23 HMU Acceleration Control Axle – Inspection and Modification ....................................... 23 Gas Generator 2nd Stage Turbine – Reduced Life Limit ................................................ 24 Cancelled – DCA/TUR/75 refers ..................................................................................... 24 Cancelled – DCA/TUR/80 refers ..................................................................................... 24 HP/LP Pump Metering Unit – Inspection and Replacement ........................................... 24 Fuel Ejector Assembly – Inspection and Rework ............................................................ 26 nd Module M03 2 Stage Nozzle Guide Vanes – Inspection and Replacement ................. 27 Issued 29 January 2015 Page 2 of 36 CAA of NZ Hydromechanical Metering Unit (HMU) – Inspection and Replacement ......................... 29 DCA/TUR/76 DCA/TUR/77A P3 Air Pipe – Inspection and Modification ...................................................................... 30 DCA/TUR/78 Cancelled – EASA AD 2012-0249 refers ........................................................................ 31 DCA/TUR/79 Module M04 PT Blades – Life Limitation......................................................................... 31 DCA/TUR/80 Cancelled – DCA/TUR/84 refers ..................................................................................... 32 DCA/TUR/81 FCU 3-Way Union Plug – Inspection .............................................................................. 32 DCA/TUR/82 Gas Generator Rotating Assembly - Inspection, Cleaning and Replacement ................ 32 DCA/TUR/83 Gas Generator Rotating Assembly – Inspection and Replacement................................ 33 DCA/TUR/84 Cancelled – EASA AD 2012-0124R1 refers ................................................................... 33 DCA/TUR/85 Digital Engine Control Unit – Software Modification........................................................ 33 DCA/TUR/86A Privilege Injectors – Replacement .................................................................................. 34 DCA/TUR/87 Gas Generator 2nd Stage Turbine – Inspection and Replacement ................................ 34 DCA/TUR/88 Cancelled – EASA AD 2013-0079 refers ........................................................................ 35 DCA/TUR/89 Cancelled – EASA AD 2012-0187R1 refers ................................................................... 35 From 1 October 2012 the Civil Aviation Authority of New Zealand (CAA) will no longer rewrite the text of State of Design ADs. Applicable State of Design ADs will be listed below and can be obtained directly from the National Airworthiness Authority (NAA) web site. The link to the NAA web site is available on the CAA web site at http://www.caa.govt.nz/Airworthiness_Directives/states_of_design.html If additional NZ ADs need to be issued when an unsafe condition is found to exist in an aircraft or aeronautical product in NZ they will be added to the list below............................................................................................. 36 2012-0124R1 Module M03 Gas Generator Turbine Blade – Modification ............................................. 36 2012-0187R2 Engine Cycle Counting Aid System – Modification/Amendment ..................................... 36 2012-0249 Airworthiness Limitations – Amendment/Implementation ............................................... 36 2013-0079R1 Hydro-mechanical Metering Unit – Replacement ........................................................... 36 2013-0082 Hydro-Mechanical Metering Unit – Inspection and Replacement ................................... 36 2013-0120 Free Turbine Bearing Plug – Inspection and Rework ..................................................... 36 2013-0170 Hydro-mechanical Metering Unit – Inspection and Replacement ................................... 36 2013-0171 HMU Constant Delta Pressure Valve Diaphragm – Replacement ................................. 36 2013-0243 Ejector Assembly Nozzle – Inspection ............................................................................ 36 2014-0036 Accessory Gearbox (M01) 41/23 Tooth Bevel Gear Assembly – Inspection and Replacement ................................................................................................................... 36 2014-0036 Accessory Gearbox (M01) – 41/23 Tooth Bevel Gear Assembly – Inspection ............... 36 Issued 29 January 2015 Page 3 of 36 CAA of NZ Engines DCA/TUR/1 Turbomeca Turbines Condition Monitoring System - Modification Applicability: All Arriel 1B engines not incorporating Mod. TU49. Requirement: Modify per Arriel Turbomeca SB 72-292-0021. (BV AD 79-254-12(B) refers) Compliance: By 31 March 1980 Effective Date: 22 February 1980 DCA/TUR/2A Electric Fuel Valve - Modification Applicability: Artouste III series engines Requirement: To prevent power loss due to partial closing of the fuel valve, modify as follows: Artouste III D; per Turbomeca SB 218 80 0098 (Mod TU 164), Artouste III B and B1; per Turbomeca SB 218 80 0093 (Mod TU 167). Until modified, the engine operating cycle (start up to shut down) is limited to a maximum of 2 hours. (DGAC AD 1999-005(A) refers) Compliance: By 1 January 2000. Effective Date: DCA/TUR/2 - 29 July 1988 DCA/TUR/2A - 12 March 1999 DCA/TUR/3 Turbine Case - Identification Plate Removal And Modification Applicability: All Arriel 1A, 1A1, 1A2, 1B, 1C, 1C1, 1D, 1K and 1M. Requirement: Remove identification plate and inspect turbine casing per Turbomeca SB Arriel 72.292.0093. (BV AD 86-29(B) refers) Compliance: Effective Date: DCA/TUR/4 Turbine cases with more than 2000 hours TTIS or 5 years from new, unless already accomplished: 1. Arriel 1B - within next 100 hours TIS or two months, whichever is the sooner. 2. All other variants - within next four months. 29 July 1988 Gas Generator Rear Bearing Oil Pipe - Modification Applicability: All Arriel 1A, 1A1, 1A2, 1B, 1C, 1C1 and 1M not incorporating Mod. TU144. Requirement: To prevent a failure which could result in an oil fire, modify per Turbomeca SB Arriel 72.292.0088. (BV AD 86-147(B) refers) Compliance: By 31 October 1988 Effective Date: 29 July 1988 Issued 29 January 2015 Page 4 of 36 CAA of NZ Engines DCA/TUR/5B Effective Date: DCA/TUR/6A Turbomeca Turbines Cancelled – DCA/TUR/82 refers 31 May 2012 Reduction Gear Module - Inspection, Modification and Removal Applicability: All Arriel 1A, 1A1, 1B, 1D and 1D1. Requirement: To prevent deterioration of the intermediate pinion in the reduction gear module, power turbine overspeed and uncontained failure accomplish the following:1. Inspect the reduction gearbox (MO 5) magnetic plug per Turbomeca SB 292 72 0157. 2. Modify gearboxes to TU 39 standard per SB 292 72 0157. 3. Remove from service the following reduction gearbox modules if the TIS since last overhaul or repair is less than 200 hours, and the last overhaul or repair was performed before 1 June 1992. MO 5 S/Ns; 120, 178, 182, 197, 244, 280, 354, 379, 500, 589, 628, 629, 643, 2030, 2074, 2219, 2326, 2334, 2469, 2484, 2651 and 2686. (BV AD92-078(B)R2 refers) Compliance: 1. Inspect magnetic plug at intervals not exceeding 5 hours TIS or after the last flight of the day at the latest. 2. By 31 October 1992. 3. By 1 October 1993. Effective Date: DCA/TUR/6 - 16 May 1992 DCA/TUR/6A - 3 September 1993 DCA/TUR/7 Free Wheel Assembly - Modification Applicability: All Arriel 1B, 1D and 1D1. Requirement: To prevent premature wear of the free wheel during desynchronized operation, incorporate modification TU 221 per Turbomeca SB 292 72 0146. (BV AD 91-156(B)R1 refers) Compliance: By 30 June 1992 Effective Date: 16 May 1992 DCA/TUR/8C Second Stage Nozzle Guide Vanes - Inspection and Modification Applicability: Arriel 1 all variants Requirement: To detect deterioration of the gas generator second stage turbine nozzle guide vane, accomplish the following:1. For engine models Arriel 1A, 1A1, 1A2 and 1B post-mod TU 76 and pre-mod TU 197 or TU 202. Arriel 1C, 1C1, 1C2, 1D, 1D1, 1S, 1K, and 1K1 pre-mod TU 197 or TU 202. Check for unusual noise during gas generator run-down per Turbomeca SB 292 72 0181 Rev 3. If a rubbing noise is detected in the M03 module, remove the M03 from service before further flight. Any module from Arriel 1B, 1D, 1D1 which have TU 76 and which have not TU 197 or TU 202 must not be used. Issued 29 January 2015 Page 5 of 36 CAA of NZ Turbomeca Turbines 2. For all Arriel 1 variants post-mod TU 197. Perform inspections and actions per Turbomeca SB 292 72 0212 Rev 4. (DGAC AD 98-311(A) R1 refers) Compliance: 1. Inspect as detailed per Turbomeca SB 292 72 0181 Rev 3. 2. As detailed per Turbomeca SB 292 72 0212 Rev 4. Note: Daily inspections may be accomplished by pilot subject to: (a) Adequate instruction by the engineer responsible for the maintenance of the aircraft. (b) Certificate of Release to Service endorsed to refer to inspection requirement. (c) Copy of Turbomeca SB is attached to the Certificate of Release to Service. Effective Date: DCA/TUR/9B Applicability DCA/TUR/8B - 9 May 1997 DCA/TUR/8C - 28 August 1998 Free Power Turbine - Containment Modifications Arriel 1A, 1A1, 1B, 1D, 1D1 which incorporate the following modifications:Arriel 1A, 1A1 with TU 13 and without TU 215 or TU 254 or TU 255. Arriel 1B, 1D, 1D1 without TU 215 or TU 254 or TU 255. Requirement: To prevent uncontained failure as the result of power turbine overspeed, incorporate the SBs listed in the following table. ARRIEL VERSION and CONFIGURATION 1A 1A1 modified TU 13 and not modified TU 99 and not modified TU 215 1B 1D not modified TU 99 and not modified TU 215 1A 1A1 modified TU 13 and modified TU 99 and not modified TU 215 1B 1D 1D1 SB TO BE INCORPORATED 292-72-0206 (TU 254) and 292-72-0208 (TU 259) 292-72-0207 (TU 255) and 292-72-0208 (TU 259) modified TU 99 and not modified TU 215 (BV AD 95-069(A)R3 refers) Compliance: By 30 April 2001. Effective Date: DCA/TUR/9A - 1 September 1995 DCA/TUR/9B - 29 March 2001 DCA/TUR/10 Overspeed Sensor - One Time Inspection Applicability: Arriel 1A and 1A1 not modified to TU13 standard. Arriel 1A2, 1C, 1C1, 1C2, 1E, 1E2, 1K, 1K1, 1S and 1S1. Requirement: To ensure correct operation of the free power turbine overspeed sensor, inspect per Turbomeca SB 292 77 0194 Rev 1. Correct any defects found before further flight. Issued 29 January 2015 Page 6 of 36 CAA of NZ Turbomeca Turbines (DGAC AD 94-218(B) refers) Compliance: By 9 June 1997, unless already accomplished. Effective Date: 9 May 1997 DCA/TUR/11 Gas Generator Rear Bearing Chip Detector - Installation Applicability: Arriel 1 all variants Requirement: To provide a means of warning the pilot of gas generator rear bearing deterioration, embody modification TU208 per Turbomeca SB 292.72.0163 Rev 1. (DGAC AD 98-394(A) refers) Compliance: By 12 June 1999 Effective Date: 12 March 1999 DCA/TUR/12 Cancelled – Purpose Fulfilled DCA/TUR/13 Power Turbine Nozzle Assembly - Inspection Applicability: Arriel 1 variants 1A, 1A1, 1A2, and 1B fitted with a non mod TU 38 power turbine nozzle assembly. Requirement: To detect cracks on the rear bearing support which could lead to an in-flight engine shut down, inspect per Turbomeca SB 292 72 0213. If a crack is detected replace the nozzle guide vane per SB 292 72 0213. (DGAC AD 98-493(A) refers) Compliance: By 30 April 1999 Effective Date: 12 March 1999 DCA/TUR/14A Cancelled – DCA/TUR/20 now refers DCA/TUR/15A Cancelled – DCA/TURN/21 now refers DCA/TUR/16A Cancelled – DCA/TUR/86 refers Effective Date: DCA/TUR/17 30 August 2012 Fuel Pump Body - Inspection Applicability: All Arriel 2S1, 2B and 2C. Requirement: To prevent fuel seepage from the fuel pump body and possible engine bay fire, accomplish the following:1. Inspect engine bay floor per Turbomeca SB 292 73 2803, for presence of fuel. If fuel is detected, refer to the Maintenance Manual for rectification and perform the inspection per part 2 of this AD. 2. Inspect the area specified by SB 292 73 2803 for fuel seepage. If fuel seepage is detected, remove and replace the HP/LP pump assembly before further flight. Issued 29 January 2015 Page 7 of 36 CAA of NZ Turbomeca Turbines 3. Check the pump body material thickness per SB 292 73 2803. If the measured thickness is less than the criteria per the SB, replace the pump assembly with a pump body having correct thickness before further flight. This constitutes terminating action for this AD. (DGAC AD 1999-285(A) refers) Compliance: 1. After the last flight of each day, until part 3 of this AD is accomplished. This inspection may be accomplished by the pilot following instruction by the engineer responsible for the maintenance of the helicopter. 2. Within next 50 hours TIS and thereafter at intervals not to exceed 50 hours TIS, until part 3 of this AD is accomplished. 3. By 1 May 2000. Effective Date: DCA/TUR/18 24 September 1999 Fuel Control Unit - Modification Applicability: ARRIUS 2F engines fitted to EC 120 B helicopters and equipped with a fuel control unit (FCU) listed in Turbomeca SB A 319 73 4808. Requirement: To prevent reduction in fuel flow due to a variation in the position of the max fuel flow mechanical stop, rework the max fuel flow stop per Turbomeca SB A 319 73 4808 Issue 1. (DGAC AD 2000-482(A) refers) Compliance: By 31 March 2001. Effective Date: 21 December 2000 DCA/TUR/19 Effective Date: DCA/TUR/20 Cancelled – Superseded by DCA/TUR/36 30 March 2006 Centrifugal Impeller - Modification Applicability: All Arriel 1 series turboshaft engines Requirement: To prevent excitation of the impellor vanes leading to release of a vane and possible engine failure, accomplish the following:1. Modify Arriel 1S, 1S1, 1D, 1D1 engines by installation of a of a sleeve in the bleed valve boss, per Turbomeca SB 292 72 0261. 2. For other Arriel engine variants, on which TU 300 modification is embodied, ensure the bonding of the sleeve in the bleed valve boss, per Turbomeca SB A 292 72 0275 (Modification TU 316A). (DGAC AD 2002-126(A) refers) Compliance: Before 31 May 2002 Effective Date: 28 March 2002 Issued 29 January 2015 Page 8 of 36 CAA of NZ Turbomeca Turbines DCA/TUR/21 Centrifugal Impeller - Modification Applicability: Arriel 2 series engines Requirement: To prevent excitation of the impellor vanes leading to release of a vane and possible engine failure, accomplish the following:1. Modify Arriel 2S1, 2B engines by installation of a of a sleeve in the bleed valve boss, per Turbomeca SB 292 72 2054. 2. For other Arriel engine variants, on which TU 54 modification is embodied, ensure the bonding of the sleeve in the bleed valve boss, per Turbomeca SB A 292 72 2070 Rev 1 (modification TU 70A). (DGAC AD 2002-127(A) refers) Compliance: Before 31 May 2002 Effective Date: 28 March 2002 DCA/TUR/22 Second Stage Turbine Blade - Replacement Applicability: All Arriel 1B, 1D and 1D1 with modification TU204 embodied and installed in single engine helicopters. Requirement: To prevent failure of the gas generator 2 stage turbine blades leading to possible power loss, replace turbine blades that have been modified by TU 204 in accordance with Turbomeca SB 292 72 0258 (Arriel 1B) or SB 292 72 0265 (Arriel 1D, 1D1). nd (DGAC AD 2002-258(A) refers) Compliance: Before 31 May 2004 unless already accomplished Effective Date: 31 July 2003 DCA/TUR/23 Engine Operation - Limitation Applicability: Arrius 2B1, 2B1A, 2B1A_1/2K1 series Turboshaft engines Requirement: To ensure continued reliable operation of the engine, operation of the engine at the OEI 2.5 minute power setting is limited to 5 minutes cumulative time before the engine must be removed for checks to the Module 2. Engines that have accumulated 5 minutes or more of operation at OEI 2.5 must be inspected per Turbomeca SL 2174/02/ARRIUS 2B1/19 for 2B1, 2B1A, and 2B1A_1 variants or SL 2175/ARRIUS 2K1/3 for the 21B1A-2K1 variants. (DGAC AD 2003-98 refers) Compliance: Before further flight Effective Date: 30 October 2003 Issued 29 January 2015 Page 9 of 36 CAA of NZ Turbomeca Turbines DCA/TUR/24 Fuel Control System – Software Upgrade Applicability: Arrius 2B1, 2B1A, 2B1A_1 and 2B2 series turboshaft engines Requirement: To prevent the possible simultaneous transition of both engines to manual control, which in certain phases of flight could prove difficult for the pilot to control, install fuel control system software upgrades per the applicable SB listed below: 2B1 with overspeed option without overspeed option 2B1A, 2B1A_1 2B2 SB 319 732080R1 SB 319 732081R1 SB 319 732082R1 SB 319 732090 (DGAC AD F-2004-017R1 refers) Compliance: Before 30 June 2004. Effective Date: 25 March 2004 DCA/TUR/25A Effective Date: DCA/TUR/26B Cancelled - DCA/TUR/43 refers 22 February 2007 Arriel 2 nd Stage NGV - Inspection Applicability: Arriel 1B, 1D and 1D1 turboshaft engines with modification TU202 embodied and installed in single engine helicopters, except those with S/N or marks as detailed in Turbomeca SB 292 72 0231 revision 5. Requirement: To detect and prevent deformation of the 2 Stage NGV that may produce a wake nd that leads to damage and failure of the 2 stage turbine blades and possibly cause an nd uncommanded in-flight shutdown, inspect the 2 stage NGV per Turbomeca SB 292 72 0231 revision 5. nd (EASA AD 2007-0002 refers and supersedes DGAC AD 2004-088 R1) Compliance: At next exposure of the 2nd stage NGV during deep level maintenance or at the next visit of the engine module to a repair centre, or before 31 May 2007 whichever occurs sooner. Effective Date: DCA/TUR/26 - 30 Sept 2004 DCA/TUR/26A - 27 July 2006 DCA/TUR/26B - 25 January 2007 DCA/TUR/27 Effective Date: Cancelled - DCA/TUR/44 refers 22 February 2007 Issued 29 January 2015 Page 10 of 36 CAA of NZ Turbomeca Turbines DCA/TUR/28 High Pressure Turbine – Inspection and Repair Applicability: ARRIUS 2F engines fitted to Eurocopter EC120B helicopters, with number 2 modules as listed in Turbomeca Alert Fax 057/05/DSO/TM, dated 26 April 2005. Requirement: To prevent HP turbine blade separation from the HP disk, accomplish a deep turbine inspection/rework to confirm the standard of the ferrule or after replacing module 2. (DGAC AD UF-2005-073 R1 refers) Compliance: Before further flight. Effective Date: 2 May 2005 DCA/TUR/29 Fuel Control Unit Fuel Filter - Inspection Applicability: All ARRIUS 2F engines fitted to EC 120B aircraft. Requirement: To prevent limitation of the fuel flow downstream of the FCU fuel filter, which could limit maximum available power, remove the filter holder assembly and check that the adjusted filter is in the correct position by performing a dimensional check, per paragraph 2 of Mandatory Alert SB A319 73 4823 Note: Repeat above mentioned requirement every time the position of the adjusted FCU fuel filter element is checked (task 73-23-06-201-801 of the ARRIUS 2F Maintenance Manual) according to the frequency defined for this task in chapter 05-20-00 of the ARRIUS 2F Maintenance Manual. (DGAC AD F-2005-088 refers) Compliance: Within next 25 hours TIS or by 29 July 2005, whichever is the later. Effective Date: 30 June 2005 DCA/TUR/30 Effective Date: DCA/TUR/31 Effective Date: DCA/TUR/32 Effective Date: Cancelled – DCA/TUR/39 refers. 29 June 2006 Cancelled - DCA/TUR/41 refers 30 November 2006 Cancelled – DCA/TUR/40 refers. 29 June 2005 Issued 29 January 2015 Page 11 of 36 CAA of NZ Turbomeca Turbines DCA/TUR/33 Free Turbine Containment Shield – Inspection and Replacement Applicability: Arriel 2B and 2B1 engines fitted to Eurocopter AS 350 B3 and EC 130 helicopters and which do not have modification TU 22 embodied. Requirement: Inspect the free turbine containment shield per paragraph 2 of Turbomeca Mandatory Service Bulletin No 292 72 2821. The free turbine containment shield must be replaced if the length or position of the crack(s) exceeds the criteria laid down in paragraph 2 of SB No. 292 72 2821. (DGAC AD F-2005-162 refers) Compliance: Within the next 10 hours TIS, and thereafter at intervals dependant on the inspection results per the inspection requirements of SB No. 292 72 2821. Effective Date: 17 October 2005 DCA/TUR/34 Effective Date: DCA/TUR/35 Effective Date: DCA/TUR/36 Cancelled - DCA/TUR/46 refers 15 March 2007 Cancelled - DCA/TUR/45 refers 22 February 2007 Turbine Shaft Labyrinth – Inspection and Replacement Applicability: Model Artouste III B, B1 and D engines. Requirement: To prevent deterioration of the turbine shaft labyrinth which may induce overheating and possibly lead to the distortion of the turbine shaft and ultimate in-flight engine shutdown, accomplish the following: 1. Inspect for smoke during engine rundown and once the engine has stopped, per the requirements in Turbomeca Alert Service Bulletin No. A218 72 0099. Depending on the inspection findings, accomplish the required actions per ASB No. A218 72 0099, before further flight. 2. Inspect the turbine shaft central labyrinth, per Turbomeca Alert Service Bulletin No. A218 72 0100. If the labyrinth is damaged, replace per the instructions in ASB No. A218 72 0100, before further flight. (DGAC AD F-2004-016 refers) Compliance: 1. After every flight, and if smoke is detected inspect the fuel system before the next flight, or after the last flight of the day, whichever is the later. (Accomplish AD by addition of note to tech log) 2. Inspect within the next 50 hours TIS, or by 30 August 2006, whichever occurs sooner, if the turbine shaft central labyrinth hours TIS are unknown, or if the hours TSN or since last inspection is greater than 1750 hours TIS, and inspect thereafter at intervals not to exceed 1750 hours TIS. Effective Date: 30 March 2006 Issued 29 January 2015 Page 12 of 36 CAA of NZ Turbomeca Turbines DCA/TUR/37 Start Electro Fuel Valve Leaks – Inspection and Repair Applicability: All Arriel 1 series engines. Requirement: To detect fuel leaks at the start electro fuel valve coupling, which could cause reduced engine power, or an uncommanded in-flight engine shutdown, inspect the start electro fuel valve for correct assembly and security of the tee coupling, per Turbomeca Service Bulletin No. A292 73 0251, revision 2 or later approved revisions. (EASA AD 2006-0068 refers) Compliance: By 1 October 2006, unless already accomplished. Effective Date: 1 June 2006 DCA/TUR/38 Flexible Fuel Pipe – Inspection and Replacement Applicability: Artouste III B and III B1 engines Requirement: To prevent fuel leakage due to the possibility of cracks on the lower union of the flexible fuel pipe between the electric fuel cock and the start valve, which if left undetected could lead to loss of engine power and pose a fire hazard, inspect per Turbomeca Mandatory Service Bulletin No. A218 73 0803. Remove fuel pipe P/N 0 202 12 800 0 and inspect the lower union of the fuel pipe (start electro-valve side) for cracks, per the instructions in MSB No. A218 73 0803. Replace if cracked, per MSB No. A218 73 0803 before further flight. (EASA AD 2006-0154 refers) Compliance: Within the next 50 hours TIS, or at the next engine/airframe maintenance operation, or by 29 August 2006, whichever occurs the sooner. Effective Date: 29 June 2006 DCA/TUR/39 Oil Check-valve Piston O-ring – Inspection and Replacement Applicability: Arrius 2F engines which do not have Tf75 embodied, and fitted to EC 120B aircraft. Requirement: To prevent uncommanded in-flight engine shutdown, replace the o-rings on the lubrication unit check-valve piston, per paragraph 2 of Turbomeca Mandatory Alert Service Bulletin No A319 79 4802. (EASA AD 2006-0141 refers) Compliance: For engines operating with STD class-oil since their introduction into service: Within next 50 hours TIS, for engines with more than 450 hours TTIS, unless already accomplished, and thereafter at intervals not to exceed 500 hours TIS. For engines operating with HTS-class oil and engines for which the history of the oils used is not available or engines which used to operate with HTS-class oil and which no longer do so: Within next 50 hours TIS for engines with more than 300 hours TTIS, unless already accomplished, and thereafter at intervals not to exceed 300 hours TIS. Note: Standard (STD) and High Thermal Stabilty (HTS) oils are listed in the engine maintenance manual section 71-00-03. Effective Date: 29 June 2006 Issued 29 January 2015 Page 13 of 36 CAA of NZ Turbomeca Turbines DCA/TUR/40 Applicability: Oil Check-valve Piston O-ring – Inspection and Replacement Arrius 2B1, 2B1A, 2B1A_1, 2B2, 2K1 and 2K2 engines which do not have modification Tu122 embodied. These engines may be fitted to, but not limited to, EC135 T1, EC135 T2, A 109 and A 109 LUH aircraft. Requirement: To prevent uncommanded in-flight engine shutdown, replace the o-rings on the lubrication unit check-valve piston, per paragraph 2 of Turbomeca Mandatory Alert Service Bulletin No A319 79 2832, update No. 1 for Arrius 2 B series engines, or Turbomeca Mandatory Alert Service Bulletin No A319 79 2833, update No. 1 for Arrius 2K series engines. (EASA AD 2006-0142 refers) Compliance: For engines operating with STD class-oil since their introduction into service: Within next 50 hours TIS for engines with more than 450 hours TTIS, unless already accomplished, and thereafter at intervals not to exceed 500 hours TIS. For engines operating with HTS-class oil and engines for which the history of the oils used is not available or engines which used to operate with HTS-class oil and which no longer do so: Within next 50 hours TIS for engines with more than 300 hours TTIS, unless already accomplished, and thereafter at intervals not to exceed 300 hours TIS. Note: Standard (STD) and High Thermal Stabilty (HTS) oils are listed in the engine maintenance manual section 71-00-03. Effective Date: 29 June 2006 DCA/TUR/41 Fuel Control Unit Constant Delta Pressure Valve Diaphragm – Modification Applicability: All Arrius 2F turbo-shaft engines installed on EC120B aircraft. Requirement: To prevent an increase in fuel flow which can result in an engine overspeed condition with possible turbine blade-shedding and lead to uncommanded in-flight engine shutdown, embody modification Tf55 per paragraph 2 of Turbomeca Mandatory Service Bulletin No. 319 73 4055. (EASA AD 2006-0237 refers) Compliance: By 30 November 2007. Effective Date: 30 November 2006 DCA/TUR/42 Effective Date: DCA/TUR/43A Effective Date: DCA/TUR/44 Effective Date: Cancelled – DCA/TUR/52 refers 31 May 2007 Cancelled – DCA/TUR/68 refers 26 November 2009 Cancelled – DCA/TUR/69 refers 26 November 2009 Issued 29 January 2015 Page 14 of 36 CAA of NZ Turbomeca Turbines DCA/TUR/45 Applicability: Engine Fuel Pump Maximum Flow – Inspection and Replacement Artouste III B, III B1 and III D turboshaft engines. These engines are installed on, but not limited to Alouette III (SE 3160 / SA 316 B) and Lama (SA 315 B) aircraft. Requirement: The European Aviation Safety Agency (EASA) has advised that an additional 58 fuel pumps may have been returned to service after overhaul with a low fuel flow rate. This may restrict the power available at maximum power settings. To prevent an unsafe condition, inspect the fuel pumps listed in table 1 of this AD, per the instructions in Turbomeca Mandatory Service Bulletin (MSB) No. 218 73 0802, revision 1, dated 08 January 2007. Replace fuel pumps that fail to deliver the required maximum fuel flow rate, per the instructions in MSB No. 218 73 0802, before further flight. Table 1 158B 1749 1750 2103 2577 2665 2728 2837 2882 2887 2894 2933 3045 3120 4213 Note: Fuel Pump S/Ns 3220 3277 3293 3323 3326 3395 3438 3581 3725 3729 3884 3923 4123 4129 F472B 4241B B52B B82B C01B D14B D2B D71B D93B E67B F129B F151B F164B F335B F350B F48B F551B F620B F652B F66B F776B F801B F817B F833B F944B F971B G58B G61B 3200 Table 1 of this AD lists affected fuel pumps additional to those that were listed in DCA/TUR/35. That AD is canceled as those affected pumps should all have been addressed by DCA/TUR/35 (or equivalent DGAC F-2005-201). For a complete list of all affected engine fuel pumps, refer to MSB No. 218 73 0802 revision 1, dated 08 January 2007. (EASA AD 2007-0030 refers) Compliance: By 22 March 2007 Effective Date: 22 February 2007 Issued 29 January 2015 Page 15 of 36 CAA of NZ Turbomeca Turbines DCA/TUR/46 Effective Date: DCA/TUR/47 Applicability: Cancelled – EASA AD 2013-170 refers 13 August 2013 Engines Returned to Civil Use – Conformity Inspection and Rework Arriel 1A,1A1,1A2,1B, 1C, 1C1, 1C2, 1D, 1D1, 1E2, 1K, 1K1, 1S, 1S1 turboshaft engines which have previously been used by an operator (such as the military) which have not been operated in compliance with the requirements of a National Civil Authority. These engines are installed on, but not limited to, Eurocopter AS350 B/BA/B1/B2, AS365 N/N1/N2/C/C1/C2/C3 and BK117 C1/C2 (EC 145), Agusta A109 K/K2 and Sikorsky S76 A+/A++/C aircraft. Requirement: Engines which have previously been used by an operator (such as the military) may not have been operated in compliance with the requirements of Civil Authority rules, and may not conform to the applicable approved design data and be in a condition for safe operation. Before these engines can be released to service in the CAANZ civil regime, comply with the instructions in Turbomeca Service Bulletin A292 72 0806, issue 1 or later approved revisions. (EASA AD 2007-0045 refers) Compliance: From the effective date of this AD, unless already accomplished. Effective Date: 29 March 2007 DCA/TUR/48 Gas Generator Front Bearing - Modification Applicability: All Arrius 2F turboshaft engines. Requirement: To prevent failure of the front bearing of the gas generator which could be caused by fatigue cracks initiating in the lubrication slots of the separator cage, embody modification Tf12 per paragraph 2 of Turbomeca Mandatory Service Bulletin No. 319 72 4012, revision 1 or later approved revision. (EASA AD 2007-0057 refers) Compliance: By 30 April 2008 Effective Date: 29 March 2007 DCA/TUR/49 Effective Date: Cancelled – DCA/TUR/85 refers 30 August 2012 Issued 29 January 2015 Page 16 of 36 CAA of NZ Turbomeca Turbines DCA/TUR/50A Applicability: Module 03 Turbine – Inspection and Replacement Arriel 2B, 2B1, 2B1A turboshaft engines not embodied with modification TU166. These engines are known to be installed on, but not limited to, Eurocopter AS 350 B3 and EC 130 B4 aircraft. Note: Revision A of this AD limits the applicability to those engines not embodied with modification TU166. This modification introduces HP blade dampers between the HP disc and the HP blade platform. Requirement: To prevent the loss of blades on the HP turbine due to blade displacement and eventual blade fatigue, accomplish the following: Inspect the HP turbine per the instructions in Turbomeca MSB No. 292 72 2825 version B dated 21 September 2009 or later EASA approved revisions. If the inspections reveal rearward displacement of the HP turbine blades, accomplish the instructions in paragraph 2.B of MSB No. 292 72 2825. (EASA AD 2007-0109R1 refers) Compliance: Within the next 600 hours TIS or 500 cycles on the engine, whichever occurs sooner since the last HP turbine borescope inspection, unless previously accomplished, or Within the next 100 hours TIS for module 03 HP turbines that have logged more than 600 hours TIS or 500 cycles since new, repair or overhaul and on which a borescope inspection was last performed more than 600 hours or 500 cycles ago, and Thereafter repeat the inspection at intervals not to exceed 600 hours TIS or 500 cycles, whichever occurs sooner. Effective Date: DCA/TUR/51 Applicability: DCA/TUR/50 - 31 May 2007 DCA/TUR/50A - 26 November 2009 Engines Returned to Civil Use – Conformity Inspection and Rework Arriel 2B, 2B1, 2B1A, 2C, 2C1, 2C2, 2S1 and 2S2 turboshaft engines which have previously been used by an operator (such as the military) which have not been operated in compliance with the requirements of a National Civil Authority. These engines are installed on, but not limited to Eurocopter AS 350 B3, AS 365 N3, EC 130 B4, EC 155 B/B1 and Sikorsky S76 C+/C++ aircraft. Requirement: Engines which have previously been used by an operator (such as the military) may not have been operated in compliance with the requirements of Civil Authority rules, and may not conform to the applicable approved design data and be in a condition for safe operation. Before these engines can be released to service in the CAANZ civil regime, comply with the instructions in Turbomeca Mandatory Service Bulletin 292 72 2817. (EASA AD 2007-0117 refers) Compliance: From the effective date of this AD, unless already accomplished. Effective Date: 31 May 2007 Issued 29 January 2015 Page 17 of 36 CAA of NZ Turbomeca Turbines DCA/TUR/52 Effective Date: DCA/TUR/53 Effective Date: DCA/TUR/54 Applicability: Cancelled – DCA/TUR/64 refers 25 June 2009 Cancelled – DCA/TUR/81 refers 26 April 2012 HMU Low Fuel Pressure Switch – Inspection and Replacement Model Arriel 2B, 2B1 and 2B1A turboshaft engines, all S/N These engines are known to be installed on, but not limited to Eurocopter AS 350 B3 and EC 130 B4 aircraft. Requirement: To prevent failure of the Hydro Mechanical Unit (HMU) low fuel pressure switch which could result in the internal components from the failed switch to jam the HP-LP fuel pump and cause the pump drive pin to shear, accomplish the following: 1. Inspect the HMU per the instructions in paragraph 2 of Turboméca Mandatory Service Bulletin (MSB) No. 292 73 2826 and determine the P/N of the low fuel pressure switch fitted to the HMU. 2. If a Hydra-Electric low fuel pressure switch P/N 9 550 17 956 0 is fitted, inspect the low fuel pressure switch and chamber of the HMU body. If any parts from the low fuel pressure switch are found missing, or found in the HMU chamber, replace the HMU with a new or overhauled HMU which is fitted with an INLHC low fuel pressure switch. If no parts are found missing, replace the low fuel pressure switch with an IN-LHC low fuel pressure switch. 3. If a IN-LHC low fuel pressure switch P/N 9 550 17 199 0 or P/N 9 550 17 913 0 is fitted, inspect and determine if a Hydra-Electric switch P/N 9 550 17 956 0 is fitted. If a Hydra-Electric switch P/N 9 550 17 956 0 has been or may have been fitted, inspect the chamber of the HMU body. If any parts are found in the HMU chamber, replace the HMU with a new or overhauled HMU which is fitted with an IN-LHC low fuel pressure switch. If the IN-LHC low fuel pressure switch has been fitted since new, repair or overhaul, no further action is required. Note: Accomplish these requirements per the instructions in Turboméca Mandatory Service Bulletin 292 73 2826 original issue, or later approved revisions. (EASA AD 2008-0077 refers) Compliance: 1. 3. & 3. Effective Date: 29 May 2008 Issued 29 January 2015 By 30 September 2009. Page 18 of 36 CAA of NZ Turbomeca Turbines DCA/TUR/55 Applicability: Balancing Piston – Life Limit Reduction Model Arrius 1A turboshaft engines, all S/N. These engines are known to be installed on, but not limited to Eurocopter AS355N aircraft. Requirement: To prevent failure of the balancing piston possibly resulting in an inflight engine shutdown, accomplish the following: Change the balancing piston life cycle limit value in the engine logbook and update the maintenance programme per the instructions in Turboméca Mandatory Service Bulletin N° 319 72 0811 original issue or later approved revisions. (EASA AD 2008-0133 refers) Compliance: By 31 December 2008, unless previously accomplished. Effective Date: 31 July 2008 DCA/TUR/56A Effective Date: DCA/TUR/57 Cancelled – DCA/TUR/77 refers 27 October 2011 Fuel Injection System – Modification Applicability: Model Arrius 1A and 1E turboshaft engines, all S/N not embodied with Modification TU 63. Requirement: To prevent an uncommanded inflight engine shutdown with a sudden selection of decreased collective pitch accomplish the following: Embody modification TU 63 in accordance with Turbomeca SB No. 319 73 0016 revision 1 dated 22 December 1997. (DGAC AD 1998-200 refers) Compliance: By 30 December 2008 unless previously accomplished. Effective Date: 30 October 2008 DCA/TUR/58 Fuel Injectors – Replacement Applicability: Model Arrius 1A and 1E turboshaft engines, all S/N. Requirement: To prevent an uncommanded inflight engine shutdown with a sudden selection of decreased collective pitch, replace main fuel injectors per the instructions in turbomeca SB No. A319 73 0071 origianl issue or later approved revisions. (DGAC AD 2000-532 refers) Compliance: At 1250 hours TTIS or within next 100 hours TIS, whichever is the later and thereafter at intervals not to exceed 1250 hours TIS. Effective Date: 30 October 2008 Issued 29 January 2015 Page 19 of 36 CAA of NZ Turbomeca Turbines DCA/TUR/59 Turbine Overspeed Protection System – Inspection Applicability: Model Arrius 1A and 1E turboshaft engines, all S/N. Requirement: To prevent uncontained failure as a result of malfunction of the free power turbine overspeed protection system, accomplish the instructions in Turbomeca ASB No A319 77 0804 original issue or later approved revisions. (DGAC AD 2005-063R1 refers) Compliance: Within the next 50 hours TIS or by 30 November 2008 whichever occurs sooner unless previously accomplished, and thereafter at the intervals when task card 77-3001 is accomplished per chapter 05-10-02 in the applicable Turbomeca Arrius 1 maintenance manual. Effective Date: 30 October 2008 DCA/TUR/60 Applicability: Lubrication Unit – Modification Model Arrius 2F turboshaft engines, all S/N not embodied with modification Tf75. These engines are known to be installed on, but not limited to Eurocopter EC120B helicopters. Requirement: To prevent engine bearing failure due to check valve blockage which could result in a lack of lubrication to the bearings and an inflight engine shutdown, replace the check valve piston and remove the preformed packing per the instructions in Turbomeca SB No 319 79 4075 or later approved revisions. (EASA AD 2008-0170 refers) Compliance: By 30 June 2009 Effective Date: 30 October 2008 DCA/TUR/61 Applicability: Reduction Gearbox Intermediate Pinion – Modification Model Arriel 1B, 1D and 1D1 turboshaft engines, all S/N. These engines are known to be installed on, but not limited to Eurocopter AS 350 B, AS 350 BA, AS 350 B1 and AS 350 B2 helicopters. Requirement: To prevent failure of the reduction gearbox intermediate pinion due to possible stress cracks caused by vibration which could result in loss of engine power, accomplish the following: Issued 29 January 2015 Page 20 of 36 CAA of NZ Turbomeca Turbines Replace the reduction gearbox intermediate pinion P/N 0 292 70 779 0 with a pinion embodied with Turboméca modification TU 232 per Turboméca MSBulletin No. 292 72 0276 version B dated 06 November 2008 or later EASA approved revisions. (EASA AD 2009-0002 refers) Compliance: By 28 February 2011. Effective Date: 29 January 2009 DCA/TUR/62 Effective Date: DCA/TUR/63 Effective Date: DCA/TUR/64 Effective Date: DCA/TUR/65A Applicability: Cancelled – DCA/TUR/65 refers 25 June 2009 Cancelled – DCA/TUR/67 refers 13 November 2009 Cancelled - EASA AD 2013-0171 refers 13 August 2013 Module 04 Power Turbine – Life Limitation and Replacement Model Arriel 1B, 1D and 1D1 turboshaft engines, fitted with Modules M04 (Power Turbine) listed in figure 1 of Turboméca MSB A292 72 0827 version C. Model Arriel 2B, 2B1 and 2B1A turboshaft engines, fitted with Modules M04 listed in figure 1 of Turboméca MSB A292 72 2833 version C. Affected engines are installed on single engine helicopters. Arriel 1B, 1D and 1D1 turboshaft engines are known to be installed on, but not limited to, Eurocopter AS 350 B, AS 350 BA, AS 350 BB, AS 350 B1 and AS 350 B2 helicopters, and Arriel 2B, 2B1 and 2B1A turboshaft engines are known to be installed on, but not limited to, Eurocopter AS 350 B3 and EC 130 B4 helicopters. Note 1: This AD revised to extend the life limit of the Module 04 power turbine blades from 2000 hours to 5000 hours TTIS and introduce later Turboméca MSB revisions which do not list any additional nonconforming turbine wheels. Requirement: To prevent failure of the power turbine due to possible blade fatigue which could result in loss of engine power, accomplish the following: 1. For engines with 5000 or more cycles on the Module M04 Power Turbine (PT): Replace the module M04, or the PT wheel assembly, or the PT blades per paragraph 2.B.(1)(b) of Turboméca MSB A292 72 0827 version C dated 15 July 2009 or later approved revisions for Arriel 1 engines and MSB A292 72 2833 version C dated 15 July 2009 or later approved revisions for Arriel 2 engines. 2. For engines with less than 5000 cycles on the Module M04 PT: 2.1 Change the cycle life limit of the PT blades in the engine log book to 5000 cycles per paragraph 2.B.(1)(a) of MSB A292 72 0827 for Arriel 1 engines and MSB A292 72 2833 for Arriel 2 engines. 2.2 Replace the module M04, or PT wheel assembly, or PT blades per paragraph 2.B.(1)(b) of MSB A292 72 0827 for Arriel 1 engines and A292 72 2833 for Arriel 2 engines. Issued 29 January 2015 Page 21 of 36 CAA of NZ Turbomeca Turbines Note 2: The S/N of affected PT wheel assemblies and Modules M04 (PT) are listed in figure 1 of the referenced MSB. These PT are known to be fitted with affected blades. The engine S/N are also provided where this information is available. If there is a conflict with S/N contact Turboméca for clarity. (EASA AD 2009-0112R1 refers) Compliance: 1. Before further flight unless previously accomplished 2.1 By 3 September 2009 unless previously accomplished. 2.2 Before accumulating 5000 cycles unless previously accomplished. Effective Date: DCA/TUR/66 Effective Date: DCA/TUR/67 Applicability: DCA/TUR/65 - 25 June 2009 DCA/TUR/65A - 27 August 2009 Cancelled – DCA/TUR/73 refers 28 October 2010 Module M05 Reduction Gearbox – Inspection and Repair Model Arriel 1A1, 1A2, 1B, 1C, 1C1, 1C2, 1D, 1D1, 1E2, 1K, 1K1, 1S and 1S1 turboshaft engines, all S/N embodied with modification TU332, and Fitted with a Module M05 (Reduction Gear Box) as identified in figure 1 of Turboméca MSB A292 72 0825 Turboméca MSB A292 72 0825, version B dated 6 October 2009. These engines are known to be installed on, but not limited to Eurocopter AS350B/BA/BB/B1/B2 helicopters, EC145/MBB-BK117-C1 helicopters, AS365N helicopters, Agusta A109K2 helicopters, Sikorsky S-76A+ helicopters and S-76A++ helicopters. Note 1: This AD supersedes DCA/TUR/63 to introduce Turboméca MSB A292 72 0825 version B dated 6 October 2009 which includes six additional affected Modules M05. Affected modules are listed by S/N in figure 1 of MSB A292 72 0825. The engine S/Ns are also provided, where available. If there is a conflict between the module S/N and the engine S/N contact Turboméca. Requirement: To prevent loss of the reduction gearbox oil due to the possible loss of the duct plug which could result in an engine fire and loss of engine power, accomplish the following: 1. Inspect the M05 lubrication duct for oil leaks per paragraphs 1.C.(1)(a), 2.A and figure 2 of Turboméca MSB A292 72 0825, version B dated 6 October 2009 or later EASA approved revisions. If an oil leak is found accomplish the repair with elastomer per paragraph 2.B.(1)(a) and figures 3 and 4 of MSB A292 72 0825, or Install a steel plug per paragraph 2.B.(1)(b) and figure 5 of Turboméca MSB A292 72 0825. 2. Accomplish the repair with elastomer per paragraph 2.B.(1)(a) and figures 3 and 4 of MSB A292 72 0825, or Install a steel plug per paragraph 2.B.(1)(b) and figure 5 of Turboméca MSB A292 72 0825. Issued 29 January 2015 Page 22 of 36 CAA of NZ Turbomeca Turbines Note 2: The accomplishment of requirement 2 is a termination action to this AD. (EASA AD 2009-0245-E refers) Compliance: 1. Accomplish the initial inspection before further flight unless previously accomplished. If no oil leaks are found continue to inspect at intervals not to exceed 4 hours TIS or after the last flight of the day whichever occurs sooner, until a further 75 hours TIS has accrued. After 75 hours TIS if no oil leaks are found continue the regular oil leak inspections after the last flight of the day per chapter 05-20 of the applicable Arriel 1 Engine Maintenance Manual, paying particular attention to the M05 lubrication duct per figure 2 of MSB A292 72 0825. If an oil leak is found with any of these inspections accomplish the corrective actions per requirement 1 of this AD. 2. Effective Date: DCA/TUR/68A Effective Date: DCA/TUR/69 Applicability: By 13 February 2010. 13 November 2009 Cancelled – DCA/TUR/87 refers 30 August 2012 HMU Acceleration Control Axle – Inspection and Modification Arriel 2B turboshaft engines not embodied with modification TU149. These engines are known to be installed on, but not limited to, Eurocopter AS 350 B3 helicopters. Note 1: This AD supersedes DCA/TUR/44 to introduce modification TU149 per Turbomeca SB 292 73 2149 version D dated 16 October 2009 to prevent the acceleration controller axle from sticking in its bearing. Requirement: To prevent the acceleration controller axle from sticking in its bearing, which can result in difficulty or failure to control the fuel flow rate in manual or mixed mode, leading to unpredictable engine running which can cause gas generator or power turbine overspeed and in-flight engine shutdown, accomplish the following: 1. Perform a ground check in the mixed mode operation until accomplishment of paragraph 3 in Turboméca MSB A292 73 2814 version D dated 16 October 2009 or later EASA approved revisions. For the control system mixed mode refer to section 8 task 3C in the AS350 B3 AFM. 2. Inspect the fuel metering system and perform maintenance procedures per paragraph 2 of Turbomeca MSB A292 73 2814. Note 2: Requirement 1 of this AD may be accomplished by adding the inspection requirement to the tech log. The ground check may be performed and certified under the provision in Part 43 Appendix A.1 (7) by the holder of a current pilot licence, if that person is rated on the aircraft, appropriately trained and authorised (Part 43, Subpart B refers), and the maintenance is recorded and certified as required by Part 43. Note 3: The embodiment of modification TU149 is a terminating action to the requirements of this AD. (EASA AD 2009-0246 refers) Compliance: 1. Before the first flight of the day. 2. Within 20 hours TIS of receiving parts from Turbomeca, and thereafter at intervals not to exceed 200 hours TIS. Effective Date: 26 November 2009 Issued 29 January 2015 Page 23 of 36 CAA of NZ Turbomeca Turbines DCA/TUR/70D Applicability: Gas Generator 2nd Stage Turbine – Reduced Life Limit Model Arriel 1A, 1A1, 1B, 1C, 1C1, 1C2, 1D, 1D1 and 1S1 turbo-shaft engines, all S/N embodied with Turboméca TU347, except those engines fitted with Gas Generator 2nd stage Turbine Discs embodied with Turboméca Modification TU365 in production, or embodied with Turboméca SB 292 72 0365 in-service. These engines are known to be installed on, but not limited to, Eurocopter AS350 series helicopters, AS365 and SA365 series helicopters, and Sikorsky S-76A and S76C series helicopters. Note 1: DCA/TUR/70D revised to reduce the AD applicability to exclude those engines fitted with 2nd stage Turbine Discs embodied with Turboméca Modification TU365 or embodied with SB 292 72 0365. To reflect this situation, this AD introduces Turboméca MSB A292 72 0831 revision D. In addition, some editorial changes have been made to EASA AD 2010-0101R3 to improve the clarity. Requirement: To prevent uncontained failure of the gas generator 2 stage turbine disc which could result in an in-flight engine shutdown, accomplish the requirements in EASA AD 20100101R3. Note 1: A copy of EASA AD 2010-0101R3 can be obtained from the EASA AD web site at http://www.easa.eu.int/certification/airworthiness-directives.php Note 2: Turboméca MSB A292 72 0831 version D dated 11 June 2012 or later approved revisions are acceptable to comply with the requirements of this AD. nd (EASA AD 2010-0101R3 refers) Compliance: At the compliance times specified in EASA AD 2010-0101R3. Effective Date: DCA/TUR/70A DCA/TUR/70B DCA/TUR/70C DCA/TUR/70D DCA/TUR/71 Effective Date: DCA/TUR/72 Effective Date: DCA/TUR/73 Applicability: - 11 June 2010 26 August 2010 21 April 2011 27 September 2012 Cancelled – DCA/TUR/75 refers 31 March 2011 Cancelled – DCA/TUR/80 refers 26 April 2012 HP/LP Pump Metering Unit – Inspection and Replacement Arriel 2B, 2B1, 2B1A turboshaft engines with applicability defined in Turboméca Mandatory Service Bulletin (MSB) A292 73 2836 version A and Turboméca Mandatory Service Bulletin (MSB) A292 73 2830 version B. These engines are known to be installed on, but not limited to Eurocopter AS 350 B3, EC 130 B4 helicopters and Changhe Z11 helicopters. Note 1: This AD supersedes DCA/TUR/66 to introduce additional requirements. Requirement: To prevent uncoupling of the LP fuel pump impeller and the HP fuel pump shaft which can result in a reduction of engine power or, at worst, an uncommanded in-flight shutdown (IFSD) which on a single-engine helicopter may result in an emergency autorotation landing, accomplish the following: Issued 29 January 2015 Page 24 of 36 CAA of NZ Turbomeca Turbines 1. Accomplish the inspection and if any discrepancies are found, replace the HP/LP pump metering unit per the instructions in the applicable Turboméca Mandatory Service Bulletins. 2. Do not install a HP/LP Pump Metering Unit on any aircraft unless the requirements of this AD have been accomplished. Table 1 - HP/LP Pump Metering Unit Inspection and Replacement Requirements: Condition: Inspection: Compliance time for the inspection: Action to be accomplished: HP/LP Pump Metering Units which do not have modification TU147 embodied. Check the transmissible torque between the LP pump impeller and the HP pump shaft in accordance with paragraph 2 of Turboméca MSB A292 73 2830 version B. Check the transmissible torque between the LP pump impeller and the HP pump shaft per the instructions in paragraph 2 of Turboméca MSB A292 73 2836 version A. Within 500 hours TIS on the engine after 29 October 2009 (the effective date of DCA/TUR/66) but no later than 28 November 2010. If no discrepancies are found, apply the nominal tightening torque to the screw of the LP pump impeller. HP/LP Pump Metering Units which have modification TU147 embodied and on which modification TU 147 was embodied before or on 31 March 2010, and are not listed in figures 2 and 3 of Turboméca MSB A292 73 2836 version A. Note 2: Within 750 hours TIS on the engine after the effective date of this AD, but no later than 14 months after the effective date of this AD. If any discrepancies are found, before next flight, replace the HP/LP Pump Metering Unit with a serviceable pre-TU147 unit or a serviceable postTU147 unit If no discrepancies are found, no further AD actions are required. If any discrepancies are found, before next flight, replace the HP/LP Pump Metering Unit with a serviceable post-TU147 unit. The replacement of the HP/LP Pump Metering Unit with a serviceable part is a terminating action to the requirements of this AD. (EASA AD 2010-0215 refers) Compliance: Effective Date: 1. Within the compliance times specified in table 1 of this AD. 2. From 28 October 2010. 28 October 2010 Issued 29 January 2015 Page 25 of 36 CAA of NZ Turbomeca Turbines DCA/TUR/74 Applicability: Fuel Ejector Assembly – Inspection and Rework Model Arriel 1E2, 1S and 1S1 turboshaft engines, all S/N embodied with Turbomeca Internal Consign (IC) No. 298468 or Turbomeca SB No. 292 73 0826 version A. These engines are known to be installed on, but not limited to, Eurocopter Deutschland MBB BK117-C2 and BK117-C1 aircraft, and Sikorsky S-76A and C series aircraft. Requirement: To prevent fuel flow fluctuation or disruption due to a possible incorrectly assembled fuel ejector in the body of the fuel ejector assembly which could result in an in-flight loss of engine power, accomplish the following: 1. Inspect the fuel ejector in the body of the fuel ejector assembly for correct installation per the instructions in paragraph 2.B of Turboméca MSB No. A292 73 0834 version B within the compliance times specified in the compliance table of this AD. If the fuel ejector is found incorrectly assembled, replace the ejector assembly with a serviceable unit before further flight. As an alternative to the above mentioned actions, the instructions in Turbomeca SB No. 292 73 0826 version B are acceptable to comply with all the requirements of this AD provided that the actions are accomplished within the same compliance times specified in the compliance table of this AD. 2. An engine embodied with Turbomeca IC No. 298468 or Turbomeca SB No. 292 73 0826 version A shall not be fitted to any aircraft unless in compliance with the requirements of this AD. Note 1: Ejector assembly inspections and replacements accomplished before the effective date of this AD per the instructions in Turbomeca SB No. A292 73 0834 version A are acceptable to comply with the requirements of this AD. Note 2: Turbomeca MSB No. A292 73 0834 version B, dated 08 February 2011, and Turbomeca SB A292 73 0826 version B, dated 4 February 2011 and later EASA approved revisions of these documents are acceptable to comply with the requirements of this AD. (EASA AD 2011-0023-E refers) Issued 29 January 2015 Page 26 of 36 CAA of NZ Turbomeca Turbines Compliance: 1. Compliance Table: Engine and aircraft configuration: SB No. 292 73 0826 version A (*) or IC No. 298468 has been accomplished on both engines fitted to the aircraft, and Starting difficulties (**) have been encountered with at least one of the engines. SB No. 292 73 0826 version A (*) or IC No. 298468 has been accomplished on only one engine on a twin engine aircraft, and Compliance time: Within the next 5 hours TIS or 3 days, whichever occurs sooner. Within 20 hours TIS or 30 days, whichever occurs sooner. Starting difficulties (**) have been encountered on the related engine. SB No. 292 73 0826 version A (*) or IC No. 298468 has been accomplished on one or both engines fitted to the aircraft, and Starting difficulties (**) have not been encountered. Note 3: Text marked thus (*) in the compliance table of this AD denotes: In the engine log book, the SB may be recorded as “SB No. 292 73 0826” or “SB No. 292 73 0826 version A”, and text marked thus (**) in the compliance table of this AD denotes: Starting difficulties are considered to be when N1 stagnation or variation has been encountered. Applicable guidance can be found in paragraph 1.A.(1) of Turboméca MSB No. A292 73 0834 version B. 2. Effective Date: DCA/TUR/75 Applicability: Within the next 100 hours TIS or 90 days, whichever occurs sooner. From 17 February 2011. 17 February 2011 Module M03 2 nd Stage Nozzle Guide Vanes – Inspection and Replacement Model Arriel 1B turboshaft engines embodied with TU76 or TU202, and not embodied nd with TU148 and fitted with a repaired 2 Stage Nozzle Guide Vane. These engines are known to be installed on, but not limited to Eurocopter AS350 series helicopters. Note 1: DCA/TUR/75 supersedes DCA/TUR/71 to extend the applicability to include Arriel 1B turboshaft engines embodied with TU-202. Requirement: To prevent engine over temperature due to possible incorrectly drilled holes in the nd flange of the 2 Stage Nozzle Guide Vane (NGV) which could result in engine damage and loss of engine power, accomplish the following: 1. Inspect the gas generator per the instructions in paragraph 2.B(1)(a)3 of Turboméca MSB A292 72 0829 version B and the applicable Arriel 1B Maintenance Manual tasks 71-02-09-760-801 and 05-20-01-200-801 or later approved revisions of these documents. If any defects are found per the instructions in paragraph 2.B(1)(a)3 of MSB A292 72 0829, no further flight is permitted. Accomplish corrective actions before further flight. Issued 29 January 2015 Page 27 of 36 CAA of NZ Turbomeca Turbines 2. Complete a M03 log card and engine identification sheet per the instructions in MSB A292 72 0829 version B and determine whether the requirements in the MSB are applicable to the aircraft engine. If the engine manufacturer confirms that MSB A292 72 0829 is not applicable to the engine, no further AD action is required. If the engine manufacturer confirms that MSB A292 72 0829 is applicable to the engine, then accomplish requirement 3 of this AD. 3. For engines affected by MSB A292 72 0829 version B: nd Inspect the 2 Stage Turbine NGVs per the instructions in MSB A292 72 0829. nd If the 2 Stage Turbine NGVs are found non-compliant, replace the affected Module M03 with a serviceable part per the instructions in paragraph 2.B of MSB A292 72 0829 before further flight. 4. A Module M03 gas generator embodied with TU76 and not embodied with TU148 shall not be fitted to any engine unless the requirements of this AD are accomplished, and A Module M03 gas generator embodied with TU202 and not embodied with TU148 shall not be fitted to any engine unless the requirements of this AD are accomplished Note 2: The replacement of the Module M03 with a serviceable part is a terminating action to the requirements of this AD. Note 3: The life limit of “monobloc” Gas Generator 2 Stage Turbine Wheels affected by this AD is 3000 cycles. Note 4: Turboméca MSB A292 72 0829 version B, dated 13 December 2010 and Arriel 1B Maintenance Manual X 292 65 452 1 / X 292 65 452 2 (French Version / English Version) and later approved revisions of these documents are acceptable to comply with the requirements of this AD. nd (EASA AD 2010-0273R1 refers) Compliance: 1. At every last flight of the day. 2. By 26 March 2011 unless previously accomplished. 3. Compliance required per the following table: st nd Total cycles on the 1 and/or 2 Turbine: Stage st nd Compliance time: (1 or 2 accumulated cycles) Stage Turbine For affected turbines with up to 1199 cycles. Before accumulating 1500 total cycles. For affected turbines with 1200 cycles and up to 1799 cycles. Within the next 300 cycles, or within the next 6 months, whichever occurs sooner. For affected turbines with 1800 cycles and up to 2399 cycles. Within the next 200 cycles, or within the next 4 months, whichever occurs sooner. For affected turbines with 2400 cycles and up to 2999 cycles. Within the next 100 cycles, or before accumulating 3000 total cycles, or within the next 2 months, whichever occurs sooner. For affected turbines with more than 3000 cycles. Before further flight. 4. Effective Date: From 19 March 2011. 19 March 2011 Issued 29 January 2015 Page 28 of 36 CAA of NZ Turbomeca Turbines DCA/TUR/76 Applicability: Hydromechanical Metering Unit (HMU) – Inspection and Replacement Model Arriel 2B engines, all S/N fitted with HMU listed in Turboméca MSB A292 73 2841 version A. These engines are known to be installed on, but not limited to Eurocopter AS 350 B3 helicopters. Requirement: To correct possible incorrectly adjusted HMU which could result in loss of engine power in flight, accomplish the following: 1. Review the aircraft records or inspect the AMU installed on the aircraft and determine the P/N and S/N of the AMU. If a HMU with P/N and S/N listed in Turboméca MSB A292 73 2841 version A is found fitted to the aircraft and the HMU is not already in compliance with SB 292 73 2840 version A, then accomplish either requirement 2 or 3 of this AD. 2. Replace the affected HMU with a serviceable HMU per the instructions in MSB A292 73 2841 version A. 3. Accomplish an engine functional test per the instructions in paragraph 2.B.(1)(a) of Turboméca MSB A292 73 2841 version A. If the engine fails the functional test, replace the HMU with a serviceable part. If the engine passes the functional test, accomplish the following actions: • Within the next 4 months after the effective date of this AD, install software modification TU143 on the Engine Electronic Control Unit (EECU) per the instructions in Turboméca SB 292 73 2143, and • Within the next 12 months after the effective date of this AD, replace the affected HMU with a serviceable HMU. 4. A HMU shall not be fitted on any aircraft or engine, unless the HMU is in compliance with the requirements of this AD. Note 1: A serviceable HMU is a part which is not listed in MSB A292 73 2841 version A, or a HMU which has passed the inspection per the instructions in Turboméca SB 292 73 2840 version A. Note 2: The replacement of an HMU with a serviceable HMU is a terminating action to the requirements of this AD. Note 3: Turboméca MSB A292 73 2841 version A dated 04 July 2011, SB 292 73 2840 version A dated 28 June 2011 and SB 292 73 2143 initial issue dated 24 July 2007 and later approved revisions of these documents are acceptable to comply with the requirements of this AD. ( EASA AD 2011-0128-E refers) Compliance: 1. 2. & 3. 4. Effective Date: Before further flight. From 9 July 2011. 9 July 2011 Issued 29 January 2015 Page 29 of 36 CAA of NZ Turbomeca Turbines DCA/TUR/77A Applicability: P3 Air Pipe – Inspection and Modification Model Arrius 2F turbo-shaft engines, all S/N These engines are known to be installed on, but not limited to Eurocopter EC120B helicopters. Note 1: This AD revised to introduce note 5 with no change to the AD applicability or requirement. The repetitive inspections mandated by this AD remains applicable for aircraft fitted with a RH rear half-wall P/N 0319 99 82 40 and the distance between the P3 air pipe and the RH rear half-wall is found to be less than 0.5 mm. Requirement: To prevent premature wear and failure of the P3 air pipe due to possible interference with the bulkhead which could result in loss of engine power, accomplish the following: 1. For engines installed on a helicopter and fitted with a RH rear half-wall P/N 0319 99 82 40, and For engines installed on a helicopter and being fitted with a RH rear half-wall P/N 0319 99 82 40: Inspect the P3 air pipe and the RH rear half-wall per the instructions in Turbomeca Mandatory Service Bulletin (MSB) N° 319 7 5 4810 issue B dated 25 January 2011 and later approved revisions. If both the P3 air pipe and the RH rear half-wall are found undamaged, and the distance between the P3 air pipe and the RH rear half-wall is found to be less than 0.5 mm, repeat the inspection at intervals not to exceed 100 hours TIS. If the RH rear half-wall is found damaged, or the P3 air pipe interferes with RH rear half-wall, install a RH rear half-wall P/N 0319 99 008 0 per the instructions in Turbomeca MSB N° 319 75 4810 before further flight. If the P3 air pipe is found damaged, install a serviceable P3 air pipe and determine that the distance between P3 air pipe and RH rear half-wall is equal to or greater than 0.5 mm per the instructions in Turbomeca MSB N° 319 75 4810 before further flight. 2. After an engine has been embodied with a RH rear half-wall P/N 0319 99 008 0, then a RH rear half-wall P/N 0319 99 82 40 shall not be installed on that engine. 3. A RH rear half-wall P/N 0319 99 82 40 shall not be installed on an engine, or an engine with a RH rear half-wall P/N 0319 99 82 40 shall not be installed on a helicopter, unless in compliance with the requirements of this AD. Note 2: The installation of a serviceable P3 air pipe on an engine and determination that the distance between the P3 air pipe and RH rear half-wall P/N 0319 99 82 40 is equal to or greater than 0.5 mm, is a terminating action for the repetitive inspections for that engine. Note 3: The modification of an engine by installation of a RH rear half-wall P/N 0319 99 008 0 is a terminating action for the repetitive inspections for that engine. Note 4: TURBOMECA Mandatory Service Bulletin N°. 319 75 4810 issue B, dated 25 January 2011 and later approved revisions are acceptable to comply with the requirements of this AD. Note 5: For engines installed on an aircraft that have been inspected and corrected per the instructions in Turbomeca MSB N° 319 75 4810 issue A before 27 October 2011 (the effective date of DCA/TUR/77) are in compliance with requirement 1 of this AD provided that the engine has not been removed from that aircraft. (EASA 2011-0182R1 refers) Issued 29 January 2015 Page 30 of 36 CAA of NZ Turbomeca Turbines Compliance: Effective Date: DCA/TUR/78 Effective Date: DCA/TUR/79 Applicability: 1. Within the next 100 hours TIS unless previously accomplished and thereafter if both the P3 air pipe and the RH rear half-wall are found undamaged, and the distance between the P3 air pipe and the RH rear half-wall is found to be less than 0.5 mm, repeat the inspection at intervals not to exceed 100 hours TIS. 2. From 23 February 2012. 3. From 23 February 2012. DCA/TUR/77 - 27 October 2011 DCA/TUR/77A - 23 February 2012 Cancelled – EASA AD 2012-0249 refers 5 December 2012 Module M04 PT Blades – Life Limitation Model Arriel 2B, 2B1, 2B1A, 2B1B engines, all S/N. These engines are known to be installed on, but not limited, to Eurocopter AS 350 B3, EC 130 B4, AS 350 C3 helicopters and Changue Z11 helicopters. Requirement: To prevent power turbine (PT) blade failure accomplish the following: 1. Review the aircraft records and determine if the M04 Power turbine wheel assembly is fitted with a PT blade P/N 2 292 81 A01 0 and S/N 102782 through to 120230, or S/N 120293 through to 120390. The instructions to determine the S/N of the module M04 PT blades is provided in paragraph 2B(1)(a) of Turboméca MSB A292 72 2842 version A. If an affected blade is found fitted, record the blade life limit of 5000 cycles for that PT blade in the module M04 logbook and the engine logbook per the instructions in paragraph 2.B.(1)(b) of MSB A292 72 2842 version A, and Before accumulating 5000 cycles on the PT blade since first installation on the engine, accomplish one of the following actions per the instructions in paragraphs 2.B.(1)(b) and 2.B.(2) of MSB A292 72 2842 version A: • Replace the PT blade with a serviceable PT blade, or • Replace the module M04 with a module M04 with serviceable PT blades, or • Replace the PT wheel assembly with a PT wheel assembly fitted with serviceable PT blades. 2. A PT blade affect by this AD shall not be installed on any engine or any engine which is to be installed on a helicopter unless the PT blade is in compliance with the requirements of this AD. Note: Turboméca MSB A292 72 2842 version A, dated 23 September 2011 and later approved revisions of this document is acceptable to comply with the requirements of this AD. Issued 29 January 2015 Page 31 of 36 CAA of NZ Turbomeca Turbines (EASA AD 2011-0218 refers) Compliance: Effective Date: DCA/TUR/80 Effective Date: DCA/TUR/81 Applicability: 1. By 8 January 2012 unless previously accomplished. 2. From 8 December 2011. 8 December 2011 Cancelled – DCA/TUR/84 refers 26 July 2012 FCU 3-Way Union Plug – Inspection Arriel 1E2, 1S and 1S1 turboshaft engines, all S/N. These engines are installed on, but not limited to, Eurocopter Deutschland MBB-BK 117 and Sikorsky S-76A aircraft. Note 1: This AD supersedes DCA/TUR/53 to introduce Turboméca, S.A. MSB No. 292 73 0817 version D, dated 29 February 2012. This AD retains the requirements of superseded DCA/TUR/53, reduces the applicability and prevents the installation of affected FCU on any engine unless the actions of this AD have been accomplished. Requirement: To prevent a high pressure fuel leak at the fuel pump outlet possibly causing an inflight flame-out and/or a fire, accomplish the inspections and corrective actions specified in EASA AD 2012-0063. Note 2: A copy of EASA AD 2012-0063 can be obtained from the EASA AD website at http://www.easa.eu.int/certification/airworthiness-directives.php (EASA AD 2012-0063 refers) Compliance: As specified in EASA AD 2012-0063. Effective Date: 26 April 2012 DCA/TUR/82 Gas Generator Rotating Assembly - Inspection, Cleaning and Replacement Applicability: Model Arriel 1A, 1A1, 1A2, 1B, 1C, 1C1, 1C2, 1D, 1D1, 1E2, 1K, 1K1, 1S and 1S1 turbo-shaft engines, all S/N not embodied with Turboméca modification TU360. Note 1: DCA/TUR/82 supersedes DCA/TUR/5B to introduce the requirement to determine the engine history and operating conditions of the engine. The AD also introduces a repetitive cleaning of the shaft. The embodiment of Turboméca modification TU360 (which can be done during overhaul) is a terminating action for the AD requirements. Requirement: The accumulation of mineral or chemical particles in the turbine shaft could occur when the engine is operated in a dusty environment. This may result in an unbalance gas generator rotating assembly which could damage the rear bearing, and result in an in-flight loss of engine power. To prevent this, accomplish the inspections and corrective actions specified in EASA AD 2012-0071. Note 2: A copy of EASA AD 2012-0071 can be obtained from the EASA AD website at http://www.easa.eu.int/certification/airworthiness-directives.php Note 3: Turboméca MSB A292 72 0230 Version C, dated 29 February 2012 or later approved revisions are acceptable to comply with the requirements of this AD. (EASA AD 2012-0071 refers) Compliance: At the compliance times specified in EASA AD 2012-0071. Effective Date: 31 May 2012 Issued 29 January 2015 Page 32 of 36 CAA of NZ Turbomeca Turbines DCA/TUR/83 Gas Generator Rotating Assembly – Inspection and Replacement Applicability: Model Arriel 1A1, 1A2, 1B, 1C, 1C1, 1C2, 1D, 1D1, 1E2, 1K, 1K1, 1S and 1S1 turboshaft engines, all S/N. Requirement: To prevent failure of the gas generator (GG) rear bearing due to an unbalanced GG rotating assembly which could result in loss of engine power, accomplish the inspections and corrective actions specified in EASA AD 2012-0117. Note 1: A copy of EASA AD 2012-0117 can be obtained from the EASA AD website at http://www.easa.eu.int/certification/airworthiness-directives.php Note 2: The Turboméca Arriel 1 maintenance manuals listed in the appendix of EASA AD 2012-0117 or later approved revisions are acceptable to comply with the requirements of this AD. (EASA AD 2012-0117 refers) Compliance: From 17 July 2012. Effective Date: 17 July 2012 DCA/TUR/84 Effective Date: DCA/TUR/85 Applicability: Cancelled – EASA AD 2012-0124R1 refers 29 January 2013 Digital Engine Control Unit – Software Modification Model ARRIEL 2B1 and 2B1A engines, all S/N. These engines are known to be installed on, but not limited to, Eurocopter AS 350 B3 and EC 130 B4 helicopters, and Changhe Aircraft Industries Corporation Z11 singleengine helicopters. Note 1: This AD supersedes DCA/TUR/49 to expand the applicability to include ARRIEL 2B1A engines which require the embodiment of modification TU175 (software version 6). No AD action required for those ARRIEL 2B1 engines embodied with modification TU144C (software version 5.02). Requirement: To prevent engine flame-out due to limitations of the Digital Engine Control Unit (DECU) software, accomplish the requirements in EASA AD 2012-0147. Note 2: A copy of EASA AD 2012-0147 can be obtained from the EASA AD website at http://www.easa.eu.int/certification/airworthiness-directives.php Note 3: Turboméca MSB A292 73 2144 original issue, dated 05 January 2007, and Turboméca MSB A292 73 2175 version A, dated 06 July 2012 or later approved revisions of these documents is acceptable for compliance with the requirements of this AD. (EASA AD 2012-0147 refers) Compliance: At the compliance times specified in EASA AD 2012-0147 unless previously accomplished. Effective Date: 30 August 2012 Issued 29 January 2015 Page 33 of 36 CAA of NZ Turbomeca Turbines DCA/TUR/86A Applicability: Privilege Injectors – Replacement Model Arrius 2F engines, all S/N. These engines are known to be installed on, but not limited to Eurocopter EC 120B helicopters. Note 1: DCA/TUR/86A revised to correct the AD applicability with no change to the AD requirement. This AD introduces the requirements in Turbomeca MSB N° A319 73 4001 issue K, dated 10 February 2012. Requirement: To prevent engine flame out during rapid engine deceleration due to blocked main injectors, accomplish the requirements in EASA AD 2012-0150. Note 2: A copy of EASA AD 2012-0150 can be obtained from the EASA AD website at http://www.easa.eu.int/certification/airworthiness-directives.php Note 3: Turbomeca MSB N° A319 73 4001 issue K, dated 10 February 2012 or later approved revisions are acceptable to comply with the requirements of this AD. (EASA AD 2012-0150 refers) Compliance: At the compliance times specified in EASA AD 2012-0150 unless previously accomplished. Effective Date: DCA/TUR/86 - 30 August 2012 DCA/TUR/86A - 31 August 2012 DCA/TUR/87 Applicability: Gas Generator 2nd Stage Turbine – Inspection and Replacement All ARRIEL 1B embodied with mod TU 148, ARRIEL 1D, 1D1 and 1S1 turboshaft engines, all S/N except those engines fitted with Gas Generator 2nd stage turbine wheels embodied with Turbomeca modification TU347 at manufacture, or those engines embodied with the modification per Turbomeca SB 292 72 0347. These engines are known to be installed on, but not limited to Eurocopter AS 350 B/BA/BB/B1/B2 and Sikorsky S-76A+/A++/C. Note 1: This AD retains the requirements in superseded DCA/TUR/68A and introduces repetitive inspections of the 2nd stage turbine wheels fitted in engines not embodied with Turboméca modification TU347. This AD also introduces life limits for affected 2nd stage turbine blades. Requirement: To prevent failure of gas generator 2nd stage turbine blades which could result in an in-flight engine shutdown, accomplish the inspections and corrective actions specified in EASA AD 2012-0143. Note 2: A copy of EASA AD 2012-0143 can be obtained from the EASA AD website at http://www.easa.eu.int/certification/airworthiness-directives.php Note 3: Turboméca MSB A292 72 0807 Version E, dated 29 October 2009, urboméca MSB A292 72 0810 Version C, dated 24 July 2009 and Turboméca SB 292 72 0347 (any revision) or later approved revisions of these documents are acceptable to comply with the requirements of this AD. (EASA AD 2012-0143 refers) Compliance: At the compliance times specified in EASA AD 2012-0143. Effective Date: 30 August 2012 Issued 29 January 2015 Page 34 of 36 CAA of NZ Turbomeca Turbines DCA/TUR/88 Effective Date: DCA/TUR/89 Effective Date: Cancelled – EASA AD 2013-0079 refers 5 April 2013 Cancelled – EASA AD 2012-0187R1 refers 25 October 2012 Issued 29 January 2015 Page 35 of 36 CAA of NZ Turbomeca Turbines From 1 October 2012 the Civil Aviation Authority of New Zealand (CAA) will no longer rewrite the text of State of Design ADs. Applicable State of Design ADs will be listed below and can be obtained directly from the National Airworthiness Authority (NAA) web site. The link to the NAA web site is available on the CAA web site at http://www.caa.govt.nz/Airworthiness_Directives/states_of_design.html If additional NZ ADs need to be issued when an unsafe condition is found to exist in an aircraft or aeronautical product in NZ they will be added to the list below. 2012-0124R1 Effective Date: 2012-0187R2 Effective Date: 2012-0249 Effective Date: 2013-0079R1 Effective Date: 2013-0082 Effective Date: 2013-0120 Effective Date: 2013-0170 Effective Date: 2013-0171 Effective Date: 2013-0243 Effective Date: 2014-0036 Effective Date: 2014-0036 Effective Date: Module M03 Gas Generator Turbine Blade – Modification 2012-0124 - 23 July 2012 2012-0124R1 - 29 January 2013 Engine Cycle Counting Aid System – Modification/Amendment 2012-0187R1 - 25 October 2012 2012-0187R2 - 13 December 2012 Airworthiness Limitations – Amendment/Implementation 5 December 2012 Hydro-mechanical Metering Unit – Replacement EASA AD 2013-0079 - 5 April 2013 EASA AD 2013-0079R1 - 3 February 2014 Hydro-Mechanical Metering Unit – Inspection and Replacement 16 April 2013 Free Turbine Bearing Plug – Inspection and Rework 18 June 2013 Hydro-mechanical Metering Unit – Inspection and Replacement 13 August 2013 HMU Constant Delta Pressure Valve Diaphragm – Replacement 13 August 2013 Ejector Assembly Nozzle – Inspection 15 October 2013 Accessory Gearbox (M01) 41/23 Tooth Bevel Gear Assembly – Inspection and Replacement 25 February 2014 Accessory Gearbox (M01) – 41/23 Tooth Bevel Gear Assembly – Inspection 25 February 2014 Issued 29 January 2015 Page 36 of 36 CAA of NZ
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