Airworthiness Directive Schedule

(Austrian AD A-2004-002 refers) Compliance: 1. Before further flight. 2. Within 50 hours TIS or 31 March 2004 whichever occurs first. Effective Date: 26 February 2004 DCA/DIAMOND/3 Cancelled – DCA/DIAMOND/9 refers Effective Date: 30 April 2009 DCA/DIAMOND/4A Fuel Selector Valve – Inspection Applicability: DA40 aircraft, S/Ns 40.006 through 40.079, and 40.081 through 40.083, and 40.201 through 40.417 fitted with fuel shaft P/N D41-2823-20-00 Rev “-“. Requirement: To prevent universal joint failures between the fuel selector and the fuel valve, which might remain unrecognized by the pilot and could result in fuel starvation during flight and/or the unavailability of the emergency fuel shut-off function, inspect the universal joints of the fuel selector/fuel valve assembly, per Diamond Aircraft Industries GmbH Mandatory Service Bulletin No. MSB 40-030/3. If any defects are found, replace the complete drive assembly per MSB No. MSB 40-030/3, prior to further flight. Note 2: The installation of universal joints per MSB No. MSB 40-030/3 is a terminating action to the repetitive 50 hours TIS inspection. Thereafter inspections to be accomplished per Aircraft Maintenance Manual AMM-TR-MÄM-40-142/a. (EASA AD 2006-0067 refers and supersedes Austrian AD A-2004-003) Compliance: For aircraft with less than 200 hours TSN, within 50 hours TIS or by 25 April 2007, whichever is the sooner, and thereafter at intervals not to exceed 50 hours TIS until a modified universal joint has been fitted per MSB No. MSB 40-030/3. For aircraft with more than 200 hours TSN, within the next 15 hours TIS or by 25 April 2007, whichever is the sooner, and thereafter at intervals not to exceed 50 hours TIS until a modified universal joint has been fitted per MSB No. MSB 40-030/3. Effective Date: DCA/DIAMOND/4 - 30 March 2006 DCA/DIAMOND/4A - 25 January 2007 Diamond DA 40 Series Issued 31 July 2025 Page 3 of 7 CAA of NZ DCA/DIAMOND/5 Engine Fuel System Contamination – Inspection Applicability: DA 40 aircraft fitted with Garmin G1000 EASA STC.IM.A.S.01023 (FAA STC SA01254WI) with less than 50 hours TTIS, S/Ns 40.448 through 40.673, excluding 40.538, 40.590, 40.641, 40.642, 40.644, 40.651, 40.654, 40.655 and 40.669. Requirement: To prevent contamination of the fuel supply lines and indicating system possibly causing improper engine operation, or in flight engine failure, accomplish the instructions in Diamond Aircraft Industries Mandatory Service Bulletin MSB 40-048/2. (EASA AD 2006-0295-E refers) Compliance: Before further flight or by 31 January 2007, whichever is the sooner. Effective Date: 30 November 2006 DCA/DIAMOND/6 Mixture Control Cable – Inspection Applicability: DA40 aircraft, S/N 40.006 through to 40.020, 40.022 through to 40.027, 40.030, 40.031, 40.038 through to 40.040, 40.046, 40.047, 40.050, 40.052, 40.054, 40.055 and 40.057. Requirement: To prevent failure of the crimp between the cable and connector due to possible poor crimp quality combined with high cable friction which could result in loss of mixture control, inspect the mixture cable per Diamond Aircraft Industries GmbH SB No. MSB40-012 dated 19 July 2002. If any defect is found or the quality of the crimp is suspect, replace the cable per SB No. MSB40-012 before further flight. (Austrian AD 112 refers) Compliance: Before further flight unless previously accomplished. Effective Date: 30 April 2009 DCA/DIAMOND/7 Aileron/Flap Bellcrank and Rod Ends – Inspection Applicability: DA 40 D aircraft, all S/N fitted with P/N DA4-2717-50-00 aileron bellcranks or P/N DA4-2757-30-00 flap bellcranks. Note 1: DA 40 D aircraft with S/N 40.080, 40.084, D4.001 through to D4.188, D4.190 through to D4.261, D4.263 through to D4.317, D4.326 through to D4.329 and 40.DS001 through to 40.DS004 are known to have been delivered with P/N DA4-2717-50-00 aileron bellcranks, P/N DA4-2757-30-00 flap bellcranks and bent P/N DAI-9027-00-01 rod ends. Requirement: To prevent failure of the aileron or flap control system due to possible chafing damage of control rods which could result in loss of aircraft control, accomplish the following: 1. Replace the aileron bellcrank P/N DA4-2717-50-00 with improved design aileron bellcrank P/N DA4-2717-50-00_01. Replace the flap bellcrank P/N DA4-2757-30-00 with improved design flap bellcrank P/N D60-2757-30-00. If any bent rod ends are found, replace with straight parts per Diamond Aircraft Industries GmbH MSB No. D4-059 before further flight. 2. Aileron bellcranks P/N DA4-2717-50-00 and flap bellcranks P/N DA4-2757-30- 00 or any bent rod ends shall not be fitted to any aircraft as replacement parts. Note 2: Accomplish the requirements of this AD per Diamond Aircraft Industries GmbH MSB- D4-059 dated 14 February 2008 or MSB-D4-059/1 dated 31 March 2008 or later approved revisions. (EASA AD 2008-0114 refers) Compliance: 1. Within the next 200 hours TIS unless previously accomplished. 2. From 30 April 2009. Effective Date: 30 April 2009 Diamond DA 40 Series Issued 31 July 2025 Page 4 of 7 CAA of NZ DCA/DIAMOND/8 Upper Wing Skin-to-Main Spar Adhesive Joint – Inspection Applicability: DA 40 aircraft, S/N 40.377, 40.420, 40.422, 40.644 through to 40.693, 40.695 through to 40.842, 40.844, 40.846 through to 40.887, 40.889 through to 40.912, 40.915 through to 40.917, 40.919 through to 40.929, 40.931, 40.932, 40.934 through to 40.940, 40.944 through to 40.949, 40.951 through to 40.953, 40.955 through to 40.957, 40.961, 40.964 and 40.971. DA 40 F aircraft, S/N 40.FC007 through to 40.FC029. Requirement: A number of wings manufactured by Diamond Aircraft Industries Inc. in Canada have been found with voids in the adhesive joint between the main spar caps and the upper wing skins. The available information indicates that wings with voids within established criteria continue to meet the certification design limits. To determine whether the voids in the adhesive joint between the main spar caps and the upper wing skin are within established criteria, inspect the adhesive joint per Diamond Aircraft Industries GmbH MSB-40-060 / MSBF4-016 dated 20 October 2008 or later approved revisions. Report the results to Diamond Aircraft Industries per MSB-40-060 / MSB-F4-016. If any voids are found that exceed the criteria specified in MSB-40-060 / MSB-F4-016 accomplish a manufacturer approved repair before further flight. (EASA AD 2008-0224 refers) Compliance: Within the next 100 hours TIS or by 30 June 2009 whichever occurs sooner, unless previously accomplished. Effective Date: 30 April 2009 DCA/DIAMOND/9 Cancelled – CF-2023-50 refers Note: Transport Canada AD CF-2023-50 supersedes DCA/DIAMOND/9 (EASA AD 2009- 0016 refers). Effective Date: 24 July 2023 DCA/DIAMOND/10A Rear Passenger Door – Inspection Applicability: DA 40, DA 40 D and DA 40 F aircraft, all S/N. Note: The requirements of this AD revised to include the AFM at the latest revision (which includes the requirements in AFM-TR-MAM 40-428) as an acceptable means to comply with the requirements in this AD. Requirement: To prevent loss of the rear passenger door in flight, accomplish the following: 1. Accomplish the following actions concurrently per the instructions in Diamond Aircraft Industries GmbH Mandatory Service Bulletins No. MSB 40-070, MSB D4-079 and MSB F4-024 dated 30 April 2010 (single document) and the associated Work Instructions or later approved revisions of these documents. Determine the P/N of the rear passenger door retaining bracket. If a P/N DA4-5200-00-69 is found fitted, replace with a bracket P/N DA4-5200-00-69-SB, and revise the AFM and incorporate DAI Temporary Revision AFM-TR-MAM 40-428 or amend the AFM with a revision that includes the information in AFM-TR-MAM 40-428. 2. A rear passenger door retaining bracket P/N DA4-5200-00-69 shall not be fitted to any aircraft. (EASA AD 2010-0235R1 refers) Compliance: 1. Within the next 200 hours TIS after 25 November 2010 (the effective date of DCA/DIAMOND/10) or by 25 November 2011 whichever occurs sooner. 2. From 25 November 2010 (the effective date of DCA/DIAMOND/10). Effective Date: DCA/DIAMOND/10 - 25 November 2010 DCA/DIAMOND/10A - 30 June 2011 Diamond DA 40 Series Issued 31 July 2025 Page 5 of 7 CAA of NZ DCA/DIAMOND/11 Cabin Air Conditioning System – Deactivation Applicability: DA 40 aircraft, all S/N embodied with STC SA03674AT (a vapor cycle system (VCS) cabin air conditioning system) per DER Services Master Document List MDL-2006- 020-1 revision C, dated 3 February 2009; or revision D, dated 22 April 2009; or revision E, dated 12 May 2010; or revision F, dated 6 July 2010. Note 1: STC SA03674AT is held by Premier Aircraft Service (formerly held by DER Services, Inc.) Requirement: To correct an unsafe condition with the vapor cycle system (VCS) due to reports of damage found around the VCS compressor mounting areas during maintenance inspections, accomplish the following actions per Premier Aircraft Service Work Instruction PAS-WI-MSB-40-2011-001, dated 4 March 2011 and Premier Aircraft Service MSB No. PAS-MSB-40-2011-001, dated 4 March 2011: • Deactivate the VCS system. • Pull and collar the compressor circuit breaker and place a placard above the circuit breaker stating ''INOP.'' • Remove the VCS compressor and associated mounting hardware. • Revise the aircraft weight and balance. Note 2: Optional actions: If all the above mentioned actions have been accomplished, the VCS compressor may be reinstalled and the air conditioning system reactivated per the instructions in Premier Aircraft Service Bulletin No. PAS-SB-40-2011-002, dated 18 August 2011; Seamech International Inc. Vapor Cycle Air Conditioning with Automatic Climate Control Instructions for Continued Airworthiness ASI-772216A revision G, dated 9 August 2011; Seamech International Inc. Kit Compressor Mounting, Drawing SII 2216155 revision D, dated 21 July 2011 and DER Services Installation Instructions Engineering Order EO-2006-020-1 revision F, dated 18 August 2011. (FAA AD 2011-21-10 refers) Compliance: Within 100 hours TIS after installation of STC SA03674AT, or by 16 December 2011 whichever occurs later. Effective Date: 16 November 2011 DCA/DIAMOND/12 Cancelled – EASA AD 2012-0024R1 refers Effective Date: 26 May 2015 Diamond DA 40 Series Issued 31 July 2025 Page 6 of 7 CAA of NZ The State of Design ADs listed below are available directly from the National Airworthiness Authority (NAA) websites. Links to NAA websites are available on the CAA website at Links to state of design airworthiness directives | aviation.govt.nz 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. EASA AD 2013-0145 Aft Main Spar / Cabin Area – Modification Effective Date: 29 July 2013 EASA AD 2012-0024R1 Turbocharger Hose – Inspection Effective Date: 26 May 2015 EASA AD 2016-0126 Alternator Cable – Inspection Effective Date: 6 July 2016 EASA AD 2017-0086 Electronic Control Unit – Modification Effective Date: 26 May 2017 Transport Canada AD CF-2019-39R1 Fuel Tank Connection Hose – Inspection Applicability: DA 40, DA 40 D, DA 40 F and DA 40 NG aircrafts, all S/N. Effective Date: CF-2019-39 - 21 November 2019 CF-2019-39R1 - 4 June 2025 EASA AD 2012-0180 Airspeed Indicator Markings / Placard – Installation Applicability: DA 40 NG aircrafts, S/N 40.N001 through to 40.N087 inclusive, and any DA 40 D aircraft modified in-service to DA 40 NG through application of Optional Service Bulletin (OSB) D4-080 by using Working Instruction WI-OSB- D4-080 up to Revision 6. Note: This AD adopted with the NZ type acceptance of DA 40 NG aircrafts. Compliance: Initial compliance required before the issue of a New Zealand Certificate of Airworthiness, or at the next Review of Airworthiness (RA), whichever is the sooner, unless previously accomplished. Repetitive inspections, if required, are to be accomplished at intervals not to exceed the times specified in the EASA AD. Effective Date: 26 November 2020 EASA AD 2013-0018 Turbo Intercooler Installation – Inspection Applicability: DA 40 NG aircrafts, S/N 40.N001 through to 40.N084 inclusive, and DA 40 NG aircrafts, all S/N, when converted from DA 40 D aircraft through embodiment of Optional Service Bulletin (SB) D4-080 by using Working Instruction WI-OSB-D4-080 up to Revision 6. Note: This AD adopted with the NZ type acceptance of DA 40 NG aircrafts. Compliance: Initial compliance required before the issue of a New Zealand Certificate of Airworthiness, or at the next Review of Airworthiness (RA), whichever is the sooner, unless previously accomplished. Repetitive inspections, if required, are to be accomplished at intervals not to exceed the times specified in the EASA AD. Effective Date: 26 November 2020 Diamond DA 40 Series Issued 31 July 2025 Page 7 of 7 CAA of NZ EASA AD 2016-0190 Auto-pilot Bridle Cable Clamps – Inspection Applicability: DA 40 NG aircrafts, all S/N. Note: This AD adopted with the NZ type acceptance of DA 40 NG aircrafts. Compliance: Initial compliance required before the issue of a New Zealand Certificate of Airworthiness, or at the next Review of Airworthiness (RA), whichever is the sooner, unless previously accomplished. Repetitive inspections, if required, are to be accomplished at intervals not to exceed the times specified in the EASA AD. Effective Date: 26 November 2020 EASA AD 2016-0203 V-band Clamps – Inspection Applicability: DA 40 NG aircrafts, all S/N, including aircrafts converted from DA 40 D aircraft through embodiment of Optional Service Bulletin D4-080. Note: This AD adopted with the NZ type acceptance of DA 40 NG aircrafts. Compliance: Initial compliance required before the issue of a New Zealand Certificate of Airworthiness, or at the next Review of Airworthiness (RA), whichever is the sooner, unless previously accomplished. Repetitive inspections, if required, are to be accomplished at intervals not to exceed the times specified in the EASA AD. Effective Date: 26 November 2020 Transport Canada AD CF-2021-24 Baggage Nets – Inspection Applicability: DA 40, DA 40 D, DA 40 F and DA 40 NG aircraft, all S/N. Effective Date: 4 August 2021 Transport Canada AD CF-2023-50R1 NLG Leg Pivot Axle – Inspection Applicability: DA 40, DA 40 D and DA 40 F aircraft, all S/N. Effective Date: CF-2023-50 - 24 July 2023 CF-2023-50R1 - 21 December 2023 * Transport Canada AD CF-2025-30 Passenger Door – Inspection Applicability: DA40 NG, DA40, DA40 F and DA40 D, all S/N. Effective Date: 31 July 2025