AIRWORTHINESS DIRECTIVES Amendment Nr 26-02

require repetitive inspection of the affected parts and, depending on findings, replacement. That AD also provided additional requirements for installation of affected parts. After that AD was issued, AH developed a simplified optional inspection method (E – visual inspection), revised EASB EC135-64-11-0001 (now at issue 02) which introduced reduced inspection intervals for parts which have been inspected using inspection method E, and EASA issued AD 2024-0028R1 to add reference to the optional inspection method E, and related inspection intervals. Since EASA AD 2024-0028R1 was issued, it has been determined that the inspection method A can be discontinued, and that additional limitations are now provided. For the reason described above, EASA AD 2026-0032 partially retains the requirements in superseded EASA AD 2024-0028R1, and requires the repetitive inspections specified in the related ASB for tail rotor blade assembly P/N L642A2002121. EASA AD 2026-0032 is issued simultaneously with EASA AD 2026-0031. List of New or Revised Airworthiness Directives Amendment Nr 26-02 Page 3 of 4 Aircraft Seats and Harnesses EASA AD 2025-0294R1 B/E Aerospace Fischer Medical Seats – Modification EASA AD 2025-0294 was prompted by the determination that affected seats, certified for aft facing (AF) and forward facing (FF) installations, have been delivered with an incorrect version of the swivel unit, which has been certified only for AF installation. This condition, if not corrected, could result in injury of the occupant of a FF seat during a survivable accident. To address this potential unsafe condition, Fischer Seats issued an ASB, with instructions to reconfigure the swivel unit, and EASA issued AD 2025-0294 to require modifications of the seats. Since that AD was issued, comments have been received during the post publication consultation period. Consequently, EASA AD 2025-0294R1 is revised to correct a typographical error in the ASB definition, and to add Appendix 1, which lists the complete P/N of the affected seats as delivered by Fischer Seats. Bell 429 Series TC AD CF-2025-60R1 TRGB Support Assembly to Tail Boom Attachment - Inspection Transport Canada (TC) and Bell received multiple in-service reports of failed rivets at the joint between the tailboom skin and the tail rotor gearbox support assembly P/N 429-034-701-101 or P/N 429-035-705- 101. In-service reports also revealed that a quality escape resulted in a gapping condition between the tailboom skin and the tail rotor gearbox support fitting at some locations around the joint, and that rivets of inadequate grip length have been installed at the affected joint. The investigation is ongoing to determine the root cause of the failed rivets. Failed rivets at the affected joint, if not detected and corrected, could result in progressive deterioration of the joint structural integrity, potentially resulting in the detachment of the tail rotor gearbox support assembly from the fuselage and consequent loss of control of the helicopter. To address this unsafe condition, TC issued AD CF-2021-15 that mandated the accomplishment of inspections as detailed in the Bell ASB 429-19-47, Revision B, dated 27 January 2021. It provided accomplishment instructions for the initial and repetitive general visual inspection (GVI) and detailed inspection (DET) of the affected rivets at the joint between the tailboom skin and the tail rotor gearbox support assembly, and replacement of the discrepant rivets, as required. The ASB also required repair if an excessive gap (>0.005” or >0.127mm) was found between the tail rotor gearbox support and the tailboom skin during inspections. Following a report of numerous failed rivets discovered within the repetitive inspection interval mandated by AD CF-2021-15, Bell revised ASB 429-19-47 to Rev C on May 6th, 2025 to increase the frequency of repetitive inspections until a terminating action is introduced and to request that operators record whether the rivets were failed, or of finding an improper length while performing the inspection. The compliance statement in AD CF-2025-60 did not accurately capture the intent of the initial inspection for new helicopters. AD CF-2025-60R1 clarifies the statement. TC AD CF-2025-60R1 is considered an interim action and further AD action may follow. Emergency Equipment EASA AD 2025-0297R1 Portable Breathing Equipment – Removal from Service EASA AD 2025-0297 was prompted by occurrences reported of PBE not delivering oxygen once donned. Following an investigation, a manufacturing defect was identified affecting certain PBEs manufactured between November 2015 and March 2017 (inclusive). This condition, if not corrected, could result in incapacitation of flight and/or cabin crew members, impairing their ability to accomplish his/her tasks during an emergency, and could result in fatal injury to the affected flight/cabin crewmember. To address this potential unsafe condition, Safran Aerosystems issued a SB with a list of affected PBEs and instructions to remove affected PBE from service, and EASA issued AD 2025-0297 to prohibit use of those PBEs. Since that AD was issued, comments have been received during the post-publication consultation period, and the SB has been revised to remove inconsistencies in the list of the affected PBEs (removal of duplicated S/N). Consequently, EASA AD 2025-0297R1 is revised to correct a typographical error in Note 1, and to include reference to the revised SB. List of New or Revised Airworthiness Directives Amendment Nr 26-02 Page 4 of 4 Microlights - Eurofox Aircraft UK MPD 2026-002R1-E Rudder Pedal Torque Tube – Inspection UK MPD 2026-002-E was prompted by five reported instances in the UK of Eurofox aircraft finding cracks in the vicinity of the welded joint between the rudder pedals and the rudder pedal torque tube on the right rudder bar, resulting in the pedal no longer being rigidly attached to the torque tube. One event was potentially linked to a seized toe brake pivot pin, causing additional force to be transmitted through the joint. More detail of the failures (including images) can be found within the LAA’s MTD-05-2025 Issue 4 (or later issue) which can be found on the LAA website. Despite an on-going investigation, the exact cause or mechanism of the failure has not been positively identified. Whilst the failures have so far affected aircraft involved in towing gliders, all the circumstances and factors potentially influencing each of the failures are not unique to aircraft used in this type of operation. This condition, if not detected and corrected, could result in loss of control of the aircraft. For the reasons described above, the UK CAA issued MPD 2026-002-E which required a repetitive inspection to detect and correct any potential cracks in this area. UK MPD 2026-002R1-E retains the requirements in superseded MPD 2026-002-E at original issue and is revised to allow embodiment of a modification which is a terminating action for the repetitive inspection. Tecnam Aircraft EASA AD 2026-0023 Exhaust Muffler – Inspection EASA Emergency AD 2026-0023 with effective date 16 February 2026 is applicable to Tecnam P2010 aeroplanes fitted with a Lycoming IO-390 engine (MOD2010/078), up to S/N 335 inclusive. EASA Emergency AD 2026-0023 is prompted by an occurrence of unrecoverable loss of engine power on a P2010 aeroplane. A subsequent investigation identified a 95% blockage of the exhaust, due to disconnection of a component in the muffler. Similar impending failure was detected on another aeroplane. This condition, if not detected and corrected, could result in loss of engine power, and possible loss of control of the aeroplane. To address this potential unsafe condition, Tecnam issued a SB, providing instructions for repetitive inspections of the muffler. For the reason described above, this AD requires repetitive inspections of the muffler and, in case of findings, to contact Tecnam for repair instructions. The EASA AD can be obtained from the EASA AD webpage at: http://ad.easa.europa.eu/ CIVIL AVIATION AUTHORITY OF NEW ZEALAND A/L 26-02 AIRWORTHINESS DIRECTIVE SCHEDULE REVISION STATUS 26 February 2026 Page 1 Schedule: Date: AD Schedule Cover Page 26 FEB 26 AD Schedule Revision Status 26 FEB 26 List of New or Revised ADs 26 FEB 26 Aeroplanes Aeroplanes General - Large (Greater than 5700kg MCTOW) 27 JUL 23 Aeroplanes General - Small (Up to 5700kg MCTOW) 29 JUN 23 Aero Commander 100 Series 24 JUN 21 Aerostar 600 and 601 Series 25 FEB 21 Air Tractor AT-402, AT-502 & AT-504 Series 29 APR 21 Air Tractor AT-602 29 APR 21 Airtourer Series (NZ Aerospace) 26 OCT 00 Alpha Aviation HR200 & R2000 Series 27 AUG 15 American Champion 7 and 8 Series 26 JUL 18 Auster & Beagle Series 26 JUL 12 Aviat A-1 Series (Husky) 27 AUG 20 BAC-167 Strikemaster 30 OCT 14 Beagle Aircraft B.121 Series 2 30 JUN 11 Beechcraft 17 Series 31 AUG 00 Beechcraft 18 Series 31 AUG 00 Beechcraft 23 & 24 Series 31 AUG 00 Beechcraft 33, 35 & 36 Series 19 DEC 19 Beechcraft 60 Series 22 FEB 01 Beechcraft 76 Series 29 APR 21 Beechcraft 77 Series 28 AUG 08 Beechcraft 90 Series 27 MAY 10 Beechcraft 58 & 95 Series 29 AUG 13 Beechcraft 99 Series 27 JUL 06 Beechcraft 200 Series 30 OCT 25 Beechcraft 300LW 24 FEB 22 Boeing-Stearman E75 & A75N1 28 AUG 08 Bolkow BO 208 C Junior 18 DEC 25 Bolkow BO 209 Monsun 18 DEC 25 British Aerospace Dove (DH 104) 19 FEB 93 British Aerospace Heron (DH 114) 19 FEB 93 Britten-Norman Islander BN2 Series 25 JUL 24 Cessna 120 Series 28 APR 22 Cessna 150/152 Series 29 SEP 11 Cessna 170 Series 30 JUN 11 Cessna 172 Series (includes R172) 29 OCT 20 Cessna 175 Series 28 JUL 16 Cessna 177 Series 23 FEB 23 Cessna 180 Series 26 NOV 20 Cessna 182 Series 27 NOV 25 Cessna 185 Series 26 NOV 20 Cessna 188 Series 27 AUG 20 Cessna 195 Series 28 NOV 13 Cessna 206 Series 29 OCT 20 Cessna 207 Series 29 OCT 20 Cessna 208 Series 25 MAR 21 Cessna 210 & 205 Series 23 FEB 23 Cessna 303 Series 30 JUN 11 Cessna 337 Series 27 JUL 17 Cessna 310 & 320 Series 29 SEP 16 Cessna 402 Series 31 MAY 18 Cessna 404 Series 29 NOV 07 Cessna 414 Series 24 FEB 00 Cessna 421 Series 31 MAY 18 Cessna 425 Series 27 APR 06 Cessna 441 Series 27 MAR 14 Cessna 500 Series 27 MAY 10 Cessna 501 Series 24 SEP 15 Cessna 510 Series 26 APR 18 Cessna 525 Series 26 SEP 24 Cessna 560 Series 27 MAY 10 Cirrus SR20 and SR22 Aircraft 19 DEC 24 De Havilland DH60 Series (Moth) 26 APR 18 De Havilland DH80 Series (Puss Moth) 26 MAR 09 De Havilland DH82 Series (Tiger Moth) 26 APR 18 De Havilland DH83 Series (Fox Moth) 26 APR 18 De Havilland DH89 Series (Dragon Rapide / 28 OCT10 Dominie) De Havilland DH94 Series (Moth Minor) 31 AUG 17 De Havilland DHC-1 Series (Chipmunk) 22 FEB 18 De Havilland DHC-2 Series (Beaver) 30 MAR 23 De Havilland DHC-3 Series (Otter) 28 AUG 25 Diamond DA 20 Series 29 JAN 26 Diamond DA 40 Series 31 JULY 25 Diamond DA 42 Series 19 DEC 24 Diamond DA 62 Series 18 JAN 24 Douglas DC3C-S1C3G 18 APR 19 Dornier Do 228 Series 27 SEP 07 Eagle X-TS & 150 Series 30 AUG 07 Embraer EMB-500 26 NOV 20 Embraer EMB-820 Series 25 FEB 21 Erco 415-D Series (Ercoupe) 31 JAN 13 Extra EA 300 Series 1 OCT 20 Fairchild SA227 25 JUNE 09 G-164 Ag-Cat Series 25 MAY 23 Gippsland GA200 Fatman 27 SEP 12 Gippsland GA8 Airvan 30 JAN 25 Grumman American AA-1 & AA-5 Series 29 JUL 21 Grumman G-44 Series 25 NOV 94 Gulfstream Aerospace G-IV Series 27 SEP 07 Gulfstream Aerospace GA-7 28 FEB 19 Harvard 2, 2A and 3 Series 26 SEP 13 Helio H-250 (Courier) 27 OCT 16 Jabiru Aeroplane Series 27 MAY 21 Kodiak 100 27 JULY 23 Lake LA-4, LA-4-200 & Model 250 28 SEP 17 Maule Series 30 JAN 25 Miles M38 Messenger 18 JUN 24 Mitsubishi MU-2B-26A/ -60 Series 28 JAN 21 Mitsubishi MU-2B-30 Series 25 JUN 20 Mooney M20 Series 23 FEB 23 Moravan Zlin Z-50 28 JUL 05 Moravan Zlin Z-137T 28 JUL 05 Nanchang CJ-6 Series 23 FEB 17 North American P-51 Series 30 MAY 13 Nomad N22 and N24 Series 21 APR 11 Pacific Aerospace CT/4 Series 29 APR 21 Pacific Aerospace FBA-2C Series 29 SEP 22 Pacific Aerospace Fletcher FU24 Series 28 JUL 16 Pacific Aerospace Cresco 08-600 30 APR 20 Pacific Aerospace 750XL 29 AUG 19 Percival Proctor Mk1 26 JUL 07 Percival Proctor Mk5 24 FEB 00 Pilatus PC-6 Series 18 DEC 25 Pilatus PC-12 Series 18 DEC 25 Piper J3 Series 27 FEB 25 Piper PA-14 Series 27 FEB 25 Piper PA-18 Series 27 FEB 25 Piper PA-20 Series 27 FEB 25 Piper PA-22 Series 27 FEB 25 Piper PA-23 Series 27 JAN 22 Piper PA-24 Series 28 JUN 18 Piper PA-25 Series 30 JAN 25 Piper PA-28 Series 25 SEP 25 Piper PA-30 Series 28 JUN 18 Piper PA-31 Series 29 JUL 21 Piper PA-32 Series 28 JAN 21 Piper PA-34 Series 30 MAY 24 Piper PA-38 Series 27 OCT 11 Piper PA-39 Series 17 DEC 15 Piper PA-42 Series 27 OCT 11 Piper PA-44 Series 30 MAY 24 Piper PA-46 Series 21 DEC 23 Pitts S-1 & S-2 Series 26 SEP 19 PZL-M18 Dromander Series 25 SEP 03 PZL-104 Wilga 35 and 80 27 JUN 13 Reims F406 Series 31 JAN 19 Robin DR400 Series 18 JUN 24 Robin R1180 Series 22 FEB 18 Robin R3000 Series 27 NOV 14 Rockwell Commander 112 & 114 Series 24 JUN 21 Slingsby T67 Series 24 NOV 16 Rallye, MS880 and MS890 Series 27 APR 23 Socata TB9, TB10 and TB20 Series 31 JULY 25 CIVIL AVIATION AUTHORITY OF NEW ZEALAND A/L 26-02 AIRWORTHINESS DIRECTIVE SCHEDULE REVISION STATUS 26 February 2026 Page 2 Sud Aviation Gardan Horizon GY 80 18 DEC 08 Supermarine Spitfire 26 AUG 20 Taylorcraft BC12-D 26 AUG 20 Tecnam Aircraft 26 FEB 26 Thrush S2R Series 26 OCT 17 Transavia PL-12 Series 29 JAN 26 Twin Commander 500/600 Series 30 MAY 13 Univair Stinson 108 Series 22 FEB 18 Vulcanair P68B, P68C and P68C-TC 26 OCT 23 Yakovlev/Aerostar Series 27 OCT 16 Yeoman YA-1 Series 25 OCT 12 Amateur Built Amateur Built Aircraft 30 MAY 24 Ex-military & Vintage Factory Built Aircraft, not type certified Ex-military and Vintage Factory Built Aircraft 29 JAN 26 Microlight Microlight 26 FEB 26 Helicopters Helicopter - General 25 SEP 25 Agusta Bell AB212 30 MAY 24 Airbus Helicopters SA 315 & SA 316 27 OCT 11 Airbus Helicopters AS 350 26 FEB 26 Airbus Helicopters AS 355 29 JAN 26 Airbus Helicopters EC 120 31 JULY 25 Airbus Helicopters EC 130 27 NOV 25 Airbus Helicopters EC 155 and SA 365 26 FEB 26 Airbus Helicopters Deutschland BO 105 30 OCT 25 Airbus Helicopters Deutschland EC 135 26 FEB 26 Airbus Helicopters Deutschland MBB-BK 117 29 JAN 26 Bell/Kawasaki-Bell 47 Series 25 JUN 09 Bell 205 Series 31 OCT 24 Bell 206 Series and Agusta Bell AB206 Series 25 JUL 24 Bell 212 Series 31 OCT 24 Bell 214 Series 26 JUN 14 Bell 222 Series 28 JUL 22 Bell 407 Series 27 NOV 25 Bell 412 Series 31 OCT 24 Bell 427 Series 27 NOV 25 Bell 429 Series 26 FEB 26 Bell 505 Series 29 JAN 26 Bell OH-58 Series 27 NOV 14 Bell UH-1, TH-1 and HH-1 Series 31 OCT 24 Boeing Vertol 107-II 31 AUG 06 Brantly Aircraft B-2 Series 23 DEC 21 Enstrom F-28, 280 & 480 Series 27 SEP 18 Fairchild FH-1100 Series 30 NOV 06 Guimbal Cabri G2 18 DEC 25 Hiller UH-12C & UH-12E Series 28 AUG 25 Kaman K-1200 Kmax 24 FEB 11 Kawasaki BK117 Series 30 OCT 25 Leonardo A109 and AW109 Series 25 SEP 25 Leonardo A119 and AW119 Series 25 SEP 25 Leonardo AW169 29 MAY 25 MD 369, Kawasaki/Hughes 369 & 500N 25 SEP 25 MD 600N 25 SEP 25 MD 900N 22 OCT 15 Robinson R22 Series 31 OCT 24 Robinson R44 Series 19 JUNE 25 Robinson R66 Series 29 FEB 24 Sikorsky/Schweizer (Hughes) 269 Series 22 MAR 18 Sikorsky Aircraft S-55 Series 25 AUG 05 Sikorsky Aircraft S-76 Series 24 JUN 21 Gliders Gliders General 25 NOV 21 DG Aviation -100 /-200 /-300 /-400 /-500 /-800 /-808 & /-1000 Series 29 JAN 26 DG-Flugzeugbau LS1, LS3, LS4, LS6 & LS8 Series 22 DEC 22 Diamond/Hoffmann H36 Dimona 30 JUN 11 Eiravion OY Pik 20 Series 11 JUN 93 Elliots Eon 463 Series 29 AUG 97 Glasflugel and HPH Glasflugel 28 OCT 21 Grob 31 JULY 25 KR-03A Puchatek 26 July 18 Lange E1 Antares 28 AUG 14 LET Blanik L-13 Series 31 AUG 17 M&D Gliders JS-MD Series 25 NOV 21 MBB Phoebus Series 11 JUN 93 PW-5 Smyk 26 JUL 18 PW-6U 26 JUL 18 Schempp-Hirth Series 31 JULY 25 Schleicher Series 28 JUL 22 Schneider ES52/II Kookaburra 29 OCT 09 Slingsby Series 22 FEB 18 Sportine Aviacija LAK-17 series 25 JUL 19 Start & Flug 28 AUG 98 Stemme S10 Series 31 AUG 22 SZD Series (Allstar PZL) 31 JAN 19 Technoflug Series 26 APR 02 Vliegtuigbouw NV Sagitta 11 JUN 93 Balloons Balloons 28 AUG 25 Ultramagic Balloons 25 FEB 16 Engines Austro E4 Series 26 SEP 24 Engines General – Reciprocating Engines 29 JUNE 23 Blackburn Cirrus 27 JUN 02 Continental 6-285-C Series 28 MAY 20 Continental A-50, A-65, C-75 & C-85 Series 28 MAY 20 Continental C-90 & O-200 Series & RR C-90 Series 28 MAY 20 Continental 240 Series & RR O-240-A Series 28 MAY 20 Continental 300 Series 28 SEP 23 Continental 360 Series 28 SEP 23 Continental 470 Series 28 SEP 23 Continental 520 Series 28 SEP 23 Continental 550 Series 28 SEP 23 Continental TAE 125-01 & TAE 125-02 Series (previously Technify Motors & Thielert Aircraft Engines) 19 DEC 24 De Havilland Gipsy 28 AUG 08 Franklin 30 OCT 03 GE Aviation Czech M601 Series (previously Walter Engines) 30 JAN 25 General Electric T-58 Series 25 MAR 04 Honeywell Int. LTS101 & T53 Series 30 JUN 22 Honeywell International T5508D 26 JUL 12 Honeywell International TFE731 Series 30 APR 09 Honeywell International TPE331 Series 29 NOV 18 Jabiru 2200 & 3300 27 SEP 12 Kinner R-55 (R-540-1) 29 NOV 07 Limbach Engines 29 JUL 10 Lycoming Engines - FAA TC E-223 28 NOV 24 Lycoming Engines - FAA TC E-229 28 FEB 19 Lycoming Engines - FAA TC 1E12 28 NOV 24 Lycoming Engines - FAA TC E-274 28 NOV 24 Lycoming Engines - FAA TC 1E13 28 NOV 24 Lycoming Engines - FAA TC E-279 28 NOV 24 Lycoming Engines - FAA TC 1E10 28 NOV 24 Lycoming Engines - FAA TC E-286 28 NOV 24 Lycoming Engines - FAA TC 1E1 28 NOV 24 Lycoming Engines - FAA TC E26EA 28 NOV 24 Lycoming Engines - FAA TC E16EA 28 NOV 24 Lycoming Engines - FAA TC E-275 28 FEB 19 Lycoming Engines - FAA TC 1E4 28 NOV 24 Lycoming Engines - FAA TC 1E7 28 FEB 19 Lycoming Engines - FAA TC E14EA 28 NOV 24 Lycoming Engines - FAA TC E-295 28 NOV 24 Lycoming Engines - FAA TC E-304 28 NOV 24 Lycoming Engines - FAA TC 1E15 28 FEB 19 Lycoming Engines - FAA TC 108 27 AUG 15 Lycoming Engines - FAA TC E00004NY 28 NOV 24 Lycoming Engines - FAA TC E00006NY 28 NOV 24 Mikron III Series 28 JAN 16 Pratt & Whitney Piston Series 23 FEB 23 Pratt & Whitney JT8D Series 27 OCT 95 Pratt & Whitney JT15D Series 30 JUN 22 CIVIL AVIATION AUTHORITY OF NEW ZEALAND A/L 26-02 AIRWORTHINESS DIRECTIVE SCHEDULE REVISION STATUS 26 February 2026 Page 3 Pratt & Whitney PT6 Series 18 DEC 25 Pratt & Whitney PW206 and PW207 Series 30 AUG 12 Pratt & Whitney PW210 Series 29 MAY 25 Pratt & Whitney PW615 Series 25 FEB 10 Pratt & Whitney PW617F Series 26 NOV 20 Rolls-Royce 250 Series 26 MAY 22 Rolls-Royce Avon Series 28 JUN 18 Rolls-Royce Deutschland Tay 25 MAR 04 Rolls-Royce Merlin & Packard Merlin 28 MAY 20 Rolls-Royce Viper MK522 31 AUG 17 Rolls-Royce Viper MK535 30 OCT 14 Rotax Engines 18 DEC 25 Safran Helicopter Engines – Arriel 1 Series 27 MAR 25 Safran Helicopter Engines – Arriel 2 Series 24 APR 25 Safran Helicopter Engines – Arrius 1A Series 28 AUG 24 Safran Helicopter Engines – Arrius 2B1, 2B2 & 2K1 Series 26 FEB 26 Safran Helicopter Engines – Arrius 2F & 2R Series 25 SEP 25 Safran Helicopter Engines – Artouste III 27 OCT 16 Solo 2350 Series 26 MAY 22 Solo 2625 Series 26 MAR 20 Superior Air Parts Engines 17 DEC 20 Technify Motors (previously Thielert) 25 JAN 18 Vedeneyev M-14, Ivchenko AI-14 & Housai HS-6 Series 18 APR 19 Williams International FJ44 Series 31 OCT 24 Propellers & Prop Governors Propellers General AD Supplements (NZCAR III A6-3) JUL 54 (NZCAR III A6-4) JUL 54 Dowty Rotol Series 29 AUG 13 DUC Hélices H-FLR2 (FLAIR-2) Series 28 JUN 18 Fairey-Reed Series AD Supplements (NZCAR III A6-2) AUG 64 Hamilton Standard Series 29 SEP 16 Hartzell Series 27 MAY 21 Hoffman Series 28 APR 22 McCauley Series 1 OCT 20 MT Propeller Series 28 JUL 22 Ontic Propeller Governors 29 JUL 10 PZL – Warszawa Series 25 SEP 03 Sensenich Series 26 JUL 07 Tarver F200 26 NOV 09 Woodward Propeller Governors 31 JULY 25 Components & Equipment Aircraft Seats & Harnesses 26 FEB 26 Avionics (previously Radio Communication & Navigation Equipment) 29 MAY 25 Brakes and Wheels 28 AUG 25 Carburettors & Injection Systems 30 JUL 20 Electrical Equipment – Reciprocating Engines 27 OCT 22 Electrical Equipment – Aircraft General 29 SEP 16 Emergency Equipment 26 FEB 26 Fuel System Equipment 20 JAN 95 Instruments and Automatic Pilots 25 JUL 24 Role Equipment - Aeroplanes 24 SEP 15 Role Equipment - Helicopters 27 OCT 22 Issued 26 February 2026 Page 1 of 59 CAA of NZ Airworthiness Directive Schedule Helicopters Airbus Helicopters AS 350 Series 26 February 2026 Notes: 1. This AD schedule is applicable to Airbus Helicopters AS 350 series manufactured under Type Certificate Numbers: Aircraft Model: Type Certificate Number: AS 350B EASA R.008 (previously DGAC 157) AS 350B1 EASA R.008 (previously DGAC 157) AS 350B2 EASA R.008 (previously DGAC 157) AS 350BA EASA R.008 (previously DGAC 157) AS 350BB EASA R.008 (previously DGAC 157) AS 350B3 EASA R.008 (previously DGAC 157) AS 350D FAA H9EU 2. The European Union Aviation Safety Agency (EASA) is the National Airworthiness Authority (NAA) responsible for the issue of State of Design Airworthiness Directives (ADs) for these helicopters. State of Design ADs can be obtained directly from the EASA website at: http://ad.easa.europa.eu/ Links to other NAA websites are available on the CAA website at: Links to state of design airworthiness directives | aviation.govt.nz 3. The ADs in this schedule are aligned with those applicable ADs issued by Direction générale de l'Aviation civile (DGAC) and European Union Aviation Safety Agency (EASA). 4. Upgraded Eurocopter/Aerospatiale AS 350 series helicopters require that ADs applicable to the original model be reviewed for applicability and complied with accordingly. 5. Modified Eurocopter/Aerospatiale AS 350 series helicopters fitted with AS 355 aircraft parts require that ADs applicable to the AS 355 series be reviewed for applicability and complied with accordingly. 6. The date above indicates the amendment date of this schedule. 7. New or amended ADs are shown with an asterisk * Contents DCA/AS350/1 Tail Rotor Swivel Joint - Inspection ................................................................................... 6 DCA/AS350/2 Tail Rotor Pitch Control Links - Inspection ........................................................................ 6 DCA/AS350/3 Tail Rotor Gear Box, Attachment Screws - Replacement ................................................. 6 DCA/AS350/4 Flying Controls - Modification ............................................................................................ 6 DCA/AS350/5 Main Rotor Dampers - Inspection...................................................................................... 6 DCA/AS350/6 Baggage Door - Inspection ............................................................................................... 6 DCA/AS350/7 Tail Rotor Gear Box - Modification .................................................................................... 7 DCA/AS350/8 Tail Rotor Hub - Modification ............................................................................................. 7 DCA/AS350/9A Engine Condition Monitoring System - Modification .......................................................... 7 DCA/AS350/10 Main Gear Box Temperature Probe - Inspection and Modification .................................... 7 DCA/AS350/11A Main Rotor Head Assembly - Inspection ........................................................................... 7 DCA/AS350/12 Main Rotor Drive - Inspection ............................................................................................ 8 DCA/AS350/13 Main Gear Box Oil - Inspection ......................................................................................... 8 DCA/AS350/14 Cargo-Swing Installation - Modification ............................................................................. 8 DCA/AS350/15 Engine To Main Gear Box Coupling - Inspection .............................................................. 8 DCA/AS350/16 Tail Rotor Installation - Inspection ..................................................................................... 8 Issued 26 February 2026 Page 2 of 59 CAA of NZ DCA/AS350/17A Tail Rotor Blade Assembly - Retirement ........................................................................... 8 DCA/AS350/18B Fin Installation - Inspection and Modification .................................................................... 9 DCA/AS350/19C Cancelled – DCA/AS350/31A refers ................................................................................. 9 DCA/AS350/20 Tail Rotor Blades - Inspection ........................................................................................... 9 DCA/AS350/21C Cancelled – DCA/AS350/50 now refers ............................................................................ 9 DCA/AS350/22A Main Gear Box, Bevel Ring Gear Assembly - Inspection .................................................. 9 DCA/AS350/23F Cancelled – EASA AD 2024-0133 refers ........................................................................ 10 DCA/AS350/24 Main Gear Box Oil Filter - Inspection .............................................................................. 10 DCA/AS350/25B Main Rotor Shaft - Inspection .......................................................................................... 10 DCA/AS350/26 Emergency Flotation System - Modification .................................................................... 10 DCA/AS350/27 Fuel Filter Drain - Modification ........................................................................................ 11 DCA/AS350/28 Oil and Fuel Filters - Inspection ...................................................................................... 11 DCA/AS350/29 Raised Skid Landing Gear - Modification ........................................................................ 11 DCA/AS350/30 Main Rotor Head - Life Limitation and Inspection ........................................................... 11 DCA/AS350/31A Fuel Filter - Inspection and Modification.......................................................................... 12 DCA/AS350/32 Fuel Filter - Inspection..................................................................................................... 12 DCA/AS350/33E Main Rotor Head, Main Gear Box and Landing Gear – Inspection ................................. 12 DCA/AS350/34 Sliding Doors - Modification ............................................................................................ 13 DCA/AS350/35 Main and Tail Rotor Servo Controls - Inspection ............................................................. 13 DCA/AS350/36B Main Rotor, Rotating Swash Plate - Inspection ............................................................... 13 DCA/AS350/37 Cancelled - CAR 91.603(b) refers ................................................................................... 13 DCA/AS350/38 Tail Rotor Pitch Control Lever Expansion Pin - Inspection .............................................. 13 DCA/AS350/39 Emergency Location Transmitter (ELT) Antenna - Modification ...................................... 14 DCA/AS350/40 Hydraulic Reservoir - Modification................................................................................... 14 DCA/AS350/41A Pitch Change Lever Bushes - Inspection ........................................................................ 14 DCA/AS350/42 Engine Fire Detection System - Modification .................................................................. 14 DCA/AS350/43 Main Rotor Mast Assembly - Inspection .......................................................................... 14 DCA/AS350/44A Sliding Windows - Inspection and Modification ............................................................... 15 DCA/AS350/45 MGB Oil Pressure Switch - Removal .............................................................................. 15 DCA/AS350/46 Cyclic Pitch Change Control Rod - Inspection ................................................................ 15 DCA/AS350/47 Main Rotor Shaft Oil Jet - Inspection............................................................................... 15 DCA/AS350/48 MGB Suspension Bi-directional Cross Beam - Inspection .............................................. 16 DCA/AS350/49 Tail Boom Attachment Screws - Replacement ................................................................ 16 DCA/AS350/50 Cancelled – EASA AD 2015-0195 refers ........................................................................ 17 DCA/AS350/51 Single Pole Circuit Breakers – Inspection and Removal ................................................. 17 DCA/AS350/52B Tail Rotor Hub Pitch Change Plate Bearings - Inspection ............................................... 17 DCA/AS350/53 NR Indicator Lighting - Modification ................................................................................ 18 DCA/AS350/54A Tail Rotor Pitch Change Rotating Plates – Inspection and Modification.......................... 18 DCA/AS350/55 Engine Oil Tank Breather Pipe - Fireproofing ................................................................. 19 DCA/AS350/56 Ferry Fuel Tanks - Electrical Bonding ............................................................................. 19 DCA/AS350/57B Tail Rotor Drive Shaft Forward Fairing - Inspection ........................................................ 19 DCA/AS350/58 Tail Rotor Hub Pitch Change Plate Bearings - Replacement .......................................... 21 DCA/AS350/59 Cancelled – DCA/AS350/108 refers ................................................................................ 21 DCA/AS350/60 Engine Indication System – Resistor Installation ............................................................ 21 DCA/AS350/61A Cancelled – DGAC AD 2001-557-086R3 refers .............................................................. 21 DCA/AS350/62 Cancelled – DCA/AS350/74 refers .................................................................................. 21 DCA/AS350/63B Tail Servo Control Eye End Fitting – Inspection and Rework .......................................... 22 DCA/AS350/64 Engine Control Switch – Inspection................................................................................. 22 DCA/AS350/65 Hydraulic Cut-Off Control - Modification .......................................................................... 22 DCA/AS350/66 Cancelled - DCA/AS350/94 refers................................................................................... 23 DCA/AS350/67 HSI - Inspection .............................................................................................................. 23 DCA/AS350/68 Hawker Pacific TRW-SAMM Main Servocontrols - Replacement ................................... 23 DCA/AS350/69 Eurocopter Canada Collective Lock - Replacement ........................................................ 23 DCA/AS350/70 Cancelled – EASA AD 2019-0228 refers ........................................................................ 23 Issued 26 February 2026 Page 3 of 59 CAA of NZ DCA/AS350/71 Cyclic Friction Cup - Inspection ....................................................................................... 24 DCA/AS350/72 Dynamic Components – Life Correction.......................................................................... 24 DCA/AS350/73A Battery Lug - Inspection .................................................................................................. 24 DCA/AS350/74 TRW-SAMM Servo Controls - Replacement ................................................................... 25 DCA/AS350/75A Flight Control Stops – Inspection and Modification ......................................................... 26 DCA/AS350/76 Collective Lever Lock – Inspection .................................................................................. 26 DCA/AS350/77 Fuel Bleed Lever - Modification ....................................................................................... 26 DCA/AS350/78 Rear Fuselage - Inspection ............................................................................................. 26 DCA/AS350/79 Tail Rotor Control Cable - Replacement ......................................................................... 27 DCA/AS350/80A Cancelled – DCA/AS350/112 refers ................................................................................ 27 DCA/AS350/81 Hydraulic System Cut-off- Modification ........................................................................... 27 DCA/AS350/82 Cancelled - DCA/AS350/98 refers................................................................................... 27 DCA/AS350/83 Tail Rotor Blade Trailing Edge Tab – Inspection and Modification .................................. 28 DCA/AS350/84B Cancelled - DCA/AS350/99 refers................................................................................... 28 DCA/AS350/85 Cancelled – DCA/AS350/86 refers .................................................................................. 28 DCA/AS350/86 Cancelled - DCA/AS350/97 refers................................................................................... 28 DCA/AS350/87 Breeze Eastern 450-lb Electric Hoist - Inspection ........................................................... 28 DCA/AS350/88 Cancelled – DCA/AS350/91 refers .................................................................................. 29 DCA/AS350/89 Main Servo Controls – Inspection and Replacement ...................................................... 29 DCA/AS350/90 Cancelled – DCA/AS350/109 refers ................................................................................ 30 DCA/AS350/91 Cancelled – DCA/AS350/109 refers ................................................................................ 30 DCA/AS350/92 Cancelled – DCA/AS350/126 refers ................................................................................ 30 DCA/AS350/93 Twist Grip Solenoid – Inspection, Operation and Replacement ...................................... 30 DCA/AS350/94 Cancelled – DCA/AS350/103 refers ................................................................................ 30 DCA/AS350/95 Cancelled - DCA/EMY/27 refers ..................................................................................... 30 DCA/AS350/96A Tail Rotor Servo Control – Inspection and Rework ......................................................... 31 DCA/AS350/97B Cancelled – DCA/AS350/106 refers ................................................................................ 31 DCA/AS350/98 Sliding Door Rollers and Rails – Inspection and Modification ......................................... 31 DCA/AS350/99 RH Cabin Vibration Damper and Blade Assy – Inspection and Modification................... 32 DCA/AS350/100 Starter Generator – Load Limitation ................................................................................ 32 DCA/AS350/101 Yaw Control Load Compensator Lever – Inspection ....................................................... 33 DCA/AS350/102 Main & Tail Rotor Servo Controls – Inspection and Rework ........................................... 33 DCA/AS350/103C Tail Rotor Blade Skin – Inspection and Repair................................................................ 34 DCA/AS350/104 Cabin Floor Cross Member – Inspection and Rework ..................................................... 34 DCA/AS350/105 Main & Tail Rotor Servo Controls – Inspection and Replacement .................................. 35 DCA/AS350/106 Sliding Door Rear Fitting and Support Shaft – Inspection and Replacement .................. 36 DCA/AS350/107 Collective Lever Recess - Modification ........................................................................... 36 DCA/AS350/108 Rear Bench Seat Cushions – Removal or Modification................................................... 37 DCA/AS350/109 Cancelled – DCA/AS350/114 refers ................................................................................ 37 DCA/AS350/110 Aerazur Emergency Flotation Gear - Inspection and Replacement ............................... 37 DCA/AS350/111A Cancelled – DCA/AS350/115 refers ................................................................................ 38 DCA/AS350/112 Emergency Flotation Gear – Inspection, Placard and Replacement ............................... 38 DCA/AS350/113 Cancelled – DCA/AS350/116 refers ................................................................................ 39 DCA/AS350/114 Fin Attach Fittings – Inspection, Modification & Replacement......................................... 39 DCA/AS350/115B Collective Lever Lock – Inspection and Rework .............................................................. 40 DCA/AS350/116 Starter Generator Damping Assembly – Adjustment and Marking .................................. 41 DCA/AS350/117 Cancelled – EASA AD 2013-0061 refers ........................................................................ 41 DCA/AS350/118 Cancelled – EASA AD 2010-0006 refers ........................................................................ 41 DCA/AS350/119 Cancelled – DCA/AS350/120 refers ................................................................................ 42 DCA/AS350/120 Tail Gearbox Control Lever – Inspection, Rework and Replacement .............................. 42 DCA/AS350/121 Hydraulic Servo Hoses – Inspection and Rework ........................................................... 43 DCA/AS350/122 EASA AD 2011-0072 Cancelled by EASA on 4 March 2022 .......................................... 43 DCA/AS350/123 Tail Gearbox Casing Assembly – Inspection and Replacement...................................... 43 DCA/AS350/124 Cancelled – EASA AD 2011-0164R1 refers .................................................................... 44 Issued 26 February 2026 Page 4 of 59 CAA of NZ DCA/AS350/125 Cancelled – EASA AD 2013-0281 refers ........................................................................ 44 DCA/AS350/126 Cancelled – EASA AD 2012-0252 refers ........................................................................ 44 DCA/AS350/127 Fire Detection System – Modification .............................................................................. 44 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. ..... 45 2012-0205 Sliding Door Lower Ball-joint – Modification .................................................................... 45 2012-0207-E Cancelled – EASA AD 2012-0217-E refers ..................................................................... 45 2012-0217-E Cancelled – EASA AD 2013-0029 refers ........................................................................ 45 2012-0252 Cancelled – EASA AD 2017-0035 refers ........................................................................ 45 2012-0257-E Cancelled by EASA AD 2012-0257-CN – Purpose fulfilled ............................................. 45 2013-0029 Tail Rotor Laminated Half Bearings – Inspection ............................................................ 45 2013-0044-E Cancelled – EASA AD 2013-0284-E refers ..................................................................... 45 2013-0061 Cancelled – EASA AD 2013-0191-E refers ..................................................................... 45 2013-0088 Cancelled – EASA AD 2015-0132 refers ........................................................................ 45 2013-0095-E Main/Tail Rotor Servo-Control Bearings – Inspection and Replacement ........................ 45 2013-0133-CN Cancelled – Purpose fulfilled........................................................................................... 45 2013-0191-E Cancelled – EASA AD 2017-0052 refers ........................................................................ 46 2010-0006 Cancelled by EASA on 3 September 2021 ..................................................................... 46 2013-0281R1 Position Strobe Light – Inspection ................................................................................... 46 2013-0284R1 Cancelled – EASA AD 2014-0233 refers ........................................................................ 46 2013-0287 Cancelled – EASA AD 2021-0195 Refers ....................................................................... 46 2014-0076R3 Cancelled – EASA AD 2022-0051 refers ........................................................................ 46 2014-0132R1 Rotating Star Swashplate – Inspection ........................................................................... 46 2014-0233 Hydraulic Pump Bearing - Inspection .............................................................................. 46 Transport Canada AD CF-2015-10 STC SR00825NY-D - Hydraulic Test Switch Replacement....................... 46 2015-0094 Cancelled by EASA on 3 September 2021 ..................................................................... 46 DGAC AD 1991-165-058R1 Electric Hoist Bonding – Inspection .................................................................. 47 2015-0132 Cancelled – EASA AD 2021-0194 Refers ....................................................................... 47 2015-0178 Normal Procedures – AFM Amendment ......................................................................... 47 2015-0195 Tail Rotor Drive Shaft Bearings – Inspection .................................................................. 47 DCA/AS350/128C Forward Two-place Seat - Operating Limitations .......................................................... 47 2016-0020 Main Gearbox Casings – Inspection ............................................................................... 50 2016-0021 Main Gearbox Bottom Casing – Inspection ..................................................................... 50 2016-0220 Dual Hydraulic System – Inspection................................................................................ 50 2016-0260 Main Rotor NR Indicator – Inspection ............................................................................. 50 2017-0020R1 Tail Rotor Pitch Rod – Inspection .................................................................................... 50 2011-0164R3 Tail Rotor Control Stop Screws – Inspection................................................................... 50 2017-0032 Cancelled by EASA on 11 August 2021 .......................................................................... 51 2017-0035 Twist Grip Assembly – Inspection ................................................................................... 51 2017-0052 Cancelled – EASA AD 2017-0059 refers ........................................................................ 51 2017-0059 Cancelled – EASA AD 2023-0133 refers ........................................................................ 51 2017-0089R1 Main Rotor Mast Upper Bearing - Inspection ................................................................ 51 2017-0109 (Correction) Starter Generator and Brushes - Inspection ............................................................ 51 2017-0114 Cancelled - EASA AD 2020-0186 refers ....................................................................... 51 2017-0143 Direct Current (Optional) Second Battery – Replacement............................................... 51 Transport Canada AD CF-2017-37 Restriction of Directional Control Pedal Movement ............................... 51 DCA/AS350/129A Cargo Swing Modification OAL114 – Inspection ........................................................... 52 2018-0152 Cancelled – EASA AD 2022-0128 refers ........................................................................ 52 2018-0206 Mast Upper Bearing Sealant Bead/Inner Race Retaining Rings - Inspection................ 52 FAA AD 2018-18-12 Cancelled – FAA AD 2019-16-16 refers .......................................................................... 52 FAA AD 2018-25-17 Air Comm Corp Air Conditioning System – Inspection .................................................... 52 2018-0287 Cancelled – EASA AD 2019-0060 refers ........................................................................ 52 DCA/AS350/130 HETS STC 11/21E/34 – Removal from Service ............................................................ 53 Issued 26 February 2026 Page 5 of 59 CAA of NZ Transport Canada CF-2019-01 Helicopter External Transport System (HETS) STC SH98-35..................... 53 2019-0060 Tail Rotor Gearbox Actuating Rod – Inspection .............................................................. 53 DGAC AD 2001-557-086R3 Starflex Star – Inspection ................................................................................. 53 2019-0184 Main Rotor Servo Actuators – Inspection ........................................................................ 54 FAA AD 2019-16-16 Inlet Barrier Filter – Inspection ........................................................................................ 54 2019-0225-E MGB Drive Shaft / Engine Coupling – Inspection ............................................................ 54 2019-0228 Electric Hoist Installation – Inspection ............................................................................. 54 2019-0280 Spherical Bearing – Inspection ....................................................................................... 54 FAA AD 2020-02-23 Emergency Float System STC SR00470LA – Inspection ............................................... 54 DCA/AS350/131 Dual Front Seat Modification MB 25.20.05 - Inspection ................................................ 54 2020-0064 Emergency Flotation System – Inspection ...................................................................... 55 2020-0175 Cancelled by EASA on 13 September 2021 ................................................................... 55 2020-0186 Cancelled – EASA AD 2021-0099 refers ........................................................................ 55 2020-0217-E Cancelled – EASA AD 2021-0023 refers ........................................................................ 55 2020-0224R1 Tail Rotor Blades – Inspection ........................................................................................ 55 2021-0023 Cyclic Stick Grip UP / Down Hoist Control Switch – Modification .................................... 55 2021-0048 Cancelled – EASA AD 2023-0064 refers ........................................................................ 56 2021-0099 Cancelled – EASA AD 2023-0075 refers ........................................................................ 56 2021-0123-E Tail Rotor Load Compensator – Inspection ..................................................................... 56 2021-0168 Cancelled – EASA AD 2024-0018 refers ........................................................................ 56 2021-0194R1 Cancelled – EASA AD 2024-0133 refers ........................................................................ 56 2021-0195 Engine Digital ECU Emergency Procedure – AFM Amendment ..................................... 56 2021-0282R1 (Correction) Tail Rotor Head Pitch Change Unit Bearing Spacer - Inspection........................ 56 2022-0051 (Correction) Rear Structure Junction Frame Reinforcement Angles - Inspection.......... 56 2022-0077-E Flight Control Flexball Cables - Replacement ............................................................... 56 2022-0128 Main Gearbox Bracket Bolts - Inspection ...................................................................... 56 2022-0246 Main Rotor Blades - Inspection ..................................................................................... 56 2023-0044 Main Gearbox Planet Gear - Inspection ........................................................................ 57 2023-0064 Main Rotor Pitch Rod Upper Links - Inspection ............................................................ 57 2023-0075 Cancelled – EASA AD 2023-0089 refers ........................................................................ 57 2023-0089 Cancelled – EASA AD 2024-0139 refers ........................................................................ 57 2023-0107 (Correction) Cargo Swing Frame - Inspection ................................................................. 57 2023-0127 Main Gearbox Engine Coupling - Inspection ................................................................... 57 2023-0131 Sliding Doors - Inspection ............................................................................................... 57 2023-0133 Cancelled – EASA AD 2023-0187 refers ........................................................................ 57 2023-0187R1 Microswitches - Inspection .............................................................................................. 57 2024-0018 Indicating / Recording Systems Control Unit – Inspection............................................... 58 2024-0133R1 Airworthiness Limitations Section - Amendment ............................................................. 58 2024-0139 Vertical Fin - Inspection................................................................................................... 58 2025-0025 Emergency Release Control of Cargo Swing Installation – Inspection............................ 58 2025-0036 Cargo Hook Assembly – Inspection ................................................................................ 58 2025-0137 (Correction) Airworthiness Limitations Section - Amendment ..................................................... 58 2025-0159 Sliding Door Placards - Installation ................................................................................. 58 2025-0263 (Correction) Single Generation Hydraulic System Wiring Diode – Cut-off Test........................... 58 * 2026-0021 MGB to Fuselage Mounts and Attachment - Inspection .................................................. 59 Airbus Helicopters AS 350 Series Issued 26 February 2026 Page 6 of 59 CAA of NZ DCA/AS350/1 Tail Rotor Swivel Joint - Inspection Applicability: All Model AS350 not incorporating mods. AMS 350A.07.6513 and AMS 350A.07.8515. Requirement: Inspect per Aerospatiale SB 05.01. (DGAC AD 1978-193-001 refers) Compliance: At intervals not exceeding 50 hours TIS. Effective Date: 17 August 1979 DCA/AS350/2 Tail Rotor Pitch Control Links - Inspection Applicability: All Model AS350 not incorporating mods. AMS 350A.07.6510 or AMS 350A.07.6512 and AMS 350A.07.5524. Requirement: Inspect per Aerospatiale SB 05.02 paras 1C.1(A) and 1C.1(B). (DGAC AD 1978-193-001 refers) Compliance: Para 1C.1(A) - Prior to every flight. Para 1C.1(B) - At intervals not exceeding 10 hours TIS. Effective Date: 17 August 1979 DCA/AS350/3 Tail Rotor Gear Box, Attachment Screws - Replacement Applicability: All Model AS350 not incorporating mod. AMS 350A.07.8517. Requirement: Embody replacement screws per Aerospatiale SB 65.07. (DGAC AD F-1979-012-004 refers) Compliance: Within the next 50 hours TIS Effective Date: 17 August 1979 DCA/AS350/4 Flying Controls - Modification Applicability: All Model AS350 not incorporating mod. AMS 350A.07.0452. Requirement: Embody control rod P/N 704A.34.113 per Aerospatiale SB 67.01. (DGAC AD 1979-013-005 refers) Compliance: Within next 100 hours TIS unless already accomplished. Effective Date: 17 August 1979 DCA/AS350/5 Main Rotor Dampers - Inspection Applicability: All Model AS350 not incorporating mod. AMS 350.07.6063. Requirement: Inspect per Aerospatiale SB 05.03. (DGAC AD 1979-104-006 refers) Compliance: At intervals not exceeding 25 hours TIS. Effective Date: 17 August 1979 DCA/AS350/6 Baggage Door - Inspection Applicability: All Model AS350. Requirement: Inspect L.H. baggage door for correct latching per Aerospatiale SB 52.04. Deficient installations shall be corrected before further flight. (DGAC AD 1979-133-007 refers) Compliance: By 8 August 1979 Effective Date: 31 July 1979 Airbus Helicopters AS 350 Series Issued 26 February 2026 Page 7 of 59 CAA of NZ DCA/AS350/7 Tail Rotor Gear Box - Modification Applicability: All Model AS350 not incorporating mod. AMS 07.8519. Requirement: Modify per Aerospatiale SB 65.08. (DGAC AD 1979-174-009 refers) Compliance: By 31 October 1979 Effective Date: 28 September 1979 DCA/AS350/8 Tail Rotor Hub - Modification Applicability: All Model AS350 Requirement: Modify per Aerospatiale SB 65.13. (DGAC AD 1979-217-011 refers) Compliance: By 31 January 1980 Effective Date: 21 December 1979 DCA/AS350/9A Engine Condition Monitoring System - Modification Applicability: All Model AS350B not incorporating mods. AMS 07.0615 and 07.0804. Requirement: Embody modifications AMS 07.0615 and 07.0804 per Aerospatiale SB 77.02 issue 2. (DGAC AD 1980-165-014 refers) Compliance: Mod. 07.0615 - By 31 March 1980 Mod. 07.0804 - By 31 March 1981 Effective Date: DCA/AS350/9 - 22 February 1980 DCA/AS350/9A - 21 November 1981 DCA/AS350/10 Main Gear Box Temperature Probe - Inspection and Modification Applicability: All Model AS350 not incorporating mod. AMS 350A.07.0733. Requirement: Inspect and modify per Aerospatiale SB 65.18. Probe installations found defective shall be modified before further flight. (DGAC AD F-1980-104-013 refers) Compliance: Inspection - Prior to next flight unless already accomplished. Modification - not later that next 300 hour inspection. Effective Date: 6 June 1980 DCA/AS350/11A Main Rotor Head Assembly - Inspection Applicability: All Model AS350 Requirement: Check starflex attachment bolt torque, inspect and/or renew bolts as necessary, per Aerospatiale SB 05.04 Rev.1. (DGAC AD 1980-184-015R1 refers). Compliance: At 600 hours TTIS and thereafter at intervals not exceeding 400 hours TIS. Aircraft with 590 hours or more TIS shall be initially inspected within next 10 hours TIS unless already accomplished Effective Date: DCA/AS350/11 - 21 November 1980 DCA/AS350/11A - 18 March 1988 Airbus Helicopters AS 350 Series Issued 26 February 2026 Page 8 of 59 CAA of NZ DCA/AS350/12 Main Rotor Drive - Inspection Applicability: All Model AS350 with bevel gear module P/N 350A32.0300.00, .01 or .02. Requirement: Inspect per Aerospatiale telex service bulletin 05.05. Modules with indications of excessive wear must be removed from service before further flight. Compliance: At 600 hours TTIS and thereafter at intervals not exceeding 150 hours TIS. Modules with 580 hours or more TIS, shall be initially inspected within next 20 hours TIS unless already accomplished. Effective Date: 9 January 1981. DCA/AS350/13 Main Gear Box Oil - Inspection Applicability: All Model AS350 with spiro conical modules not incorporating mods. 07.7027 or 07.7042. Requirement: Accomplish spectrometric oil analysis per Aerospatiale telex SB 05.06. Modules with indication of excessive wear must be removed from service before further flight. (DGAC AD F-1981-094-018 refers) Compliance: At 300 hours TTIS and thereafter at intervals not exceeding 300 hours TIS. Effective Date: 3 April 1981 DCA/AS350/14 Cargo-Swing Installation - Modification Applicability: All Model AS350 with cargo-swing installation. Requirement: Modify per Aerospatiale SB 25.19. (DGAC AD 1981-067-016 refers). Compliance: Prior to next use of cargo-swing installation. Effective Date: 12 June 1981. DCA/AS350/15 Engine To Main Gear Box Coupling - Inspection Applicability: All Model AS350. Requirement: Inspect attachment bolts per Aerospatiale SB 01.06 and renew as necessary before further flight. (DGAC AD 1981-084-017 refers) Compliance: At next 300 hour inspection. Effective Date: 12 June 1981. DCA/AS350/16 Tail Rotor Installation - Inspection Applicability: All Model AS350 Requirement: Accomplish dye penetrant and visual inspections per Aerospatiale telex SB 01.07A. Compliance: Dye penetrant inspection - within next 10 hours TIS. Visual inspection - following last flight on each day aircraft is operated. Effective Date: 13 June 1981 DCA/AS350/17A Tail Rotor Blade Assembly - Retirement Applicability: All Model AS350 Requirement: Retire tail rotor pitch change horn assemblies P/N 350A12.1368.01 and 350A12.1368.02 from service. (DGAC AD 1981-184-020 refers) Compliance: P/N 350A12.1368.01 - at 450 hours TTIS. P/N 350A12.1368.02 - at 1250 hours TTIS. Effective Date: DCA/AS350/17 - 6 July 1981 DCA/AS350/17A - 11 December 1981 Airbus Helicopters AS 350 Series Issued 26 February 2026 Page 9 of 59 CAA of NZ DCA/AS350/18B Fin Installation - Inspection and Modification Applicability: All Model AS350 not incorporating mod. 07.1047. Requirement: 1. Inspect per Aerospatiale telex SB 05.07 and SB 05.09. 2. Modify per Aerospatiale SB 55.02 Rev.1. (DGAC AD F-1982-098-026 refers) Compliance: 1. Inspections - At intervals not exceeding 10 hours TIS until modified per Aerospatiale SB's 55.02 Rev.1 and 55.03 respectively. 2. Modification - within next 100 hours TIS. Effective Date: DCA/AS350/18A - 12 February 1982 DCA/AS350/18B - 27 August 1982 DCA/AS350/19C Cancelled – DCA/AS350/31A refers Effective Date: 30 August 2007 DCA/AS350/20 Tail Rotor Blades - Inspection Applicability: All Model AS350 with tail rotor blades, P/N 350.12.0020 all dash numbers, 350.12.0030.00 all dash numbers and 350A.08.1011.00. Requirement: Inspect tail rotor blades for bonding separation of leading edge stainless steel protection strips per Aerospatiale work card AS350.65.20.601. (DGAC AD 1982-024-024 refers). Compliance: 1. Blades with 100 hours or less TTIS or since overhaul - at intervals not exceeding 10 hours TIS until accumulation of 100 hours TIS and thereafter per Aerospatiale M.S.R. AS350 CH5.24 P.2 latest issue. 2. Blades which have exceeded 100 hours TTIS or since overhaul - within next 10 hours TIS, and thereafter per Aerospatiale M.S.R. AS350 CH5.24 P.2 latest issue. Effective Date: 30 April 1982 DCA/AS350/21C Cancelled – DCA/AS350/50 now refers Effective Date: 28 August 1998 DCA/AS350/22A Main Gear Box, Bevel Ring Gear Assembly - Inspection Applicability: All Model AS350 with bevel reduction gear assemblies P/N 350A32.0300.00.01 and .02 not incorporating mods. AMS 07.7082, AMS 07.7083 or AMS 07.7098. Requirement: Visually inspect per Aerospatiale SB 05.10 para 1C(1) and check screw torques per para 1C(2). Correct defective screw installations before further flight. (DGAC AD 1985-068-038 refers). Compliance: Visual inspection - at intervals not exceeding 50 hours TIS until screw torque check accomplished and thereafter at intervals not exceeding 300 hours TIS. Torque check - Within next 300 hours TIS unless already accomplished. Effective Date: DCA/AS350/22 - 11 February 1983 DCA/AS350/22A - 2 August 1985 Airbus Helicopters AS 350 Series Issued 26 February 2026 Page 10 of 59 CAA of NZ DCA/AS350/23F Cancelled – EASA AD 2024-0133 refers Effective Date: 25 July 2024 DCA/AS350/24 Main Gear Box Oil Filter - Inspection Applicability: All model AS350 fitted with 'TEDECO' magnetic plug P/N B4439 per mod 350A.07.0720 (AS 350 SB 65-20). Requirement: Inspect oil filter per Aerospatiale SB 05.12. (DGAC AD 82-175-29 refers). Compliance: At intervals not exceeding 100 hours TIS. Effective Date: 11 February 1983. DCA/AS350/25B Main Rotor Shaft - Inspection Applicability: All Model AS350 with rotor shaft P/N 350A37.1076.00 to .06. Requirement: Inspect per Aerospatiale SB 05.13 Rev.2. Renew defective part before further flight. (DGAC AD 1983-173-036 refers) Compliance: 1. At 300 hours TTIS or within next 50 hours TIS, whichever is the later and thereafter at intervals not exceeding 300 hours TIS. 2. Before further flight following severe rotor tracking abnormalities. Effective Date: DCA/AS350/25A - 2 March 1984 DCA/AS350/25B - 2 May 1986 DCA/AS350/26 Emergency Flotation System - Modification Applicability: All Model AS350B, C and D-1 with air cruiser flotation system installed per STC SH4032SW or SH2825SW. Requirement: Modify floation system per FAA AD 83-11-01 R1. (FAA AD 83-11-01R1 refers) Compliance: Prior to next overwater flight, unless already accomplished. Effective Date: 1 March 1985 Airbus Helicopters AS 350 Series Issued 26 February 2026 Page 11 of 59 CAA of NZ DCA/AS350/27 Fuel Filter Drain - Modification Applicability: Model AS350B and AS350D S/Ns 1 through 1808, 1813 through 1826 except 1818 and 1822 Requirement: Modify fuel filter drain in accordance with SB 28.06. (DGAC 1985-066-039 refers) Compliance: Before 1 September 1985 Effective Date: 2 August 1985. DCA/AS350/28 Oil and Fuel Filters - Inspection Applicability: All Model AS350 Requirement: 1. Inspect main gear box filter and fuel filter cartridges for correct installation per Aerospatiale Telex SB No. 01.14 including amendment 01.14A. 2. When installing replacement `LEBOZEC' and `GAUTHIER' filters ensure that: Fuel filter P/N 432 B12.30 filter cartridge is marked `FUEL' Oil filter P/N 434 B12.11 filter cartridge is marked `OIL'. (DGAC AD 1985-135-042 refers) Compliance: 1. Inspection - Within next 5 hours TIS unless already accomplished 2. Filter check - Prior to installation Effective Date: 28 February 1986 DCA/AS350/29 Raised Skid Landing Gear - Modification Applicability: All Model AS350 with raised skid landing gear and flotation gear installation not incorporating mod. AMS 350A.07.1755 Requirement: To prevent possible interference between landing gear steps and flotation bags when inflated, remove steps per Aerospatiale Telex SB 32.06A (DGAC AD 1986-030-043 refers) Compliance: By 31 May 1986, or prior to flotation gear installation. Effective Date: 2 May 1986 DCA/AS350/30 Main Rotor Head - Life Limitation and Inspection Applicability: All Model AS350B and AS350D with roving sleeve upper and lower beams P/N 350A31.1830.00 and .01; 350A31.1831.00, .04, .05, .06 and .07 Requirement: 1. Remove affected beams from service per Aerospatiale telex SB 01.16 para BB at 4000 hours TTIS. Beams with 3900 hours or more TIS must be removed within next 100 hours TIS. 2. In the event of sudden or repeated occurrence or severe rotor tracking problems inspect per telex SB 01.16 para CC before further flight. If sleeve bush separation found remove beam from service before further flight. (DGAC AD 1986-057-044 refers) Effective Date: 1 August 1986 Airbus Helicopters AS 350 Series Issued 26 February 2026 Page 12 of 59 CAA of NZ DCA/AS350/31A Fuel Filter - Inspection and Modification Applicability: All Model AS350B and AS350D without modification 07.1671 embodied. Note: This AD is no longer applicable once modification 07.1671 is embodied and supersedes DCA/AS350/19C. Requirement: To prevent leaks at the fuel system filter and drain valve, accomplish the following: 1. Pull the drain valve to ensure it is correctly seated. Switch the fuel pump on and confirm that the drain valve does not leak. If any leak is detected repair as required, before further flight. 2. Embody modification 07.1671 per the instructions in Aerospatiale SB 28.07. (DGAC ADs 1986-077-046(B)R2 and 1986-070-045(B) refers) Compliance: 1. Check the drain valve whenever the filter drain is operated until requirement 2 of this AD is accomplished. 2. By 30 November 2007, unless aready accomplished. Effective Date: DCA/AS250/31 - 1 August 1986 DCA/AS350/31A - 30 August 2007 DCA/AS350/32 Fuel Filter - Inspection Applicability: All Model AS350 with LEBOZEC and GAUTHIER fuel filter P/N 432B12.3, .3C or P/N 350A52-1070.00 (post mod. 07.1671) Requirement: To prevent leaks at fuel system filter, check that filter bowl is correctly tightened per instruction given on M.E.T. work card 28.00.00.302 page 3 rev.5A dated 86.21 and subsequent revisions. (DGAC AD 1986-097-047 and Aerospatiale telex SB 28.08 refer) Compliance: Within 50 hours TIS and thereafter whenever filter bowl is disturbed for any other reason. Effective Date: 1 August 1986 DCA/AS350/33E Main Rotor Head, Main Gear Box and Landing Gear – Inspection Applicability: All model AS350 B, B1, C, D and D1 aircraft. Note: The compliance time for requirement 1 extended to 600 hours TIS with no change to the AD requirement. Aerospatiale SB 01.17A can be obtained from the Eurocopter T.I.P.I. web site under AS 350 ASB 01.00.17 Requirement: To prevent failure of main rotor (M/R) star arms and main gear box (MGB) suspension bars, accomplish the following: 1. Inspect the M/R head components, the MGB suspension bars (struts) and landing gear per paragraph CC3, subparagraph CCA, CCB and CCC in Aerospatiale SB 01.17A or later approved revisions. Rework or renew defective parts before further flight. 2. Inspect the M/R head components and MGB suspension bars per paragraph CC3 subparagraphs CCA and CCB in SB 01.17A. Rework or renew defective parts before further flight. (BV AD 1986-125-48R1 refers) Compliance: 1. At intervals not to exceed 600 hours TIS. Prior to further flight following a hard landing which causes abnormal self sustained dynamic vibrations (ground resonance type). 2. Prior to further flight following a hard landing or exposure to high winds without the M/R blades secured. Effective Date: DCA/AS350/33C - 16 January 1998 DCA/AS350/33D - 25 September 1998 DCA/AS350/33E - 30 September 2010 Airbus Helicopters AS 350 Series Issued 26 February 2026 Page 13 of 59 CAA of NZ DCA/AS350/34 Sliding Doors - Modification Applicability: All Model AS350 with LH and/or RH sliding doors. Requirement: To preclude the possibility of door loss in flight, modify per Aerospatiale SB 52.18. (DGAC AD 1987-088-049 refers) Compliance: By 31 May 1988 Effective Date: 18 March 1988 DCA/AS350/35 Main and Tail Rotor Servo Controls - Inspection Applicability: All Model AS350 with Dunlop main and tail rotor servo controls P/N AC64182, AC67030, AC67244, AC66442, AC67034, AC67246, AC66436, AC67032. Requirement: To preclude possible failure of servo control assembly bolts, inspect per Aerospatiale SB 01.21 and renew bolts as prescribed. (DGAC AD 1988-184-052 refers) Compliance: Within next 50 hours TIS or by 31 May 1989 whichever is the sooner. Effective Date: 10 March 1989 DCA/AS350/36B Main Rotor, Rotating Swash Plate - Inspection Applicability: All Model AS350B, B1, B2 and D with swash plates fitted with bearings P/Ns VH 36132 (704A33.651.051), Y 51BB 10843 SIM 73 (704A33.651.080), INA 36132 A (704A33.651.126). Requirement: To prevent seizing of the swash plate bearing, inspect and lubricate per Aerospatiale SB 62.12R2. Renew defective parts before further flight. (DGAC AD 1989-155-054R4 refers) Compliance: 1. Within next 10 hours TIS (T.I.S.), unless already accomplished, and thereafter relubricate per SB 62.12R2 para 1.C-i at intervals not exceeding 100 hours T.I.S. 2. Check per SB 62.12R2 para 1.C-g following last flight on each day aircraft is operated. Effective Date: DCA/AS350/36A - 2 March 1990 DCA/AS350/36B - 29 November 1991 DCA/AS350/37 Cancelled - CAR 91.603(b) refers Effective Date: 27 August 2009 DCA/AS350/38 Tail Rotor Pitch Control Lever Expansion Pin - Inspection Applicability: All Model AS350B, B1, B2 and D. Requirement: To prevent failure of the tail rotor pitch control lever hinge yoke lugs due to incorrect assembly, accomplish the following:- 1. Inspect the pitch control rod support yoke for cracks per para B of Aerospatiale Telex SB NR 01-33. If a crack is found replace the TGB per the SB before further flight. 2. Inspect for correct installation of the expansion pin per para C of Aerospatiale Telex SB NR 01-33. Rectify if necessary as prescribed by the SB, before further flight. (DGAC AD 1991-137-059 refers) Compliance: 1. Within next 10 hours TIS (TIS) and thereafter at intervals not to exceed 10 hours TIS until part 2 is accomplished. 2. Within next 50 hours TIS. Effective Date: 4 July 1991 Airbus Helicopters AS 350 Series Issued 26 February 2026 Page 14 of 59 CAA of NZ DCA/AS350/39 Emergency Location Transmitter (ELT) Antenna - Modification Applicability: Model AS350 Series fitted with the JOLLIET ELT system Requirement: To prevent loss of the ELT antenna in flight, modify per Eurocopter AS 350 SB 25.45. (DGAC AD 1992-144-061 refers) Compliance: Within next 400 hours TIS or by 1 April 1993 whichever is the sooner. Effective Date: 30 October 1992 DCA/AS350/40 Hydraulic Reservoir - Modification Applicability: All Model AS350B, BA, B1, B2 and D fitted with hydraulic reservoir P/N 350A75-1030- 00. Requirement: To decontaminate the hydraulic system and prevent water entering the hydraulic reservoir, modify and flush the system per paragraph 2B1 or 2B2 of Eurocopter SB 01.36. (DGAC AD 1992-145-062 refers) Compliance: For aircraft operating in temperatures of -10° C or less, within next 100 hours TIS or 3 months whichever is the sooner. For all other aircraft, within next 400 hours TIS. Effective Date: 30 October 1992 DCA/AS350/41A Pitch Change Lever Bushes - Inspection Applicability: All Model AS350B, BA, D, B1, B2 and L1 with pitch change lever P/N 350A 31.1877.02 not marked with an "X" and have a S/N less than 100,000. Requirement: To prevent failure of the pitch change rod/lever coupling bolt and loss of pitch control, inspect per Eurocopter SB 62.21 R1. Renew defective parts per SB 62.21 R1. (DGAC AD 1992-179-064R1 refers) Compliance: Within next 50 hours TIS. Effective Date: DCA/AS350/41 - 27 November 1992 DCA/AS350/41A - 11 June 1993 DCA/AS350/42 Engine Fire Detection System - Modification Applicability: Model AS350B1 and B2 Requirement: To ensure correct operation of the engine bay fire detection system, modify per Eurocopter SB 26-01. (DGAC AD 1992-159-063R2 refers) Compliance: By 31 May 1993 Effective Date: 19 March 1993 DCA/AS350/43 Main Rotor Mast Assembly - Inspection Applicability: Model AS350B, BA, B1, B2 and D fitted with main rotor mast assembly P/N 350A37.0004.02, 350A37.0004.03, 355A37.0005.01. Requirement: As a result of an accident overseas involving an AS350B2, inspect per Eurocopter Telex Service 01-41, paragraphs DD (A) or (B) as appropriate and EE. (DGAC AD 1993-030-065 refers) Compliance: 1. Whenever abnormal noises appear (metal rubbing) in flight or when the rotor is turning on the ground. Flights must be terminated as soon as practicable. 2. Within the next 5 hours TIS, for any main rotor mast shaft on which maintenance requiring the removal of the mast epicyclic reduction gear assembly has been performed during the last 100 hours TIS, unless the maintenance was performed by Eurocopter Marignane. Effective Date: 27 March 1993 Airbus Helicopters AS 350 Series Issued 26 February 2026 Page 15 of 59 CAA of NZ DCA/AS350/44A Sliding Windows - Inspection and Modification Applicability: All Model AS350B, BA, B1, B2, D and L1 fitted with sliding window panes P/N: 704A41-512-003, -004, -005, -006, -010, -011, -025 and 355A25-2030-00. Requirement: To prevent window separation in flight accomplish the following:- 1. Inspect per Eurocopter SB 05.25 R1. If cracks are found, or if a piece of the slide is unstuck and/or has been lost, replace the window per paragraph 1C3 of SB 05.25 R1 before further flight. 2. Modify (Repair) per paragraph 1C2 of SB 05.25 R1. (DGAC AD 1993-090-067R1 refers) Compliance: 1. Inspect within next 50 hours TIS and thereafter at intervals not to exceed 25 hours TIS, until modification per paragraph 1C2 of SB 05.25 R1. After modification, inspect at intervals not to exceed 100 hours TIS. 2. Modify within next 100 hours TIS. Effective Date: DCA/AS350/44 - 3 September 1993 DCA/AS350/44A - 18 March 1994 DCA/AS350/45 MGB Oil Pressure Switch - Removal Applicability: Model AS350B, BA, B1, B2, D and L1, fitted with MGB oil pressure switch P/N 704A37.721.082 (S 1130.021.082). Requirement: Replace MGB oil pressure switch P/N 704A37.721.082 (S 1130.021.082) per Eurocopter Telex Service 01.43. (DGAC AD 1994-087-068 refers) Compliance: By 1 August 1994 Effective Date: 8 July 1994 DCA/AS350/46 Cyclic Pitch Change Control Rod - Inspection Applicability Model AS 350B, BA, B1, B2 and D, fitted with cyclic pitch change control rod P/N 704A34-113-279. This airworthiness directive does not apply to aircraft fitted with an autopilot. Requirement: To ensure that cyclic pitch change control rods have been correctly safetied, inspect per Eurocopter SB 01-42. Replace any rods found not safetied per SB 01-42 before further flight. (DGAC AD 1994-180-069 refers) Compliance: Within next 100 hours TIS. Effective Date: 23 December 1994 DCA/AS350/47 Main Rotor Shaft Oil Jet - Inspection Applicability Model AS350B, BA, B1, B2, D and L1, fitted with a “TIMKEN” main rotor shaft P/N 350A37-0003 (all dash numbers), that has logged less than 100 operating hours since new or overhaul. Requirement: To ensure correct lubrication of the shaft bearing, accomplish the inspection per Eurocopter France AS 350 Telex Service No 01-44. Replace any assembly that does not comply with Telex Service No 01-44, before further flight. (DGAC AD 1994-279-070R1 refers) Compliance: Before further flight. Effective Date: 9 March 1995 Airbus Helicopters AS 350 Series Issued 26 February 2026 Page 16 of 59 CAA of NZ DCA/AS350/48 MGB Suspension Bi-directional Cross Beam - Inspection Applicability: Model AS 350B, BA, B1, B2 and D fitted with a MGB suspension bi-directional cross beam P/N 350A38.1018 - (all dash numbers), installed on the complete cross beam assemblies P/N 350A38.0210 - (all dash numbers), not modified per MOD. 072720. Requirement: To prevent failure of the suspension cross beam, accomplish the following:- 1. Cross beams that have logged at least 2000 hours TIS or 10,000 cycles: 1.1 Within next 30 hours TIS and thereafter at intervals not to exceed 30 hours TIS or 150 cycles, whichever is the sooner, visually inspect the cross beam for cracks, per paragraph 2B(1) of Eurocopter France SB 05.00.28 and rectify defects if necessary as detailed. 1.2 Each time the cross beam or the MGB is removed, irrespective of whether the removal was scheduled or not, comply with paragraph 2B(2) of SB 05.00.28. 2. For cross beams that have logged more than 5000 hours TIS and which have not been checked during or since the last major inspection per paragraph 2B(2) of SB 05.00.28 accomplish the following: 2.1 Within next 30 hours TIS and thereafter at intervals not to exceed 30 hours TIS or 150 cycles, whichever is the sooner, visually inspect both the upper faces of the cross beam for cracks, per paragraph 2B(1) of SB 05.00.28 and rectify any defects found as detailed. 2.2 Within 550 hours TIS or 2750 cycles whichever is the later, comply with paragraph 2B(2) of SB 05.00.28. Note: If there is no record of the number of the flying hours logged or of the number of cycles completed: If the component has been installed on the aircraft since new, refer to the number of the flying hours and cycles logged by the airframe. If the component has not been installed on the aircraft since new, comply with the instructions given in paragraph 2.1. 3. Before installing a cross beam as a replacement part that has already been installed on an aircraft, comply with the instructions given in paragraph 2B(2) of SB 05.00.28. (DGAC AD 1996-156-071R1 refers) Compliance: Compliance is required at the times specified within the requirement of this airworthiness directive. Effective Date: 29 August 1997 DCA/AS350/49 Tail Boom Attachment Screws - Replacement Applicability: Model AS 350B, BA, BB, B1, B2 and D fitted with tail boom attachment screws P/N 22201BC060008L (N5103337287). This AD does not apply to new or overhauled aircraft delivered after 15 May 1997 or to aircraft on which no tail boom attachment screws have been replaced since 1 July 1994. Requirement: To prevent failure of the tail boom attachment screws, accomplish the following:- Check the marking on the heads of the 23 attachment screws which are located above the cargo compartment floor. Remove and scrap all screws which are marked with the letter “M” on their head above the designation “BC” per paragraph 2.B.1 of Eurocopter Alert Service Bulletin No. 01.00.46. Any affected screws held as spares must be scrapped per paragraph 2.B.2 of Eurocopter Alert Service Bulletin 01.00.46. (DGAC AD 1997-147-072R1 refers) Compliance: Within next 100 hours TIS or by 29 September 1997, whichever is the sooner. Effective Date: 29 August 1997 Airbus Helicopters AS 350 Series Issued 26 February 2026 Page 17 of 59 CAA of NZ DCA/AS350/50 Cancelled – EASA AD 2015-0195 refers Effective Date: 7 October 2015 DCA/AS350/51 Single Pole Circuit Breakers – Inspection and Removal Applicability: AS 350 helicopters, versions: B, BA, BB, B1, B2, B3 and D equipped with single-pole CROUZET circuit breakers, P/Ns: -5 amperes : 84 4000 032 Emergency flotation gear optional installation -10 amperes : 84 4000 034 -1 ampere : 84 4000 028 Other optional installations -3 amperes : 84 4000 031 -7.5 amperes : 84 4000 033 -15 amperes : 84 4000 035 -20 amperes : 84 4000 036 (a) Delivered new between April 24, 1995, and August 31, 1996. (b) Delivered new before April 24, 1995 or after August 31, 1996 if: - Circuit breakers have been replaced on an optional equipment (emergency flotation gear or another optional equipment) since April 24, 1995. - An optional equipment (emergency flotation gear or another optional installation) was installed on the aircraft between April 24, 1995 and August 31, 1996. Requirement: To ensure that there is no loss of electrical continuity, accomplish the following:- 1. Inspect the circuit breakers and replace if necessary per Eurocopter SB 01.00.47. 2. Remove from service all circuit breakers listed in the applicability section of this AD. (DGAC AD 1998-511-074 refers) Compliance: 1. Inspect within next 200 hours TIS or by 12 June 1999, whichever is the sooner. For those circuit breakers held as spares, inspect before installation. 2. Replace by 1 January 2000. Effective Date: 12 March 1999 DCA/AS350/52B Tail Rotor Hub Pitch Change Plate Bearings - Inspection Applicability: AS 350 helicopters, versions: B, BA, BB, B1, B2, B3 and D fitted with tail rotor hub pitch change plate, P/Ns 350A33-2004-00, -01, -02, -03, -05 or 350A33-2009-00, -01 that do not incorporate MOD 076551 (new generation bearing P/N 6010F234M16 (704A33.651.190) introduced by AS 350 SB 65.00.38 R1) Requirement: To prevent seizure of the tail rotor hub pitch change plate bearings and loss of control of the helicopter, accomplish the following:- 1. Check the rotation torque of the bearing per paragraph 2.B 1) of Eurocopter AS350 ASB 05.00.29. 2. Inspect for axial play, friction point and brinelling per paragraph 2.B 2) of Eurocopter AS350 ASB 05.00.29. 3. Check any pitch change plate assemblies held as spares per paragraph 2.B 1) b) and 2.B 2) of Eurocopter AS350 ASB 05.00.29. If the measured rotational load is greater than 300 grams, remove the pitch change plate assembly from the aircraft or do not install if the assembly as held as a spare. If the measured rotational load is less than 300 grams, and if the axial play is greater than or equal to 0.4mm and/or friction points or brinelling are detected: Check the condition of the parts (excluding the pitch change plate bearing) and replace them per paragraph 2.B 3) b) of Eurocopter AS350 ASB 05.00.29. Airbus Helicopters AS 350 Series Issued 26 February 2026 Page 18 of 59 CAA of NZ Replace the pitch change plate bearing with a bearing in airworthy condition. (DGAC AD 1999-085-076R3 refers) Compliance: 1. Unless already accomplished, within the next 10 hours TIS or 14 days, whichever is the sooner. 2. Within next 10 hours TIS and thereafter at intervals not to exceed 50 hours TIS or 6 months whichever is the sooner. 3. Before installing a pitch change plate assembly or a tail rotor gear box assembly held as spare. Effective Date: DCA/AS350/52A - 10 June 1999 DCA/AS350/52B - 17 December 1999 DCA/AS350/53 NR Indicator Lighting - Modification Applicability: AS 350B3 that do not incorporate MOD 072810 or any other approved modification enabling full NR indicator lighting in normal and emergency mode. Requirement: To ensure lighting of the NR indicator by the emergency lighting power supply, modify per Eurocopter AS 350 SB 33.00.17. (DGAC AD 1999-512-077 refers) Compliance: By 24 May 2000 Effective Date: 24 February 2000 DCA/AS350/54A Tail Rotor Pitch Change Rotating Plates – Inspection and Modification Applicability: AS 350 aircraft, versions B, BA, BB, B1, B2, B3, and D fitted with tail rotor pitch change rotating plates all P/Ns, which have not had MOD 07 6554 embodied. Requirement: To prevent rotation of the bearing spacers and the inner bearing race of the tail rotor pitch change plate, which may cause excessive wear and cut the rotating plate and result in loss of pitch control of the tail rotor, accomplish the following: 1. Mark the position of the spacer and the tail rotor pitch change rotating plate, per paragraph 2.B.1. of Eurocopter AS 350 ASB 05.00.33 R1 or later revision. 2. Inspect the paint index marks on the tail rotor pitch change rotating plate and on the spacer for alignment, per paragraph 2.B.2. of ASB 05.00.33. If the paint index marks are not aligned, accomplish paragraph 2.B.4. per ASB 05.00.33 within the next 25 hours TIS. 3. Embody MOD 07 6554 per paragraph 2.B.3. of ASB 05.00.33. (DGAC F-2000-222-079R1 refers) Note 1: This AD does not apply to aircraft fitted with pitch change plate assembly P/N 350A33-2030-00 (MOD 076550). Note 2: Before installing any pitch change plate assembly or a tail gear box assembly held as spares, accomplish paragraph 2.B.3. per AS 350 ASB 05.00.33 (embodiment of MOD 07 6554). Note 3: The inspection detailed in requirement 2 may be accomplished by the pilot in accordance with CAR Part 43, Appendix A. The pilot must be trained and authorised (Part 43, Subpart B refers) and certification must be provided (Part 43, Subpart C refers). Compliance: 1. Within next 10 hours TIS, unless previously accomplished. 2. After the last flight of the day. 3. Within 400 hours TIS after 15 June 2000. Effective Date: DCA/AS350/54 - 15 June 2000 DCA/AS350/54A - 28 July 2005 Airbus Helicopters AS 350 Series Issued 26 February 2026 Page 19 of 59 CAA of NZ DCA/AS350/55 Engine Oil Tank Breather Pipe - Fireproofing Applicability: AS 350 helicopters, versions: B, B1, B2, BA, BB and D which have not had MOD 07 2793 embodied. Requirement: Fireproof the engine oil tank breather pipe, by fitting a heat-resistant silicone sheath per paragraph 2 of Eurocopter AS 350 SB 79.00.11 Rev 1. (DGAC AD 2000-268-078 refers) Compliance: By 31 December 2000 Effective Date: 27 July 2000 DCA/AS350/56 Ferry Fuel Tanks - Electrical Bonding Applicability: AS 350 B, BA, B1, B2, B3, BB and D helicopters equipped with metal ferry fuel tanks, P/N 330A 871310 .00, .01, .02, .03 and .04. Requirement: To prevent the generation of an electrostatic spark between the re-fueling nozzle and the ferry fuel tank caused by the absence of this electrical bonding and possible explosion of the fuel tank, accomplish the electrical bonding per Eurocopter Service Telex AS 350 No. 28.00.14, paragraph C.C. (DGAC AD 2000-302 refers) Compliance: For ferry fuel tanks which are already installed on a helicopter, before the next re- fueling. For ferry fuel tanks which are not installed on a helicopter before installation. Effective Date: 27 July 2000 DCA/AS350/57B Tail Rotor Drive Shaft Forward Fairing - Inspection Applicability: AS 350B3 helicopters equipped with forward fairing P/N 350A.23.0032.09 pre Mod 073097. AS 350B3 helicopters equipped with forward fairing P/N 350A23.1075.00 post Mod 073097. Requirement: To prevent separation of the tail rotor drive shaft forward fairing heat shield and possible loss of control of the helicopter, accomplish the following:- 1. P/N 350A23.0032.09 without the repair 350-53-42-00 or pre mod 073097 1.1 Before the first flight and at each check after the last flight of the day (ALF check): a) Visually check the fairing in the 6 areas of attachment to the heat shield per Eurocopter AS 350 ASB 05.00.35. b) In case of detection of a crack or in case of doubt about the presence of crack, apply the instructions of paragraphs 1.2 a) and 1.2 b) below. 1.2 Within 50 hours TIS and thereafter at intervals not exceeding 50 hours TIS: a) After removal of the fairing, visually check the internal face of the fairing in the 9 areas of attachment to the heat shield per paragraph 2.B.1 of the ASB. b) In case of detection of a crack and before the next flight, discard the fairing or repair it, if the repair criteria in paragraph 2.B.1 of the ASB are not exceeded, per repair sheet 350 53 42 00 (crack stop and 3 stiffeners setting). 2. P/N 350A23.0032.09 with repair 350-53-42-00 2.1 At each check after the last flight of the day (ALF check): a) Visually check the fairing in the 6 areas of attachment to the heat shield per paragraph 2.B.2 of Eurocopter AS350 ASB 05.00.35. b) In case of propagation of an existing crack out of the crack stop or in case of a new crack or in case of doubt, before the next flight and after removal the Airbus Helicopters AS 350 Series Issued 26 February 2026 Page 20 of 59 CAA of NZ fairing, visually check the stiffeners and the external face of the fairing under the heat protection per paragraph 2.B.1 of the Telex Service. c) In case of presence of a crack in one or more stiffeners or in case of propagation of an existing crack out of the crack stop or in case of detection of a new crack on the fairing, discard the fairing. 2.2 Every 100 hours TIS and after removal of the fairing: a) Visually check the stiffeners and the external face of the fairing under the heat protection per paragraph 2.B.1 of the ASB. b) In case of presence of a crack in one or more stiffeners or in case of propagation of an existing crack out of the crack stop or in case of detection of a new crack on the fairing discard the fairing. 3. Fairing P/N 350A23.1075.00 with the Modification 073097 3.1 At each check after the last flight of the day (ALF check): a) Visually check the fairing in the 6 areas of attachment to the heat shield per paragraph 2.B.2 of Eurocopter AS350 ASB 05.00.35. b) In case of doubt of existing cracks, before the next flight and after removal the fairing, visually check the stiffeners and the external face of the fairing under the heat protection per paragraph 2.B.1 of the ASB. c) In case of presence of a crack, discard the fairing. 3.2 Every 100 hours TIS and after removal of the fairing: a) Visually check the stiffeners and the external face of the fairing under the heat protection per paragraph 2.B.1 of the ASB. b) In case of presence of a crack, discard the fairing. 4. Replacement Fairing P/N 350A23.0032.09 4.1 Embody Mod 073097 before installing a tail rotor drive shaft forward fairing P/N 350A23.0032.09. (DGAC AD 2000-340-080R2 refers). Compliance: Compliance is required at the times specified within the requirement of this airworthiness directive. Note: The daily inspections may be accomplished by the pilot in accordance with CAR Part 43, Appendix A. The pilot must be trained and authorised (Part 43, Subpart B refers) and certification must be provided (Part 43, Subpart C refers). Effective Date: DCA/AS350/57A - 26 October 2000 DCA/AS350/57B - 28 February 2002 Airbus Helicopters AS 350 Series Issued 26 February 2026 Page 21 of 59 CAA of NZ DCA/AS350/58 Tail Rotor Hub Pitch Change Plate Bearings - Replacement Applicability: AS 350, versions B, BA, BB, B1, B2, B3 and D fitted with tail rotor pitch change plate SNR bearing, P/N 6010F234M16 (704A33-651-190). Requirement: To prevent failure of the tail rotor hub pitch-change bearings and subsequent loss of control of the helicopter, replace tail rotor pitch change plate bearings, P/N 6010F234M16 (704A33-651-190) at the compliance times specified below. (DGAC AD 2001-074-081 refers) Compliance: (a) AS 350 B3 version: For bearings with less than 270 hours TTIS, replace no later than 300 hours TTIS. For bearings with between 270 and 600 hours TTIS, replace within the next 30 hours TIS. For bearings with between 600 and 900 hours TTIS, replace within the next 20 hours TIS. For bearings with 900 hours or higher TTIS, replace within the next 10 hours TIS. Thereafter, bearing life is not to exceed 300 hours TTIS. (b) AS 350 B, BA, BB, B1, B2 and D versions: For bearings with less than 1150 hours TTIS, replace no later than 1200 TTIS. For bearings with between 1150 and 1550 hours TTIS, replace within the next 50 hours TIS. For bearings with 1550 hours or higher TTIS, replace within the next 10 hours TIS. Thereafter, bearing life is not to exceed 1200 hours TTIS. (c) Transfer of bearings between AS 350 versions: If bearings are to be transferred from one AS 350 version to another, apply the transfer rules per Master Servicing Manual, Chapter 05.99, Page P8. Effective Date: 15 March 2001 DCA/AS350/59 Cancelled – DCA/AS350/108 refers Effective Date: 27 March 2008 DCA/AS350/60 Engine Indication System – Resistor Installation Applicability: AS 350B3 helicopters delivered new before 1 May 1999 or containing ASU No 2 circuit boards, P/N SE 03022 (704A47720110), that were manufactured before 1 May 1999. Requirement: To ensure the correct functioning of the BATT.TEMP, ENGINE CHIP and the rotor rpm signal output to the VEMD, accomplish the following:- Determine if the resistor R8 is installed on the ASU No 2-circuit board, per paragraph 2.B of Eurocopter SB 77.00.07. If the resistor is not fitted, replace the circuit board with a serviceable item. (DGAC 2001-319-083 refers) Compliance: Within 50 hours TIS Inspect all uninstalled boards prior to installation. Effective Date: 30 August 2001 DCA/AS350/61A Cancelled – DGAC AD 2001-557-086R3 refers Effective Date: 27 June 2019 DCA/AS350/62 Cancelled – DCA/AS350/74 refers Effective Date: 30 October 2003 Airbus Helicopters AS 350 Series Issued 26 February 2026 Page 22 of 59 CAA of NZ DCA/AS350/63B Tail Servo Control Eye End Fitting – Inspection and Rework Applicability: Model AS350 B, BA, B1, B2, B3, BB and D aircraft fitted with all types and all P/N tail servo controls except those aircraft embodied with modification 073139 or those aircraft embodied with Eurocopter AS350 SB No. 67.00.22. Note: DCA/AS350/63B revised to clarify the AD requirement when no play is detected and the lockwasher is found correctly installed in the tail servo control coupling with no change to the AD requirement. The repetitive inspection interval revised to 500 hours TIS. A repetitive inspection per DCA/AS350/63B may be deferred for a period of not more than 10% of the AD inspection interval to allow the inspection to be carried out during other scheduled maintenance (CAA Rule Part 39.55 refers). Requirement: To prevent the progressive reduction of the servo yaw control range which could cause loss of servo control power assistance, inspect the eye end fitting to servo control coupling locking, per the instructions in paragraph 2.A. of Eurocopter AS350 Alert Service Bulletin (ASB) No. 05.00.37 revision 1 or later approved revisions. If no play is found and the lockwasher is correctly installed, then the aircraft may be returned to service. If any play is detected and/or the lockwasher is not correctly installed, accomplish the corrective actions per paragraph 2.B. of ASB No. 05.00.37 before further flight. (DGAC AD F-2001-580-085R2 refers) Compliance: At 500 hours TTIS or within the next 50 hours TIS whichever occurs later, unless previously accomplished within the last 500 hours TIS, and thereafter at intervals not to exceed 500 hours TIS. Effective Date: DCA/AS350/63A - 28 June 2007 DCA/AS350/63B - 30 August 2012 DCA/AS350/64 Engine Control Switch – Inspection Applicability: AS 350 B3 delivered before 15 October 2001 and equipped with engine control switching unit P/N 200192. Requirement: To prevent ingress of water, which may freeze, and jam the engine control switching unit preventing manual engine governing, inspect the unit for watertightness per Eurocopter AS 350 ASB 76.00.16. If water is discovered comply with paragraphs 2.B.2a and S.B.3 of the ASB. If no water is discovered apply sealing procedure as described in paragraph 2.B.3 of the ASB. (DGAC 2001-548-084 refers) Compliance: Within the next 100 hours TIS or before next flight into freezing conditions whichever occurs first. Effective Date: 20 December 2001 DCA/AS350/65 Hydraulic Cut-Off Control - Modification Applicability: Model AS 350B helicopters with S/N less than 1525. Requirement: To prevent accidental or uncommanded cut-off of the hydraulic system, modify the electrical connection to hydraulic cut-off push button on the pilot’s collective lever, per Aerosp