identifier: AMC to Part-66 — Amendment 14

beslut: ED Decision 2015/020/R

title: AMC to Part-66 — Amendment 14

text: Annex to ED Decision 2015/020/R

text: The text of the amendment is arranged to show deleted, new or amended text as shown below: — deleted text is marked with strike through; — new or amended text is highlighted in grey; and — an ellipsis (…) indicates that the remaining text is unchanged in front of or following the reflected amendment.

text: Appendix I to Annex IV to ED Decision 2003/019/RM is hereby amended as follows:

text: APPENDIX I AIRCRAFT TYPE RATINGS FOR PART-66 AIRCRAFT MAINTENANCE LICENCES

text: The following aircraft type ratings should be used to ensure a common standard throughout the Member States. The inclusion of an aircraft type in the licence does not indicate that the aircraft type has been granted a type certificate under the Basic Regulation and its Implementing Rules,; this list is only intended for the maintenance purposes. In order to keep this list current and the type ratings consistent, such information should be first passed on to the Agency using the Rulemaking Enquiry form (http://easa.europa.eu/webgate/rulemaking-enquiry/) in case a Member State needs to issue a type rating that is not included in this list. Notes on when the licences should be modified: When a modification is introduced by this Decision to an aircraft type rating or to an engine designation in the rating which affect licences already issued, the ratings on the Aircraft Maintenance Licences (AMLs) may be modified at the next renewal or when the licence is reissued, unless there is an urgent reason to modify the licence. Notes on aircraft modified by Supplemental Type Certificate (STC):  It is not the intention of this document to include all aircraft modified by STCs because a great number of STCs were approved before 2003 and are unknown to the Agency.  This Appendix I intends to include the type ratings of aircraft resulting from STCs for installation of another engine. These STCs are those approved by the Agency and those approved by the Member States before 2003 and grandfathered by the Agency. Other STCs than those for engines are not considered. o Example: The STC from Jet Aviation Basel approved by the LBA for replacement of GE CF 700 by Honeywell TFE731 on Fan Jet Falcon Series E results in a new rating called Fan Jet Falcon E (Honeywell TFE731).  However, the ratings from STCs for installation of an engine: o on part of the original airframe models, or o from the same manufacturer, but of a type very similar to the original one,

text: Annex to ED Decision 2015/020/R

text: have not been added because they would have resulted in an already existing rating. Examples: o The STC from SILVERHAWK CONVERSIONS approved by EASA for installation of PT6A-135A on Beech C90, C90A and E90 would result in the Beech C90/C90A/E90 (PWC PT6) rating, but this is not listed because it is already included in the original Beech 90 Series (PWC PT6) rating. o The STC from Air-Service Wildgruber GmbH approved by LBA for replacement of PWC PT6A-20 by PWC PT6A-27 would result in the De Havilland DHC-6-100 (PWC PT6) rating, but this is not listed because it is already included in the De Havilland DHC-6 (PWC PT6) rating in the table.  At the time of publication of this Decision, the Agency has not received all the information concerning STCs that have been previously approved by the Member States. As a result, not all STCs are considered by this publication.  When the STC concerns the installation of an engine that falls under a different subcategory, e.g. replacement of a piston engine by a turbo-prop (a turbine engine), then the new type rating needs to be listed in the new subcategory.  In case a type rating resulting from an STC has not been yet defined by the Agency, the latter shall be contacted by the competent authority to agree on a new type rating to be used.  When an aircraft has been modified by an STC for installation of another engine, the Part-66 type rating of this aircraft may change i.e. from Group 2 to Group 1. This is not reflected in this document. In case the applicant to a licence faces such a case, he/she or his/her competent authority can inform the Agency and a new type rating will be defined by the Agency.

text: In the following tables:  The column ‘TC Holder’ includes the TC holder as defined in the Type Certificate Data Sheets (TCDS) (EASA, FAA or other) or the Specific Airworthiness Specifications (SAS).  The column ‘STC Holder’ includes the STC holder as defined in the Supplemental Type Certificate Data Sheets (STCDS) (EASA, FAA or other).  Some TC holders’ designations have been corrected to add the information : ’Aircraft with an SAS’, this means that the aircraft listed under this TC holder designation is considered an ‘orphan aircraft’.  In Group 3, a third column has been added which is called ‘Type of structure’ and which intends to assist the competent authorities in identifying the experience required for this type with a view on removing existing limitations on the licence.  Wooden structure covered with fabric is considered to fall under wooden structure. For Aaeroplanes with a combination of structures,; e.g. metal tubing fuselage and wooden wings, both experiences ‘metal tube covered with fabric’ and ‘wooden structure’ are required.  In Group 3, a fourth column has been added which is called ‘MTOM’ and which intends to assist the competent authorities in identifying the aeroplanes types where the Maximum Take-Off Mass (MTOM) is: — above 2T and is subject to a B1.2 licence, or — 2T and below and is subject to a B1.2 or B3 licence.

text: Annex to ED Decision 2015/020/R

text: GROUP 1 AEROPLANES Commercial TC holder Model Part-66 Type rating endorsement designation

text: 328 Support 328-100 series Dornier 328-100 (PWC PW119) Services 328-300 series Dornier 328-300 (PWC PW306)

text: AIR TRACTOR AT-802 Series Air Tractor AT-800 Series (PWC PT6) AIRBUS SN 601 Corvette Aerospatiale SN-601 (PWC JT15D) (Aircraft with SAS) AIRBUS A300 B1 Airbus A300 basic model (GE CF6) A300 B2-1A A300 B2-1C A300 B2-202 A300 B2-203 A300 B2K-3C A300 B4-102 A300 B4-103 A300 B4-203 A300 B4-2C A300 C4-203 A300 F4-203 A300 B2-320 Airbus A300 basic model (PW JT9D) A300 B4-120 A300 B4-220 A300 B4-601 Airbus A300-600 (GE CF6) A300 B4-603 A300 B4-605 R A300 C4-605 R Variant F A300 F4-605 R A300 B4-622 Airbus A300-600 (PW 4000) A300 B4-622 R A300 F4-622 R A300 B4-620 Airbus A300-600 (PW JT9D) A300 C4-620 A300F4-608ST Beluga Airbus A300-600ST (GE CF6) A310-203 Airbus A310 (GE CF6) A310-203 C A310-221 A310-304 A310-308 A310-324 Airbus A310 (PW 4000) A310-325 A310-204 Airbus A310 (PW JT9D) A310-222 A310-322

text: Annex to ED Decision 2015/020/R

text: A318-120 series Airbus A318 (PW 6000) A318-110 series Airbus A318/A319/A320/A321 (CFM56) A319-110 series A320-111 A320-210 series A321-110 series A321-210 series A319-130 series Airbus A319/A320/A321 (IAE V2500) A320-230 series A321-130 series A321-230 series A319-170 A319 NEO Airbus A319/A320/A321 (IAE PW1100G) A320-270 A320 NEO A321-270 A321 NEO A319-150 A319 NEO Airbus A319/A320/A321 (CFM LEAP-1A) A320-250 A320 NEO A321-250 A321 NEO A330-200 series Airbus A330 (GE CF6) A330-300 series A330-220 series Airbus A330 (RPW 4000) A330-320 series A330-240 series Airbus A330 (RR RB 211 Trent 700) A330-340 series A340-210 series Airbus A340 (CFM56) A340-310 series A340-540 series Airbus A340 (RR RB 211 Trent 500) A340-640 series A350-900 series Airbus A350 (RR Trent XWB) A380-860 series Airbus A380 (EA GP7200) A380-840 series Airbus A380 (RR RB 211 Trent 900) Airbus Military Sociedad Limitada A400M-180 Airbus A400M (EPI TP400) (AMSL) AIRCRAFT L-410 M/UVP Turbolet Let L-410 (Walter M601) INDUSTRIES

text: Annex to ED Decision 2015/020/R

text: L-410 UVP-E Turbolet L-410 UVP-E20 Turbolet

text: Turbolet L-410 UVP-E20 CARGO L-410 UVP-E9 Turbolet L-410 UVP-E-LW Turbolet L-410 UVP-LW Turbolet Turbolet Let L-410 (GE H80) L-410 UVP-E20 Turbolet L-410 UVP-E20 CARGO L-420 Let L-420 (Walter M601) ALENIA C-27J Alenia C-27 (Allison/RR AE2100) AERMACCHI ANTONOV AN-26 Antonov AN26 (Ivchenko AI-24) AN-26B Antonov Antonov An-28 Antonov An-28 (ТВД) Aeronautical Scientific and Technical Complex (Aircraft with SAS) ATR-GIE Avions de ATR 42-200 ATR 42-200/300 series (PWC PW120) Transport Régional ATR 42-300 ATR 42-320 ATR 42-400 ATR 42-400/500/72-212A (PWC PW120) ATR 42-500 42-500 ATR 42-500 42-600 ATR 72-212 A 72-500 ATR 72-212 A 72-600 ATR 72-101 ATR 72-100/200 series (PWC PW120) ATR 72-102 ATR 72-201 ATR 72-202 ATR 72-211 ATR 72-212 BAE SYSTEMS BAe ATP ATP (PWC PW120) (OPERATIONS) Ltd

text: Annex to ED Decision 2015/020/R

text: AVRO 146-RJ100 BAe 146/AVRO 146-RJ (Honeywell ALF500 Series) AVRO 146-RJ115 AVRO 146-RJ70 AVRO 146-RJ85 BAe 146 Series 100 BAe 146 Series 200 BAe 146 Series 300 HP.137 Jetstream 1 HP.137 (Turbomeca Astazou) Jetstream Mk.1 HP.137 Jetstream 2 Jetstream Mk.1 HS 748 Series 2A HS748 (RRD Dart) HS 748 Series 2B HS.748 Series 1 HS.748 Series 2 Jetstream 200 Jetstream 200 (Turbomeca Astazou) Jetstream 3100 Jetstream 31 Jetstream 31/32 (Honeywell TPE331) Jetstream 3200 Jetstream 32/32EP Jetstream 4100 Jetstream 41 (Honeywell TPE331) HAWKER 65-90 King Air Beech 90 Series (PWC PT6) BEECHCRAFT Corporation 65-A90 65-A90-1 65-A90-2 65-A90-4 B90 C90 C90A C90GT C90GTi E90 F90 H90 200/A200 Beech 200 Series (PWC PT6)

text: Annex to ED Decision 2015/020/R

text: 200C/A200C 200CT/A200CT 200T B200 B200C B200CGT B200CT B200GT B200T 390 Premier 1, 1A Beech 390 (Williams FJ44) 99 Beech 99/100 Series (PWC PT6) 100 King Air 99A A100 King Air A100A/C King Air A99 Airliner A99A Airliner B99 Airliner C99 Airliner B100 Beech B100 (Honeywell TPE331) 1900 Airliner Beech 1900 (PWC PT6) 1900C Airliner 1900D Airliner 300 Super King Air Beech 300 Series (PWC PT6) 300LW Super King Air B300 Super King Air 350 B300C Super King Air 350 C BERIEV Aircraft Be-200ES-E Beriev 200 (Ivchenko D-436TP) Company B-N GROUP Ltd. BN2T/-2/-2R/- Turbine Islander Britten-Norman BN2T Series (RR Corp 250) (Britten-Norman) 4R/-4S BOEING COMPANY B707-200 Boeing 707 (PW JT4) (THE) B707-200B B707-300 Series

text: Annex to ED Decision 2015/020/R

text: B707-400 Series Boeing 707 (RR Conway) B707-100 Long Body Boeing 707/720 (PW JT3D) B707-100B Long Body B707-100B Short Body B707-300B Series B707-300C Series B720 B720B B727 Series Boeing 727 (PW JT8D) B727-100 Series B727-100C Series B727-200 Series B727C Series B737-100 Boeing 737-100/200 (PW JT8D) B737-200 B737-200C B737-300 Boeing 737-300/400/500 (CFM56) B737-400 B737-500 B737-600 Boeing 737-600/700/800/900 (CFM56) B737-700 B737-800 B737-900 B737-900ER B747-100 Boeing 747-100 (PW JT9D) B747-200B Boeing 747-200/300 (GE CF6) B747-200C B747-200F B747-300 B747-200B Boeing 747-200/300 (PW JT9D) B747-200C B747-200F B747-300 B747-200B Boeing 747-200/300 (RR RB211) B747-200C

text: Annex to ED Decision 2015/020/R

text: B747-200F B747-300 B747-400 Boeing 747-400 (GE CF6) B747- 400F/SF(BCF) B747-400 Boeing 747-400 (PW 4000) B747- 400F/SF(BCF) B747-400 Boeing 747-400 (RR RB211) B747- 400F/SF(BCF) B747-8F Freighter Boeing 747-8 (GE GEnx) B747-8I Intercontinental B747SP Boeing 747SP (PW JT9D) B747SP Boeing 747SP (RR RB211) B757-200 Boeing 757-200/300 (PW 2000) B757-200PF B757-300 B757-200 Boeing 757-200/300 (RR RB211) B757-200PF B757-300 B767-200 Boeing 767-200/300 (PW 4000) B767-300 B767-300BCF B767-200 Boeing 767-200/300 (PW JT9D) B767-300 B767-300BCF B767-200 Boeing 767-200/300/400 (GE CF6) B767-300 B767-300F B767-300BCF B767-400ER B767-300 Boeing 767-300 (RR RB211) B777-200 Boeing 777-200/300 (GE 90) B777-200LR B777-300ER B777F Freighter

text: Annex to ED Decision 2015/020/R

text: B777-200 Boeing 777-200/300 (PW 4000) B777-300 B777-200 Boeing 777-200/300 (RR RB211 Trent 800) B777-300 Dreamliner Boeing 787-8/-9 (GE GEnx) B787-8 B787-9 Dreamliner Boeing 787-8/-9 (RR RB 211 Trent 1000) B787-8 B787-9 BOMBARDIER BD-100-1A10 Challenger 300 Bombardier BD-100-1A10 (Honeywell AS907) Challenger 350 BD-500-1A10 CSeries CS100 Bombardier BD-500 Series (PW PW1500G)

text: BD-500-1A11 CSeries CS300 Bombardier BD-500 Series (PW PW1500G)

text: BD-700-1A10 Global Express Bombardier BD-700 Series (RRD BR710) Global 6000 BD-700-1A11 Global 5000 Global 5000 GVFD CL600-1A11 Challenger 600 Bombardier CL-600-1A11 (Honeywell ALF502)

text: CL-600-2A12 Challenger 601 Bombardier CL-600-2A12/-2B16 (variant CL (601 Variant) 601/601-3A/3R) (GE CF34) CL-600-2B16 Challenger 601- (601-3A Variant) 3A CL-600-2B16 Challenger 601- (601-3R Variant) 3R CL-600-2B16 (CL Challenger-604 Bombardier CL-600-2B16 (variant CL 604) (GE 604 Variant) (MSN < 5701) CF34) CL-600-2B16 (CL Challenger-605 604 Variant) (MSN > 5701) CL-600-2B19 Regional Jet Bombardier CL-600-2B19 (GE CF34) Series 100

text: CL-600-2C10 Regional Jet Bombardier CL-600-2C10/-2D15/-2D24/-2E25 Series (GE CF34) 700/701/702 CL-600-2D15 Regional Jet Series 705 CL-600-2D24 Regional Jet Series 900 CL-600-2E25 Regional Jet Series 1000 DHC-8-102 DHC-8 Series 100 Bombardier DHC-8-100/200/300 (PWC PW 120) DHC-8-103 DHC-8 Series 100

text: Annex to ED Decision 2015/020/R

text: DHC-8-106 DHC-8 Series 100 DHC-8-201 DHC-8 Series 200 DHC-8-202 DHC-8 Series 200 DHC-8-301 DHC-8 Series 300 DHC-8-311 DHC-8 Series 300 DHC-8-314 DHC-8 Series 300 DHC-8-315 DHC-8 Series 300 DHC-8-401 DHC-8 Series 400 Bombardier DHC-8-400 (PWC PW150) DHC-8-402 DHC-8 Series 400 CL-215-1A10 Canadair CL-215 (PW R2800) CL-215-6B11 (CL- Canadair CL-215 (PWC PW120) 215T Variant) CL-215-6B11 (CL- Canadair CL-415 (PWC PW123) 415 Variant) CESSNA AIRCRAFT 401/402 Cessna 400 Series (Continental) Company 404 411 414 421 425 Corsair/ Cessna 425 (PWC PT6) Conquest I 441 Cessna 441 (Honeywell TPE331) 500 Citation/ Citation Cessna 500/ 501 (PWC JT15D) I 501 Citation I 510 Cessna 510 (PWC PW615) 525 Citation Jet CJ1 Cessna 525/525A (Williams FJ 44) Citation M2 525A Citation Jet CJ2 525B Citation Jet CJ3 Cessna 525B (Williams FJ 44) 525C Citation Jet CJ4 Cessna 525C (Williams FJ 44) 550 Citation II Cessna 550/551/560 (PWC JT15D) 560 Citation V 560 Citation Ultra S550 Citation S/II 551 Citation II 550 Citation Bravo Cessna 550/560 (PWC PW530/535) 560 Citation Encore 560 Citation Encore + 560 XLS Citation XLS Cessna 560XL/XLS (PWC PW545) 560 XLS+ Citation XLS+ 560 XL Citation Excel

text: Annex to ED Decision 2015/020/R

text: 650 Citation III, VI Cessna 650 (Honeywell TFE731) 650 Citation VII 680 Sovereign Cessna 680 (PWC PW306) Sovereign+ 750 Citation X Cessna 750 (RR Corp AE3007C)

text: DASSAULT Falcon 10 Falcon 10 (Honeywell TFE731) AVIATION Fan Jet Falcon (Basic) Fan Jet Falcon 20 (GE CF700) Falcon Fan Jet Falcon Series C Fan Jet Falcon Series D Fan Jet Falcon Series E Fan Jet Falcon Series F Fan Jet Falcon Falcon 200 (Honeywell ATF 3-6) Series G Mystère Falcon 200 Mystère Falcon 20GF Falcon 2000 Falcon 2000 (CFE 738)

text: Falcon 2000EX Falcon 2000EX (PWC PW308)

text: Falcon 2000EX F2000EX EASy Falcon 2000EX EASy (PWC PW308)

text: F2000DX F2000LX F2000LXS F2000S Mystère Falcon Falcon 20-5 (Honeywell TFE731) 20-C5 Mystère Falcon 20-D5 Mystère Falcon 20-E5 Mystère Falcon 20-F5 Mystère Falcon Falcon 50 (Honeywell TFE731) 50 Mystère Falcon F50EX Falcon 50EX (Honeywell TFE731) 50 Falcon 7X Falcon 7X (PWC PW307A)

text: Mystère Falcon Falcon 900 (Honeywell TFE731) 900

text: Annex to ED Decision 2015/020/R

text: Mystère Falcon F900B 900 Mystère Falcon F900C Falcon 900C (Honeywell TFE731) 900 Falcon 900EX Falcon 900EX (Honeywell TFE731) Falcon 900EX F900EX EASy Falcon 900EX EASy (Honeywell TFE731) Falcon 900EX F900DX Falcon 900EX F900LX DORNIER Seastar Seastar CD2 Dornier Seastar CD2 (PWC PT6) EADS CASA C-212-CB Aviocar CASA C-212 (Honeywell TPE331) C-212-CC Aviocar C-212-CD Aviocar C-212-CE Aviocar C-212-CF Aviocar C-212-DD Aviocar C-212-DF Aviocar C-212-EE Aviocar C-212-VA Aviocar C-212-DE Aviocar CASA C-212 (PWC PT6) C-295 CASA C-295 (PWC PW127) CN-235 CASA CN-235 (GE CT7) CN-235-100 CN-235-200 CN-235-300 ECLIPSE AEROSPACE EA500 Eclipse EA500 (PWC PW610) Inc. EMBRAER EMB-110P1 Bandeirante Embraer EMB-110 (PWC PT6) EMB-110P2 Bandeirante EMB-121A Xingu I Embraer EMB-121 (PWC PT6) EMB-121A1 Xingu II EMB-120 Brasilia Embraer EMB-120 (PWC PW110 Series) EMB-120ER Brasilia EMB-120RT Brasilia EMB-135BJ Legacy 600 Embraer EMB-135/145 (RR Corp AE3007A) Legacy 650 EMB-135ER EMB-135LR EMB-145 EMB-145EP EMB-145ER EMB-145EU EMB-145LR EMB-145LU EMB-145MK

text: Annex to ED Decision 2015/020/R

text: EMB-145MP EMB-500 Phenom 100 Embraer EMB-500 (PWC PW617) EMB-505 Phenom 300 Embraer EMB-505 (PWC PW535) EMB-545 Legacy 450 Embraer EMB-545/550 (Honeywell AS907) EMB-550 Legacy 500 ERJ 170-100 LR ERJ-170 Embraer ERJ-170 Series (GE CF34) ERJ 170-100 STD ERJ-170 ERJ 170-200 LR ERJ-175 ERJ 170-200 STD ERJ-175 ERJ 190-100 ECJ Lineage 1000 Embraer ERJ-190 Series (GE CF34) ERJ 190-100 IGW ERJ-190 AR ERJ 190-100 LR ERJ-190 ERJ 190-100 SR ERJ-190 ERJ 190-100 STD ERJ-190 ERJ 190-200 IGW ERJ-195 AR ERJ 190-200 LR ERJ-195 ERJ 190-200 STD ERJ-195 F-27A to -M Fokker F27/Fairchild F-27/FH-227 Series (RRD Dart) MARYLAND AIR FH-227 INDUSTRIES (FOKKER- FH-227B FAIRCHILD) FH-227C FH-227D FH-227E FOKKER SERVICES F27 Mark 100 Friendship F27 Mark 200 Friendship F27 Mark 300 Friendship F27 Mark 400 Friendship F27 Mark 500 Friendship F27 Mark 600 Friendship F27 Mark 700 Friendship FOKKER SERVICES F27 Mark 050 Fokker 50 Fokker 50/60 Series (PWC PW 125/127) F27 Mark 0502 Fokker 50 F27 Mark 0604 Fokker 60 F28 Mark 0070 Fokker 70 Fokker 70/100 (RRD Tay)

text: Annex to ED Decision 2015/020/R

text: F28 Mark 0100 Fokker 100 F28 Mark 1000 Fellowship Fokker F28 Series (RRD Spey)

text: F28 Mark 1000C Fellowship

text: F28 Mark 2000 Fellowship F28 Mark 3000 Fellowship F28 Mark 3000C Fellowship F28 Mark 3000R Fellowship F28 Mark Fellowship 3000RC F28 Mark 4000 Fellowship GOMOLZIG Dornier Do 28 (Walter M601)

text: GOVERNMENT N22/N22A to Nomad N22/24 Series (RR Corp 250) AIRCRAFT N22S FACTORIES (ASTA) N24/N24A GROB Luft- und Grob G 520 Series (Honeywell TPE331) Raumfahrt Aircraft AG GULFSTREAM G-1159 Gulfstream II Gulfstream G-1159 Series (RRD Spey) AEROSPACE Corporation G-1159A Gulfstream IIB G-1159B Gulfstream III G-159 Gulfstream I Gulfstream G-159 (RRD Dart) GIV (G300) Gulfstream G300 Gulfstream G-IV Series (RRD Tay) GIV (G400) Gulfstream G400 G-IV/GIV-SP Gulfstream G- IV/GIV-SP GIV-X (G350) Gulfstream G350 Gulfstream GIV-X Series (RRD Tay) GIV-X (G450) Gulfstream G450 GV Gulfstream GV Gulfstream GV basic model (RRD BR710)

text: GV-SP (G500) Gulfstream G500 Gulfstream GV-SP Series (RRD BR710)

text: GV-SP (G550) Gulfstream G550

text: GVI G650 Gulfstream GVI (RRD BR725)

text: GULFSTREAM 1125 Westwind Gulfstream (IAI) 100/1125/Astra SPX (Honeywell AEROSPACE LP Astra TFE731) (GALP) c/o Israel Aircraft Industries Astra SPX

text: G100 Gulfstream 100

text: Gulfstream Galaxy 200 Gulfstream (IAI) 200/Galaxy (PWC PW306) 200/IAI Galaxy

text: Annex to ED Decision 2015/020/R

text: Gulfstream G150 Gulfstream G150 Gulfstream (IAI) G150 (Honeywell TFE731)

text: Gulfstream G280 Gulfstream G280 Gulfstream (IAI) G280 (Honeywell AS907)

text: HAWKER 400 Beechjet Beech 400/Mitsubishi MU-300 (PWC JT15) BEECHCRAFT Corporation 400A Beechjet (Hawker 400XP) 400T Beechjet MU-300 Diamond I/IA MU-300-10 Diamond II BH.125 series ‘Beechcraft BAe 125 Series (RR Viper) 400 Hawker’ BH.125 series ‘Beechcraft 600 Hawker’ DH.125 series 1 ‘Hawker Siddeley’ DH.125 series 3 ‘Hawker Siddeley’ DH.125 series ‘Hawker 400 Siddeley’ HS.125 series 1 ‘Hawker Siddeley’ HS.125 series 3 ‘Hawker Siddeley’ HS.125 series ‘Hawker 400 Siddeley’ HS.125 series ‘Hawker 600 Siddeley’ HS.125 series F3 ‘Hawker Siddeley’ HS.125 series ‘Hawker F400 Siddeley’ HS.125 series ‘Hawker F600 Siddeley’ BAe.125 series BAe 125 Series 700/800 (Honeywell TFE731) 800 BH.125 series ‘Beechcraft 400 Hawker’ BH.125 series ‘Beechcraft 600 Hawker’ DH.125 series 1 ‘Hawker Siddeley’ DH.125 series 3 ‘Hawker Siddeley’

text: Annex to ED Decision 2015/020/R

text: DH.125 series ‘Hawker 400 Siddeley’ Hawker 800 HS.125 series 3 ‘Hawker Siddeley’ HS.125 series ‘Hawker 600 Siddeley’ HS.125 series ‘Hawker 700 Siddeley’ HS.125 series F3 ‘Hawker Siddeley’ HS.125 series ‘Hawker F400 Siddeley’ HS.125 series ‘Hawker F600 Siddeley’ BAe.125 series BAe 125 Series 1000 (PWC PW305) 1000A/B Hawker 1000 Hawker 750 Hawker 750 BAe 125 Series 750/800XP/850XP/900XP (Honeywell TFE731) Hawker 800XP Hawker 800XP

text: Hawker 850XP Hawker 850XP

text: Hawker 900XP Hawker 900XP

text: 4000 Hawker 4000 Hawker 4000 (PWC PW308)

text: ISRAEL AIRCRAFT IAI 1121 Jetcommander IAI 1121/1123 (GE CJ610) INDUSTRIES IAI 1121A Jetcommander IAI 1121B Jetcommander IAI 1123 Commodore Jet IAI 1124 Westwind IAI 1124 (Honeywell TFE731) IAI 1124A Westwind JSC Sukhoi Civil RRJ-95B Superjet 100 RRJ-95 (PowerJet SaM146) Aircraft KELOWNA (Convair) 440 Convair 580 (RR Corp 501)

text: LEARJET LJ 23 Learjet 23 (GE CJ610) 24 /24A Learjet 24/25 (GE CJ610) 24B/24B-A 24C 24D/24D-A 24E 24F/24F-A

text: Annex to ED Decision 2015/020/R

text: 25 25A 25B 25C 25D 25F 31/31A Learjet 31 (Honeywell TFE731) 35/35A Learjet 35/36 (Honeywell TFE731) 36/36A 55/55B/55C Learjet 55 (Honeywell TFE731) Learjet 60 LJ60 Learjet 60 (PWC PW305) LJ60XR Learjet 40 LJ45 Learjet Model 45 (Honeywell TFE731) LJ40XR Learjet 45 LJ45 LJ 45XR Learjet 70 LJ 70 Learjet 75 LJ 75 LOCKHEED MARTIN 1329-25 JetStar II Lockheed 1329 (Honeywell TFE731) Corporation 1329-23D JetStar Lockheed 1329 PW (PW JT12) Model 188C Electra Lockheed 188 (RR Corp 501) Model L188A Electra 382G Hercules Lockheed 382 (RR Corp 501) L-1011-385-1 TriStar Lockheed L-1011 (RR RB211) L-1011-385-1-15 TriStar L-1011-385-3 TriStar M7 AEROSPACE SA-26-T Fairchild SA26-T (PWC PT6) SA26AT Fairchild SA26 AT (Honeywell TPE331) SA226-AT Fairchild SA226 Series (Honeywell TPE331) SA226-T SA226-T(B) SA226-TC SA227-AC Swearingen Fairchild SA227 Series (Honeywell TPE331) Metro SA227-AT SA227-BC Swearingen

text: Annex to ED Decision 2015/020/R

text: Metro SA227-CC SA227-DC SA227-TT SA227-PC Swearingen Fairchild SA227 Series (PWC PT6) Metro McDONNELL DC-10-10 DC-10/MD-10 (GE CF6) DOUGLAS Corporation DC-10-30 BOEING COMPANY DC-10-30F DC-8 Series 70 DC-8 (CFM56) DC-8 Series 70F DC-8 Series 50 DC-8 (PW JT3D) DC-8 Series 60 DC-8 Series 60F DC-8F DC-8 Series 40 DC-8 (RR Conway) DC-9-10 Series DC-9 (PW JT8D) DC-9-20 Series DC-9-30 Series DC-9-40 Series DC-9-50 Series 717-200 MD 717-200 (RRD BR700-715) MD-11 MD-11 (GE CF6) MD-11F MD-11 MD-11 (PW 4000) DC-9-81 (MD-81) MD-81 MD-80 Series (PW JT8D) Series DC-9-82 (MD-82) MD-82 Series DC-9-83 (MD-83) MD-83 Series DC-9-87 (MD-87) MD-87 Series MD-88 MD-90 Series MD-90 (IAE V2500) MITSUBISHI MU-2B-26A Mitsubishi MU-2B (Honeywell TPE331) Heavy Industries MU-2B-36A MU-2B-40 MU-2B-60

text: Annex to ED Decision 2015/020/R

text: PIAGGIO Aero P.166 DP1 Piaggio P166 (PWC PT6) Industries P180 Avanti Piaggio P180 Avanti/Avanti II (PWC PT6) P180 Avanti II PILATUS PC-12 Pilatus PC-12 (PWC PT6) AIRCRAFT PC-12/45 PC-12/47 PC-12/47E PIPER AIRCRAFT PA31T to T3 Cheyenne Piper PA-31T Series (PWC PT6) PA-42-1000 Cheyenne 400LS Piper PA-42 (Honeywell TPE-331) PA-42 Cheyenne III Piper PA-42 (PWC PT6) PA-42-720 Cheyenne IIIA PA-42-720R PA-46-500TP Malibu Meridian Piper PA-46-500TP (PWC PT6) POLSKIE ZAKLADY PZL M28 00 PZL M 28 (PWC PT6) LOTNICZE PZL M28 02 PZL M28 05 REIMS AVIATION F 406 Caravan II Reims-Cessna F 406 (PWC PT6) ASI AVIATION RUAG Aerospace DO 28 D-6 Dornier Do 28 Series (PWC PT6) Services GmbH Dornier 128-6 228-100 series Dornier 228 (Honeywell TPE331) 228-200 series SAAB AB, SAAB 340A(SF340A) Saab-Fairchild Saab (SF) 340 (GE CT7) Aerosystems 340A 340B 2000 Saab 2000 (RR Corp AE2100) SABRELINER NA-265-65 Sabreliner NA-265 (Honeywell TFE731) Corporation NA-265-65 Sabreliner NA-265 (PW JT12) SHORT BROTHERS SC7 Series 3 Skyvan Shorts SC7 (Honeywell TPE331) SD3-30 Variant 200 Shorts SD3 Series-30/SD3-60 (PWC PT6) SD3-60 Variant 200 SD3-60 SHERPA Variant 200 SD3-SHERPA Variant 200 SOCATA TBM 700 A Socata TBM 700/850 700 Series (PWC PT6) TBM 700 B

text: Annex to ED Decision 2015/020/R

text: TBM 700 C1 TBM 700 C2 TBM 700 N TBM 850 TBM 900 TUPOLEV PSC TU 204-120CE Tupolev TU 204 (RR RB211)

text: TWIN COMMANDER 681 Twin Commander 680/681/690/695 Series (Honeywell TPE331) AIRCRAFT 690 Corporation 695 680-T 680-V 680-W 690A 690B 690C 690D 695A 695B VIKING AIR DHC-6-1 Twin Otter De Havilland DHC-6 (PWC PT6) (Bombardier) (De Havilland) DHC-6-100/110 DHC-6-200/210 DHC-6- 300/310/320 DHC-6-400 DHC-7-100 De Havilland DHC-7 (PWC PT6) DHC-7-101 DHC-7-102 DHC-7-103 DHC-7-110 DHC-7-111 VULCANAIR AP68TP300 Spartacus Vulcanair AP68TP Series (RR Corp 250) AP68TP600 Viator SF600 Vulcanair SF600 (RR Corp 250) SF600A

text: STCs in AEROPLANES GROUP 1

text: GROUP 1 AEROPLANES Commercial STC holder Model Part-66 Type rating endorsement designation

text: GOMOLZIG Dornier Do 28 Dornier Do 28 (Walter M601) FLUGZEUG-UND D-2 MASCHINENBAU

text: Annex to ED Decision 2015/020/R

text: JET AVIATION AG Fan Jet Falcon Falcon 20E (Honeywell TFE731) Series E NEXTANT Beech 400A Beech 400A (Williams FJ44) AEROSPACE, L.L.C.

text: GROUP 1 HELICOPTERS Commercial TC holder Model Part-66 Type rating endorsement Designation

text: AGUSTAWESTLAND A109E Agusta A109 Series (PWC PW206/207) A109N A109S AW109SP A109 Agusta A109 Series (RR Corp 250) A109A A109AII A109C A109K2 Agusta A109 (Turbomeca Arriel 1)

text: A109E Agusta A109 Series (Turbomeca Arrius 2) A109LUH AB139 Agusta AB139/AW139 (PWC PT6) AW139 EH101-500 Agusta/Westland EH-101 (GE CT7) Series EH101-510 Series EH101-300 AW169 AW169 (PWC 210) AW189 AW189 (GE CT7)

text: AB 212 Bell 212/Agusta AB212 (PWC PT6) BELL HELICOPTER 212 TEXTRON, INC. AGUSTA AB 204 B Series Agusta AB204, AB205/Bell 204, 205 (Honeywell T53) AB 205 A1 BELL HELICOPTER 204B TEXTRON, INC. 205A-1 BELL HELICOPTER 412 Bell 412/Agusta AB412 (PWC PT6) TEXTRON, INC 412EP 412CF AGUSTA AB 412 AB 412 EP

text: Annex to ED Decision 2015/020/R

text: BELL HELICOPTER 214B Bell 214 (Honeywell T5508) TEXTRON 214B-1 214ST Bell 214ST(GE CT7) BELL HELICOPTER 222 Bell 222 (Honeywell LTS 101) CANADA 222B 222U 230 230 Executive Bell 230 (RR Corp 250) 230 230 Utility 230 230 EMS 427 Bell 427 (PWC PW207D) 429 Bell 429 (PWC PW207D) 430 Bell 430 (RR Corp 250) ERICKSON AIR- EAC S-64F Erickson S-64 (PW JFTD 12) CRANE EUROCOPTER SA 330 J Eurocopter SA 330 (Turbomeca Turmo) AIRBUS AS 332 C Eurocopter AS 332 (Turbomeca Makila HELICOPTERS 1A/1A1) AS 332 L AS 332 C1 AS 332 L1 AS 332 L2 Eurocopter AS 332 L2 (Turbomeca Makila 1A2) AS 355 E Eurocopter AS 355 (RR Corp 250) AS 355 F AS 355 F1 AS 355 F2 AS 355 N Eurocopter AS 355 (Turbomeca Arrius 1) AS 355 NP SA 365 N Eurocopter SA 365 N/N1, AS 365 N2 (Turbomeca Arriel 1) SA 365 N1 Dauphin AS 365 N2 Dauphin AS 365 N3 Dauphin Eurocopter AS 365 N3 (Turbomeca Arriel 2C) EC 155 B Eurocopter EC 155 (Turbomeca Arriel 2) EC 155 B1 EC 175 B Eurocopter EC 175 (PWC PT6C) EC 225 LP Eurocopter EC 225 (Turbomeca Makila 2A) SA 365 C Dauphin Eurocopter SA 365 C Series (Turbomeca Arriel 1) SA 365 C1 Dauphin SA 365 C2 Dauphin SA 365 C3 Dauphin SA 366 G1 Dauphin Eurocopter SA 366 G1 Series (Lycoming LTS101) Philippine P-BO 105 C BO 105 series (RR Corp 250)

text: Annex to ED Decision 2015/020/R

text: Aerospace P-BO 105 S Development Corp EUROCOPTER BO 105 A AIRBUS BO 105 C HELICOPTERS DEUTSCHLAND BO 105 D Series GmbH BO 105 LS A-1 BO 105 LS A-3 BO 105 S EC 135 P1 Series Eurocopter EC 135 (PWC PW206) EC 135 P2 Series EC 135 P2+ EC 135 P3 EC 635 P2+ EC 635 P3 EC 135 T1 Series Eurocopter EC 135 (Turbomeca Arrius 2B) EC 135 T2 Series EC 135 T2+ EC 135 T3 EC 635 T1 EC 635 T2+ Series EC 635 T3 MBB-BK 117 A Eurocopter MBB-BK 117 A/B (Honeywell LTS Series 101) MBB-BK 117 B Series MBB-BK 117 C1 Eurocopter MBB-BK 117 C1 (Turbomeca Arriel 1) MBB-BK 117 C2 EC145 Eurocopter MBB-BK 117 C2 (Turbomeca Arriel 1) MBB-BK 117 D2 EC145 T2 Eurocopter MBB-BK 117 D2 (Turbomeca Arriel H145 2) KAMAN K-1200 Kaman K-1200 (Honeywell T5317) AEROSPACE CORPORATION KAMOV Ka-32A11BC Kamov Ka 32 (Klimov)

text: MD HELICOPTERS, MD900 MD Helicopters MD900 (PWC PW206/207) Inc. PZL-ŚWIDNIK W-3A PZL-Swidnik W-3A/W-3AS (Rzeszow PZL-10W) W-3AS AGUSTA AS61N Agusta AS61N/Sikorsky S-61N (GE CT58)

text: Annex to ED Decision 2015/020/R

text: AS61NI SIKORSKY S-61N AIRCRAFT S-61NM S-58 BT to JT Sikorsky S-58 (PWC PT6T) S-76A Sikorsky S-76A (RR Corp 250) S-76A S-76A+ Sikorsky S-76 (Turbomeca Arriel 1) S-76A S-76A++ S-76B S-76B Sikorsky S-76B (PWC PT6) S-76C Sikorsky S-76C (Turbomeca Arriel 1) S-76C S-76C+ Sikorsky S-76C (Turbomeca Arriel 2) S-76C S-76C++ S-76D Sikorsky S-76D (PW210S) S-92A Sikorsky S-92A (GE CT7-8)

text: STCs in HELICOPTERS GROUP 1

text: GROUP 1 HELICOPTERS Commercial STC holder Model Part-66 Type rating endorsement Designation

text: Heli-Air Inc. Bell 222 Bell 222 (RR Corp 250)

text: SUBGROUP 2a: SINGLE TURBO-PROPELLER ENGINE AEROPLANES (Other than those in Group 1)

text: TC holder Part-66 Type rating endorsement

text: AERO VODOCHODY Aero Ae-270 (PWC PT6) AIR TRACTOR Air Tractor AT-302 (Lycoming LTP-101) Air Tractor AT-400/500/600 Series (PWC PT6) ALENIA AERMACCHI Aermacchi SF260 (RR Corp 250) ALLIED AG CAT Productions Grumman G-164 (PWC PT6) CESSNA AIRCRAFT Company Cessna (Soloy) 206/207 (RR Corp 250) Cessna 208 Series (PWC PT6) Cessna 210 (RR Corp 250) EADS PZL ‘WARSZAWA-OKECIE’ EADS PZL PZL-106 BT (Walter M601) EADS PZL PZL-106 BTU (PWC PT6) EXTRA Flugzeugproduktions- und Extra EA-400-500 (RR Corp 250) Vertriebs-GmbH

text: Annex to ED Decision 2015/020/R

text: GROB Aircraft AG Grob G 120TP (RR Corp 250) MAULE AEROSPACE TECHNOLOGY Maule MX-7 (RR Corp 250) PACIFIC AEROSPACE Corporation PAC 750XL (PWC PT6) PILATUS AIRCRAFT Pilatus PC-6 Series (Turbomeca Astazou) Pilatus PC-6 (PWC PT6) Pilatus PC-6 Series (Honeywell TPE 331) THRUSH AIRCRAFT Ayres S2R Series (PWC PT6) VIKING AIR (Bombardier) (De De Havilland DHC-2 (PWC PT6) Havilland) ZLIN AIRCRAFT Zlin Z-37 T Series (Walter M601)

text: STCs in AEROPLANES SUBGROUP 2a

text: STC holder Part-66 Type rating endorsement

text: AERO TWIN, Inc. / Cessna 208/208B (Honeywell TPE331) SUPERVAN SYSTEMS, LTD. JETPROP, LLC. Piper PA-46 Pressurised (PWC PT6) SOLOY, LLC Cessna 206 (RR Corp 250) SOLOY, LLC Cessna 207 (RR Corp 250) WEST PACIFIC AIR, LLC Beech 36TC (PWC PT6)

text: SUBGROUP 2b: SINGLE TURBINE ENGINE HELICOPTERS (Other than those in Group 1) Commercial TC holder Model Part-66 Type rating endorsement Designation

text: AGUSTA A119 Koala Agusta A119/ Agusta AW119MkII (PWC PT6) AW119 MkII Koala BELL HELICOPTER 407 Bell 407 (RR Corp 250) CANADA AGUSTA AB 206A Agusta AB206/Bell 206 (RR Corp 250) AB 206B BELL HELICOPTER 206 Series from TEXTRON CANADA A to L LIMITED THE ENSTROM 480/480B Enstrom 480 (RR Corp 250) HELICOPTER CORPORATION EUROCOPTER AS 350 B Écureuil Eurocopter AS 350 (Turbomeca Arriel 1) AIRBUS AS 350 B1 HELICOPTERS

text: Annex to ED Decision 2015/020/R

text: AS 350 B2 AS 350 BA AS 350 BB AS 350 B3 Eurocopter AS 350 (Turbomeca Arriel 2) AS 350 D Eurocopter AS 350 (Honeywell LTS 101) EC 120 B Colibri Eurocopter EC 120 (Turbomeca Arrius 2F) EC 130 B4 Eurocopter EC 130 (Turbomeca Arriel 2) EC 130 T2 SA 315 B Lama Eurocopter SA 315B (Turbomeca Artouste) SA 3180 Alouette- Eurocopter SA 318 (Turbomeca Astazou) Astazou SA 318 B SA 318 C SA 319 B Alouette III Eurocopter SA 319 (Turbomeca Astazou XIV) SA 341 G Gazelle Eurocopter SA 341 (Turbomeca Astazou) SA 342 J Gazelle Eurocopter SA 342 J (Turbomeca Astazou XIV) SE 3160 Alouette III Eurocopter SA 316 B/SA 316 C (Turbomeca Artouste) SA 316 B SA 316 C MD HELICOPTERS 369 H series MD Helicopters 369 Series/SEI NH-500D (RR INC. (MDHI) Corp 250) 369 D, E and FF Mecaer Aviation NH-500D Group MD HELICOPTERS 500N MD Helicopters 500N/600N AMD500N (RR INC. (MDHI) Corp 250) 600N Mecaer Aviation AMD-500N Group PZL-ŚWIDNIK SW-4 PZL SW-4 (RR Corp 250) ROBINSON R66 Robinson R66 (RR Corp 250) HELICOPTER COMPANY SCHWEIZER 269D Schweizer 269D (RR Corp 250) AIRCRAFT CORPORATION

text: SUBGROUP 2c: SINGLE PISTON-ENGINE HELICOPTERS (Other than those in Group 1) Commercial TC holder Model Part-66 Type rating endorsement Designation

text: ANTARES SH-4 Silvercraft SH-4 (Franklin) INTERNATIONAL (Aircraft with SAS)

text: Annex to ED Decision 2015/020/R

text: BRANTLY B-2 Brantly B2 (Lycoming) INTERNATIONAL, INC. HELICOPTÈRES G2 Cabri Cabri G2 (Lycoming) GUIMBAL THE ENSTROM F-28 series Enstrom

text: (Lycoming) HELICOPTER CORPORATION 280 series Mecaer Aviation NH 300C Model 300C Schweizer/Breda Nardi 269/300 (Lycoming) Group SCHWEIZER 269A Model 300C AIRCRAFT CORPORATION 269B Model 300C 269C Model 300C 269C-1 Model 300C ROBINSON R22 Robinson R22/R44 Series (Lycoming) HELICOPTER COMPANY R22 ALPHA R22 BETA R22 MARINER R44 R44 II SIKORSKY S-58 A to J Sikorsky S-58 (Wright Cyclone) AIRCRAFT

text: GROUP 3: PISTON-ENGINE AEROPLANES (Other than those in Group 1) Type of structure MTOM Part-66 Type rating TC holder 2T and ABOVE endorsement BELOW 2T

text: AD Holdings, Inc Thorp T-211 (Continental) Metal X Thorp T-211 (Jabiru) Metal X AERO Sp.z.o.o Aero AT-3 (Rotax) Metal X AERODIF (Dyn'aviation) CAP 10 (Lycoming) Wood X CAP 20/21 (Lycoming) Wood X CAP 230 Series (Lycoming) Composite + Wood X AEROSTAR AIRCRAFT Piper PA-60/61 Series Metal X Corporation (Lycoming) Piper PA-60/61 Pressurised Metal+Pressurised X (Lycoming) AIR TRACTOR Air Tractor AT-250/300 (PW Metal X R985) Air Tractor AT-301/401/501 Metal X (PW R1340) Air Tractor AT-401 (PZL-3S) Metal X

text: Annex to ED Decision 2015/020/R

text: Air Transport Group Lake C/LA Series (Lycoming) Metal X Holdings, Inc AIRCRAFT Design and (WD) D4 Fascination (Rotax) Composite X Certification Lightwing AC4 (Rotax) Composite X AIRCRAFT INDUSTRIES Let L 200 (LOM) Metal X Let Z-37 Series (LOM) Metal tubing fabric X ALENIA AERMACCHI Aermacchi F260 Series Metal X (Lycoming) SIAI-Marchetti S.205 (Franklin) Metal X SIAI-Marchetti S.205/S.208 Metal X (Lycoming) ALEXANDRIA Aircraft LLC Bellanca 14-19 Series Wood + X (Continental) Metal tubing fabric Bellanca 17-30/17-31 Series Wood + X (Continental) Metal tubing fabric Bellanca 17-31 Series Wood + X (Lycoming Metal tubing fabric ALLIED AG CAT Grumman G-164 (Continental) Metal X Productions Grumman G-164 (Jacobs) Metal X Grumman G-164 (PW R Series) Metal X ALPHA AVIATION Robin HR 200/ R 2000 series Metal X (Lycoming) AMERICAN CHAMPION Champion 7 (Superior) Wood + X Metal tubing fabric Aircraft Corp. Champion 7 (Lycoming) Wood + X Metal tubing fabric Champion 7 (Continental) Wood + X Metal tubing fabric Champion 8 Series (Lycoming) Wood + X Metal tubing fabric AQUILA Aviation by Aquila AT01 (Rotax) Composite X Excellence AG AUGUSTAIR VARGA 2150/2180 (Lycoming) Metal X BEECHCRAFT Corporation Beech 19 Series (Lycoming) Metal X Beech 23 Series (Lycoming) Metal X Beech 24 Series (Lycoming) Metal X Beech 33 Series (Continental) Metal X Beech 35 Series (Continental) Metal X Beech 36 Series (Continental) Metal X Beech 50 Series (Lycoming) Metal X Beech 55 Series (Continental) Metal X Beech 56 Series (Lycoming) Metal X Beech 58 Series (Continental) Metal X

text: Annex to ED Decision 2015/020/R

text: Beech 58P (Continental) Metal + Pressurised X Beech 58TC (Continental) Metal X Beech 60 Series (Lycoming) Metal X Beech 65-80 Series (Lycoming) Metal X Beech 76 (Lycoming) Metal X Beech 77 (Lycoming) Metal X Beech 95 Series (Lycoming) Metal X Beech 95 Series (Continental) Metal X Beech A23 (Continental) Metal X BERIEV Beriev Be-103 (Continental) Metal X B-N GROUP Ltd. (Britten- Britten-Norman BN.2A Mark III Metal X Norman) (Lycoming) Britten-Norman BN2A Series Metal X (Lycoming) Britten-Norman BN2B Series Metal X (Lycoming) CEAPR Robin ATL/ATL S (JPX 4T60) Wood + X Composite Robin ATL L (Limbach L2000) Wood + X Composite Robin DR 200 series (Potez) Wood X Robin DR 220 series Wood X (Continental) Robin DR 221 series (Lycoming) Wood X Robin DR 250 series (Lycoming) Wood X Robin DR 253 series (Lycoming) Wood X

text: Robin DR 300 series (Lycoming) Wood X Robin DR 400 series (Lycoming) Wood X Robin DR 400 Series (Technify) Wood X Robin DR 400RP (Porsche) Wood X Robin HR 100 series Metal X (Continental) Robin HR 100 series (Lycoming) Metal X Robin R 1180 series (Lycoming) Metal X Robin R 3000 series (Lycoming) Metal X CESSNA AIRCRAFT Cessna 150 Series (Rotax) Metal Company Cessna 175 Series Metal X (Continental) Cessna 175 Series (Lycoming) Metal Cessna 177 Series (Lycoming) Metal X Cessna 180 Series Metal X (Continental) Cessna 185 Series Metal X

text: Annex to ED Decision 2015/020/R

text: (Continental) Cessna 188 (Continental) Metal X Cessna 206 Series Metal X (Continental) Cessna 206 Series (Lycoming) Metal X Cessna 207 Series Metal X (Continental) Cessna 210 Series Metal X (Continental) Cessna P210 (Continental) Metal + Pressurised X Cessna 310/320 Series Metal X (Continental) Cessna 321 (Continental) Metal X Cessna 335 (Continental) Metal + Pressurised X Cessna 336 (Continental) Metal X Cessna 340 (Continental) Metal + Pressurised X Cessna T303 (Continental) Metal X Cessna/Reims-Cessna Metal X 150/F150 Series (Continental) Cessna/Reims-Cessna Metal X 152/F152 Series (Lycoming) Cessna/Reims-Cessna Metal X 172/F172 Series (Continental) Cessna/Reims-Cessna Metal X 172/F172 Series (Lycoming) Cessna/Reims-Cessna Metal X 182/F182 Series (Continental) Cessna/Reims-Cessna Metal X 182/F182 Series (Lycoming) Cessna/Reims-Cessna Metal 182/F182 Series (SMA) Cessna/Reims-Cessna 337 Metal X Series (Continental) (not pressurised) Cessna/Reims-Cessna 337 Metal + Pressurised X Series (Continental) (pressurised) Cessna C300/C350/C400 Composite X (Continental) CIRRUS Design Cirrus SR20/SR22/SR22T Series Composite X Corporation (Continental) Cirrus SR22 Series (Thielert) Composite COMMANDER PREMIER Commander 112 (Lycoming) Metal X AIRCRAFT CO. Commander 114 (Lycoming) Metal X Czech Sport Aircraft a.s. Czech Sport PS-28 (Rotax) Metal X

text: Annex to ED Decision 2015/020/R

text: DE HAVILLAND Support Beagle B.121 series 1 Metal X (Continental) (Aircraft with SAS) Beagle B.121 series 2/3 Metal X (Lycoming) DECOURT Decourt DMS 884 (Franklin) Wood X (Aircraft with SAS) DIAMOND AIRCRAFT Diamond DA20 (Continental) Composite X Industries Diamond DA20/DV20 (Rotax) Composite X Diamond DA40 (Austro Engine) Composite X Diamond DA40 (Lycoming) Composite X Diamond DA40 D (Technify) Composite X Diamond DA42 Series (Austro Composite X Engine) Diamond DA42 Series Composite X (Technify) Diamond DA62 (Austro Engine) Composite X DYNAC AEROSPACE Aerocommander 100 Metal X Corporation (Lycoming) EADS Deutschland Bölkow BO 208 (Continental) Metal X Military Air Syst Bölkow BO 209 (Lycoming) Metal X Bölkow F.207 (Continental) Wood + Composite Bölkow F. BO 207 (Lycoming) Wood X + Composite SIAT 223 (Lycoming) Metal X EADS PZL ‘WARSZAWA- PZL-104 Wilga (Lycoming) Metal X OKECIE’ PZL-104 Wilga Series (PZL) Metal X PZL-104A Wilga (Ivchenko) Metal X PZL-110 Koliber (Franklin) Metal X PZL-Koliber 150 Series Metal X (Lycoming) PZL-Koliber 160 (Lycoming) Metal X EADS PZL ‘WARSZAWA- PZL-106 Series (PZL) Metal X OKECIE’ (Aircraft with SAS) E.I.S Aircraft GmbH RS 180 (Lycoming) Wood X EVEKTOR Evektor EV-97 VLA (Rotax) Metal X SportStar RTC (Rotax) Metal X EXTRA Extra EA-200/300 Series Composite X Flugzeugproduktions- (Lycoming) und Vertriebs-GmbH

text: Annex to ED Decision 2015/020/R

text: Extra EA-400 (Continental) Composite + X Pressurised FFA ALTENRHEIN AS202 Series (Lycoming) Metal X FFT GYROFLUG SC01 Series (Lycoming) Composite X (Aircraft with SAS) Flight Design GmbH CTLS-ELA (Rotax) Composite X FLS AEROSPACE Club Sprint/Sprint 160 Metal X (Lycoming) (Aircraft with SAS) OA7 Optica Series (Lycoming) Metal X Fournier, René RF 47 (Limbach) Wood X RF 6B (Continental) Wood X RF 6B (Lycoming) Wood X FUJI Heavy Industries Fuji FA-200 Series (Lycoming) Metal X GA8 Airvan Pty Ltd Gippsland GA8 (Lycoming) Metal X GARDAN Gardan GY 80 (Lycoming) Metal X (Aircraft with SAS) GENERAL AVIA General Avia F.22 (Lycoming) Metal X Costruzioni Aeronautiche (Aircraft with SAS) General Avia F20 Series Metal X (Lycoming) (Continental) Bernd Hager/Anatoli Ruschmeyer R90-230RG Composite X Stobbe GbR (Lycoming) GOMOLZIG FLUGZEUG- UND MASCHINENBAU GmbH GROB Aircraft AG Luft- Grob G115/120 Series Composite X und Raumfahrt (Lycoming) Hoffmann GmbH & Co. H 40 (Lycoming) Composite X KG Magnaghi Aeronautica III Sky Arrow 650/710 (Rotax) Composite X S.p.A. (INIZIATIVE INDUSTRIALI ITALIANE) INSTYTUT LOTNICTWA Instytut Lotnictwa I-23 Composite X Manager (Lycoming) INTERCEPTOR AIRCRAFT Aerocommander 200 Metal X Corporation (Continental) ISSOIRE AVIATION Issoire APM 20/30 (Rotax) Composite X Issoire APM 40 (Continental) Composite X LAVIA ARGENTINA S.A. Piper PA-25 Series (Lycoming) Metal tubing fabric X (LAVIASA) LIBERTY AEROSPACE Liberty XL-2 (Continental) Composite X Incorporated MAULE AEROSPACE Maule M4 (Continental) Metal tubing fabric X TECHNOLOGY Maule M4 (Franklin) Metal tubing fabric X Maule M4 (Lycoming) Metal tubing fabric X

text: Annex to ED Decision 2015/020/R

text: Maule M5 (Continental) Metal tubing fabric X Maule M5 (Franklin) Metal tubing fabric X Maule M5 (Lycoming) Metal tubing fabric X Maule M6 (Lycoming) Metal tubing fabric X Maule M7 Series (Lycoming) Metal tubing fabric X Maule MX-7 (Lycoming) Metal tubing fabric X MOONEY AIRPLANE Mooney M18L (Continental) Metal + Wood X Company Mooney M20 (Continental) Metal X Mooney M20/M20A Metal + Wood X (Lycoming) Mooney M20B to M20S/M22 Metal X (Lycoming) NIPPER Nipper T-66 (Stark) Wood + X Metal tubing fabric OMA SUD SPA Sky SKYCAR (Lycoming) Metal X Technolgies PIAGGIO Aero Industries Piaggio P166 (Lycoming) Metal X PILATUS AIRCRAFT Pilatus PC-6 Series (Lycoming) Metal X PIPER AIRCRAFT Piper PA-23 Aztec (Lycoming) Metal X Piper PA-24 Series (Lycoming) Metal X Piper PA-28 Series Metal X (Continental) Piper PA-28 Series (Lycoming) Metal X Piper PA-28 Series (Thielert) Metal Piper PA-30 Series (Lycoming) Metal X Piper PA-31 Series (Lycoming) Metal X Piper PA-31P (Lycoming) Metal + Pressurised X Piper PA-32 Series (Lycoming) Metal X Piper PA-34 Series Metal X (Continental) Piper PA-34 Series (Lycoming) Metal X Piper PA-36 Series Metal X (Continental) Piper PA-36 Series (Lycoming) Metal X Piper PA-38 Series (Lycoming) Metal X Piper PA-39/40 Series Metal X (Lycoming) Piper PA-44 Series (Lycoming) Metal X Piper PA-46 Pressurised Series Metal + Pressurised X (Continental) Piper PA-46 Pressurised Metal + Pressurised X (Lycoming) Piper PA-46 Series (Lycoming) Metal X Polskie Zakłady Lotnicze PZL M 18 (PZL) Metal X

text: Annex to ED Decision 2015/020/R

text: Sp. z o. o. PZL M 26 (Lycoming) Metal X Polskie Zakłady Lotnicze PZL-M20 (PZL) Metal X Sp. z o. o. (Aircraft with SAS) PZL MIELEC PZL-M20 (PZL) Metal REGAL AIR, INC REGAL AIR 305 Series Metal X (Continental) REVO, Inc REVO C/LA-4 Series (Lycoming) Metal X RUAG AEROSPACE Do 28 Series (Lycoming) Metal X Services GmbH S.C.Constructii IAR-46 (Rotax) Metal X Aeronautice S.A SCHEIBE Flugzeugbau SF 23 Series (Continental) Wood + X Metal tubing fabric SCHEIBE Flugzeugbau SF 23 Series (Lycoming) Wood + X (Aircraft with SAS) Metal tubing fabric SEASTAR CORP TSC Series (Lycoming) Composite X SKY INTERNATIONAL Aviat Husky A (Lycoming) Metal X Pitts S-1 Series (Lycoming) Wood+ X Metal tubing fabric Pitts S-2 Series (Lycoming) Wood + X Metal tubing fabric Skyfox Aviation Ltd CA25 Series (Rotax) Wood + X Metal tubing fabric SLINGSBY Aviation Slingsby T67A (Lycoming) Wood X Slingsby Composite X T67A/T67B/T67C/T67M Series (Lycoming) SOCATA Grumman GA-7 (Lycoming) Metal X SOCATA MS 881 (Potez) Metal X SOCATA MS 884/894/PZL Metal X Koliber (Franklin) SOCATA Rallye Series Metal X (Continental) SOCATA Rallye Series Metal X (Lycoming) SOCATA TB Series (Lycoming) Metal X SOCATA (Aircraft with SOCATA ST10 (Lycoming) Metal X SAS) Sportavia Putzer Sportavia Putzer RS180 Wood + Composite X (Aircraft with SAS) (Lycoming) STOL AIRCRAFT Republic UC-1 (Lycoming) Metal X Corporation STEMME AG Stemme ASP S15 (Rotax) Composite X SUKHOI Sukhoi Su-29/31 (MGA) Composite X

text: Annex to ED Decision 2015/020/R

text: SUKHOI Sukhoi SU-29 (Vedeneyev) Composite X (Aircraft with SAS) Sukhoi SU-31 (Vedeneyev) Composite X Symphony Aircraft Symphony OMF-100-160 Metal X Industries Inc (Lycoming) NAFTAA TAYLORCRAFT 2000 Taylorcraft 19 Series Wood + X (Continental) Metal tubing fabric Taylorcraft F21/F22 Series Wood + X (Lycoming) Metal tubing fabric TECNAM Costruzioni Tecnam P2006T (Rotax) Metal X Aeronautiche Tecnam P92 (Rotax) Metal X Tecnam P96/P2002/P2004 Metal X (Rotax) Tecnam P2008 (Rotax) Composite + Metal X Tecnam P2010 (Lycoming) Composite + Metal X THRUSH Aircraft Ayres S2R (PW R-985) Metal tubing fabric X

text: TRUE FLIGHT Holdings Grumman/American AA-1 Metal X Series (Lycoming) Grumman/American AA-5 Metal X Series (Lycoming) TWIN COMMANDER Commander 500 Series/680 Metal X AIRCRAFT Corporation Series (Lycoming) Commander 680P (Lycoming) Metal + Pressurised X Commander 685 (Continental) Metal + Pressurised X Rockwell 700 (Lycoming) Metal + Pressurised X Commander 720 (Lycoming) Metal + Pressurised X VULCANAIR Partenavia P.64 (Lycoming) Metal X Partenavia P.66 (Lycoming) Metal X Partenavia P57 (Lycoming) Wood + Metal tubing fabric Vulcanair F600A (Lycoming) Metal Vulcanair P.68 Series Metal X (Lycoming) WACO Aircraft Company Waco YMF (Jacobs) Wood + X Metal tubing fabric WACO Classic Aircraft Waco 2T Series (Lycoming) Wood + X Corp Metal tubing fabric WASSMER CERVA CE43 (Lycoming) Metal X (Aircraft with SAS) CERVA CE44 (Continental) Metal X WA4/21 Series (Lycoming) Wood + X Metal tubing fabric WA40 Series (Lycoming) Wood + X

text: Annex to ED Decision 2015/020/R

text: Metal tubing fabric WA41 (Lycoming) Wood + X Metal tubing fabric XtremeAir GmbH XtremeAir XA42 (Lycoming) Composite X YAKOVLEV (Aircraft Yakovlev YAK-18T (Vedeneyev) Metal X with SAS) ZAKŁADY LOTNICZE EM-11 (Lycoming) Composite X ZENAIR LTD Zenair CH2000 (Lycoming) Metal X ZLIN AIRCRAFT Zlin Z-143 L (Lycoming) Metal X (MORAVAN AVIATION) Zlin Z-242 L (Lycoming) Metal X Zlin Z-26 Series (Walter Metal X Minor/AVIA) Zlin Z-42 Series (LOM) Metal X Zlin Z-43 Series (LOM) Metal X Zlin Z-50 Series (LOM) Metal X Zlin Z-50L Series (Lycoming) Metal X Zlin Z-526 L (Lycoming) Metal X

text: STCs in AEROPLANES GROUP 3

text: GROUP 3: PISTON-ENGINE AEROPLANES (Other than those in Group 1) Type of structure MTOM Part-66 Type rating STC holder 2T and ABOVE endorsement BELOW 2T

text: BARBARA AND ROPERT Cessna 150 Series (Lycoming) Metal X WILLIAMS HOFFMANN GmbH & Co. Cessna Metal X KG 150/A150/F150/FA150 (Rotax) LTB SAMMET GmbH Cessna 150 (Rotax) Metal X PORSCHE AG Cessna 182Q/F182Q Metal X (Porsche) SMA ENGINES INC. Cessna 182Q/182R (SMA) Metal X SPERL TECHNIK & Cessna Metal X ENTWICKLUNGEN 150/A150/F150/FA150 (Rotax) TECHNIFY MOTORS GmbH Robin DR 400 (Technify) Wood X Cessna 172/F172 (Technify) Metal X Piper PA-28- Metal X 140/150/151/160/161/180/ 181 (Technify) Cirrus SR22 (Technify) Composite X Cessna 206 (Technify) Metal X


text: ED Decision 2006/11/R 18/12/2006

text: OJ L 240, 7.9.2002, p.1. Regulation as last amended by

text: Commission Regulation (EC) 1701/2003 of 24 September 2003

text: (OJ L 243, 27.9.2003, p. 5) OJ L 315, 28.11.2003, p. 1 Regulation as amended by

text: Commission Regulation (EC) No 707/2006 of 8 May 2006

text: (OJ L 122, 9.5.2006, p. 17).

text: ED Decision 2006/11/R 18/12/2006

text: Decision of the Management Board concerning the procedure to be applied by the Agency for the issuing of opinions, certification specifications and guidance material (“Rulemaking Procedure”), EASA MB/7/03, 27.6.2003.

text: ED Decision 2006/11/R 18/12/2006

identifier: AMC to Part-M — Amendment 1

amnesord: Part-M - Continuing airworthiness requirements

beslut: ED Decision 2006/011/R

publisher: Europeiska unionens byrå för luftfartssäkerhet

sprak: en

title: AMC to Part-M — Amendment 1

serie: amc

text: European Aviation Safety Agency

type: rubrik

text: DECISION No 2006/11/R

type: stycke

text: OF THE EXECUTIVE DIRECTOR OF THE AGENCY

text: of 18-12-2006

text: amending Decision No 2003/19/RM of 28 November 2003 on acceptable means of compliance and guidance material to

text: Commission Regulation (EC) No 2042/2003

text: THE EXECUTIVE DIRECTOR OF THE EUROPEAN AVIATION SAFETY AGENCY,

text: Having regard to

text: Regulation (EC) No 1592/2002 of 15 July 2002

text: on common rules in the field of civil aviation and establishing a European Aviation Safety Agency (hereinafter referred to as the “Agency”), and in particular Articles

text: and

text: thereof.

text: Having regard to the

text: Commission Regulation (EC) No 2042/2003 of 28 November 2003

text: on the continuing airworthiness of aircraft and aeronautical products, parts and appliances, and on the approval of organisations and personnel involved in these tasks. (Hereinafter referred to as

text: Commission Regulation (EC) No 2042/2003

text: Whereas:

text: (1) To clarify the meaning of “Officially recognised standard” each time the term is used in

text: Commission Regulation (EC) No 2042/2003

text: (2) National authorities as well as industry requested a definition of the concept of “Officially recognised standard”

text: (3) The Agency shall issue certification specifications, including airworthiness codes and acceptable means of compliance (hereinafter referred to as AMC), as well as any guidance material for the application of the Basic Regulation and its implementing rules.

text: (4) The Agency, pursuant to Article 43 of the Basic Regulation and articles 5(3) and 6 of the Agency rulemaking procedure , has widely consulted interested parties (see: NPA No 1-2006) on the matters which are the subject of this Decision and has provided thereafter a written response to the comments received called CRD

text: HAS DECIDED:

text: Article 1

text: In AMC M.A.402 (b) the following paragraph is added after the first paragraph “In this context officially recognised standard means those standards established or published by an official body whether having legal personality or not, which are widely recognised by the air transport sector as constituting good practice”.

text: Article 2

text: In AMC M.A.606 (f) the following paragraph 11 is added “In this context officially recognised standard means those standards established or published by an official body whether having legal personality or not, which are widely recognised by the air transport sector as constituting good practice”.

text: Article 3

text: In AMC M.A.608 (b) the following paragraph 3 is added “In this context officially recognised standard means those standards established or published by an official body whether having legal personality or not, which are widely recognised by the air transport sector as constituting good practice”.

text: Article 4

text: In AMC 145.A.30 (f ) the following paragraph 11 is added “In this context officially recognised standard means those standards established or published by an official body whether having legal personality or not, which are widely recognised by the air transport sector as constituting good practice”.

text: Article 5

text: In AMC 145.A.40 (b) the following paragraph 3 is added “In this context officially recognised standard means those standards established or published by an official body whether having legal personality or not, which are widely recognised by the air transport sector as constituting good practice”.

text: Article 6

text: This decision shall enter into force on 25 December 2006. It shall be published in the Official Publication of the Agency.

text: Done in Cologne on 18 December 2006.

text: P. GOUDOU

type: vagledning

utgivare: easa


text: Annex to ED Decision 2013/025/R

text: Annex to ED Decision 2013/025/R

text: Type certificate, Supplemental Type Certificate or repair design approval holder as applicable

text: Annex to ED Decision 2013/025/R

text: R b) At the TBO the component should be inspected (and possibly tested, depending on the type of component) by an appropriately B or C rated maintenance organisation in accordance with the maintenance data for obvious defect or abnormal functioning.

text: Annex to ED Decision 2013/025/R

text: R This appendix provides criteria on the procedures needed for the extension of TBO of a piston engine. Refer to AMC2 M.A.302 (d).

text: Annex to ED Decision 2013/025/R

text: Annex to ED Decision 2013/025/R

text: Annex to ED Decision 2013/025/R

text: Annex to ED Decision 2013/025/R

identifier: AMC to Part-M — Amendment 10

beslut: ED Decision 2013/025/R

title: AMC to Part-M — Amendment 10

text: European Aviation Safety Agency

text: Acceptable Means of Compliance (AMC) to Part-M

text: I. Draft Decision Part-M - Annex to Decision 2013/005/R

text: Annex I to ED Decision 2003/19/RM of the Executive Director of the Agency of 28 November 2003, on ‘Acceptable means of compliance and guidance material to

text: Commission Regulation (EC) No 2042/2003 of 20 November 2003

text: on the continuing airworthiness of aircraft and aeronautical products, parts and appliances, and on the approval of organisations and personnel involved in these tasks’, is hereby amended as follows:

text: The text of the amendment is arranged to show deleted text, new text or new paragraph as shown below:

text: 1. deleted text is marked with strike through.

text: 2. new or amended text is highlighted in grey.

text: 3. an ellipsis (…) indicates that the remaining text is unchanged in front of or following the reflected amendment.

text: 1) A new AMC, AMC2 M.A.302 (d) is added:

text: AMC2 M.A.302 (d) —Aircraft Maintenance programme

text: TIME BETWEEN OVERHAULS 1. Introduction When the instructions for continuing airworthiness referred to in M.A.302 (d) (ii) contain overhaul intervals for components, typically referred to as Time Between Overhauls (TBO), they should be taken into account when developing the aircraft maintenance programme. Unless paragraph 2 or 3 below is followed, TBO values established by the design approval holder (DAH) should apply. TBOs included in the Airworthiness Limitations Section or otherwise mandated by the Agency cannot be deviated from. TBOs are normally defined in terms of calendar time and/or operating or flying hours/cycles/landings, whichever occurs first. Intervals proposed by the DAH as TBOs may be different for different variants of the component and for components with design changes or service bulletins embodied. 2. Eligibility and process for TBO extension Except for the cases mentioned in paragraph (l) below, for non-powered and piston engine aircraft other than complex motor-powered aircraft (CMPA), the owner or the CAMO managing the aircraft maintenance programme may propose, in accordance with E M.A.302(d)(iii), extended intervals for overhauling the components (TBO from now on) R compared to those TBOs recommended by the DAH (hereinafter referred to as TBO ). In order to obtain the approval of a different overhaul interval compared to the one established by the DAH, the following should be observed: a) Inspection standards and tests conditions as well as pass-fail criteria should be stated before the component is inspected and be based on the components’ typical parameters provided by the DAH in the form of manuals. In addition to the provisions of Appendix I to the AMC M.A.302 and AMC M.B.301(b) ‘Content of maintenance programme’, these standards, conditions and criteria should be considered part of the aircraft maintenance programme.

text: c) For ELA1 aircraft not used in commercial air transport these inspections may also be performed by M.A.801 (b) 2 certifying staff in accordance with M.A.502(d). For piston engines, these inspections should satisfy Appendix XIV to this AMC2. R d) All component’s parts identified by the DAH for replacement at TBO which are accessible during the inspection should be individually inspected and replaced if necessary. e) The results of the inspection should be considered as maintenance records by the maintenance organisation and should be conclusive. A copy of the inspection results should be provided to the aircraft owner. f) Airworthiness Directives affecting the component and required to be completed at the R time of the overhaul should be completed not later than TBO . g) If the inspection is satisfactory and there is no reason to believe that the component will not function as intended (e.g. consideration of past occurrences affecting the E individual aircraft), the TBO will be reflected in the aircraft maintenance programme (refer to paragraph j)) together with any additional maintenance action identified as necessary so that the component functions as intended until that time. As a minimum, another conclusive inspection should be programmed when 50 % of the extended E R E R interval ((TBO – TBO )/2) is reached. TBO should not exceed 20 % of TBO in calendar time or operating hours, whichever comes first. E E2 R h) At TBO , a second extension (TBO from now on) of a maximum of 20 % of TBO may be granted when conditions a) to g) are similarly met.

text: i) No further TBO extension should be allowed except for components fitted on privately operated aircraft with a MTOM of 2 730 kg or below, for which there is no limit on the R number of extensions (20 % of TBO each) when conditions a) to g) are similarly met. In this case, at the time of the third TBO extension, the fact that the aircraft is privately operated should be stated in the aircraft’s continuing airworthiness records (e.g. aircraft logbook). The components affected should also be identified. j) Based on the results of the inspection mentioned in paragraphs g), the aircraft maintenance programme amendment containing the extended TBO should be approved by the competent authority. Alternatively, and notwithstanding the provisions of paragraph 7 of AMC M.A.302(d), for privately operated aircraft with a MTOM of 2 730 kg or below the maintenance programme may be approved in accordance with the M.A.302 (c) indirect approval procedure. k) A component with an extended TBO should not be installed on a different aircraft unless agreed by the competent authority of the Member State of registry.

text: l) TBO extensions in accordance with this AMC2 should not be considered for components: i. installed in aircraft used in commercial air transport

text: ii. installed in aircraft used for ‘ab initio’ training activities, iii. linked to IFR operations, and iv. for which their normal serviceable condition could be affected because of the aircraft’s utilisation (e.g. engine on an aircraft used for aerobatic flights). m) Despite (l)(iv) above, the TBO extensions in accordance with this AMC2 can be considered for the components affected by the operation of the aircraft in highly

text: corrosive environment or installed on aircraft used for towing provided that the inspections/checks of the components are performed at intervals of 25 % of the E R extended interval ((TBO – TBO )/4). In these cases, for the extension of the engine’s TBO in addition to the measures defined by the paragraph 3 of Appendix XIV to AMC2 M.A.302 (d), a boroscoping inspection and/or an oil spectrographic analysis should be part of the inspection. 3. Components’ Trend Monitoring Alternatively to the maintenance programme containing scheduled overhaul intervals of the components, the owner or the CAMO managing the aircraft maintenance programme may propose a maintenance programme based on trend monitoring and analysis of these trends, together with component rejection criteria. This maintenance programme should start at the beginning of the component’s life or include a minimum of 6 scheduled condition checks performed before the TBO is reached.

text: 2) AMC M.B.301(b) is modified with M.B.301(b)(9):

text: AMC M.B.301 (b) — Maintenance programme

text: In respect of the extension of the TBOs mentioned in AMC2 M.A.302 (d):

text: 1. the competent authority may elect not to extend the component’s TBO when the individual aircraft has been under its Member State register for less than 12 months or has been operated under that registration for less than 100 flying hours. If necessary, CAMO procedures allowing maintenance programme indirect approval should be limited accordingly. 2. for aircraft types/components for which the competent authority considers not having enough experience, it may elect not to extent the TBO of components until the sufficient service experience is gained. 3. in the case described in paragraph 3 of AMC2 M.A.302(d), the competent authorities may accept the trend monitoring approach based on a positive opinion of the DAH or, when having enough knowledge and history record of the subject component, considering also the particular circumstances (e.g. intended utilisation) of the individual aircraft.

text: 4. In respect to the paragraph 2.2 of the Appendix XIV to AMC2 M.A.302 (d), competent authorities may accept alternative inspections/test that would provide equivalent information or findings.

text: 3) A new appendix, Appendix XIV to AMC2 M.A.302 (d) is added:

text: Appendix XIV to AMC2 M.A.302 (d) — Aircraft Maintenance programme

text: PISTON ENGINE CRITERIA FOR OPERATION BEYOND DESIGN APPROVAL HOLDERS’ RECOMMENDED OVERHAUL PERIODS

text: 1 Subject

text: 2 Introduction

text: A piston engine that has reached the end of its DAH recommended overhaul interval may be expected to have suffered some wear to cylinders, pistons, valves, bearings and other moving

text: parts, but an engine that has been carefully operated and maintained may still be in a condition suitable for a further period of service. 2.1 Many factors affect the wear that takes place in an engine. The most important of these include: the efficiency of the air intake filter; the techniques used in engine handling, particularly during starting; the quality of the fuel and oil used in the engine; and the conditions under which the aircraft is housed when not in use. Conditions of operation are also relevant; the length of flights; the atmospheric conditions during flight and on the ground; and the type of flying undertaken. Many of these factors are outside the duties of the maintenance personnel, but meticulous compliance with the approved maintenance programme and any instructions provided in the form of service bulletins or DAH’s recommendations will undoubtedly help to prolong the life of an engine. 2.2 The inspections and tests that may be necessary to assess the condition of an engine in compliance with AMC2 M.A.302 (d) are detailed in the following paragraphs. Alternative inspections/tests that would provide equivalent information or findings may be proposed.

text: 3 Inspection and maintenance

text: A number of items included in the normal scheduled maintenance of an engine may be repeated to determine the condition of an engine at the end of its normal overhaul period, and additional inspections may also be specified.

text: 3.1 External condition

text: The engine should be examined externally for obvious defects such as a cracked crankcase, excessive play in the propeller shaft, overheating and corrosion, which would make it unacceptable for further use. Special attention should be drawn to the cables, plugs, connectors and sensors of engines equipped with electronic control systems regarding improper mounting, shaving, worn contacts, and other kind of damage. Worn or damaged parts have to be repaired/replaced according to the Design Approval Holder’s (DAH) instructions. External tubes and houses should be checked and if necessary replaced in accordance with the DAH’s instructions.

text: 3.2 Internal condition

text: Significant information concerning the internal condition of an engine may be obtained from an examination of the oil filters and magnetic plugs, for metal particle contamination. These checks may be sufficient to show that serious wear or breakdown has taken place and that the engine is unacceptable for further service.

text: 3.3 Oil consumption

text: Since the oil consumption of an engine may have increased towards the end of its normal overhaul period, an accurate check of the consumption over the last 10 flying hours would show whether it is likely to exceed the maximum recommended consumption defined by the DAH, if the overhaul period were to be extended.

text: 3.4 Compression check

text: Piston ring or cylinder wear, or poor valve sealing could, in addition to increasing oil consumption, result in a significant loss of power. A cylinder compression check should be carried out in accordance with the DAH’s instructions. The usual method of checking engine compression is the differential pressure test. In this test a regulated air supply (normally 560 kPa (80 lbf/in )) is applied to each cylinder in turn and a pressure gauge is used to record the actual air pressure in the cylinder. Since some leakage will normally occur, cylinder pressure will usually be less than the supply pressure and the difference will be an indication of the condition of the piston rings and valves. By listening for escaping air at the carburettor intake, exhaust and crankcase breather, a defective component may be located. It is usually recommended that the differential pressure test is carried out as soon as possible after running the engine.

text: 4 Power output of aeroplane engines

text: The power developed by an aeroplane engine after initial installation is established in the form of a reference engine speed, which is recorded in the appropriate logbook so that a comparison can be made during subsequent power checks. The reference engine speed is the observed engine speed obtained using specified power settings and conditions corrected, by means of graphs supplied by the engine DAH, to the figure which would be obtained at standard sea-level atmospheric temperature and pressure; changes in humidity do not produce large changes of power and are ignored for the purpose of establishing a reference engine speed or subsequently checking engine power. Power checks should be corrected in the same way.

text: 4.1 Power checks

text: The majority of light aeroplane piston engines are air-cooled and rely on an adequate flow of air for proper cooling of the cylinders. This condition can only be obtained during flight and ground runs should therefore be as brief as possible. Cooling can be assisted by facing the aircraft into wind, but high wind conditions must be avoided when making power checks, as they will significantly affect the results obtained. Before running the engine at high power the normal operating temperatures should be obtained (not the minimum temperatures specified for operation) and during the test careful watch should be kept on oil and cylinder temperatures to prevent the appropriate limitations being exceeded. 4.1.1 Normally-aspirated engines are tested at full throttle and, where a controllable-pitch propeller is fitted, with fully fine pitch selected. The changes in barometric pressure affecting engine power are considered to be balanced by changes in propeller load, so that only temperature correction is necessary. This correction factor may be obtained from a graph supplied by the engine DAH (if not provided by the DAH, Leaflet 70-70 Piston Engine Overhaul – Correcting Engine Test Results of CAA UK CAP 562 could be used). The observed full throttle speed multiplied by the correction factor will give the corrected speed. 4.1.2 Although normally-aspirated engines are often fitted with variable-pitch propellers, the engine speed obtained at full throttle is usually less than the governed speed and the propeller remains in fully fine pitch. With supercharged engines, however, the propeller is usually governed to a constant speed at high power settings and small changes in power will not affect engine speed. The power of a supercharged engine is, therefore, checked by establishing a reference speed at prescribed power settings. a) Since a supercharged engine is run at a specified manifold pressure regardless of the atmospheric pressure, corrections must be made for both temperature and pressure variations from the standard atmosphere. b) The procedure is to run the engine until normal operating temperatures are obtained, open up to maximum take-off manifold pressure, decrease power until a fall in engine speed occurs (denoting that the propeller blades are on their fine pitch stops), then throttle back to the manifold pressure prescribed by the DAH and observe the engine speed obtained. c) The correction factor to be applied to the observed engine speed of a supercharged engine may be obtained from graphs supplied by the engine DAH. 4.1.3 Although the engine speed obtained during a check of engine power is corrected as necessary for atmospheric temperature and pressure, no correction is made for humidity, ambient wind conditions or instrument errors and, consequently, the corrected engine speed is seldom exactly equal to the reference speed even if the engine condition is unchanged. However, engine power may usually be considered satisfactory if the corrected speed obtained during a power check is within 3 % of the reference speed. 4.1.4 If it is not possible to assess power deterioration by means of a power check (e.g. due to fitting a different propeller), a rate-of-climb flight test should be carried out.

text: 5 Power output of helicopter engines

text: The power developed by the engine of a single-engine helicopter is considered to be adequately checked during normal operations; any loss of power should be readily apparent. It is thus not considered necessary to check the power output of a helicopter engine separately specifically for the purpose of complying with this annex.

text: 6 Power loss

text: If the power check (paragraph 4) or normal engine operation reveal an unacceptable loss of power or rough running, it may be possible to rectify this by carrying out certain normal servicing operations or by replacement of components or equipment. The replacement of spark plugs, resetting of tappets or magneto contact breaker points, or other adjustments to the ignition or carburation systems, are all operations that may result in smoother running and improve engine power.

text: 7 Servicing

text: If the engine proves to be suitable for further service, a number of servicing operations will normally be due in accordance with the approved maintenance programme. Unless carried out previously (paragraph 6), these operations should be completed before the engine is returned to service.

text: 8 Logbook entries

text: A record of the checks made, and any rectification or servicing work, must be entered and certified in the engine logbook before the engine is released to service for its recommended or extended service life under the provision of AMC2 M.A.302 (d). The logbook entry made should also specify any restriction on further use (refer to AMC2 M.A.302 (d)).

text: 9 Maintenance programme amendments

text: The aircraft maintenance programme should reflect the provisions for TBO extension and the additional maintenance tasks required with their periodicity to operate the aircraft engine beyond its recommended overhaul period as detailed in AMC2 M.A.302 (d).


text: OF THE EXECUTIVE DIRECTOR OF THE AGENCY

text: Regulation (EC) No 216/2008

text: of the European Parliament and of the Council of 20 February 2008 on common rules in the field of civil aviation and establishing a European Aviation Safety Agency, and repealing

text: Council Directive 91/670/EEC

text: Regulation (EC) No 1592/2002

text: and Directive

text: (OJ L 79, 19.3.2008, p. 1), as last amended by

text: Commission Regulation (EU) No 6/2013 of 8 January 2013

text: (OJ L 4, 9.1.2013, p. 34). 2

text: Commission Regulation (EC) No 2042/2003 of 20 November 2003

text: on the continuing airworthiness of aircraft and aeronautical products, parts and appliances, and on the approval of organisations and personnel involved in these tasks (OJ L 315, 28.11.2003, p. 1). Regulation as last amended by

text: Commission Regulation (EU) No 593/2012 of 5 July 2012

text: (OJ L 176, 06.07.2012, p. 38). 3 Decision No 2003/19/RM of the Executive Director of the European Aviation Safety Agency of 28 November 2003 on acceptable means of compliance and guidance material to

text: on the continuing airworthiness of aircraft and aeronautical products, parts and appliances, and on the approval of organisations an personnel involved in these tasks. Decision as last amended by Decision 2013/025/R of the Executive Director of the Agency of 20 September 2013.

text: TE.RPRO.00072-001 © European Aviation Safety Agency. All rights reserved. Proprietary document. Copies are not controlled. Confirm revision status through the EASA Internet/Intranet. Page 1 of 2

text: EASA MB Decision No 01-2012 of 13 March 2012 amending and replacing Decision 08-2007 concerning the procedure to be applied by the Agency for the issuing of Opinions, Certification Specifications and Guidance Material (‘Rulemaking Procedure’) (http://easa.europa.eu/officialpublication/rulemaking-procedure.php).

text: TE.RPRO.00072-001 © European Aviation Safety Agency. All rights reserved. Proprietary document. Copies are not controlled. Confirm revision status through the EASA Internet/Intranet. Page 2 of 2

identifier: AMC to Part-M — Amendment 11

beslut: ED Decision 2013/034/R

title: AMC to Part-M — Amendment 11

text: ED Decision 2013/034/R

text: European Aviation Safety Agency

text: DECISION 2013/034/R

text: of 19 December 2013

text: amending Acceptable Means of Compliance to Part M of

text: Commission Regulation (EC) 2042/2003

text: THE EXECUTIVE DIRECTOR OF THE EUROPEAN AVIATION SAFETY AGENCY,

text: Having regard to

text: Commission Regulation (EC) No 2042/2003

text: Whereas:

text: (1) The Agency shall, pursuant to

text: Article 18

text: (c) of

text: Regulation (EC) No 216/2008

text: , issue Acceptable Means of Compliance for the application of

text: Regulation (EC) No 216/2008

text: and its Implementing Rules. (2) Acceptable Means of Compliance are non-binding standards adopted by the Agency which illustrate the means to establish compliance with

text: Regulation (EC) No 216/2008

text: and its Implementing Rules. (3) With ED Decision 2013/025/R of 11 September 2013, the Executive Director adopted Acceptable Means of Compliance on ‘Recommended practice for TBO extension’, which amended Annex I ‘Acceptable Means of Compliance to Part M’ of ED Decision No 2003/19/RM . (4) Some Member States have encountered difficulties implementing ED Decision 2013/025/R, which has led to the preventable grounding of several aircraft and, consequently, a negative impact on general aviation. (5) The objective of ED Decision 2013/025/R was to assist competent authorities and stakeholders in taking the proper technical and timely

text: ED Decision 2013/034/R

text: decisions, which will not be met unless there is a clear understanding by all of its purpose. (6) Feedback received from competent authorities and stakeholders after the publication of ED Decision 2013/025/R has shown that: (a) there is a need to further evaluate which are the current policies applied by Member States in order to allow TBO extensions; and (b) there is a need to further review the technical content of its Annex, including, but not limited to, which aircraft categories and operations are covered by the Decision and which organisations are entitled to extend the Time Between Overhaul (TBO). (7) The intended objectives of the ED Decision 2013/025/R will not be met unless the issues described above are addressed. (8) The present ED Decision is, therefore, exceptionally adopted without consulting interested parties pursuant to

text: Article 52(1)

text: (c) of

text: Regulation (EC) No 216/2008

text: and Articles 5(3), 6 and 7 of the Agency’s Rulemaking Procedure , due to the urgency. (9) The Agency will review the content of ED Decision 2013/025/R with the help of competent authorities and stakeholders with a view to reach a better understanding.

text: HAS DECIDED:

text: Article 1

text: AMC2 M.A.302 (d), AMC M.B.301(b) and Appendix XIV to AMC2 M.A.302(d), as introduced by Decision 2013/025/R of the Executive Director of the Agency of 11 September 2013 on ‘Recommended practice for TBO extension’, are hereby withdrawn.

text: Article 2

text: This Decision shall enter into force the day following that of its publication in the Official Publication of the Agency.

text: Done at Cologne, 19 December 2013

text: For the European Aviation Safety Agency The Executive Director

text: Patrick KY


text: Annex II to

text: Commission Regulation (EU) No 1321/2014 of 26 November 2014

text: on the continuing airworthiness of aircraft and aeronautical products, parts and appliances, and on the approval of organisations and personnel involved in these tasks (OJ L 362, 17.12.2014, p. 1). 2 Annex III to

text: Annex to

text: Commission Regulation (EU) No 748/2012 of 3 August 2012

text: laying down implementing rules for the airworthiness and environmental certification of aircraft and related products, parts and appliances, as well as for the certification of design and production organisations and repealing

text: Commission Regulation (EC) No 1702/2003

text: (OJ L 243, 27.9.2003, p.6). 4 Acceptable Means of Compliance and Guidance Material for the airworthiness and environmental certification of aircraft and related products, parts and appliances, as well as for the certification of design and production organisations.

text: record SC/SR number(s): 2. SC/SR title & description:

text: List of parts (description/Part-No/Qty):

text: Operational limitations/affected aircraft manuals. Copies of these manuals are provided to the aircraft owner:

text: Documents used for the development and embodiment of this SC/SR:

text: * Copies of the documents marked with an asterisk are handed to the aircraft owner. 7. Instructions for continuing airworthiness. Copies of these manuals are provided to the aircraft owner:

text: Other information:

text: 9a. □ This SC complies with the criteria established in 21A.90B(a) and with the relevant paragraphs of CS-STAN.

text: 9b. □ This SR complies with the criteria established in 21A.431B(a) and with the relevant paragraphs of CS-STAN.

text: Identification data and signature of the person responsible for 10. Date of SC/SR embodiment: the embodiment of the SC/SR:

text: Signature of the aircraft owner. This signature attests that all relevant documentation is handed over from the issuer of this form to the aircraft owner, and, therefore, the latter becomes aware of any impact or limitations on operations or additional continuing airworthiness requirements which may apply to the aircraft due to the embodiment of the change/repair.

text: Form 123 Issue 00 Notes: Original remains with the legal or natural person responsible for the embodiment of the SC/SR. The aircraft owner should retain a copy of this form. The aircraft owner should be provided with copies of the documents referenced in boxes 5 and 7 and those in box 6 marked with an asterisk ‘*’. The ‘relevant paragraphs’ in boxes 9a and 9b refer to the applicable paragraphs of ‘Subpart A – General’ of CS-STAN and those of the SC/SR quoted in box 2. For box 12, when the aircraft owner has signed a contract i.a.w. M.A.201 (e) (i), it is possible that the Continuing Airworthiness Management Organisation (CAMO) representative signs box 12 and provides all relevant information to the owner before next flight.

text: Completion instructions: Use English or the official language of the State of registry to fill in the form. 1. Identify the SC/SR with a unique number and reference this number in the aircraft logbook. 2. Specify the applicable EASA CS-STAN chapter including revision (e.g. CS-SCxxxy or CS-SRxxxy) & title. Provide also a short description. 3. Identify the aircraft (a/c) registration, serial number and type. 4. List the parts' numbers and description for the parts installed. Refer to an auxiliary document if necessary. 5. Identify affected aircraft manuals. 6. Refer to the documentation developed to support the SC/SR and its embodiment, including design data required by the CS-STAN: design definition, documents recording the showing of compliance with the Certification Specifications or any test result, etc. The documents' references should quote their revision/issue. 7. Identify instructions for continuing airworthiness that need to be considered for the aircraft maintenance programme review. 8. To be used as deemed necessary by the installer. 9a., 9b., 10. and 12. Self-explanatory. 11. Give full name details and certificate reference (of the natural or legal person) used for issuing the aircraft release to service.

identifier: AMC to Part M — Amendment 12

beslut: ED Decision 2015/016/R

title: AMC to Part M — Amendment 12

text: Annex I to Decision 2003/19/RM is amended as follows: The text of the amendment is arranged to show deleted text, new or amended text as shown below: (a) deleted text is marked with strikethrough; (b) new or amended text is highlighted in grey; (c) an ellipsis (…) indicates that the remaining text is unchanged in front of or following the reflected amendment.

text: 1. A new AMC M.A.801 is introduced in Annex I to Decision 2003/19/RM: AMC M.A.801 Aircraft certificate of release to service after embodiment of a Standard Change or a Standard Repair (SC/SR)

text: 1. Release to service and eligible persons Only natural or legal persons entitled to release to service an aircraft after maintenance in accordance with Part-M or Part-145 are considered as an eligible installer responsible for the embodiment of a SC/SR when in compliance with applicable requirements. — For aircraft where there is no Part-66 licence applicable, the release to service of an aircraft after embodiment of a SC/SR is only possible by holders of an appropriate certifying staff qualification valid in a Member State (national qualification), with the following conditions:  If the holder signs the release to service on behalf of an Approved Maintenance Organisation (AMO), this is valid for aircraft registered in any Member State.  If the holder signs the release to service as an independent certifying staff (not on behalf of an AMO), this is only valid for aircraft registered in the Member State responsible for such certifying staff qualification. Depending on its nature, for certain SCs/SRs, the Certification Specification CS-STAN might restrict the eligibility for the issuance of the release to service to certain persons. Since the design of the SC/SR does not require specific approval, the natural or legal person releasing the aircraft to service after the embodiment of the change or repair takes the responsibility that the applicable Certification Specifications within CS-STAN are fulfilled while being in compliance with Part-M and/or Part-145 and not in conflict with TC holders’ data. This includes responsibility in respect of an adequate design, the selection/manufacturing of suitable parts and their identification, documenting the change or repair, generation or amendment of aircraft manuals and instructions as needed, embodiment of the change/repair, releasing the aircraft to service and record-keeping.

text: 2. Parts and appliances to be installed as part of a SC/SR The design of the parts and appliances to be used in a SC/SR is considered a part of the change/repair, and, therefore, there is no need of a specific design approval. However, it is possible that for a particular SC, these Certification Specifications specifically require the use of parts and appliances that meet a technical standard. In this case, when the parts and appliances require to be authorised as an ETSO article, other articles recognised as equivalent by means of an international safety agreement or grandfathered in accordance with

text: Regulation (EU) No 748/2012

text: are equally acceptable. Normally, a SC/SR shall not contain specifically designed parts that should be produced by a production organisation approved in accordance with Part-21 (POA). However, in the case that the change or repair would contain such a part, it should be produced by an approved Production Organisation (POA), and delivered with a Form 1. An arrangement in accordance with 21.A.122 (b) is not applicable. Eligibility for installation of parts and appliances belonging to a SC/SR is subject to compliance with the Part-21 and Part-M and Part-145 related provisions, and the situation varies depending on the aircraft in/on which the SC/SR is to be embodied, and who the installer is. The need for an EASA Form 1 is addressed in Part-21 and Part-M, while less restrictive rules may, for instance, apply for ELA1 and ELA2 aircraft parts (e.g. 21.A.307) and sailplanes parts (e.g. AMC 21A.303 of the ‘AMC and GM to Part-21’ ). Furthermore, Part-M Subpart F and Part-145 contain provisions (i.e. M.A.603(c) and 145.A.42(c)) allowing maintenance organisations to fabricate certain parts to be installed in/on the aircraft as part of their maintenance activities.

text: 3. Parts and appliances identification The parts modified or installed during the embodiment of the SC/SR need to be permanently marked in accordance with Part-21 Subpart Q.

text: 4. Documenting the SC/SR and declaring compliance with the Certification Specifications In accordance with Part-M or Part-145 (e.g. AMC M.A.801(f) and 145.A.50(b)), the legal or natural person responsible for the embodiment of a change or a repair should compile details of the work accomplished. In the case of SCs/SRs, this includes, as necessary, based on its complexity, an engineering file containing drawings, a list of the parts and appliances used for the change or repair, supporting analysis and the results of tests performed or any other evidence suitable to show that the design fulfils the applicable Certification Specifications within CS-STAN together with a statement of compliance and amendments to aircraft manuals, to instructions for continuing airworthiness and to other documents such as aircraft parts list, wiring diagrams, etc., as deemed necessary. The EASA Form 123 is prepared for the purpose of documenting the preparation and embodiment of the SC/SR. The aircraft logbook should contain an entry referring to EASA Form 123; both EASA Form 123 and the release to service required after the embodiment of the SC/SR should be signed by the same person. Form 123 and all the records listed on it should follow elementary principles of controlled documentation, e.g. contain reference number of documents, issue dates, revision numbers, name of persons preparing/releasing the document, etc.

text: 5. Record-keeping The legal or natural person responsible (see paragraph 1. above) for the embodiment of the change/repair should keep the records generated with the SC/SR as required by Part-M or Part-145 and CS-STAN. In addition, M.A.305 requires that the aircraft owner (or CAMO (Continuing Airworthiness Management Organisation), if a contract i.a.w. M.A.201 (e) exists) keeps the status of the changes/repairs embodied in/on the aircraft in order to control the aircraft configuration and manage its continuing airworthiness. With regard to SCs/SRs, the information provided to the owner or CAMO may be listed in Form 123 and should include, as required, a copy of any modified aircraft manual and/or instructions for continuing airworthiness. All this information should normally be consulted when the aircraft undergoes an airworthiness review, and, therefore, a clear system to record the embodiment of SCs/SRs, which is also easily traceable, would be of help during subsequent aircraft inspections.

text: 6. Instructions for continuing airworthiness As stipulated in M.A.302, the aircraft owner or CAMO needs to assess if the changes in the instructions for continuing airworthiness of the aircraft require to amend the aircraft maintenance programme and to obtain its approval.

text: 7. Embodiment of more than one SC The embodiment of two or more related SCs described in Subpart B of CS-STAN is permitted as a single change (the use of one Form 123 only) as long as adequate references to and records of all SCs embodied are captured. Restrictions and limitations of the two (or more) SCs would apply. It is permitted to issue a single release to service containing adequate traceability of all the SCs embodied.

text: 8. Acceptable form to be used to record the embodiment of SCs/SRs EASA Form 123 — Standard Change/Standard Repair (SC/SR) embodiment record