TCDS A16EU

Page No. 1 2 3 4 5 6 7 8 9 10 11 Rev. No. 15 8 8 12 8 15 13 8 8 8 15 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A16EU Revision 15 General Atomics AeroTec Systems Do 28 D Do 28 D-1 Dornier 228-100 Dornier 228-101 Dornier 228-200 Dornier 228-201 Dornier 228-202 Dornier 228-212 January 29, 2025 TYPE CERTIFICATE DATA SHEET NO. A16EU This data sheet which is part of Type Certificate No. A16EU prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder: General Atomics AeroTec Systems GmbH Galileostraße 396 82131 Gauting Germany Type Certificate Holder Record: DORNIER LUFTFAHRT GmbH D-8031 Wessling Federal Republic of Germany, transferred TC A16EU to Fairchild Dornier GmbH on June 1, 2000. Fairchild Dornier GmbH D-82230 Wessling, Germany, transferred TC A16EU to RUAG Aerospace Services GmbH on July 27, 2003. RUAG Aerospace Services GmbH transferred TC A16EU to General Atomics AeroTec Systems GmbH on September 28, 2021. I. Model Do 28D (Normal Category), approved July 31, 1967 Model Do 28D-1 (Normal Category), approved April 19, 1968 Engine 2 Lycoming IGSO-540 A1E Bendix Injector RS10-FBI or Lycoming P/N 78417 Fuel 100/130 minimum grade aviation gasoline Engine limits For takeoff, 5 minutes, 380 HP, 3400 rpm, 47 inch HG at S.L. For continuous operation, 360 HP, 3200 rpm, 45 inch HG at S.L. Propellers and propeller 2 Hartzell HC-B3W30-2B/W10151-8R limits Diameter: 93 in., no cutoff permitted Pitch settings at 30 in. station: Low 16° 50' ± 15' Feathered 85° ± 30' Page 2 of 11 A16EU Airspeed limits (CAS) Do 28 D Do 28 D-1 Knots m.p.h. Knots m.p.h. VNE (never exceed) 180 207 180 207 VNO (maximum structural cruising) 143 165 143 165 Maximum speed for cooling flaps operation 143 165 143 165 VP (maneuvering) 115 133 117 113 VFE (flaps extended) 102 118 104 120 VMC (minimum control) 58 67 60 69 C.G. Range (+126.0) to (+141.0) at 6060 lbs. (+131.5) to (+141.0) at 8050 lbs. All airplanes except S/N 4001, 4002, and 4003. (+126.0) to (+141.0) at 5950 lbs, (+131.5) to (141.0) at 7720 lbs. - S/N 4001, 4002 and 4003. Straight line variation between points given. I. Model Do 28D, Do 28D-1 Empty weight C.G. range None Datum A vertical line 118 inch forward of wing slat leading edge Leveling means A water level on cabin floor rails Maximum weights 8050 lb. (See Note 1.) Minimum crew 1 pilot Number of seats Maximum 15 Maximum baggage 110 lbs. in fuselage nose hold (+35.5 in.) and 175 lbs. in the rear baggage hold (+275 in.) Fuel capacity 232 U.S. gallons usable (+ 131.5 in.) Oil capacity 3.3 U.S. gallons usable per engine (+ 105.5 in.) Control surface movements Wing flaps Down 20° Up 52° Ailerons Up 25° Down 25° Elevator (no stabilizer) Up 22° Down 17° Rudder Right 27.5° Left 27.5° II. Model Dornier 228-100 (Normal Category), approved May 11, 1984 Model Dornier 228-101 (Normal Category), approved February 28, 1985 Model Dornier 228-200 (Normal Category), approved May 11, 1984 Model Dornier 228-201 (Normal Category), approved February 28, 1985 Model Dornier 228-202 (Normal Category), approved September 10, 1986 Engines 2 Garrett AiResearch TPE 331-5-252D Fuel Fuel grades: See Pilot’s Operating Handbooks Dornier 228-100/-101/-200/-201/-202 Section 2 Limitations. Engine limits For takeoff and continuous operation, 715 SHP (533 KW). Propellers and Propeller Limits For Dornier 228 Models - 100/-101/-200/-201 2 Hartzell HC-B4TN-5ML/LT 10574 or “ “ 10574 K or “ “ 10574 B (length of deicing mat 17 inches) or “ “ 10574 B (length of deicing mat 21 inches) Page 3 of 11 A16EU or “ “ 10574 A or “ “ 10574 AK or “ “ 10574 AB (length of deicing mat 17 inches) or “ “ 10574 AB (length of deicing mat 21 inches) or “ “ 10574 AS or “ “ 10574 ASK or “ “ 10574 ASB (length of deicing mat 17 inches) or “ “ 10574 ASB (length of deicing mat 21 inches) or “ “ 10574 FS or “ “ 10574 FSK or “ “ 10574 FSB (length of deicing mat 17 inches) or “ “ 10574 FSB (length of deicing mat 21 inches) II. Model Dornier 228-100, 228-101, 228-200, 228-201, 228-202 (cont’d) Propellers and Propeller Limits For Dornier 228, Model -202 2 Hartzell HC-B4TN-5ML/LT 10574 AS or “ “ 10574 ASK or “ “ 10574 ASB (length of deicing mat 17 inches) or “ “ 10574 ASB (length of deicing mat 21 inches) or “ “ 10574 FS or “ “ 10574 FSK or “ “ 10574 FSB (length of deicing mat 17 inches) or “ “ 10574 FSB (length of deicing mat 21 inches) The following limitations apply: a) For all type of propellers: 1. Diameter limits are 106” maximum, 105” minimum. (No further reduction permitted.) 2. All blades of the propeller of the individual airplanes must be of one type only. 3. Avoid sustained ground operation below 1050 (67%) RPM. b) For all type of propellers except those with suffix “F”: Regulations according to the FAA Airworthiness Directive No. 87-15-05, R1, Amendment 39-5658, have to be considered. c) For Dornier 228 Model -202 equipped with propeller with suffix “A”: Avoid “power on” stalls above 60 percent torque. d) Blade angle position with power lever in FI at 30 in. station: 1. For the Dornier Models 228-100/-101/-200/-201 is: 13° ± 20' 2. For the Dornier Models 228-202 and 228-201/-202 equipped with keel (K) is: 15° ± 20'. Refer also to Notes 1.b3 and 1.b4 respectively. Airspeed Limits (CAS) 228-100 Knots 228-101 Knots 228-200 Knots 228-201 Knots 228-201(K) Knots 228-202 Knots 228-202(K) Knots VMO (max. operating) 199 199 199 199 197 199 197 VA (maneuvering) 141 144 140 140 143 147 146 VFE (flaps extended) Pos. 1 (5°) 149 149 149 149 149 149 149 Pos. 2 (20°) 128 128 128 128 129 128 129 Pos. DN (30° 128 128 128 x 128 x 129 x 128 x 129 x VLO (gear operating) 160 160 160 160 158 160 158 VLE (gear extended) 160 160 160 160 158 160 158 VMC (minimum control) 81 81 81 81 74 80 74 Airspeed Limits (CAS) x = with optionally installed trim coupling system (SCN C01 only) (cont’d) C.G. Range Refer to Pilot’s Operating Handbook applicable to the individual airplane. Page 4 of 11 A16EU Empty Weight C.G. Range None Datum A vertical line 290.71 inches forward of the main jacking point under the fuselage. Leveling Means A water level in cabin floor rails. 228-201 228-202 228-100 228-101 228-200 and-201 (K) and-202 (K) Maximum Weight 12,500 lbs. 13,184 lbs. 12,500 lbs. 13,184 lbs. 13,669 lbs. I. Model Dornier 228-100, 228-101, 228-200, 228-201, 228-202 Minimum Crew 1 pilot 1 pilot 1 pilot 1 pilot 1 pilot Maximum Operating Altitude 15,000 feet 15,000 feet 15,000 feet 15,000 feet 15,000 feet The maximum operating altitude is 25,000 ft. if SCN No. DO8 (maximum allowable airspeed indicator: manufacturer: Intercontinental Dynamics Corp.) is installed. Maximum Number of Passenger Seats 15 15 19 19 19 Maximum Baggage In Fuselage Nose Hold Station (inch) + 130.7 in. + 130.7 in. + 100.7 in. + 100.7 in. + 100.7 in. Weight (lbs) 200 lbs. 200 lbs. 200 lbs. 200 lbs. 200 lbs. 265 lbsx 265 lbs.x 265 lbs.x 265 lbs.x 265 lbs.x x = if SCN 2152 is installed and in Rear Baggage Hold Station (inch) + 487.4 in. + 487.4 in. + 503.9 in. + 503.9 in. + 503.9 in. Weight (lbs.) 331 lbs. 331 lbs. 463 lbs. 463 lbs. 463 lbs. Fuel Capacity 630.3 U.S. gallons usable (+ 312.4 in.) Oil Tank Capacity 6.25, U.S. quarts per engine (+ 267.9 in.) Control surface movements See Maintenance Manual DORNIER 228. III. Model Dornier 228-212 (Commuter Category), approved June 26, 1990 Engines 2 Garrett AiResearch TPE 331-5A-252D. Fuel Fuel grades: See Pilot’s Operating Handbook Dornier 228-212, Section 2 Engine limits For takeoff and continuous operation 776 SHP (579 KW). Propeller and propeller limits 2 Hartzell HC-B4TN-5ML/LT 10574 FS or 2 Hartzell HC-B4TN-5ML/LT 10574 FSB (length of deicer mat 21 inches) The following limitations apply: 1. All blades of the propellers of the individual airplane must be of one type only. 2. Diameter limits are 106° maximum, 105° minimum. (No further reduction permitted.) 3. Avoid sustained ground operation below 1050 (67%) RPM. 4. Blade angle position with power lever in FI at 30 in. Station is 15° ± 20’. Airspeed Limits (CAS) S/N 8176 thru 8190 S/N 8191 and up Knots Knots VMO (max. operating) 197 220 VA (maneuvering) 149 149 VFE (flaps extended) Page 5 of 11 A16EU Pos. 1 ( 5°) 149 158 Pos. 2 (20°) 129 129 Pos. DN (30°) 129x 129 VLO (gear operating) 158 158 VLE (gear extended) 158 158 VMC (minimum control) 75 75 x = with optionally installed trim coupling system (SCN C01) only. C.G. Range Refer to Pilot’s Operating Handbook applicable to the individual airplane. Empty Weight C.G. range None Datum A vertical line 290.71 inches forward of the main jacking point under the fuselage. Leveling Means A water level on cabin floor rails. Maximum Weights S/N 8176 thru 8190 S/N 8191 and up for takeoff 14,110 lbs. 14,110 lbs. Zero fuel up to 13,668 lbs TOW 12,324 lbs. 13,095 lbs. up to 14,110 lbs TOW 11,905 lbs. 13,095 lbs. Minimum Crew 1 pilot Maximum operating altitude 15,000 feet The maximum operating altitude is 25,000 ft. if SCN DO8 (maximum allowable airspeed indicator: manufacturer: Intercontinental Dynamics Corp.) is installed. Maximum number of passenger seats 19 Maximum Baggage in Fuselage Nose Hold Station + 100.7 in. 265 lbs. and in Rear Baggage Hold Station + 503.9 in. Weight 463 lbs. Fuel Capacity 630.3 U.S. gallons usable (+312.4 in.) Oil Capacity 6.25 U.S. quarts per engine (+267.9 in.) Control surface movements See Airplane Manual Dornier 228. DATA APPLICABLE TO ALL MODELS Serial numbers eligible See Import Requirements. (See Note 6) Certification basis a) For Do 28D and Do 28D-1 FAR 23, including Amendments 23-1 through 23-3. Date of application for type certificate: June 13, 1966 b) For Dornier 228-100 and Dornier 228-200, under the provisions of FAR 21.29 FAR 23, effective February 1, 1965, including amendments 23-1 thru 23-23. SFAR 41C Section (1a) which incorporates by reference FAR 135 Appendix A in effect on September 26, 1978. SFAR 27, effective February 1, 1974, including Amendments 27-1 through 27-4 (Fuel Venting). See Note 4. FAR 36, effective December 1, 1969, including Amendments 36-1 through 36-12. Date of application for Amended Type Certificate: December 3, 1979. Page 6 of 11 A16EU c) For Dornier 228-101, Dornier 228-201 and Dornier 228-202 under the provisions FAR 21.29. FAR 23, effective 1965, including amendment 23-1 through 23-23. SFAR 41C effective September 13, 1982. SFAR 27, effective February 1, 1974, including Amendments 27-1 through 27-4 (fuel venting), see Note 4. FAR 36, effective December 1, 1969, including Amendments 36-1 through 36-12. Date of application for Amended Type Certificate: August 22, 1983. d) For Dornier 228-212, under the provisions of FAR 21.29. FAR 23, effective February 1, 1965, including Amendments 23-1 thru 23-34. SFAR 27, effective February 1, 1974, including Amendments 27-1 thru 27-5 (Fuel Venting), see Note 4. FAR 36, effective December 1, 1969, including Amendments 36-1 thru 36-16. Date of application for Amended Type Certificate: February 15, 1989. In addition, for the Dornier 228-212NG/228-212NXT version (created by the incorporation of General Atomics AeroTec Systems Major Change CN-228-247 and FAA supplemental type certificates (STCs) ST329CH-D (new engine) and SA03052NY (new propeller): 23.1457 and 23.1459 at amendment 23-35; 23.1322 and 23.1331 at amendment 23-43; 23.1525 at amendment 23-45; 23.867, 23.1303, 23.1309, 23.1311, 23.1321, 23.1323, 23.1329, 23.1351, 23.1353, 23.1359, 23.1361, 23.1365, 23.1431 at amendment 23-49; 23.1325, 23.1543, 23.1545 and 23.1555 at amendment 23-50; 23.1308 at amendment 57; 23.1306 at amendment 61, (The applicable certification bases for STCs ST329CH-D and SA03052NY are listed on their respective certificates.) The Dornier 228-212NG/228-212NXT version approval included approval of STOL Operation, General Atomics AeroTec Systems Change Notice CN-228-273. The Luftfahrt Bundesamt originally type certificated this aircraft under its type certificate Numbers 2031, 2031a, 2031b and 2031c. The FAA validated this product under U.S. Type Certificate Number A16EU. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of Germany. The EASA type certificate for models Do 28D and Do28D-1 is EASA.A.360. The EASA type certificate for models Dornier 228-100, 228-101, 228-200, 228-201, 228- 202 and 228-212 is EASA.A.359. Import Requirements The FAA can issue a U.S. airworthiness certificate based on an NAA Export Certificate of Airworthiness (Export C of A) signed by a representative of the Luftfahrt Bundesamt on behalf of the European Community. The Export C of A should contain the following statement: ‘The aircraft covered by this certificate has been examined, tested, and found to comply with U.S. airworthiness regulations 14 CFR Part 23 approved under U.S. Type Certificate No. A16EU and to be in a condition for safe operation.’ (See Note 5 and Note 6). Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used aircraft based on the scope of the agreement, to identify any required statements by the exporting authority on the export certificate of airworthiness (or equivalent document), and for procedures for coordinating exceptions to conformity statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certification of Aircraft, for requirements for issuance of an airworthiness certificate for imported aircraft. Page 7 of 11 A16EU Service Information Each of the documents listed below must state that it is approved by the European Aviation Safety Agency (EASA) or – for approvals made before September 28, 2003 – by the Luftfahrt Bundesamt. • Service bulletins, • Structural repair manuals, • Vendor manuals, • Aircraft flight manuals, and • Overhaul and maintenance manuals. The FAA accepts such documents and considers them FAA-approved unless one of the following conditions exists: • The documents change the limitations, performance, or procedures of the FAA approved manuals; or •The documents make an acoustical or emissions changes to this product’s U.S. type certificate as defined in 14 CFR § 21.93. The FAA uses the post type validation procedures to approve these documents. The FAA may delegate on case-by-case to EASA to approve on behalf of the FAA for the U.S. type certificate. If this is the case it will be noted on the document. Equipment/ Basic required equipment as prescribed in the applicable airworthiness regulations (see Airplane Flight Manual “Certification Basis”) must be installed in the aircraft for certification. a) For Models Do 28D and Do 28D-1. The approved equipment is marked with an “X” in the LBA-approved equipment list dated 14 August 1968 in the approved AFM. The airplane Flight Manual approved at the original issue for U.S. Type Certification is dated November 6, 1967. b) For Models Dornier Do 228-100 and Dornier 228-200 The installed equipment is marked with an “X” in the Equipment List in Section 6 in the LBA-approved AFM. The Airplane Flight Manuals (Edition 1) for the Dornier Model 228-100 (7XXX) or 228-200 (8XXX) approved at the original issue for U.S. type certification are dated 15 November 1983, LBA approved April 4, 1984. NOTE: “XXX” denotes aircraft serial numbers. AFM consists of basic POH + Supplement 74. c) For Models Dornier 228-101 The installed equipment is marked with an “X” in the Equipment List in Section 6 of the LBA-approved “Edition 1” AFM. c1) The Airplane Flight Manuals (Edition 1) for the Dornier Model 228-101 (7XXX) with ICAO Annex 8 are LBA-approved October 15, 1984. AFM consists of basic POH + Supplement 42, 74, 74A. c2) The Airplane Flight Manuals (Edition 1) for the Dornier Model 228-101 (7XXX) without ICAO Annex 8 are LBA-approved December 11, 1984. AFM consists of basic POH + Supplements 42, 74, 74B. d) For Models Dornier 228-201 and Dornier 228-202 The installed equipment is marked with an “X” in the “Airplane Master Equipment List” in Section 6, part 2 of the LBA-approved AFM. d1) The Airplane Flight Manual (Edition 2) for the Dornier Model 228-201 (8XXX) Page 8 of 11 A16EU with and without ICAO Annex 8 are LBA-approved February 8, 1989. d2) The Airplane Flight Manuals (Edition 2) for the Dornier Model 228-201 (8XXX) equipped with keel (K) with and without ICAO Annex 8 are LBA-approved December 14, 1988. d3) The Airplane Flight Manuals (Edition 2) for the Dornier Model 228-202 (8XXX) with and without ICAO Annex 8 are LBA-approved February 8, 1989. d4) The Airplane Flight Manuals (Edition 2) for the Dornier Model 228-202 (8XXX) equipped with keel (K) with and without ICAO Annex 8 are LBA-approved December 14, 1988. NOTE (1): “XXX” denotes aircraft serial numbers. 228-201 with ICAO and 228-201 without ICAO are physically identical except for flight manual requirements. 228-202 with ICAO and 228-202 without ICAO are physically identical except for flight manual requirements. NOTE (2): For model -201 and landing weights of 13,007 lbs. for main landing gear S/N’s 1036 onwards the main landing gear must comply with part numbers A-510 000 C000 and A-520 000 C000 or higher change index. e) For Model Dornier 228-212 The installed equipment is marked with an “X” in the “Airplane Master Equipment List” in Section 6, Part 2, of the LBA approved AFM. e1) The Airplane Flight Manuals (Edition 1) for the Dornier Model 228-212 (8XXX) commuter category valid for aircraft serial numbers S/N 8155 and S/N 8176 through 8190 are LBA-approved July 21, 1989. e2) The Airplane Flight Manuals (Edition 1) for the Dornier Model 228-212 (8XXX) Commuter Category valid for aircraft serial numbers S/N 8191 and up are LBA-approved November 17, 1989. NOTE: “XXX” denotes aircraft serial numbers. There may be approved Airplane Flight Manuals (AFM) amendments of supplements issued after the original type certificate, that are required to operate the airplane when additional optional equipment is installed and/or when certain modifications are embodied. The airplane owner/operator should ensure that the correct LBA approved Airplane Flight Manual (AFM) amendments or supplements are incorporated in the approved AFM, for the approved model. NOTES Page 9 of 11 A16EU Note 1. Weight and Balance Current weight and balance data together with a list of equipment included in the certificated empty weight, and loading instructions, must be provided for each aircraft at the time of original certification. a) For Do 28D and Do 28D-1 a1) The certificated empty weight and corresponding center of gravity locations must include unusable fuel of 8 U.S. gallons (+ 131.5 in.) and undrainable system oil of 2.15 U.S. gallons (+ 105.5 in.). a2) Serial numbers 4001, 4002 and 4003 eligible at a maximum weight of 7720 pounds. a3) Do 28-1 airplanes of the following serial numbers are eligible at a maximum takeoff weight of 8160 pounds when equipped with Wing Serial Numbers shown in brackets: 4006(06), 4018(18), 4023(23), 4024(24), 4025(35), 4026(26), 4027(27), 4028(28), 4030(30), 4031(34), 4033(33), 4034(31), 4035(25), 4040(40), 4041(41), 4042(42), 4043(43), 4044(44), 4045(45), 4046(46), 4047(55), 4048(49), 4049(51), 4051(52), 4052(53), 4053(54), 4054(56), 4055(57), 4056(58), 4057(59), 4058(60), 4059(47) Landing weight remains unchanged. a4) Do 28 D-1 airplanes of the following serial numbers are eligible to a maximum takeoff weight of 8160 pounds when equipped with wing serial numbers shown in brackets and Service Bulletin No SB 2 044-1101 has been complied with: 4022(22), 4021(21) Landing weight remains unchanged. b) For Do 228-100/-101, Dornier 228-200/-201/-202, and Dornier 228-212. b1) The certificated empty weight and corresponding center of gravity locations must include unusable fuel of 14.4 U.S. gallons (+ 312.4 in.) and full system oil of 5.9 gallons (+ 267.9 in.) per airplane. b2) Dornier 228-100/-200 airplanes can be changed to Models -101/-201 if they are modified according to, and comply with the following Change Notice: CN-228- 043-USA, “Increase of Maximum Takeoff Weight to 13,184 lbs.” Also see Airplane Master Equipment List/Airplane Flight Manual and Note 3. b3) Dornier 228-200 and -201 airplanes can be changed to Model -202 if they are modified according to, and comply with the following Change Notice: CN-228- 164-USA, “Increase of Maximum Takeoff Weight to 13,669 lbs.” Also see Airplane Master Equipment List/Airplane Flight Manual and Note 3. b4) Dornier 228-201 and -202 models can be modified and equipped with keels (k) if after modification they comply with the following LBA Change Notice: A-228- 174 “Retrofit measures to improve flight performance and rear center-of-gravity range extended from 35% to 40%.” Also see Airplane Master Equipment List/Airplane Flight Manual and Note 3. Note 2. Operation a) Placards All placards listed in the approved AFM must be installed in the appropriate locations. Each airplane has to be supplied with a placard that specifies the kind of operations to which the operation of the individual airplane is limited by its installed equipment. The following placard must be displayed on the instrument panel in full view of the pilot: a1) For Do 28 D/D-1 “THIS AIRPLANE MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF Page 10 of 11 A16EU PLACARDS MARKINGS AND MANUAL. NO ACROBATIC MANEUVERS, INLCUDING SPINS, ARE APPROVED.” a2) For Dornier 228-100/-101/-200/-201/-202 “THE MARKINGS AND PLACARDS INSTALLED IN THIS AIRPLANE CONTAIN OPERATING LIMITATION WHICH MUST BE COMPLIED WITH WHEN OPERATING THIS AIRPLANE IN THE NORMAL CATEGORY.” “OTHER OPERATING LIMITATIONS WHICH MUST BE COMPLIED WITH WHEN OPERATING THIS AIRPLANE IN THE NORMAL CATEGORY ARE CONTAINED IN THE PILOT’S OPERATING HANDBOOK AND LBA-APPROVED AIRPLANE FLIGHT MANUAL.” “NO ACROBATIC MANEUVERS, INCLUDING SPINS, APPROVED.” a3) For Dornier 228-212 “THE MARKINGS AND PLACARDS INSTALLED IN THIS AIRPLANE CONTAIN OPERATING LIMITATION WHICH MUST BE COMPLIED WITH WHEN OPERATING THIS AIRPLANE IN THE COMMUTER CATEGORY. “OTHER OPERATING LIMITATIONS WHICH MUST BE COMPLIED WITH WHEN OPERATING THIS AIRPLANE IN THE COMMUTER CATEGORY ARE CONTAINED IN THE PILOT’S OPERATING HANDBOOK AND LBA-APPROVED AIRPLANE FLIGHT MANUAL.” “NO ACROBATIC MANEUVERS, INCLUDING SPINS, APPROVED.” b) Certificate of Airworthiness for Dornier 228-101/-201/-202 If Dornier 228-101/-201/-202 aircraft are to be operated without ICAO Annex 8, the airworthiness certificate shall be endorsed: “This airplane at weights in excess of 5,700 kg does not meet the airworthiness requirements of ICAO, as prescribed by Annex 8 of the Convention of International Civil Aviation.” Also see Item Equipment/Airplane Flight Manual. Note 3. Airworthiness Limitations Chapter 05 of the Dornier 228 Airplane Maintenance Manual, for the models Dornier 228-100/-101 and Dornier 228-200/-201/-202/-212; which includes the Airworthiness Limitation Section 05-05-00, specifies