TCDS TA4CH

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TA4CH Revision 17 DIAMOND DA20-A1 DA20-C1 August 30, 2021 TYPE CERTIFICATE DATA SHEET NO. TA4CH This data sheet, which is part of Type Certificate No. TA4CH, 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: Diamond Aircraft Industries Inc. 1560 Crumlin Sideroad London, Ontario Canada N5V 1S2 I - Model DA20-A1 (Utility Category) Approved December 9, 1994 Engine Rotax 912 A3 or 912 F3 or 912 S3 Fuel AVGAS 100LL See Aircraft Flight Manual for other approved fuel types. Oil API System "SF" or "SG" multi grade (See Aircraft Flight Manual recommendations). Do not use aviation grade lubricants Engine Limits (912 A3 or 912 F3) Maximum Takeoff Power Maximum Continuous Power HP 80.0 78.0 Engine R.P.M. 5800 5500 Propeller R.P.M. 2550 2420 (912 S3) Maximum Takeoff Power Maximum Continuous Power 99.0 93.0 5800 5500 2385 2260 Propeller and Propeller Limits Hoffmann HO-V352F/170FQ or HO-V352F/C70FQ Reduced Propeller speed, step-down ratio: 1:2.2727 (compared to engine speed). Diameter 66.9 in (+0, -.39 in), 170 cm (+0, -10 m) No. of Blades: Two Pitch: 10o - 35o (75% station) Airspeed Limits Vne Never Exceed Speed 161 KCAS Vno Maximum Structural Cruising Speed 116 KCAS VA Maneuvering Speed 104 KCAS Maximum Flap Extended Speed 81 KCAS Vfe C.G. Range +9.84 in to +15.35 in (+250 mm to +390 mm) Empty Weight C.G. Range None Levelling Means Wedge 52:1000, 19.69 in (500 mm) in front of rudder fin. Maximum Weight 912 A3 or 912 F3 Engine: 1609 lbs (730 kg) 912 S3 Engine: 1653 lbs (750 kg) Minimum Crew One (1) Pilot. No. of Seats Two at +5.6 in (+143 mm) Maximum Baggage 44 lbs (20 kg) at +32.44 in (+824 mm). Only permissible with baggage harness Fuel Capacity 20.9 gal (79 liters) at +32.44 in (+824 mm) Usable: 20.3 gal (77 liters) (See Note 1) Oil Capacity 3.6 qt (3.4 liters) maximum, 3.2 qt (3 liters) minimum at -41.7 in (-1060 mm) Page No. 1 2 3 4 Rev. No. 16 16 16 15 TA4 CH 2 of 4 Coolant Capacity 2.6 qt (2.5 liters) maximum, 2.5 qt. (2.4 liters) minimum at -41.7 in (-1060 mm) Control Surface Movements AILERON 16o ± 1o UP 13o ± 1o DOWN ELEVATOR 16o ± 1o UP 14o ± 1o DOWN FLAP 15o ± 1o (T/O) 40.5o ± 1.5o (LDG) RUDDER 30o ± 1o left 30o ± 1o right Manufacturer's Serial Nos. Those aircraft shown to comply with Canadian DOT Aircraft Type Certificate A-191. The Canadian Department of Transport Certificate of Airworthiness for Export endorsed as noted under "Import Requirements" must be submitted for each individual aircraft for which application for certification is made (See Note 5 and 6). II - Model DA20-C1 (Utility Category) Approved April 6, 1998 Engine Continental Motors IO-240-B Fuel AVGAS 100LL Engine Limits Maximum Continuous Power 2800 r.p.m. (125 hp) Propeller and Propeller Limits 1. Hoffmann HO-14HM-175-157 Diameter 68.9 in (175 cm) No. of Blades: Two 2. Sensenich W69EK7-63 or W69EK7-63G or W69EK7-63GM Diameter 69 in (175.2 cm) No. of Blades: Two 3. Sensenich W69EK-63 (up to Aircraft S/N C0149) Diameter 69 in (175.2 cm) No. of Blades: Two Airspeed Limits Vne Never Exceed Speed 158.7 KCAS Vno Maximum Structural Cruising Speed 117.7 KCAS VA Maneuvering Speed 106.9 KCAS Maximum Flap Extended Speed Vfe Take-off position (15o) 100 KCAS Landing position (45o) 81 KCAS C.G. Range +8.07 in to +12.16 in (+205 mm to +309 mm) at 1764 lbs (800 kg) +7.95 in to +12.48 in (+202 mm to +317 mm) at 1653 lbs (750 kg) or less Straight line variation between points given Empty Weight C.G. Range None Levelling Means Wedge 55084:1000, 78.7 in (2000 mm) behind canopy. Maximum Weight Ramp Weight 1770 lbs (803 kg) Take-off 1764 lbs (800 kg) Landing 1764 lbs (800 kg) Minimum Crew One (1) Pilot. No. of Seats Two at +5.6 in (+143 mm) Maximum Baggage 44 lbs (20 kg) at +32.44 in (+824 mm). Only permissible with baggage harness 3 of 4 TA4 CH Fuel Capacity S/N C0001 thru C0013: 25 gal (95 liters) at +32.44 in (+824 mm) Usable: 21.3 gal (80.5 liters) ( See Note 1) S/N C0014 and subsequent, and S/N C0001 thru C0013 if Service Bulletin DA C1-28-01 has been incorporated: 24.5 gal (93 liters) at +32.44 in (+824 mm) Usable: 24 gal (91 liters) (See Note 1) All S/N if 20 U.S. Gal. Fuel tank (Dwg. No. 22-2813-00-00) is installed: 20.5 gal (78 liters) at +32.44 in (+824 mm) Usable: 20 gal (76 liters) (See Note 1) Oil Capacity 6 qt (5.68 liters) maximum, 4 qt (3.79 liters) minimum at -39.6 in (-1005 mm) Control Surface Movements AILERON 15.5o ± 1o UP 13.5o ± 1o DOWN ELEVATOR 25o ± 1o UP 15o ± 1o DOWN FLAP 45o ± 1o (LDG) RUDDER 27o ± 1o left 27o ± 1o right Manufacturer's Serial Nos. Those aircraft shown to comply with Canadian DOT Aircraft Type Certificate A-191. The Canadian Department of Transport Certificate of Airworthiness for Export endorsed as noted under "Import Requirements" must be submitted for each individual aircraft for which application for certification is made. Data Pertinent to All Models Reference Datum The reference datum (RD) for the center of gravity (CG) is tangent to the leading edge of the wing at the root rib. Import Requirements A U.S. Airworthiness Certificate may be issued on the basis of the Canadian Certificate of Airworthiness for Export signed by a representative of Transport Canada Civil Aviation (TCCA), containing the following statement: "The aircraft covered by this certificate has been examined and/or tested and found to be in conformity with data forming the basis for DOT Type Certificate No. A-191, (FAA Type Certificate No. TA4CH) and to be in a condition for safe operation". Certification Basis FAR 21.29 and FAR 23 effective February 1, 1965, as amended by 23-1 through 23-42. JAR-VLA effective April 26, 1990, through Amendment VLA/92/1 effective January 1, 1992, used as a safety equivalence to FAR 23, as provided by AC 23-11. FAR 36 dated December 1, 1969, as amended by current amendment as of the date of type Certification. Model DA20-A1: Findings of Equivalent Level of Safety: FAR 23.903(a)(1) (ref. Finding ACE-95-1, dated December 2, 1994). Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. I n addition, the following equipment is also required: Transport Canada Approved Flight Manual DA20 Katana (DA20-A1 with Rotax 912 A3 or F3 engine) Document No. DA202 dated July 28, 1994 or later approved revision. Transport Canada Approved Flight Manual DA20/100 Katana (DA20-A1 with Rotax 912 S3 engine) Document No. DA202-100 Issue 1, dated June 19, 2000 or later approved revision. Transport Canada Approved Flight Manual DA20-C1 (DA20-C1) Document No. DA202-C1 Issue 1 dated Decemebr 19, 1997 or later approved revision. Fire Extinguisher. TA4 CH 4 of 4 Service Information Service Bulletins, structural repair manuals, vendor manuals, overhaul and maintenance manuals, and aircraft flight manuals which contain a statement that the document is Transport Canada approved or Transport Canada approved through the Manufacturers Design Approval Representative are accepted by the FAA and are considered FAA approved. (These approvals pertain to the design data only). NOTE 1 A current weight and balance report including list of equipment included in certificated empty weight must be providedwith each aircraft at the time of original certification. The certificated empty weight and corresponding center of gravity location must include for Model DA20 -A1, full oil and unusable fuel of 3.31 lbs (1.5 kg) at +32.44 in.; for Model DA20-C1, S/N C0001 thru C0013, full oil and unusable fuel of 22.2 lbs (10 kg) at +32.44 in.; and for Model DA20-C1, S/N C0014 and subsequent and S/N C0001 thru C0013 if Service Bulletin DA C1-28-01 has been incorporated, full oil and unusable fuel of 2.76 lbs (1.3 kg) at +32.44 in NOTE 2 All placards specified in the Transport Canada Approved Airplane Flight Manual, and those listed in Chapter 11 of the Maintenance Manual, must be displayed in the airplane in the appropriate locations. NOTE 3 Components which are life limited are listed in Maintenance Manual, Document No. DA201, Chapter 04 for Model DA20-A1 and Document No. DA201-C1, Chapter 04 for Model DA20-C1. Revisions to the Airworthiness Limitations must be approved by Transport Canada on behalf of the FAA. NOTE 4 External colors are limited to those specified in Maintenance Manual, Document No. DA201, Chapter 04 for Model DA20-A1 and Document No. DA201-C1, Chapter 04 for Model DA20-C1. NOTE 5 DA20-A1 S/N 10002 through 10092 were produced with the Rotax 912 A3 engine. S/N 10093 and subsequent were produced with the Rotax 912 F3 engine. The finding of equivalent safety to FAR 23.903(a)(1) for the Rotax 912 A3 engine is applicable only to those serial numbers originally produced with the Rotax 912 A3 engine. NOTE 6 DA20-A1 S/N 10002 through 10092, originally equipped with the Rotax 912 A3 engine, may be retrofitted with the Rotax 912 F3 engine in accordance with Diamond Aircraft Service Bulletin DA20-73-01. DA20-A1 S/N 10002 through 10331, originally equipped with the Rotax 912 A3 or 912 F3 engine, may be retrofitted with the Rotax 912 S3 engine, by Diamond Aircraft Industries or its agents, in accordance with Diamond Aircraft Drawing No. 20-0100-00-00. -- END --