TCDS No.EASA.A.576 P2010
TECNAM P2010 TDI · Checklist
Overview
This document is the Type Certificate Data Sheet (TCDS) for the Tecnam P2010 TDI aircraft, detailing its certification, technical characteristics, and operational limitations. It includes information on the aircraft's design, performance specifications, and maintenance instructions.
- The Tecnam P2010 is a single-engine, high-wing aircraft with four seats.
- It features fixed tricycle landing gear and is constructed from composite, aluminum, and steel.
- The aircraft has a maximum take-off weight of 1160 kg (2557 lb).
- It is certified under EASA CS-23 Normal category.
- The maximum operating altitude is 12000 ft.
- The aircraft can operate under day/night VFR and IFR conditions.
- It has a maximum flaps extended speed (VFE) of 92 KCAS.
- The aircraft is equipped with a Lycoming IO-360-M1A engine.
Document
Source
Originally published by tecnamair.com. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type ·
- Checklist
- Year ·
- 2015
- File size ·
- 66 KB
- Publisher ·
- tecnamair.com
- Language ·
- en
Specifications & performance
Extracted from this document.
Specifications
- Span m ·
- 10.30
- Height m ·
- 2.64
- Length m ·
- 7.97
- Wing area m2 ·
- 13.9
- Oil capacity l ·
- 7.57
- Fuel capacity l ·
- 240
Performance
- Va kcas ·
- 119
- Vfe kcas ·
- 92
- Vne kcas ·
- 164
- Vno kcas ·
- 130
- Max operating altitude (ft) ·
- 12000
V-speeds
- VA_KCAS ·
- 119
- VFE_KCAS ·
- 92
- VNE_KCAS ·
- 164
- VNO_KCAS ·
- 130
Weight & balance
- Cg aft limit m ·
- 0.440
- Max landing kg ·
- 1160
- Max takeoff kg ·
- 1160
- Cg forward limit m ·
- 0.262
What is the TCDS No.EASA.A.576 P2010?
The TCDS No.EASA.A.576 P2010 is a checklist for the TECNAM P2010 TDI, dated 2015.
Where does the TCDS No.EASA.A.576 P2010 come from?
This copy of the TCDS No.EASA.A.576 P2010 was originally published by tecnamair.com and is hosted on Sprinkle as a free, searchable reference copy.
What year was the TCDS No.EASA.A.576 P2010 published?
The TCDS No.EASA.A.576 P2010 — the TECNAM P2010 TDI checklist on file — is dated 2015.
Most owners only have the POH. Here's the essential set for the TECNAM P2010 TDI.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins on file
- Type Certificate (TCDS)
More TECNAM P2010 TDImanuals & documents
In this document
General
The Tecnam P2010 is a single-engine aircraft with a certification basis under EASA CS-23. It is manufactured by Costruzioni Aeronautiche Tecnam S.R.L.
Technical Characteristics and Operational Limitations
The P2010 features a high-wing design, fixed tricycle landing gear, and can be equipped with either fixed or variable pitch propellers. It has specific load factors and control surface deflections.
Engine
The aircraft is powered by a Lycoming IO-360-M1A engine, with specified take-off and continuous power ratings.
Dimensions
The aircraft has a wingspan of 10.30 m, a length of 7.97 m, and a height of 2.64 m.
Weights and Balance
The maximum take-off and landing weights are both 1160 kg. The center of gravity range is specified with forward and aft limits.
Operating and Service Instructions
The document references the P2010 Aircraft Flight Manual and Maintenance Manual for detailed operating instructions and airworthiness limitations.
Safety notes
- Flight into expected or actual icing conditions is prohibited.
- Refer to the Aircraft Flight Manual for detailed operational limitations.
- All temperatures above 80°F require specific oil grades.
- The aircraft must not exceed the specified VNE of 164 KCAS.
Full document text
TCDS N Issue 03 EASA Fo Issue 01 Issue 0 Issue 0 Issue 0 o.EASA.A.5 3, 15 Decemb orm NR 90 C C 01: 26 Sept 02: 05 May 03: 15 Dec 76 ber 2015 CS-23 Euro Costruzio t 2014 y 2015 2015 opean TYPE- DA EA oni Aero Vi 8 P2010 n Aviat EASA CERTIF ATA SHE ASA.A.5 P2010 onautich a Tasso, 4 0127 Napo ITALIA tion Sa A FICATE EET 576 he TECN 478 oli afety A NAM S.r. Pag Agenc .l. ge 1 of 10 cy TCDS No.EASA.A.576 P2010 Page 2 of 10 Issue 03, 15 December 2015 CONTENT SECTION A: P2010 A.I. General A.II. Certification Basis A.III. Technical Characteristics and Operational Limitations A.IV. Operating and Service Instructions A.V. Notes ADMINISTRATIVE SECTION I. Acronyms II. Type Certificate Holder Record III. Change Record TCDS No.EASA.A.576 P2010 Page 3 of 10 Issue 03, 15 December 2015 SECTION A: P2010 A.I. General 1. Data Sheet No.: EASA.A.576 2. a) Type: P2010 3. Airworthiness Category: CS-23 Normal category 4. Type Certificate Holder: Costruzioni Aeronautiche Tecnam S.R.L. Via Tasso, 478 80127 Napoli ITALIA 5. Manufacturer: Costruzioni Aeronautiche Tecnam S.R.L. Via Tasso, 478 80127 Napoli ITALIA 6. Certification Application Date: 15 September 2010 7. (Reserved) National Certifying Authority N/A 8. (Reserved) National Authority Type Certificate Date: N/A A.II. EASA Certification Basis 1. Reference Date for determining the applicable requirements: 15 September 2010 2. Airworthiness Requirements: EASA CS-23 amdt.2 dated 28 September 2010 3. Special Conditions: CRI B-52 (SC-B23.div-01 Human Factors – Integrated Avionic System); CRI F-101 (SC-F23-1309-02 Protection from the Effect of HIRF); CRI F-54 (SC-F23-1309-03 Protection from the Effects of Lightning Strike, Indirect Effects); CRI F-58 (SC-F23.1353-02 Lithium Battery Installations) CRI F-102 (ESP and USP) (see note 3) 3. Exemptions: None 4. Deviations: None 5. Equivalent Safety Findings: None 6. Requirements elected to comply: None TCDS No.EASA.A.576 P2010 Page 4 of 10 Issue 03, 15 December 2015 7. Environmental Standards: CS-36 amdt. 2 dated 31 August 2009, subpart C with reference to ICAO Annex 16, Volume 1, Chapter 10, amdt. 9 dated 30 July 2009. 8. (Reserved) Additional National Requirements: N/A 9. (Reserved) N/A A.III. Technical Characteristics and Operational Limitations 1. Type Design Definition: Document no. 2010/010 “Type Design Definition” 2. Description: 2.1 Basic: Single-engine, fixed pitch propeller, four seats, high wing aeroplane equipped with fixed tricycle landing gear, featuring composite, aluminium and steel construction. 2.2 Optional (see note 1) Single-engine, variable pitch propeller, four seats, high wing aeroplane equipped with fixed tricycle landing gear, featuring composite, aluminium and steel construction. 3. Equipment: Equipment list, AFM, doc. No. 2010/100, Section 6 4. Dimensions: Span 10.30 m (33.79 ft) Length 7.97 m (26.15 ft) Height 2.64 m (8.66 ft) Wing Area 13.9 m 2 (149.6 ft 2 ) 5. Engine: 5.1.1 Model: No.1 Lycoming Engines: IO-360-M1A 5.1.2 Type Certificate: EASA Type Certificate No. EASA.IM.E.032 5.1.3 Limitations 5.1.3.1 Basic: Take-Off Power 134 kW (180HP) at 2700 RPM Max continuous power 134 kW (180HP) at 2700 RPM Other engine’s limitations are listed in doc. No. 2010/100 “P2010 Aircraft Flight Manual”, Section 2 5.1.3.2 Optional (see note 1) Take-Off Power 134 kW (180HP) at 2700 RPM Max continuous power 129 kW (173HP) at 2600 RPM Other engine’s limitations are listed in doc. No. 2010/100 “P2010 Aircraft Flight Manual”, Section 2 6. Load factors: Flap UP Flap DOWN Positive +3.8 g +2.0 g Negative -1.52 g 0.0 g TCDS No.EASA.A.576 P2010 Page 5 of 10 Issue 03, 15 December 2015 7. Propeller: 7.1 Basic: 7.1.1 Model: MT Propeller: MT 188 R 145-4G 7.1.2 Type Certificate: EASA Type Certificate No. EASA.P.006 7.1.3 Number of blades: 2 7.1.4 Diameter: 1.880 m (74 in) – No reduction is permitted 7.1.5 Sense of Rotation: Clockwise (pilot’s view) 7.2 Optional: (see note 1) 7.2.1 Model: MT Propeller: MTV-15-B/193-52 7.2.2 Type Certificate: EASA Type Certificate No. EASA.P.098 7.2.3 Number of blades: 2 7.2.4 Diameter: 1.930 m (76 in) – No reduction is permitted 7.1.5 Sense of Rotation: Clockwise (pilot’s view) 8.1 Fuel: AVGAS Grade 91/96 or 100 LL (ASTM D910) MOGAS EN 228:2008 (E) (see note 2) Refer to doc. No. 2010/100 “P2010 Aircraft flight Manual” for further details. 8.2 Oil: Average Ambient Temperature All Temperatures Above 80°F Above 60°F 30°F to 90°F 0°F to 70°F Below 10°F MIL-L-6082B or SAEJ1966 Spec. Mineral Grades ---- SAE60 SAE50 SAE40 SAE30 SAE20 MIL-L-22851 or SAEJ1899 Spec. Ashless Dispersant Grades SAE15W50 or SAE20W-50 SAE60 SAE40 or SAE50 SAE40 SAE40, SAE30, SAE20W40 SAE30 or SAE20W30 Refer to Lycoming (L)LIO-360-M1A “Operation and Installation Manual” for list of alternative recommended commercial brands and types. TCDS No.EASA.A.576 P2010 Page 6 of 10 Issue 03, 15 December 2015 9. Fluid capacities: 9.1 Fuel: 2 Tanks: Total: Usable: 120 litres each (31.7 US gallons) 240 litres (63.4 US gallons) 231 litres (61 US gallons) 9.2 Oil: Total: Minimum: 7.57 litres (8 US qts) 3.78 litres (4 US qts) 10. Air Speeds: Never exceed speed VNE 164 KCAS Maximum Structural Cruising Speed VNO 130 KCAS Design Manoeuvring speed VA 119 KCAS Operating Manoeuvring speed V O 119 KCAS Maximum flaps extended speed V FE 92 KCAS 11. Maximum Operating Altitude: 12000 ft 12. Allweather Operations Capability: Day/Night-VFR, IFR ; Refer to KOEL contained in the AFM, doc. No. 2010/100, Section 2. Flight into expected or actual icing conditions is prohibited 13. Maximum Weights: Max Take-Off: Max Landing: 1160 kg (2557 lb) 1160 kg (2557 lb) 14. Centre of Gravity Range: Forward Limit: 0.262 m (19% MAC) behind datum Aft Limit: 0.440 m (32% MAC) behind datum Mean Aerodynamic Chord is 1.378 m (54.2 in) 15. Datum: Vertical plane tangent to wing leading edge 16. Control surface deflections: Stabilator: 17°±2° to pitch up / 6°±2° to pitch down
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Stabilator Trim Tab: 15 ±1° downward / 3°±1° upward Aileron: 19°±2° upward / 14°±2° downward Rudder: 25°±2° left / 25°±2° right Rudder Trim Tab: 20°±2° left / 20° ±2° right Flaps: 0° Fully Retracted / 40°±1° Fully Extended 17. Levelling Means: seat track supporting beams (see procedure in doc. No. 2010/100 “P2010 Aircraft Flight Manual”, Section 6) TCDS No.EASA.A.576 P2010 Page 7 of 10 Issue 03, 15 December 2015 18. Minimum Flight Crew: 1 19. Maximum Passenger Seating Capacity: 3 20. Baggage/Cargo Compartments: Max Allowable Load: 40 kg (88 lb) Location:1.56 m (61.41 in) from datum 21. Wheels and Tyres: Nose Wheel Tyre Size: Main Wheel Tyre Size 5.00-5, Type III 6.00-6, Type III For approved Types and rating see AMM, doc No. 2010/101 22. Serial Numbers Eligible: 002 to subsequent TCDS No.EASA.A.576 P2010 Page 8 of 10 Issue 03, 15 December 2015 A.IV. Operating and Service Instructions 1. Flight Manual: Doc. No. 2010/100 “P2010 Aircraft Flight Manual” Last issue. 2. Technical Manual: Doc. No. 2010/101 “P2010 Aircraft Maintenance Manual” Last issue; Airworthiness Limitations are reported in ATA chapter 4. 3. Spare Parts Catalogue: Doc. No. 2010/102 “P2010 Illustrated Parts Catalogue” Last issue. 4. Instruments and aggregates: Doc. No. 2010/101 “P2010 Aircraft Maintenance Manual” Last issue. TCDS No.EASA.A.576 P2010 Page 9 of 10 Issue 03, 15 December 2015 A.V. Notes: 1) When MOD 2010/002 (EASA approval 10052750) is installed 2) When MOD 2010/032 (EASA approval 10055692) is installed 3) When MOD 2010/001 (EASA approval 10055187) is installed TCDS No.EASA.A.576 P2010 Page 10 of 10 Issue 03, 15 December 2015 ADMINISTRATIVE SECTION I. Acronyms AFM – Aircraft Flight Manual AMM – Aircraft Maintenance Manual ASTM – American Society for Testing and Materials CRI – Certification Review Item CS – Certification Specification EASA – European Aviation Safety Agency ICAO – International Civil Aviation Organization IPC – Illustrated Part Catalogue KCAS – Knots Calibrated Air Speed KOEL – Kind of Operations Equipment List MAC – Mean Aerodynamic Chord MLW – Maximum Landing Weight MTOW – Maximum Take-Off Weight MZFW – Maximum Zero Fuel Weight TC – Type Certificate TCDS – Type Certificate Data Sheet VFR – Visual Flight Rules IFR – Instrumental Flight Rules II. Type Certificate Holder Record TC Holder Period Costruzioni Aeronautiche TECNAM S.r.l. Via Tasso, 478 80127 Napoli ITALIA Effective III. Change Record Issue Date Changes TC Issue No. & Date Issue 01 26 Sept 2014 Initial Issue 26 Sept 2014 Issue 02 05 May 2015 MT Variable Pitch Propeller Added Issue 03 15 Dec 2015 Update to include changes: MOD2010/001 “GFC 700 autopilot” (EASA approval 10055187), MOD2010/003 “Alternative avionics configuration” (EASA approval 10053996), MOD2010/032 Automobile fuel (EASA approval 10055692)