Data Sheet № TL 0023
Antonov An-2 TP · Maintenance Manual
Overview
This document is a maintenance data sheet for the Antonov An-2 TP aircraft, detailing its airworthiness certification, operational limitations, and technical specifications. It includes information on the aircraft's engines, propellers, fuel, oils, and performance characteristics.
- The Antonov An-2 TP is designed for passenger and cargo-passenger carriage.
- It is equipped with two turbo-propeller engines TVD-10B.
- The maximum take-off mass is 6500 kg.
- The aircraft can carry up to 17 passengers.
- It has a maximum altitude of 4200 m with oxygen equipment.
- The aircraft operates within a temperature range of -50 °C to +40 °C.
- The maximum permissible operating speed is 350 km/h at altitudes up to 4200 m.
- The total amount of oil in the oil system is about 27 liters.
Document
Source
Originally published by regulations.gov. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type ·
- Maintenance Manual
- Year ·
- 2019
- File size ·
- 850 KB
- Publisher ·
- regulations.gov
- Language ·
- en
Specifications & performance
Extracted from this document.
Specifications
- Height m ·
- 4.9
- Length m ·
- 13.1
- Wingspan m ·
- 22.06
- Wing area m2 ·
- 39.72
- Max payload kg ·
- 1750
- Max fuel mass kg ·
- 1520
Performance
- Max speed kmh ·
- 350
- Min speed kmh ·
- 115
- Max altitude m ·
- 4200
Weight & balance
- Max payload kg ·
- 1750
- Max landing mass kg ·
- 6500
- Max takeoff mass kg ·
- 6500
- Cg range back percent ·
- 33
- Cg range front percent ·
- 22
What is the Data Sheet № TL 0023?
The Data Sheet № TL 0023 is a maintenance manual for the Antonov An-2 TP, dated 2019.
Where does the Data Sheet № TL 0023 come from?
This copy of the Data Sheet № TL 0023 was originally published by regulations.gov and is hosted on Sprinkle as a free, searchable reference copy.
What year was the Data Sheet № TL 0023 published?
The Data Sheet № TL 0023 — the Antonov An-2 TP maintenance manual on file — is dated 2019.
Most owners only have the POH. Here's the essential set for the Antonov An-2 TP.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins on file
- Type Certificate (TCDS)
In this document
Aircraft Purpose
The Antonov An-2 TP is intended for passenger and cargo-passenger carriage.
Engine Specifications
The aircraft is powered by two turbo-propeller engines TVD-10B, each with a takeoff power of 705 kW.
Fuel Requirements
The aircraft can be refueled with various types of fuel, including T-1 and TC-1, and allows mixing of different brands.
Weight and Balance
The maximum take-off mass is 6500 kg, with a maximum commercial load of 1750 kg.
Performance Limits
The maximum permissible operating speed is 350 km/h, with specific limits for take-off and landing configurations.
Operating Conditions
The aircraft can operate in temperatures ranging from -50 °C to +40 °C, with restrictions on flying in icing conditions.
Safety notes
- Flying in icing conditions at temperatures below -20 °C is prohibited.
- Flights in the form of hail are prohibited.
- The maximum altitude of the aerodrome above sea level is 2600 m.
- Do not apply certain CAAS-2 requirements as specified in the document.
Full document text
Attachment 14 Data Sheet № TL 0023 Edition 1 March 01, 2002 STATE AVIATION ADMINISTRATION of UKRAINE TYPE CERTIFICATE DATA SHEET № TL 0004 Issue 8 March 22, 2019 Edition 2 Dated February 07, 2013 according to which the product for which the Type Certificate was issued meets the requirements for airworthiness in force in Ukraine at the date of issue of the Certificate No. TL 0023 Aircraft An-28 This Data Sheet is an inalienable part of Type Certificate No. TL 0023 and sets out the conditions and restrictions under which a product issued with a Type Certificate meets the airworthiness requirements in force in Ukraine at the date of issue of the Type Certificate No. TL 0023. 1.Aircraft Certificate Holder ANTONOV Company, 1, Tupolev str., Kyiv 03062, Ukraine 2.Category Transport 3.Aircraft purpose Passenger and cargo-passenger carriage 4.Aircraft manufacturer PXl Mielec PNR (ref. No 1AJ001-01 ... 1AJ001-05, 1AJ002-01 ... 1AJ002-10, 1AJ003-01 ... 1AJ003-15, 1AJ004-01 ... 1AJ004-20, 1AJ005-01 ... 1AJ005-25, 1AJ006-01 ... 1AJ006-25, 1AJ007-01 ... 1AJ007-25, 1AJ008-01 ... 1AJ008-25, 1AJ009-01 ... 1AJ009-20, 1AJ0010-01 ... 1AJ0010-04.) See Note 3 List of valid pages: No 1 2 3 4 5 6 7 8 Edition 2 1 1 1 1 1 1 2 4a. Certification basis On the basis of "Decisions on the Applicability of Changes and Additions to the Civil Aviation Airworthiness Standards (CAAS-2) and the Distribution on the Aircraft AN-28 of Part of the Civil Aviation Airworthiness Standards (CAAS-3) in Replacement of the Related CAAS-2 Requirements", approved by the Chairman of the Ministry of Internal Affairs of the MVK NLP USSR dated February 8,1985, and "Supplement No. 1" to it dated October 29, 1985 on Aircraft AN-28 is subject to the following requirements: - airworthiness standards-2 as amended from 1976 to July 1, 1984 (1И1-2OИ2); - "temporary additions to airworthiness standards-2 for light aircraft (G ≤ 10000 kg)"; -5.4.6. CAAS-3 instead of 5.4.6. CAAS-2; -5.5.1. CAAS-3 instead of 5.5.1. CAAS-2; -5.5.5. CAAS-3 instead of 5.5.5. CAAS-2; -5.6. CAAS-3 instead of 5.6. CAAS-2; -5.7. CAAS-3 instead of 5.7. CAAS-2; [TRANSLATION] Data Sheet № TL 0023 Edition 1 March 01, 2002 -5.8. CAAS-3 instead of 5.8. CAAS-2; -5.12. CAAS-3 instead of 5.12. CAAS-2; 7.5.3.1.3. CAAS-3 instead of 7.5.3.1.4. CAAS-2; -8.3.3.1. CAAS-3 instead of 8.3.2.1. CAAS-2. Do not apply to An-28: Requirements "Supplements to Clause 7.5.2.1.6. of CAAS-2, introduced by amendment 6И1-7, on the presence of hatches on the hoods of the engine for supplying or extinguishing agent in engine nacelle on the ground "; - requirements of item 5.11.12.4. CAAS-2, as well as "Notes to it, on the presence on board of megaphones and means of two-way communication between the cabin of the crew and passengers". 5. Sustainer engines: Two turbo-propeller twin rotor engines TVD-10B (Developer: OJSC "Omsk Motor Engineering Design Bureau", Omsk, Russia. Producer: "Omsk Motor Engineering Association named after P.I. Baranov", Omsk, Russia.) with turbocharger and free turbine screw. Main data: Engine mass …………………………… 230 kg+2% Takeoff power mode (H = O, B = O, MCA) ...... 705 kW .................................................. ......................... (960 hp) Engine performance as a percentage of installed resource: - on take-off mode .............................. not more than 6% - at nominal mode ............................... no more than 40% with the air extraction on the anti-ice system (ПОС) wings and feathers ............................. not more than 25%. Air extraction from engines is allowed: -for heating cabs-modes from "ground idle (ЗМГ)" to the nominal in the whole range outside air temperatures and altitudes flight. - on take-off at outside temperatures air 5 ° C and below at altitudes up to 2000 m; - for ПОС engines - in all modes; - for ПОС wings and plumage: a) during normal operation of engines and when flying with one engine running, in modes from «flight-idle (ПМГ)» to rated inclusive; b) at the exit to the second circle with one working engine, in accordance with the instructions of the AFM (item 11, section 8.1., page 7); c) when leaving the icing area with one engine running, in accordance with the instructions of the AFM (Section I, Section 8.1., Page 7). Engine start system - electric. Starting is by means of the starter. Time of continuous work, waves: - take-off mode ................................ no more than 6 - nominal mode ................................ no more than 60 Engine operation - in accordance with the procedures outlined in the AN-28 Flight Manual. Engine performance limitations. in the Operating and Maintenance Manual of the TVD-10B engine. 6. Air screws Two AV-24AN, three-blade, pulling, variable pitch, weathervane, reversing, development of Company Data Sheet № TL 0023 Edition 1 March 01, 2002 “Aerosyla”, Stupino, Russian Federation, production of Hydroelectric Power Plant, Pavlova-on-Otsi, Russian Federation. Diameter .......................................................... ...... 2.8 m Angles of installation of blades in the control section (R = 1000 mm): - start angle (<ро) .......................... -1.5 ° ............. -3.5 °; - angle of intermediate emphasis (<p n y.) ................ 8 °; - angle of weather vane (<p fl) ................................. 83 °; - angle of maximum reverse (<p roar) …………... – 16 ° Time of installation of blades in weather vane position: -in flight ................................................ no more than 7s - on earth: a) on the engine running no more than 10 s b) on idle engine not more than 20 sec. Time of removal of the blades from the weather vane position: -in flight .............................................. not more than 15s -on the earth ......................................... no more than 25s. The limitations and main features are specified in the An- 28 Flight Manual (Section 8.1). The engine and the air screw have protective systems:
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weather-proofing, centrifugal screw-driver, limiting the temperature of the exhaust gases. The operation of engines and propellers shall be carried out in accordance with the procedures and restrictions given in the AN-28 Aircraft Flight Manual (Section 8. I) 7. Fuel: Refuel the aircraft with the following brands: -T-1 and TC-1 (GOST 10227-62); -PT (GOST 16564-71). The fuel of these brands can be mixed in any proportions. It is allowed to use fuel of foreign brands: -PSM-2 spec. PN721c 96026 (PNR); -PL-6 spec. PND25-005-76 (CRSD); -TS-1 GUEST 10227-62 (GDR); -T-1 spec. STAS 5639-73 (CPP); Jet-1 spec. STAS 5075-71 (CPP); -TFC-1 spec. D-2-3 (Cuba); -JP-1 miL-G-5616C (USA); -DeRD-2494 AYTUR (UK); -AIR 3405/s Urade F-34 (France). At outdoor air temperature of 5 ° C and below, the liquid "I" (GOST 8313-76) is added to the fuel in the amount of 0,1 ... 0,15% by volume. Liquids may be used instead of fluid "I" "THF" (GOST 17477-75), "THF-M" (TU 6-10-1457-74), "I-M" (TU 6-10-1458-74). It is allowed to use foreign liquids (0,1% of refueled fuel): -AL-31 miL-1-27686 (USA); -AL-31 DERD-2451 (United Kingdom). The maximum amount of fuel to be refilled (at y = 0,775 g/cm3): - first of all ------------------- 2x240 kg = 480 kg (2x310 l = 620 l) -the second turn -------------- 2x520 kg = 040 kg Data Sheet № TL 0023 Edition 1 March 01, 2002 (2x670 l = 1340 l) Total: 1520 kg (1960 l) 8. Oils The oil system uses a mixture of SM-4,5 oils, which consists of 75% by volume of MK-8 or MK-8P oil, or MS-8P and 25% of MK-22 or MC-20 oil. It is allowed to use a mixture of foreign oils: 75% Aeroshell Turbine Oil (MiL-L-6081 Grade 1010) and 25% Aeroshell Oil 100 (MiL-L-60820 Crade 1100 DERD-2472 V/O). The total amount of oil in the oil system is about 27 liters. The maximum operational filling of the oil tank 16 + 0.5 l. The minimum filling of the oil tank is 14.5 liters. Oil consumption is not more than 0.5 l/h. 9. Instrument speed limit (km/h, IS): The maximum permissible operating speed of flight at an altitude from 0 to 4200 m: 350 km/h Estimated speed limit: 405 km/h (380 km/h IN) Maximum allowed flight speeds: take-off configuration (15 ° latitude) 200 km / h landing configuration (40 ° latitude) 185 km / h rejected interceptors 190 km / h Minimum flight speeds: -flight weight 4500 kg, flap angle 0 ° 135 km / h - flight weight 4500 kg, flap angle 40 ° 115 km / h - flight weight 6500 kg, flap angle 0 ° 170 to m / year - flight weight 6500 kg, flap angle 40 ° 140 km / h 10. Aircraft mass characteristics (kg): Maximum steering mass 6530 Maximum take-off mass 6500 Maximum landing mass 6500 Maximum commercial load 1750 Maximum fuel mass (p = 0,775 g/cm3) 1520 11. Range of centering (% CAX): border-front .......................... 22 border-back…………………33 12. Aircraft geometric data: The length of the aircraft …………………………..13,1 Empty aircraft height .............................................. 4,9 m at a mass of 6500 kg .................................. 4,54 m The length of the fuselage ................................... 12,68 m Maximum height fuselage .............................. 2, 14 m Fuselage maximum width .......................................1,9 m Track Chassis ...................................................... 3,405 m Wingspan ............................................................ 22,06 m Wing area .......................................................... 39,72 m2 CAX ................................................................ ... 1,886 m Wing extension ...................................................... 12,2 Rejection of flaps: a) takeoff ...................................................... ........ 15 ° b) landing .............................................................. 40 ° Area horizontal plumage .................................... 8,85 m2 Data Sheet № TL 0023 Edition 1 March 01, 2002 Area horizontal plumage..........................................10 m2 13. Minimum flight crew: 2 persons (Pilot-in-command, co-pilot) 14. Maximum number of passengers: a) by the number of seats secured by the seat belts 17 b) with the duration of the flight over water more than 30 min from the shore: -in case of installation of four PSN-6AK rafts 14 - in case of installation of rafts SP-12 10 15. Maximum altitude: -for aircrafts without oxygen equipment …….......3000 m -for aircrafts with oxygen equipment .................. 4200 m 16. General operating conditions restrictions: 1. Ground temperature: minus 50 ° C to plus 40 ° C 2. Flights in the form of hail are prohibited. C. Flying in icing conditions at temperatures below minus 20 ° C is prohibited. 4. The maximum altitude of the aerodrome above sea level is 2600 m. 17. Resources and service life: The resources and service life of aircrafts, propulsion engines, air propellers are specified in the forms in accordance with the specifications for delivery. Resources and service life for engine and propeller instances may be increased subject to condition screws of current bulletins and according to the procedure approved by Ukraviatrans. Notes: 1. The accordance of An-28 aircraft with a maximum take-off and landing mass of 6500 kg was confirmed to the standards of Chapters 6 and 10 of Annex 16 to the Convention on International Civil Aviation, dated 2.1988. Noise levels and their 90% confidence intervals (in dBA) areas designated in accordance with the requirements of Annex 16 for this type of civil aircraft shall be: Aircraft Engines Air screws Measurement checkpoints During take-off (on the runway axis) During the flight An-28 TVD-10B AV-27AN 80,8 +- 0,8 74,6 +- 0,5 Noise Limits (dBA) 88,0 80,0 2. Other limitations are listed in the operating documentation: 1. "Flight Documentation Manual. 28.00.0000.000.000RL". 2. "Technical Operation Manual. 28.00.0000.000.000RE". 3. "Maintenance Regulations. 28.00.0000.000.000RO". 4. "Instructions for loading and alignment. 28.00.0000.000.000IC". 3. The serial number of the aircraft sometimes uses the Russian letters "АЙ" instead of the Latin letters "AJ". THE END Head of type certification of aviation equipment S.F.Gaidenko