BRM AERO BRISTELL UL HD HD airplane Aircraft Operating Instructions
Below you will find brief information for airplane BRISTELL UL HD. This aircraft is designed for recreational and cross-country flying and is approved for basic training. It features a fixed tricycle undercarriage and is powered by a UL POWER 350i 118 hp engine. This manual will guide you through the assembly, pre-flight inspection, and normal operating procedures.
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B R M A E R O S. R . O. VÁCLAVA KULÍŠKA 1224, 686 05 UHERSKÉ HRADIŠTĚ, CZECH REPUBLIC phone.: +420 773 984 338 www.brmaero.com Registration: Serial Number: OM-M712 037/2012 This airplane must be operated in compliance with information and limitations contained in herein. This AOI must be available on board of the airplane. Date of Issue: 11/2010 Revision: 1.0 0-1 SECTION 0 0. TECHNICAL INFORMATION 0.1 Record of revisions 0.2 List of effective pages 0.3 Table of contents Date of Issue: 11/2010 Revision: 1.0 0-2 0.1 Record of revisions Revision No. Affected Section Any revision of the present manual (except actual weighing data, cockpit description and list of instruments and avionics) must be recorded in the following table. 1 ALL Affected Pages Date of Issue ALL, Initial 11/2010 Approved by Milan Bristela Date of Issue: 11/2010 Date of approval Date inserted 11/2010 11/2010 Sign. Revision: 1.0 0-3 0.2 List of effective pages Section Page 0 0-1 11/2010 0-2 0-3 1 2 Date of Issue Section Page Date of Issue 3-1 11/2010 11/2010 3-2 11/2010 11/2010 3-3 11/2010 0-4 11/2010 3-4 11/2010 0-5 11/2010 3-5 11/2010 0-6 11/2010 3-6 11/2010 3-7 11/2010 1-1 11/2010 3-8 11/2010 1-2 11/2010 3-9 11/2010 1-3 11/2010 1-4 11/2010 1-5 11/2010 1-6 11/2010 3 2-1 11/2010 4-1 11/2010 2-2 11/2010 4 4-2 11/2010 2-3 11/2010 4-3 11/2010 2-4 11/2010 4-4 11/2010 2-5 11/2010 4-5 11/2010 2-6 11/2010 4-6 11/2010 2-7 11/2010 4-7 11/2010 2-8 11/2010 4-8 11/2010 2-9 11/2010 4-9 11/2010 4-10 11/2010 4-11 11/2010 Date of Issue: 11/2010 Revision: 1.0 0-4 Section Page 5 5-1 11/2010 5-2 6 Date of Issue Section Page Date of Issue 7-1 11/2010 11/2010 7-2 11/2010 5-3 11/2010 7-3 11/2010 5-4 11/2010 7-4 11/2010 5-5 11/2010 7-5 11/2010 5-6 11/2010 7-6 11/2010 5-7 11/2010 7-7 11/2010 7-8 11/2010 7-9 11/2010 8-1 11/2010 7 6-1 11/2010 6-2 11/2010 6-3 11/2010 8-2 11/2010 6-4 11/2010 8-3 11/2010 6-5 11/2010 8-4 11/2010 6-6 11/2010 6-7 11/2010 9-1 11/2010 6-8 11/2010 9-2 11/2010 6-9 11/2010 9-3 11/2010 6-10 11/2010 9-4 11/2010 6-11 11/2010 9-5 11/2010 6-12 11/2010 10-1 11/2010 10-2 11/2010 10-3 11/2010 10-4 11/2010 8 9 10 Date of Issue: 11/2010 Revision: 1.0 0-5 0.3 Table of contents Section TECHNICAL INFORMATION ..................................................... 0 GENERAL INFORMATION ........................................................ 1 OPERATING LIMITATIONS....................................................... 2 EMERGENCY PROCEDURES .................................................. 3 NORMAL PROCEDURES .......................................................... 4 PERFORMANCE ....................................................................... 5 WEIGHT AND BALANCE .......................................................... 6 AIRPLANE AND SYSTEMS DESCRIPTION .............................. 7 AIRPLANE HANDLING,SERVICING AND MAINTENANCE ...... 8 REQUIRED PLACARDS AND MARKINGS ............................... 9 SUPPLEMENTS ........................................................................ 10 Date of Issue: 11/2010 Revision: 1.0 0-6 SECTION 1 1. GENERAL INFORMATION 1.1 Introduction 1.2 Warnings, cautions and notes 1.3 Descriptive data 1.3.1 1.3.2 1.3.3 1.3.4 Aircraft description Powerplant Aircraft dimensions Aircraft layout 1.4 Definitions and abbreviations Date of Issue: 11/2010 Revision: 1.0 1-1 1.1 Introduction BRISTELL UL is an aircraft built in BRM AERO s.r.o., Uherske Hradiste, Czech Republic, based on czech LAA UL 2 Standards, CS-VLA Standards and FAA Light Sport Aircraft (LSA) category according to ASTM Standards F2245, F2279 and F 2295. This Aircraft Operating Instruction has been prepared to provide pilots with information for the safe and efficient operation of BRISTELL UL aircraft. It also contains supplemental data supplied by the Aircraft Flight Training Supplement. 1.2 Warnings, cautions and notes The following definitions apply to warnings, cautions and notes in the Pilot Operating Handbook. WARNING Means that the non-observation of the corresponding procedure leads to an immediate or important degradation of the flight safety i.e. to injury or death of persons. CAUTION Means that the non-observation of the corresponding procedure leads to a minor or possible long term degradation of the flight safety. NOTE Draws attention to any special item not directly related to safety, but which is important or unusual. Date of Issue: 11/2010 Revision: 1.0 1-2 1.3 Descriptive data 1.3.1 Aircraft description BRISTELL UL is airplane intended especially for recreational and crosscountry flying, non-aerobatics operation and basic training. BRISTELL UL is a single-engine, all metal, low-wing monoplane of semimonocoque construction with two side-by-side seats. The airplane is equipped with a fixed tricycle undercarriage with stearable nose wheel. 1.3.2 Powerplant The standard powerplant is composed of UL POWER 350i, 118 Hp 4-cylinder, 4-stroke engine and Whirl Wind ground adjustable two blade propeller. 1.3.3 Aircraft dimensions Wing span............................................ 8,13 m Length .................................................. 6,45 m Height .................................................. 2.28 m Wing area ............................................ 10,5 sq m Wing loading ........................................ 45,06 kg/sq m Cockpit width ....................................... 1,3 m Deflection: Rudder deflections ............................... 30° to each side Elevator deflections ............................. + 30°/- 15° Aileron deflections ............................... + 24°/-13° Flap deflections.................................... 0°, 11°, 21°and 31° Aileron trim deflections ........................ + 15°/- 20° Elevator trim deflections ...................... + 10°/- 25° Date of Issue: 11/2010 Revision: 1.0 1-3 1.3.4 Aircraft layout 8,13 2,6 Date of Issue: 11/2010 Revision: 1.0 1-4 1.4 Definitions and abbreviations ATC Air Traffic Control ASI Airspeed Indicator BEACON anti-collision beacon CAS Calibrated Airspeed COMM communication transmitter EFIS Electronic Flight Instrument System ELT Emergency Locator Transmitter EMS Engine Monitoring System °F temperature in degree of Fahrenheit ft foot / feet ft/min feet per minute GPS Global Positioning System hp power unit IAS Indicated Airspeed IC Intercom IFR Instrument Flight Rules in inch ISA International Standard Atmosphere knot NM per hour lb pound MAC Mean Aerodynamic Chord max. maximum min. minimum or minute mph statute miles per hour NM Nautical Mile Date of Issue: 11/2010 Revision: 1.0 1-5 OFF system is switched off or control element is in off-position ON system is switched on or control element is in on-position OAT Outside Air Temperature POH Pilot Operating Handbook psi pound per square inch - pressure unit rpm revolutions per minute sec. second US gal volume unit VFR Visual Flight Rules VMC Visual Meteorological Conditions VA maneuvering airspeed VFE maximum flap extended speed VNO maximum designed cruising speed VNE never exceed speed VSO stall speed with wing flaps in extended position VS1 stall speed with wing flaps in retracted position VX best angle of climb speed VY best rate of climb speed Date of Issue: 11/2010 Revision: 1.0 1-6 SECTION 2 2. OPERATING LIMITATION 2.1 2.2 2.3 2.4 Introduction Airspeed Airspeed Indicator Markings Powerplant 2.4.1 2.4.2 2.4.3 2.5 2.6 2.7 2.8 2.9 2.10 2.11 2.12 2.13 Engine operating speeds and limits Fuel Oil Powerplant Instrument Markings Miscellaneous Instrument Markings Weight Center of Gravity Approved Maneuvers Maneuvering Load Factors Crew Kinds of Operation Other Limitations Date of Issue: 11/2010 Revision: 1.0 2-1 2.1 Introduction Section 2 includes operating limitations, instrument markings and basic placards necessary for the safe operation of the aircraft, its engine, standard systems and standard equipment. 2.2 Airspeed Airspeed limitations and their operational significance are shown below: Speed KIAS Remarks VNE Never exceed speed 145 Do not exceed this speed in any operation. VNO Max. structural cruising speed 129 Do not exceed this speed except in smooth air, and then only with caution. VA Maneuvering speed 96 Do not make full or abrupt control movement above this speed, because under certain conditions full control movement may overstress the aircraft. VFE Maximum Flap Extended Speed 75 Do not exceed this speed with flaps extended. Date of Issue: 11/2010 Revision: 1.0 2-2 2.3 Airspeed indicator markings Airspeed indicator markings and their color-code significance are shown below: Marking IAS value or range Significance Knots White arc 34-75 Green arc 43-129 Yellow arc 129-145 Red line 145 Flap Operating Range. Normal Operating Range. Maneuvers must be conducted with caution and only in smooth air. Maximum speed for all operations. Date of Issue: 11/2010 Revision: 1.0 2-3 2.4 Powerplant 2.4.1 Engine operating speeds and limits UL POWER 350i Engine Manufacturer: UL POWER, Belgium Engine RPM Power Engine Model: Max Take-off: 118 hp At 3300 rpm Max. Continuous: 118 hp at 3300 rpm Cruising: 72 hp at 2500 rpm Max. Take-off: 3300 rpm Max. Continuoust: 3000 rpm Cruising: 2500 rpm Cylinder head temperature: Minimum: - Maximum: 190° C Optimum: 130 - 160° C Oil temperature ~750 rpm Minimum: 50° C Maximum: 130° C Optimum: 80 - 110° C Oil pressure: Idling: Minimum: 0,8 bar - below 800 rpm Maximum: 7 bar - cold engine starting Optimum: 2 - 5 bar - above 1500 rpm * * Max. CHT temperature depend on the type of coolant used in engine. - see Section 2.4.4 and Section 10 Supplement No.2 Date of Issue: 11/2010 Revision: 1.0 2-4 2.4.2 Fuel This fuel can be used: (refer to engine Operator’s Manual) - min. RON 95, EN 228 Premium, EN 228 Premium plus, AVGAS100LL - Fuel according to FAA - Standard Spec. for Automotive SparkIgnition Engine Fuel, ASTM D 4814 or AVGAS 100 LL - Fuel according to DOT - CAN/CGSB-3.5 Quality 3 min AKI 91 or AVGAS 100 LL, 93 Octane Automotive Fuel Due to higher lead content in AVGAS, the wear of the valve seats and deposits in the combustion chamber will increase. Therefore, use AVGAS only if you encounter problems with vapor lock or if the other fuel types are not available. Fuel volume: Wing fuel tank volume.................... 2x60 ltr Unusable fuel quantity.................... 2x0,1 ltr 2.4.3 Oil Oil type: (refer to engine Operator’s Manual) Use motorcycle a 4 stroke engine oil of registered brand with gear additives, but not aircraft oil. Use only oil with API classification „SG“ or higher! Use of multi-grade no mineral oils is recommended. NOTE: Type of oil used by aircrafts manufacturer is shown in Section 10 Supplement No.2. Oil volume: Minimum......................................... 3,24 ltr Maximum ........................................ 3,6 ltr 2.4.4 Powerplant instrument markings Analogue engine instruments markings and their color-code significance are shown below. Date of Issue: 11/2010 Revision: 1.0 2-5 UL POWER 350i 118 hp Minimum Limit (red line) Normal Operating Range (green arc) Caution Range (yellow arc) Maximum Range (red line) Engine speed [RPM] 700 800-3000 3000-3300 3300 Oil Temperature 50°C 50-110°C 110-130°C 130°C Exhaust Gas Temp. (EGT) 800-850°C 850-880°C 880°C - Cylinder Head Temperature (CHT) 60°C 60-130°C 130-190°C * 190°C * 5-7 bar 7 bar Oil Pressure 0,8 bar 0,8-5 bar * Max. CHT temperature depend on the type of coolant used in engine. - see Section 2.4.4 and Section 10 Supplement No.2 Date of Issue: 11/2010 Revision: 1.0 2-6 2.5 Miscellaneous Instrument Marking Note: There are not any miscellaneous instrument marking Date of Issue: 11/2010 Revision: 1.0 2-7 2.6 Weight Empty weight (standard equipment) ................... 320 kg NOTE Actual empty weight is shown in SECTION 6 Max. take-off weight ............................................ 560 kg Max landing weight ............................................. 560 kg Max. weight of fuel .............................................. ...90 kg Max. baggage weight in rear fuselage ................ …15 kg Max. baggage weight in wing lockers ……………..20 kg each 2.7 Center of gravity Operating C.G. range.......................................... 25 to 35 % of MAC 2.8 Approved maneuvers Airplane Category: UL, ELA, LSA The BRISTELL UL is approved for normal and below listed maneuvers: Steep turns not exceeding 60° bank Lazy eights Chandelles Stalls (except whip stalls) WARNING Aerobatics and intentional spins are prohibited ! 2.9 Maneuvering load factors Maximum positive limit load factor ..................... +4 g Date of Issue: 11/2010 Revision: 1.0 2-8 Maximum negative limit load factor ................... - 2 g 2.10 Crew Number of seats ............................................. 2 Minimum crew ................................................ 1 pilot in the left seat Minimum crew weight ..................................... 55 kg Maximum crew weight .................................... see SECTION 6 WARNING Do not exceed maximum take-off weight 560 kg ! 2.11 Kinds of operation There are permitted Day VFR flights, Night VFR flights are permitted with installation of optional Night Lighting Package and operation by an appropriate rated pilot. WARNING IFR flights and intentional flights under icing conditions are PROHIBITED! Minimum instruments and equipment list for VFR flights: - Airspeed indicator - Altimeter - Compass (is not required by ASTM F 2245) - Fuel quantity indicator - Tachometer (RPM) - Oil temperature indicator - Oil pressure indicator - Cylinder head temperature indicator Date of Issue: 11/2010 Revision: 1.0 2-9 2.12 Other limitations No smoking on board of the aircraft! Date of Issue: 11/2010 Revision: 1.0 2-10 SECTION 3 3. EMERGENCY PROCEDURES 3.1 Introduction 3.2 Engine Failure 3.2.1 3.2.2 3.2.3 Engine failure during take-off run Engine failure during take-off Engine failure in flight 3.3 In-flight Engine Starting 3.4 Smoke and Fire 3.4.1 3.4.2 3.4.3 3.4.4 3.4.5 Fire on ground at engine starting Fire on ground with engine running Fire during take-off Fire in flight Fire in the cockpit 3.5 Glide 3.6 Landing Emergencies 3.6.1 3.6.2 3.6.3 3.6.4 Emergency landing Precautionary landing Landing with a flat tire Landing with a defective landing gear 3.7 Recovery from Unintentional Spin 3.8 Other emergencies 3.8.1 3.8.2 3.8.3. Vibration Carburetor icing Autopilot malfunction Date of Issue: 11/2010 Revision: 1.0 3-1 3.1 Introduction Section 3 provides checklists and amplified procedures for coping with various emergencies that may occur. Emergencies caused by aircraft or engine malfunction are extremely rare if proper pre-flight inspections and maintenance are practiced. However, should an emergency arise, the basic guidelines described in this section should be considered and applied as necessary to correct the problem. 3.2 Engine Failure 3.2.1 Engine failure during take-off run 1. Throttle - reduce to idle 2. Ignition - switch off 3. Apply brakes 3.2.2 Engine failure during take-off 1. Speed - gliding at 65 KIAS 2. Altitude - below 150 ft: land in take-off direction - over 150 ft: choose a landing area 3. Wind - find direction and velocity 4. Landing area - choose free area without obstacles 5. Flaps - extend as needed 6. Fuel Selector - shut off 7. Ignition - switch off 8. Safety harness - tighten 9. Master switch - switch off before landing 10. Land Date of Issue: 11/2010 Revision: 1.0 3-2 3.2.3 Engine failure in flight 1. Push control stick forward 2. Speed - gliding at 65 KIAS 3. Altitude - below 150 ft: land in take-off direction - over 150 ft: choose a landing area 4. Wind - find direction and velocity 5. Landing area - choose free area without obstacles 6. Flaps - extend as needed 7. Fuel Selector - shut off 8. Ignition - switch off 9. Safety harness - tighten 10. Master switch - switch off before landing 11. Land 3.3 In-flight Engine Starting 1. Electric pump - ON 2. Fuel Selector - switch to second fuel tank 3. Starter - switch on Date of Issue: 11/2010 Revision: 1.0 3-3 3.4 Smoke and Fire 3.4.1 Fire on ground at engine starting 1. Starter - keep in starting position 2. Fuel Selector - close 3. Throttle - full power 4. Ignition - switch off 5. Leave the airplane 6. Extinguish fire by fire extinguisher or call for a fire-brigade if you cannot do it. 3.4.2 Fire on ground with engine running 1. 2. 3. 4. 5. 6. Heating - close Fuel selector - close Throttle - full power Ignition - switch off Leave the airplane Extinguish fire by fire extinguisher or call for a fire-brigade if you cannot do it. 3.4.3 Fire during take-off 1. 2. 3. 4. 5. 6. 7. 8. Speed - 65 KIAS Heating - close Fuel Selector - close Throttle - full power Ignition - switch off Land and stop the airplane Leave the airplane Extinguish fire by fire extinguisher or call for a fire-brigade if you cannot do it. Date of Issue: 11/2010 Revision: 1.0 3-4 3.4.4 Fire in flight 1. Heating 2. Fuel Selector - close - close 3. Throttle - full power 4. Master switch - switch off 5. Ignition - switch off after the fuel in carburetors is consumed and engine shut down 6. Choose of area - heading to the nearest airport or choose emergency landing area 7. Emergency landing - perform according to 3.6 8. Leave the airplane 9. Extinguish fire by yourself or call for a fire-brigade if you cannot do it. NOTE Estimated time to pump fuel out of carburetors is 30 seconds. WARNING Do not attempt to re-start the engine! 3.4.5 Fire in the cockpit 1. Master switch - switch off 2. Heating - close 3. Use the fire extinguisher Date of Issue: 11/2010 Revision: 1.0 3-5 3.5 Glide An example of the use of gliding is in the case of engine failure 1. Speed - recommended gliding speed 65 KIAS 3.6 Landing Emergencies 3.6.1 Emergency landing Emergency landings are generally carried out in the case of engine failure and the engine cannot be re-started. 1. Speed - adjust for optimum gliding 65 KIAS 2. Trim - adjust 3. Safety harness - tighten 4. Flaps - extend as needed 5. COMM - if installed then report your location if 6. Fuel Selector - close 7. Ignition - switch off 8. Master switch - switch off possible 9. Perform approach without steep turns and land on chosen landing area. 3.6.2 Precautionary landing A precautionary landing is generally carried out in the cases where the pilot may be disorientated, the aircraft has no fuel reserve or possibly in bad weather conditions. 1. Choose landing area, determine wind direction 2. Report your intention to land and land area location if a COMM is installed in the airplane. 3. Perform low-altitude passage into wind over the right-hand side of the chosen area with flaps extended as needed and thoroughly inspect the landing area. 4. Perform circle pattern. 5. Perform approach at increased idling with flaps fully extended. Date of Issue: 11/2010 Revision: 1.0 3-6 6. Reduce power to idle when flying over the runway threshold and touch-down at the very beginning of the chosen area. 7. After stopping the airplane switch off all switches, shut off the fuel selector, lock the airplane and seek for assistance. NOTE Watch the chosen area steadily during precautionary landing . 3.6.3 Landing with a flat tire 1. During landing keep the damaged wheel above ground as long as possible using the ailerons control 2. Maintain the direction on the landing roll out, applying rudder control. 3.6.4 Landing with a defective landing gear. 1. If the main landing gear is damaged, perform touch-down at the lowest practicable speed and if possible, maintain direction during landing run. 2. If the nose wheel is damaged perform touch-down at the lowest practicable speed and hold the nose wheel above the ground by means of the elevator control as long as possible. Date of Issue: 11/2010 Revision: 1.0 3-7 3.7 Recovery from Unintentional Spin WARNING Intentional spins are prohibited! There is no an uncontrollable tendency of the airplane to enter into a spin provided the normal piloting techniques are used. Unintentional spin recovery technique: 1. Throttle - idle 2. Lateral control - ailerons neutralized 3. Rudder pedals - full opposite rudder 4. Rudder pedals rotation stops - neutralize rudder immediately when 5. Longitudinal control - neutralize or push forward and recovery dive. Date of Issue: 11/2010 Revision: 1.0 3-8 3.8 Other Emergencies 3.8.1 Vibration If any forced aircraft vibrations appear, it is necessary: 1. To set engine speed to such power rating where the vibrations are lowest. 2. To land on the nearest airfield or to perform a precautionary landing according to 3.6 3.8.2 Carburetor icing The carburetor icing shows itself through a decrease in engine power and an increase of engine temperatures. To recover the engine power, the following procedure is recommended: 1. Speed - 70 KIAS 2. Throttle - set to 1/3 of power 3. If possible, leave the icing area 4. Increase the engine power gradually up to cruise conditions after 12 minutes If you fail to recover the engine power, land on the nearest airfield (if possible) or depending on the circumstances, perform a precautionary landing according to 3.6 NOTE If your engine is equipped with carburetor heating, use it for extended period descent and in area of possible carburetor icing. Remember: Aircraft is approved to operate in VMC condition only! 3.8.3 Autopilot malfunction In the case, that autopilot starts work not properly, press immediately red button “AP OFF” on the instrument panel. WARNING Take-Off, climb, Approach and landing with AP “ON” or with malfunction AP are PROHIBITED. Date of Issue: 11/2010 Revision: 1.0 3-9 WARNING Adjusting of rudder pedals position during flight is PROHIBITED. SECTION 4 4. NORMAL PROCEDURES 4.1 4.2 4.3 4.4 Introduction Assembly and Disassembly Pre-flight Inspection Normal Procedures 4.4.1 4.4.2 4.4.3 4.4.4 4.4.5 4.4.6 4.4.7 4.4.8 4.4.9 4.4.10 4.4.11 4.4.12 4.4.13 4.4.14 4.4.15 4.4.16 Before engine starting Engine starting Engine warm up, Engine check Taxiing Before take-off Take-off Climb Cruise Descent Before landing Balked landing Landing After landing Engine shutdown Aircraft parking Flight in rain Date of Issue: 11/2010 Revision: 1.0 4-1 4.1 Introduction Section 4 provides checklists and recommended procedures for normal operation of the aircraft. 4.2 Assembly and Disassembly Refer to the BRISTELL UL Maintenance and inspection procedures manual. 4.3 Pre-flight Inspection Carry out the pre-flight inspection every day prior to the first flight or after airplane assembly. Incomplete or careless inspection can cause an accident. Carry out the inspection following the instructions in the Inspection Check List. NOTE The word "condition" in the instructions means a visual inspection of surface for damage deformations, scratching, chafing, corrosion or other damages, which may lead to flight safety degradation. Date of Issue: 11/2010 Revision: 1.0 4-2 The manufacturer recommends carrying out the pre-flight inspection as follows: Date of Issue: 11/2010 Revision: 1.0 4-3 Inspection Check List Ignition Master switch Fuel gauge ind. Master switch Avionics Control system - OFF - ON - check fuel quantity - OFF - check condition - visual inspection, function, clearance, free movement up to stops - check wing flaps operation Canopy - condition of attachment, cleanness Check cockpit for loose objects Engine cowling condition Propeller and spinner condition Engine mount and exhaust manifold condition Oil and coolant quantity check Visual inspection of the fuel and electrical system Fuel system draining Other actions according to the engine manual Wing surface condition Leading edge condition Pitot head condition Wing tip - surface condition, attachment Aileron - surface condition, attachment, clearance, free movement Flap - surface condition, attachment, clearance Landing gear - wheel attachment, brakes, condition and pressure of tires Wing lower surface and fuselage bottom surface condition Vertical tail unit - condition of surface, attachment, free movement, rudder stops Horizontal tail unit - condition of surface, attachment, free movement, elevator stops The check on left side of the fuselage and wing is the same as on right side Date of Issue: 11/2010 Revision: 1.0 4-4 WARNING Physically check the fuel level before each take-off to make sure you have sufficient fuel for the planned flight. CAUTION In case of long-term parking it is recommended to turn the engine several times (Ignition OFF!) by turning the propeller. Always handle the blade area by the palm i.e. do not grasp only the blade edge. It will facilitate engine starting. Date of Issue: 11/2010 Revision: 1.0 4-5 4.4 Normal procedures 4.4.1 Before engine starting 1. 2. 3. 4. 5. Control system Canopy Brakes Safety harness Rudder pedal position - free & correct movement - clean - fully applied - tighten - setted 4.4.2 Engine starting 1. 2. 3. 4. 5. Start the engine according to its manual procedure Master switch - switch on Fuel Selector - on - LEFT FUEL TANK !!! El. pump - switch on Starter - hold activated to start the engine CAUTION The starter should be activated for a maximum of 10 sec., followed by 2 min. pause for engine cooling. As soon as engine runs, adjust throttle to achieve smooth running at approx. 1200 rpm. Check the oil pressure, which should increase within 10 sec. Increase the engine speed after the oil pressure has reached 29 psi and is steady. To avoid shock loading, start the engine with the throttle lever set for 10% open at maximum, then wait 3 sec to reach constant engine speed before new acceleration. Only one magneto should be switched on (off) during ignition magneto check. Date of Issue: 11/2010 Revision: 1.0 4-6 4.4.3 Engine warm up, Engine check Prior to engine check block the main wheels using chocks. Initially warm up the engine to 1000 rpm for approx. 2 minutes, then continue to 1400 rpm till oil temperature reaches 50°C. The warm up period depends on ambient air temperature. Switch “ON” propeller control and check propeller adjustment in all adjustment range. Check both ignition circuits at 2000 rpm for UL POWER 350i. The engine speed drop during the time either magneto switched off should not over 300 rpm. The Max. engine speed drop difference between circuits A and B should be 120 rpm. NOTE Only one magneto should be switched on (off) during ignition magneto check Set max. power for verification of max. speed with given propeller and engine parameters (temperatures and pressures). Check acceleration from idling to max. power. If necessary, cool the engine at 1400 rpm before shutdown. CAUTION The engine check should be performed with the aircraft heading upwind and not on a loose terrain (the propeller may suck grit which can damage the leading edges of blades). 4.4.4 Taxiing Apply power and brakes as needed. Apply brakes to control movement on ground. Taxi carefully when wind velocity exceeds 20 knots. Hold the control stick in neutral position, or in a position that properly deflects a crosswind. Date of Issue: 11/2010 Revision: 1.0 4-7 4.4.5 Before take-off 1. 2. 3. 4. 5. 6. 7. 8. 9. Altimeter Trim Control system Cockpit canopy Safety harness Fuel Selector Ignition El. pump Wing flaps - set - set neutral position - check free movement - closed - tighten - ON (select LEFT tank first) - switched on - ON - extend as needed 4.4.6 Take-off 1. 2. 3. 4. 5. 6. 7. Brakes Take-off power Engine speed Instruments within limits Nose wheel unstick Airplane lift-off Wing flaps 8. Transit to climb - apply to stop wheel rotation throttle fully forward check rpm check 27 KIAS 37 KIAS retract when speed of 65 KIAS is reached, at altitude of 150 ft WARNING The Take-off is prohibited if: The engine is running unsteadily The engine instruments values are beyond operational limi ts The crosswind velocity exceeds permitted limits (see 5.2.8) Autopilot is “ON” Date of Issue: 11/2010 Revision: 1.0 4-8 4.4.7 Climb 1. Best rate-of-climb speed 2. Throttle 3. Trim 4. Instruments - 65 KIAS - Max. take-off power (max. 3300 rpm) - Max. cont.power 3300 rpm - trim the airplane - oil temperature and pressure, cylinder temperature within limits CAUTION If the cylinder head temperature or oil temperature approach their limits, reduce the climb angle to increase airspeed and thus fulfill the limits. 4.4.8 Cruise El.pump - ON for whole flight Refer to Section 5, for recommended cruising figures. 4.4.9 Descent 1. 60 – 65 KIAS Optimum glide speed CAUTION It is not advisable to reduce the engine throttle control lever to minimum on final approach and when descending from very high altitude. In such cases the engine becomes under-cooled and a loss of power may occur. Descent at increased idle (approx. 900 rpm), speed between 6570 KIAS and check that the engine instruments indicate values within permitted limits. 4.4.10 Before landing 1. 2. 3. 4. 5. Approach speed Throttle El. pump Wing flaps Trim - 60 KIAS - as needed - ON - extend as needed - as needed Date of Issue: 11/2010 Revision: 1.0 4-9 4.4.11 Balked Landing 1. 2. 3. 4. Throttle Wing flaps Trim Wing flaps - full power (max.3300 rpm) - extend as needed - adjust as needed - retract at height of 150 ft after reaching 65 KIAS - adjust 5. Trim 6. Repeat circle pattern 4.4.12 Landing 1. 2. Touch-down on main wheels Apply brakes as needed after the nose wheel touch-down 4.4.13 After landing 1. Engine speed 2. Wing flaps - set as required for taxiing - retract 4.4.14 Engine shutdown 1. 2. 3. 4. 5. 6. 7. 8. 9. Engine speed Instruments Avionics Ignition Circuit breakers Master switch Switch box El. pump Fuel Selector - idle - engine instruments within limits - switch off - switch off - switch off - switch off - turn key to switch off - off - off CAUTION Rapid engine cooling should be avoided during operation. This happens above all during aircraft descent, taxiing, low engine rpm or at engine shutdown immediately after landing. Under normal conditions the engine temperatures stabilize during descent, taxiing and at values suitable to stop engine by switching the ignition off. If necessary, cool the engine at 800 - 1000 rpm to stabilize the temperatures prior to engine shut down. Date of Issue: 11/2010 Revision: 1.0 4-10 4.4.15 Aircraft parking and tie-down 1. 2. 3. 4. 5. 6. Ignition check Master switch check Fuel selector Parking brake Canopy Secure the airplane - OFF - OFF - OFF - use it as necessary (if installed) - close, lock as necessary NOTE It is recommended to use parking brake (if installed) for short-time parking only, between flights during a flight day. After ending the flight day or at low temperatures of ambient air, do not use parking brake, but use the wheel chocks instead. NOTE Use anchor eyes on the wings and fuselage rear section to fix the airplane. Move control stick forward and fix it together with the rudder pedals. Make sure that the cockpit canopy is properly closed and locked. The anchoring before leaving the airplane is important if the airplane is not equipped with a parking brake. 4.4.16 Flight in rain When flying in the rain, no additional steps are required. Aircraft qualities and performance are not substantially changed. However VMC must be maintained. Date of Issue: 11/2010 Revision: 1.0 4-11 SECTION 5 5. PERFORMANCE 5.1 Introduction 5.2 Performance 5.2.1 5.2.2 5.2.3 5.2.4 5.2.5 5.2.6 5.2.7 5.2.8 5.2.9 5.2.10 Airspeed indicator system calibration Stall speeds Take-off performance Landing distances Climb performance Cruise Endurance and Range Demonstrated crosswind performance Optimum glide speed Ceiling Date of Issue: 11/2010 Revision: 1.0 5-1 5.1 Introduction Section 5 provides data for airspeed calibration, stall speeds, take-off performance and additional information. The presented data has been computed from actual flight tests with the aircraft and engine in good conditions and using average piloting techniques. If not stated otherwise, the performance stated in this section is valid for maximum take-off weight and under ISA conditions. The performance shown in this section is valid for aircraft fitted with given engine UL POWER 350i 118 hp and Whirl Wind on ground adjustable two blade propeller setted for static RPM on the ground 2850rpm. Date of Issue: 11/2010 Revision: 1.0 5-2 5.2 Performance 5.2.1 Airspeed indicator system calibration KIAS KCAS 27 29 32 35 37 40 43 45 48 49 54 54 59 59 64 64 70 69 75 74 80 79 86 84 91 89 97 95 102 99 107 103 113 108 118 113 123 118 129 123 134 129 140 133 145 138 Date of Issue: 11/2010 Revision: 1.0 5-3 5.2.2 Stall speeds Conditions: Max.take-off weight Engine idle run Wing level stall Co-ordinated turn 30° bank Wing flaps pos. KIAS KCAS Altitude loss at recovery [ft] 0° 43 43 85 10° 40 40 124 30° 34 34 164 0° 46 46 118 10° 42 42 164 30° 37 37 197 5.2.3 Take-off performance RUNWAY SURFACE Take-off Take-off run distance over distance 15 m obstacle [m] [m] PAVED 170 460 GRASS 280 540 Date of Issue: 11/2010 Revision: 1.0 5-4 5.2.4 Landing distances Landing distance over 15 m obstacle Landing run distance (braked) [m] [m] PAVED 190 135 GRASS 190 110 RUNWAY SURFACE 5.2.5 Climb performance Conditions: Max.Continuous Power - 5500 rpm Weight – 472,5 kg Best rate-of-climb speed KIAS [fpm] 0 ft ISA 65 1300 3000 ft ISA 64 1180 6000 ft ISA 62 1003 9000 ft ISA 59 860 Date of Issue: 11/2010 Revision: 1.0 5-5 5.2.6 Cruise Altitude [ft ISA] 0 3000 6000 9000 Airspeed Engine speed [rpm] KIAS KCAS 1700 85 83 2100 89 87 2400 92 91 2700 98 96 3000 112 109 3300 1700 128 82 121 80 2100 86 84 2400 89 87 2700 93 92 3000 98 96 3300 1700 99 79 98 78 2100 83 82 2400 85 84 2700 91 89 3000 94 92 3300 98 96 1700 77 75 2100 80 78 2400 82 80 2700 88 86 3000 90 88 Date of Issue: 11/2010 Revision: 1.0 5-6 5.2.7 Endurance and Range The table below shows fuel consumption, endurance and range Altitude [ft ISA] 3000 ft Fuel quantity [ltr] 120 Engine speed [rpm] 1800 2300 2500 3000 3300 Fuel consumption [l/h] 16,3 19 20,8 22,5 25,5 KIAS 86 92 95 112 128 KCAS 85 91 93 109 121 Endurance [hh:mm] 7:58 6:50 6:15 6:30 6:06 Range [Km] 1252 1156 1087 1318 1350 Airspeed Demonstrated crosswind performance Max. permitted head wind velocity for take-off and landing ............................................... 25 KIAS Max. permitted cross wind velocity for take-off and landing ............................................... 15 KIAS 5.2.9 Optimum glide speed Optimum glide speed.................................................. 60 KIAS 5.2.10 Ceiling Service ceiling ............................................................ 10.000ft Date of Issue: 11/2010 Revision: 1.0 5-7 SECTION 6 6. WEIGHT AND BALANCE 6.1 Introduction Introduction This section contains the payload range within which the BRISTELL UL may be safely operated. Procedures for weighing the aircraft and the calculation method for establishing the permitted payload range are contained in last revision of FAA Aviation Advisory Circular AC.43.13 – 1B 6.2 Weight and Balance Records Equipment list: Whirl Wind ground adjustable propeller Skyview D 700 Compass Radio Dittel KRT 2+ antena AV 10 TT21 Transponder +antena AV 22 Dual Brakes PARKING BRAKE CABIN HEATING WHEEL PANTS AVEO STROBE AND NAVIGATION LIGHTS LANDING LIGHT IN THE WING 12 V SOCKET LEATHER UPHOLSTARY WING LOCKERS ENGINE MONITORING SYSTEM JPI 730 ELT KANAD INTEGRA Date of issue: 11/2010 Revision: 1.0 6-1 Weight and Balance report lists: 1. Empty CG check 2. Blank form WEIGHT & BALANCE REPORT Empty Weight C.G. Check 437,4mm 341,8m m 1367mm Date of issue: 11/2010 Revision: 1.0 6-2 AIRCRAFT EMPTY CG ITEM RIGHT MAIN WHEEL LEFT MAIN WHEEL NOSE WHEEL COMPUTED CG EMPTY WEIGHT ARM MOMENT (kg) (m) (WEIGHTxARM) WR= 129,4 LR= 0,69 90,2 WL= 125,6 L L= 86,7 WN= 82 LN = - 0,76 Empty Weight: CG= 0,340 m WE= 337 kg 0,69 (negative arm) -62,2 Aircraft moment: 114,72 24,9 % MAC Date of issue: 11/2010 Revision: 1.0 6-3 WEIGHT ARM MOMENT (kg) (m) (WEIGHTxARM) PILOT 0,6 PASSENGER 0,6 BAGGAGE COMPARTMENT 1,4 FUEL TANKS 0,20 TOTAL W= M= CG= Take-Off Weight: in % MAC Max.Take-off Weight: 560 kg Serial No: 037/2012 CG Range: 25 – 35 % Date: 20.09.2012 By: Milan Bristela Forward limit: 0,341 m Rearward limit: 0.437 m Total Moment Center of Gravity (CG) = ------------------- [m ] Total Weight Date of issue: 11/2010 x 100 ---------- [ % ] MAC Revision: 1.0 6-4 WEIGHT & BALANCE REPORT Empty form 437,4mm 341,8m m 1367mm C&G OF EMPTY AIRCRAFT ITEM RIGHT MAIN WHEEL LEFT MAIN WHEEL FRONT WHEEL CALCULATED EMPTY C&G WEIGHT ARM MOMENT (kg) (m) (WEIGHTxARM) WR= LR= W L= L L= WN= LN = - Empty weight: CG= - (negative arm) WE= v Aircraft moment: % SAT Date of issue: 11/2010 Revision: 1.0 6-5 WEIGHT ARM MOMENT (kg) (m) (WEIGHTxARM) PILOT 0,6 PASSENGER 0,6 LUGGAGE - FUSELAGE 2,0 WING LOCKERS 0,63 FUEL TANKS 0,2 TOTAL W= M= CG= kg Take off weight: v % SAT Max. take off weight: 560 kg Registr. Nr: OM - M712 Serial No.: 037/2012 Rozpětí těžiště: 25 – 35 % Date: By: Max. useful load : W U. = 560 kg – W EMPTY WU. = 560 kg – = kg Do not exceed maximum take-off weight 560 kg ! Total moment Center of gravity (CG) = ------------------------------ [ in ] Total weight Date of issue: 11/2010 x 100 --------- [ % ] S Revision: 1.0 6-6 6.3 Permitted payload range Permited payload range BRISTELL UL HD SN: 037/2012 F U E L 60 min 1/4 1/2 3/4 1 litres 19 30 60 90 120 kg 14 24 48 66 89 GAUGE VOLUME WEIGHT Permited crew weight kg 199 189 165 147 124 kg 192 182 158 140 117 kg 184 174 150 132 109 1/2 WING kg 179 169 145 127 104 WING kg 159 149 125 107 84 kg 172 162 138 120 97 kg 152 142 118 100 77 kg 144 134 110 92 69 NO BAGGAGE 0 kg 1/2 REAR 7,5 kg REAR B A G A G E 15 kg 40 kg 1/2WING + 1/2 REAR 27,5 kg WING + 1/2 REAR 47,5 kg WING + REAR 55 kg * This weight values are determined with regard on rear CG range. Date of Issue: 11/2010 Revision: 1.0 6-7 SECTION 7 7. AIRPLANE AND SYSTEMS DESCRIPTION 7.1 7.2 7.3 7.4 7.5 7.6 7.7 7.8 Introduction Airframe Control System Landing Gear Seats and Safety harness Baggage Compartment Canopy Powerplant 7.9.1 7.9.2 Throttle Heating 7.9 Fuel system 7.10 Electrical system 7.11.1 7.11.2 7.11.3 7.11.4 7.11 7.12 7.13 7.14 Battery Master switch Ignition Starter button Pitot and Static Pressure System Miscellaneous Equipment Instruments and Avionics Cockpit 7.4.1 7.4.2 Photo of the cockpit Description of equipment and controls in the cockpit Date of Issue: 11/2010 Revision: 1.0 7-1 7.1 Introduction This section provides description and operation of the aircraft and its systems. 7.2 Airframe All-metal construction, single curvature metal skins riveted to stiffeners. Construction is of 6061-T6 aluminum sheet metal riveted to aluminum angles with Avex rivets. This high strength aluminum alloy construction provides long life and low maintenance costs thanks to its durability and corrosion resistance characteristics. The wing has a high lift airfoil equipped by fowler flaps controlled by the electric servo operated by the pilot. 7.3 Control system The plane is equipped with a dual stick control and classic rudder pedals, with pedal hydraulic brakes for easy ground control of the castering nose wheel. The elevator and aileron trim control, as well as wing flaps are electrically operated from the rocker switches located on the instrument panel or on the control stick. Date of Issue: 11/2010 Revision: 1.0 7-2 7.4 Landing gear Tricycle landing gear with the castering nose wheel. Main landing gear uses two fiberglass spring elements. 7.5 Seats and safety harness Side-by-side seating. Seat cushions are removable to make easier cleaning and drying. Four point safety belts provided to each seat.. Optional, is additional seat upholstery to raise the small pilot or move him forward. NOTE Prior to each flight, ensure that the seat belts are firmly secured to the airframe, and that the belts are not damaged. Adjust the buckle so that it is centered on the body. 7.6 Baggage compartment The rear baggage compartment is located behind the seats. It may accommodate up to 15 kg. This space is divide on two sections – baggage compartment A and B. Is not recommended give too heavy things into baggage compartment B. The baggage may also be loaded into the baggage compartment inside each wing up to 20 kg, in each wing locker. Make sure that baggage does not exceed maximum allowable weight, and that the aircraft CG is within limits with loaded baggage. All baggage must be properly secured. 7.7 Canopy Access to the cabin is from both sides. Make sure that the canopy is latched and mechanism is securely locked into position on both sides before operating the aircraft. 7.8 Powerplant Engine: UL POWER 350i engine 118 hp is installed on BRISTELL UL. UL POWER is 4-stroke, 4 cylinder, horizontally opposed, spark ignition, Date of Issue: 11/2010 Revision: 1.0 7-3 fuel injection engine with one central camshaft-push-rod-OHV. Air cooled cylinder heads, ram air cooled cylinders. Wet sump forced lubrication. Dual contactless capacitor discharge ignition. The engine is fitted with an electric starter, AC generator and mechanical fuel pump. Prop drive vithout reduction gear. Propeller: WHIRL WIND ground adjustable propeller. NOTE For technical data refer to documentation supplied by the propeller manufacturer 7.8.1 Throttle Engine power is controlled by means of the THROTTLE lever. THROTTLE lever is positioned in the middle channel between the seats side by side. Lever is mechanically connected (by cable) to the flap on the air inlet. Springs are added to the throttle push rods to ensure that the engine will go to full power if the linkages fail. 7.8.2 Heating Heating consists of a heat exchanger on the exhaust manifold and control mechanism located on the right hand side of instrument panel. CAUTION Incidents involving exhaust gases entering the heating or ventilation system may result in fatal accidents due to carbon monoxide poisoning of the aircraft occupants. A carbon monoxide detector is recommended. Date of Issue: 11/2010 Revision: 1.0 7-4 7.9 Fuel system Wing tanks volume 2 x 60 ltr. Each tank is equipped with a vent outlet and screen filter. Drain valve located in the lowest point of the each tank and on the bottom edge of the firewall, on the gascolator. Main fuel selector valve is on the central console in the cockpit. The electric fuel pump is located on firewall. CAUTION Do not overfill the tanks to avoid fuel overflow through venting tubes. 7.10 Electrical system 7.10.1 Battery The battery is mounted on the forward side of the firewall. 7.10.2 Master switch Master switch connects the electrical system to the 12 Volt battery and charger/coils, controlled by the regulator. See Engine Manual for electrical system details. NOTE Ignition system is independent on the power source and will operate even with Master switch and/or breaker off. 7.10.3 Ignition Switch Ignition must be on BOTH to operate the engine: For safety, remove key when engine is not running. NOTE All switches and or engine controls are "up" or "push forward" for operation, except the cabin heat which is "Pull" for "on". Optional equipment, switches and/or fuses are subject to change or installed as requested. See Aircraft Equipment List and Photo and Description of equipment and controls in the cockpit. Date of Issue: 11/2010 Revision: 1.0 7-5 7.11 Pitot and static pressure system Heated Pitot Tube is located below the left wing. Pressure distribution to the instruments is through flexible plastic hoses. Static port is located in fuselage under the luggage compartment. Keep the pitot head clean to ensure proper function of the system. 7.12 Miscellaneous equipment Adjustable pedals Heating Wheel pants Airplane cover Tow bar 7.13 Instruments and Avionics Whirl Wind ground adjustable propeller Dynon Skyview D 700 GPS Garmin 795 Compass Clock Falcon MF C500 Radio Dittel KRT2+ antena AV 10 TT21 transponder +antena AV 22 ELT KANAD INTEGRA AVEO STROBE AND NAVIGATION LIGHTS LANDING LIGHT IN THE WING 12 V SOCKET Engine monitoring system JPI 730 Date of Issue: 11/2010 Revision: 1.0 7-6 NOTE For operating instructions refer to the documentation supplied with the instruments. Date of Issue: 11/2010 Revision: 1.0 7-7 7.14 Cockpit Date of Issue: 11/2010 Revision: 1.0 7-7 SECTION 8 8. AIRPLANE HANDLING, SERVICING AND MAINTENANCE 8.1 8.2 8.3 8.4 Introduction Aircraft Inspection Periods Aircraft Alterations or Repairs Ground Handling 8.4.1 8.4.2 8.4.3 8.4.4 8.4.5 Towing Parking Mooring Jacking Road transport 8.5 Cleaning and Care Date of Issue: 11/2010 Revision: 1.0 8-1 8.1 Introduction This section contains factory-recommended procedures for proper ground handling and servicing of the airplane. It also identifies certain inspection and maintenance requirements, which must be followed if the airplane is to retain that new-plane performance and dependability. 8.2 Aircraft inspection periods Periods of overall checks and contingent maintenance depends on the condition of the operation and on overall condition of the airplane. Inspections and revisions should be carried out in the following periods, at least: a) after the first 25 flight hours b) after every 50 flight hours c) after every 100 flight hours or at least annual inspection Refer to the Engine Operator's Manual for engine maintenance. Maintain the prop according to its manual. All repairs and maintenance should be made in accordance with AC 43.13-1B. 8.3 Aircraft alterations or repairs It is recommended to contact the airplane manufacturer prior to any alternations to the aircraft to ensure that the airworthiness of the aircraft is not violated. Always use only the original spare parts produced by the airplane (engine, prop) manufacturer. If the aircraft weight is affected by that alternation, a new weighing is necessary, then record the new empty weight into the Weight and Balance record / Permitted payload range in SECTION 6 and up-date the placard showing weights in the cockpit. 8.4 Ground handling 8.4.1 Towing To handle the airplane on the ground, use the Tow Bar, or the fuselage rear pushed down in the place of a bulkhead. CAUTION Avoid excessive pressure at the airplane airframe-especially at control surfaces. Keep all safety precautions, especially in the propeller area. Date of Issue: 11/2010 Revision: 1.0 8-2 8.4.2 Parking It is advisable to park the airplane inside a hangar or alternatively inside any other suitable space (garage) with stable temperature, good ventilation, low humidity and dust-free environment. It is necessary to moor the airplane when it is parked outside a hangar. Also when parking for a long time, cover the cockpit canopy, possibly the whole airplane by means of a suitable tarpaulin. 8.4.3 Mooring The airplane should be moored when parked outside a hangar after the flight day. The mooring is necessary to protect the airplane against possible damage caused by wind and gusts. For this reason the aircraft is equipped with mooring eyes located on the lower surfaces of the wings. Mooring procedure: 1. Check: Fuel Selector shut off, Circuit breakers and Master switch switched off, Switch box switched off. 2. Fix the hand control using e.g. safety harness 3. Close air vent 4. Close and lock canopy 5. Moor the aircraft to the ground by means of a mooring rope passed through the mooring eyes located on the lower surfaces of the wings and below rear fuselage NOTE In the case of long term parking, especially during winter, it is recommended to cover the cockpit canopy or possibly the whole aircraft by means of a suitable tarpaulin attached to the airframe. 8.4.4 Jacking Since the empty weight of this aircraft is relatively low, two people can lift the aircraft easily. First of all prepare two suitable supports to support the aircraft. It is possible to lift the aircraft by handling the following parts: Date of Issue: 11/2010 Revision: 1.0 8-3 By pushing the fuselage rear section down in the place of a bulkhead the fuselage front section may be raised and then supported under the firewall. By holding the fuselage rear section under a bulkhead the fuselage rear may be raised and then supported under that bulkhead. To lift up a wing, push from underneath that wing only at the main spar area. Do not lift up a wing by handling the wing tip. 9.4.5 Road transport The aircraft may be transported after loading on a suitable car trailer. It is necessary to dismantle the wings before road transport. The aircraft and dismantled wings should be attached securely to protect these parts against possible damage. 8.5 Cleaning and care Use efficient cleaning detergents to clean the aircraft surface. Oil spots on the aircraft surface (except the canopy!) may be cleaned with gasoline. The canopy may only be cleaned by washing it with a sufficient quantity of lukewarm water and an adequate quantity of detergents. Use either a soft, clean cloth sponge or deerskin. Then use suitable polishers to clean the canopy. CAUTION Never clean the canopy under “dry“conditions and never use gas or chemical solvents! Upholstery and covers may be removed from the cockpit, brushed and eventually washed in lukewarm water with an adequate quantity of detergents. Dry the upholstery thoroughly before insertion into the cockpit. CAUTION In the case of long term parking, cover the canopy to protect the cockpit interior from direct sunshine. Date of Issue: 11/2010 Revision: 1.0 8-4 SECTION 9 9. REQUIRED PLACARDS AND MARKINGS 9.1 Limitation placards 9.2 Miscellaneous placards and markings Date of Issue: 11/2010 Revision: 1.0 9-1 9.1 Limitation placards The airplane must be placarded with: All fuses Ignition switches Choke Starter Trim: Nose UP and Tail DOWN Flaps: 0°, 10°, 20°, 30° Maximum rear baggage weight 15 kg Maximum weight in each wing locker 20 kg, if installed Instruments Canopy: Open - Close Fuel capacity: 60 ltr / min. 93 Octane - at filler neck Fireproof Identification plate to be affixed to the aircraft in a prominent position near the main point of entrance to the aircraft (plate must show required information) Date of Issue: 11/2010 Revision: 1.0 9-2 THIS AIRCRAFT WAS MANUFACTURED IN ACCORDANCE WITH LIGHT SPORT AIRCRAFT AIRWORTHINESS STANDARDS AND DOES NOT CONFORM TO STANDARD CATEGORYAIRWORTHINESS REQUIREMENTS. NO INTENTIONAL SPINS! AEROBATICS PROHIBITED! MAX. BAGGAGE WEIGHT: 15 kg MAX.WEIGHT IN WING LOCKER: 20 kg AIRSPEEDS: VNE 145 knots VA 96 knots VFE 75 knots VSO 34 knots WARNING DO NOT EXCEED MAXIMUM TAKE-OFF WEIGHT: 472,5 kg WARNING IFR FLIGHTS AND INTENTIONAL FLIGHTS UNDER ICING CONDITIONS ARE PROHIBITED! BAGGAGE COMPARTMENT - A BAGGAGE COMPARTMENT - B Date of Issue: 11/2010 Revision: 1.0 9-3 9.2 Miscellaneous placards and markings NO STEP FUEL CAPACITY: 60 ltr / 93 OCTANE O P E N C A N O P Y C L O S E P I L O T H E A D S E T C O P I L O T H E A D S E T MUSIC IN NO PUSH OILSAE 15W-50 or Equivalent FUEL DRAIN CANOPY OPENED CANOPY CLOSED PEDAL SETTING PEDAL SETTING LOW VOLTAGE FUEL PUMP ALARM EMS THROTTLE CHOKE ON OFF 12V If BRS rescue system is installed: Date of Issue: 11/2010 Revision: 1.0 9-4 - located on the both sides of fuselage between canopy and rear window - located in place rocket egress CAUTION The owner (operator) of this airplane is responsible for the readability of placards during the aircraft service life. Date of Issue: 11/2010 Revision: 1.0 9-5 SECTION 10 10. SUPPLEMENTS 10.1 Introduction 10.2 List of Inserted Supplements 10.3 Inserted Supplemets Date of Issue: 11/2010 Revision: 1.0 10-0 10.1 Introduction This section contains the appropriate supplements necessary to safely and efficiently operate the aircraft when equipped with various optional systems and equipment not provided with the standard airplane. 10.2 List of inserted supplements Date Suppl. No. 11/2010 01/2010 Aircraft Flight Training Supplement 05/2011 01/2011 Description of the aircraft S/N 037/2012 Title of inserted supplement Date of Issue: 11/2010 Revision: 1.0 10-1 Date Suppl. No. Title of inserted supplement Date of Issue: 11/2010 Revision: 1.0 10-2 10.3 Inserted Supplemets: SUPPLEMENT No. 01/2010 Date of Issue: 11/2010 Revision: 1.0 10-3 Aircraft Flight Training Supplement The BRISTELL UL flying characteristics and behavior are similar to single engine aircraft. Following training procedure is applicable if the pilot is holder of UL, PPL or LSA Pilot License. The training flight hours are recommended minimum and depends on the Flight Instructor if student pilot is ready to continue on in next training step. Training can be performed by Flight Instructor or by the experienced pilot who has minimum 20 hours on the BRISTELL UL. Type Rating Training Procedure: Ground Training - before practical Flight Training the pilot has to get familiar with following procedures and documentation Aircraft Operating Instructions (AOI) Aircraft Maintenance and Inspection Procedures Aircraft preflight inspection procedure Control Checklists Radio, avionics, aircraft and engine controls procedures Differences in control and aircraft handling Emergency procedures Date of Issue: 11/2010 Revision: 1.0 10-4 Flight training program - recommended Dual Solo Flights hr/min Flights hr/min Flight Training Procedure 1. 2. 3. Check flight Pattern training flights up to 1000 ft AGL Pattern training flights up to 500 ft AGL 1 30’ 4 20’ 3 15’ 4 20’ 3 15’ 4. Stall speed, 45°turns, side slips 1 30’ 1 20’ 5. Emergency landing training 4 20’ 3 10’ 14 2 hr 10 1 hr Total Date of Issue: 11/2010 Revision: 1.0 10-5 Flight Training Procedure - description 1. Check flight – Student Pilot will fly the airplane in local flight, instructor is giving advice as necessary. 2. Pattern training flights up to 1000 feet AGL - high pattern procedures, instructor is giving advice as necessary. 3. Pattern training flights up to 500 feet AGL - high pattern procedures, instructor is giving advice as necessary. 4. Stall speed, 45°turns, sideslips – stall speed flaps retracted and extended (landing configuration), sideslips at landing configuration. 5. Emergency landing training – emergency procedures and landing to 1/3 of runway. Note: During solo flights instructor is observing the student pilot on pattern and can advise by radio as necessary. Endorsement: Instructor will endorse the Type Rating to the Pilots Logbook, if required. Date of Issue: 11/2010 Revision: 1.0 10-6 SUPPLEMENT No. 01/2012 AIRCRAFT DESCRIPTION Registration Serial number: 037/2012 This Supplement must be contained in the Aircraft Operating Instructions during operation of the airplane. Information contained in this Supplement add or replace information from the basic Aircraft Operating Instructions in the further mentioned parts only. Limitations, procedures and information not mentioned in this Supplement are contained in the basic Aircraft Operating Instructions. Date of Issue: 11/2010 Revision: - 1 of 3 0. TECHNICAL INFORMATION This Supplement adds information necessary for airplane operation with equipment installed in the airplane BRISTELL UL HD of S/N 037/2012. 0.1 Record of revisions No changes. 1. GENERAL INFORMATION No changes. 2. OPERATING LIMITATION 2.4.3 Oil NOTE: Type of oil used by aircrafts manufacturer : AEROSHELL 15W-50 API SL/CF 3. EMERGENCY PROCEDURES No changes. 4. NORMAL PROCEDURES No changes. 5. PERFORMANCE No changes. 6. WEIGHT AND BALANCE No changes. 7. AIRPLANE AND SYSTEMS DESCRIPTION No changes. Date of Issue: 11/2010 Revision: - 2 of 3 8. AIRPLANE HANDLING, SERVICING AND MAINTENANCE No changes. Date of Issue: 11/2010 Revision: - 3 of 3 ">

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Key features
- Recreational and cross-country flying
- Basic training
- Fixed tricycle undercarriage
- UL POWER 350i 118 hp engine
- Side-by-side seating
- Four point safety belts
- Rear baggage compartment
- Electrically operated wing flaps
- Dual stick control and classic rudder pedals
Frequently asked questions
The maximum take-off weight is 560 kg.
The standard powerplant is composed of a UL POWER 350i, 118 Hp 4-cylinder, 4-stroke engine.
The BRISTELL UL HD is approved for normal maneuvers such as steep turns, lazy eights, chandelles, and stalls (except whip stalls). Aerobatics and intentional spins are prohibited.
The optimum glide speed is 60 KIAS.
The service ceiling is 10,000 ft.