Flight Testing Program for Velocity N713MR
October 21, 2002 Rev 2
Prepared by Roland Brown
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Note that the kit manufacturer has designed, built and tested the Velocity. A full flight test program has been carried out by the manufacturer including spin testing. However, intentional spins are not permitted and the cockpit is placarded with “INTENTIONAL SPINS PROHIBITED”. Information in this document is drawn from the Velocity Owner’s Flight Manual for Standard and 173 Fixed and RG Aircraft” and FAA Advisory Circular No. AC 90-89A, Amateur Built Aircraft Flight Testing Handbook. Manufacturer’s limitations Max Never Exceed Speed Maneuvering Speed Max Landing Brake Extension Speed Gear Extension 200 knots 140 knots 110 knots 120 knots
Maneuver Recommended entry Chandelles 130 knots Lazy Eights 130 knots Steep Turns 130 knots Stalls (except whip stalls) Slow deceleration Accelerated Stall 110 knots Intentional spins are not permitted. Max Crosswind Component: 15 knots take off, 20 knots landing Maximum wind for Taxi (all quarters) 40 knots Red Line Speed 200 knots Maneuver Speed 140 knots Maximum Gross Weight 2400 lb Center Gravity Limits fwd: 115.0 aft 121.5
Manufacturer’s handbook speeds Best angle of climb (Vx) Best rate of climb (Vy) Best glide speed (engine off) Stall speed – flaps down (Vso) 90-100 kts 110 kts 90-100 kts 65 kts
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TABLE OF CONTENTS
Manufacturer’s limitations ..................................................................2 Pre-first Flight Systems Checkout ......................................................4 GENERAL INSPECTION ...................................................................4 Control System..............................................................................4 Landing Gear ................................................................................5 Instrumentation..................................................................................6 Power Plant .......................................................................................6 Fuel System ......................................................................................6 Weight and Balance ..........................................................................6 FAA Records .....................................................................................7 Initial Flight Testing............................................................................7 Ground Testing ................................................................................ 11 First Flight ....................................................................................... 13 First 10 Hours after first flight ........................................................... 16 Second flight ............................................................................... 17 Third Flight .................................................................................. 17 Hours 4 through 10 .......................................................................... 17 Hours 11 through 20 .................................................................... 18 Hours 21 through 35 ................................................................ 19
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Pre-first Flight Systems Checkout Before initial taxi testing is begun, each new aircraft should have a very complete inspection and functional test of its flight systems. Factory built aircraft are given a similar series of tests before the pilot ever sees his new mount; however, the Velocity owner must perform these production test himself. The following procedure should be used for initial system checkout and for each annual inspection. GENERAL INSPECTION Check all fasteners for proper security and safetying Check canard attachment bolts for security and proper Installation. No less than 1 thread nor more than 6 threads. Check wing attachment through bolts, and nuts for installation and security. No less than 1 thread nor more than 6 threads. Check that door seals are in place and that door locking handle is adjusted so it engages the lock knob. Ensure door limit switches adjusted to show door not locked. This is extremely important to eliminate any possibility of it being bumped open in flight. Check wing incidence, canard incidence, rudder, ailerons and elevator deflections Canard incidence +3° = (Use canard incidence template) Wing incidence Zero + 0.5° = Wings must be within 0.3° incidence of each other. (Use wing incidence templates) Elevator and aileron hinge attachment screws for security and nut installation. Control System Rudder Travel 1.5" to 1.75" - Measured at the top of the rudder at trailing edge. Measure this with pilot holding full rudder pedal while someone applies a 5 lb. force inboard on the rudder trailing edge, to take any slack out of the system. Elevator Travel 26° + 2° Trailing edge down 23° + 2° Trailing edge up Ailerons must both be slightly below the trailing edge of the wing 1/3" to 1/4" when neutral. At full deflection aileron T.E. must travel 2.5" + 0.3" at inboard end (measure relative to wing T.E.). Elevator and aileron push rods for proper installation (spacers, washers, bolts, locknuts, clevis pins, and safety clips, installed properly).
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Elevator and ailerons push rods for freedom of movement throughout control travel. Pitch, roll and yaw trim mechanisms for proper function, and freedom of movement. Elevator and aileron for freedom of movement throughout range without binding or chafing. Rudder pedals for freedom of movement, cable attachment and positive return to neutral. Rudder pulleys for free rotation and cable guard installation (the four cotter pins on the pulley brackets). Cable clearance throughout control travel. Brake actuating freedom. All rod ends - reject any with evidence of bent tangs. Elevators for proper mass balance - nose down. Weight evenly distributed between inboard and outboard locations. Ailerons for proper mass balance - level to 10° nose down. Check for 1/16" minimum clearances around all mass balances. Binding can occur at elevated load factors if clearance is too small.
Landing Gear MAIN GEAR: Double check that all attach bolts and axle bolts are installed and secured. Check tires for proper inflation pressure (45 psi, wait 24 hours and see if they leak). Adjust brakes and test for proper function. Service with fluid as required. Bleed by flowing from drain up to master cylinder. Recheck rudder travel 1.5" to 1.75". Double check for proper main tire toe-in (1/4 to 1/2 degree per side) Wheel bearing packed with grease and safetied Brake mechanism for safetying NOSE GEAR: Nose gear tire inflation, 45 psi Axle nut for security and proper installation – ensure lock screws are tight Ensure bearings are lubricated Shimmy damper for friction adjustment (15-20 lb. side force at axle is required to rotate pivot)
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Instrumentation Cylinder head temp, Oil temp, Exhaust gas temp - it is important these gauges be accurately calibrated prior to use. This can be accomplished using hot oil and a high-temp candy thermometer. Pitot/static systems - leak check Oil Pressure, Tachometer, Fuel Pressure - Function check on initial engine run
Power Plant Check: Clock the prop for compression at the 10 o'clock position for proper hand-propping Propeller bolts for proper torque (30 to 45 ft Ibs - refer to prop mfg recommendations) and safetying Propeller track and cracks Spinner track and cracks Engine mount bolts for security and safety Oil level Mixture and throttle controls for security and proper function Magneto wiring. Be sure the mag is cold when the switches are off. Check that the magneto impulse coupling clicks at, or after, top dead center. Cooling plenum must fit tight all around the engine and cowl. If not, overheating will result. Fuel System Check that the fuel caps seal securely and the vent system is clear without leaks. Calibrate your fuel gauges with the aircraft level.
CAUTION: Under no circumstances should fuel of a lower octane rating than that specified by the manufacturer for your engine be used. Be sure the minimum octane is clearly labeled by each fuel cap. Color coding for 100LL is blue. Auto gas, especially the high aromatic content no-lead, should NEVER be used. Weight and Balance
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Your final weighing before initial flight tests is very important and should be done carefully. The measurements taken should be recorded in the airframe logbook and used in the weight and balance data kept aboard the airplane (see weight & balance section). When loading the aircraft for the initial flight testing and for initial pilot checkouts, it is important that the weight and CG fall in the first flight box (see weight and balance section). Note: A maximum gross weight, for takeoff of +5% may be used, but only under the following limitations: Taxi and takeoff only on smooth hard surface Maximum landing weight limited to 2400. Maneuvers limited to normal category +3.8, - 1.0 g. No abrupt maneuvers. Lift off at 75 knots and climb at 95 knots. Before conducting over-gross operation, the pilot should be a proficient/competent Velocity pilot with at least 50 landings in the aircraft. The pilot should not attempt high gross operations at high density altitudes or gusty crosswinds. Max crosswind component is 12 knots. High gross weight operations should not be considered a routine operation, since the chances of surviving an off-airport forced landing diminish rapidly as weight goes up. It should only be considered on those rare occasions when a long range, full fuel four place operation is desired. Routine operations above 2400 Ibs gross weight are not recommended. FAA Records Records required for the Velocity are basically the same as for any production airplane (F.A.R.91). A valid airworthiness certificate, issued by an FAA maintenance inspector, is required to be displayed in the cockpit, along with the aircraft registration certificate, weight and balance record and operating limitations. Radio equipped aircraft must also have a valid FCC radio telephone licenses if the aircraft is operating outside of the continental USA. Airframe and engine logbooks are required as in any other aircraft
Initial Engine Start
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An engine should be properly tested after it has been installed in the aircraft. The intercylinder baffles must be in place. The engine to cowling baffles must be new or in good condition to assure proper cooling air flow differential across the engine. The cylinder head temperature age, oil temperature age, oil pressure gauge, manifold pressure gauge, and tachometer must be calibrated to assure accuracy. The purpose of a test cell or ground run test if done in the aircraft is to assure that the engine meets all specifications, RPM, manifold pressure, fuel flow and oil pressure. The oil cooler system must hold oil temperatures within limits shown in applicable Textron Lycoming Operator's Manuals. NOTE Extended ground operation can cause excessive cylinder and oil temperatures. The purpose for engine break-in is to set the piston rings and stabilize the oil consumption. There is no difference or greater difficulty in seating the piston rings of a top overhauled engine versus a complete engine overhaul. NOTE The maximum allowable oil consumption limits for all Textron Lycoming aircraft engines can be determined by using the following formula: .006 X BHP X 4 / 7.4 = QT/Hr. (0.6 qts per hour for 200 HP) The following procedure provides a guideline for testing newly overhauled engine that is mounted in the aircraft. Information on the "ground run after top overhaul or cylinder change with new rings" and the "flight test after top overhaul or cylinder change with new rings" procedures are published in the applicable Textron Lycoming Operator's Manual. I. FIXED WING A. PREPARATION FOR TEST WITH ENGINE INSTALLED IN AIRCRAFT 1. Pre-oil the engine in accordance with latest edition of Service Instruction No. 1241. Fill oil cooler and lines with oil. Remove, one spark plug from each cylinder, and turn engine over using starter for no more than 15 seconds and check for oil pressure.
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It is particularly important that the cylinder head temperature gauge, oil temperature gauge, oil pressure gauge, manifold pressure gauge, and tachometer be calibrated prior to testing.
CAUTION CHECK THAT ALL VENT AND BREATHER LINES ARE PROPERLY INSTALLED AND SECURED AS DESCRIBED IN THE AIRFRAME MAINTENANCE MANUAL. 4. Install all intercylinder baffles. Install all airframe baffles and cowling. The regular flight propeller can be substituted but cylinder head temperature must be monitored closely.
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B. GROUND TEST 1. 2. Face the aircraft into the wind. Start the engine and observe the oil pressure gauge. If adequate pressure is not indicated within 30 seconds, shut the engine down and determine the cause. Operate the engine at 1000 RPM until the oil temperature has stabilized or reached 140 deg F. After warm up, the oil pressure should not be less than the minimum pressure specified in the applicable operator's manual. Check magneto drop-off as described in the latest edition of Service Instruction No. 1132. Continue operation at 1000/1200 PM for 15 minutes. Insure that cylinder head temperature, oil temperature and oil pressure are within the limits specified in the operator's manual. Shut the engine down and allow it to cool if necessary to complete this portion of the test. If any malfunction is noted, determine the cause and make the necessary correction before continuing with this test. Start the engine again and monitor oil pressure. Increase engine speed to 1500 PM for a 5-minute period. Run engine to full-static, airframe-recommended power for a period of no more than 10 seconds.
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After operating the engine at full power, allow it to cool down moderately. Check idle mixture adjustment prior to shutdown. Inspect the engine for oil leaks. Remove the oil suction screen and the oil pressure screen or oil filter to determine any contamination. If no contamination is evident, the aircraft is ready for flight testing.
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NOTE Compile a log of all pertinent data accumulated during both the ground testing and flight testing. FLIGHT TEST We highly recommend a complete factory check-out in our training aircraft. This is the best way to prepare you for your first flight. If this is not possible, use the following. Now that you have completed your pre-first flight systems check, it is time to taxi and flight test your new Velocity. It is critical that you have completed 100% of the steps in the previous sections! As you complete the final checkout on your new airplane, you are going to be hot to fly your first flight. You may push a little too hard at the last minute and try to fly prematurely, possibly with something wrong with your airplane. To avoid this "homebuilder syndrome, give the only key to your bird to a close friend (preferably one who really likes you and to whom you owe money) and give the absolute authority to say "go" or "no go" to your initial flight tests. With all the other things you are thinking about, it is best to give the decision of whether the airplane is ready to someone else. If you really get a bad case of "homebuilder syndrome", your friendship may be strained somewhat, but you will be able to make up after you have tested your new bird safely. The "homebuilder syndrome" has been a major factor in many first-flight accidents. Typical of this problem is where an individual spends all his time and money building his airplane, and, for several years, lets his flying proficiency lapse. Very typically we find a finished homebuilt with the owner/pilot seriously lacking in pilot proficiency. In one case, the pilot who tried to fly the first flight on his homebuilt had only one flight in the last two years! Another problem surfaces about the time the aircraft is ready to fly: "EGO" - that is, "l built the machine, I'll fly it. After all, who knows more about my machine than me...l built it." The homebuilder is understandably proud of his creation and becomes very possessive. So we find the proud builder/pilot at the end
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of the runway, "ready" for takeoff, with possibly a bad case of "homebuilder syndrome" But he will not know it until just after liftoff, when he finds himself suddenly thrust into an environment he is ill prepared to handle. The best remedy for "homebuilder syndrome" is to accept help on your flight testing from an experienced Velocity or Long EZ pilot. Then get a good checkout from him after you meet the currency requirements Ground Testing Do not just race out and fly your airplane first thing. You will spend a while checking out all of your systems on the ground before you leap off on the first flight. The first order of business is to check out your engine system thoroughly. Ground run it for an hour or so at low to medium power. Run it with the top cowling off and look for excessive vibration, unsafetied hardware, leaky fuel lines, or anything else unpleasant. After this initial run-in period (or the manufacturer's recommended run-in for new or overhauled engines), check everything over very carefully. Recheck the exhaust nuts for torque, look for leaks around gaskets, loose clamps, check fit of cowling baffles, etc. Check everything thoroughly before you button up the cowling to begin taxi tests. Be sure the engine compartment is clean. Check for nuts, washers, bits of safety wire, etc., because in a pusher everything that comes off goes right through the prop. LOW SPEED TAXI For fixed gear aircraft, make all initial taxi/runway flights WITHOUT wheel pants for better brake cooling. Low speed taxi is defined as that slower than required to lift the nose wheel off the ground - 45 knots. Spend at least a full hour doing low speed taxi to fully familiarize yourself with the cockpit environment and to thoroughly check the engine, brakes, controls, landing gear, etc. Thirty five knots is sufficient speed to evaluate rudder steering and brake effectiveness. You may find that EXTENSIVE TAXIING CAN OVERHEAT THE BRAKES. At 35 knots you will note that the sloppy feel of the control stick is gone and air loads now provide a comfortable centering feel. Now is the time for the final FAA inspection and issuance of your airworthiness certificate. The necessary inspections by the FAA must be done prior to any flight testing! Be sure you have complied with all
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pertinent FAA regulations. Refer to FAA Advisory Circular AC #20-27E for the details (Display of N numbers warning & ID plates, etc.). AC #20-27E is a must to have prior to calling for an FAA inspection. Be sure all the paper work is done! HIGH SPEED TAXI AND NOSE WHEEL LIFT OFFS Before conducting the following tests with your new Velocity do all of them first with two other different airplanes in which you are proficient. These maneuvers (nose wheel liftoffs at low power) are a little strange to the average pilot. Doing them in a familiar airplane takes the strangeness out of the maneuver and better prepares you to do them in a new airplane. It also gives you a first-hand look at runway length requirements and wind conditions. Some of the following requirements and procedures may seem excessive. This is not due to any special feature of the Velocity; we feel they should be required of any homebuilt during their initial testing. The safety record of homebuilts during first flights is not as good as it could be if the owners and pilots would follow the following cautious procedures during initial testing. Weather - wind calm or smooth wind straight down the runway. Smooth air - check turbulence in another airplane. Runway - at least 3500 ft., preferably over 4000 ft Fuel - 10 gallons each side Pilot - see pilot experience requirements for absolute minimum criteria. Do not test fly a new airplane while fatigued: go home, get some dinner, sleep; you are more alert in the morning.
The reason for the long runway requirement is to allow you to do nose wheel lift-offs and decelerations without concern for stopping distance or BRAKE HEATING. The air must be smooth and without crosswind. Set the pitch trim for takeoff. Set neutral roll trim. The purpose of this phase of testing is to evaluate the aircraft’s performance and trim during high speed taxi/nose wheel liftoffs, to acquaint the pilot with the pitch and yaw characteristics of the Velocity, and, most importantly, to give him the correct visual cue of zero height to allow him to judge flare height on his first landing. The pilot should spend enough time just below rotation speed to be thoroughly proficient/ comfortable with the unique Velocity rudder system. There should be no tendency for the pilot to inadvertently push/deploy both rudders at the same time,
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unless during braking. Next step is to practice speed control before attempting nose wheel lift offs. It is important to be able to control speed accurately so as not to get airborne inadvertently. You will find that once a speed is attained it takes VERY LITTLE power to maintain it. Practice accelerating to and maintaining different target speeds. (30, 40, 50, 60 knots) Do not rotate. You will find that once the target speed is reached you must reduce power to idle or just a "hair" above to keep from exceeding it. Be proficient and comfortable in holding speed before moving onto nose wheel liftoffs. The aircraft will rotate at different speeds depending on gross weight and center of gravity. To determine rotation speed, accelerate to 50 knots, set power to maintain speed (close to idle), and then attempt to rotate. If 50 knots is too slow to rotate, then go back to the start and try 55 knots, etc. Find the speed that will just rotate the nose (about 60 knots), reduce power to near idle and practice holding the nose at a predetermined position. Be careful to not over-rotate. Always keep the canard well below the horizon. The pilot should not allow the aircraft to exceed 65 knots or rotate to a point of becoming airborne during this exercise. When you've done enough runs down the runway so that you can comfortably, smoothly and precisely control speed, pitch and yaw with the nose wheel off the ground, you should be ready for the first flight. First Flight
Wear a parachute for your flight testing. Do all preparations on one day. Fly next day. Weather calm & clear. Any wind should be down runway at 10 kts max. No crowd. One or two key personnel only. Memorize and rehearse emergency procedures. Plan first flight at least busy time, early morning is usually best. First flight should not exceed 15-20 minutes
Complete all checklists Initial. Cockpit. External. Start.
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Engine run-up checks. Propeller checks Set engine speed at 1700 rpm Pull prop speed control until speed drops by 300-400 rpm Push speed control forward and check speed increase Repeat cycle 3 times
Never leave a squawk unresolved; find and fix problems as you encounter them. Airplanes usually give a hint of impending trouble. The problem is we pilots do not always listen. If something changes: a slight roughness/vibration, new oil leak, trim change, new squeak, etc., look until you find it - don't rationalize it away. Have bunches of fun. You should be proficient in rudder operations and positive control of pitch control and are ready for the "big one". But be sure you review and understand the following. The Velocity does not fly like a Cessna 150 or some other sluggish trainer. The Velocity is a high performance, responsive aircraft with differences. It has a side stick and the pilot should keep his forearm on the armrest and use his wrist to control pitch. Also, the rudders can both be deployed simultaneously and the pilot should be careful not to inadvertently do this in flight. There are two differences in a Velocity that must be thoroughly understood prior to flight: 1. The non-standard rudder pedals: Be sure not to inadvertently deploy both rudders at the same time in flight. If this happens, one will usually be out more than the other, producing unwanted yaw. The Velocity rudders are quite effective. Adjust the pedals so your foot does not press the pedals naturally. Pitch over-controlling: The novice pilot will expect the Velocity to handle like the C-150, or whatever he last flew. The experienced pilot knows that J-3 Cubs and Bonanzas handle differently and will make the transition easily.
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Spend enough time on the runway just above rotation speed but below lift off speed and practice controlling pitch so you can put and hold the desired/selected pitch proficiently. Hold the forearm on the armrest and control pitch with the wrist only. Do not over-rotate! The highest rotation you should see during this or the later flights is the canard up to, but never above, the horizon. Better yet, keep it always at least 2°
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below the horizon. Remember the first flight of your aircraft is just one baby step up from the lift off that you've just completed and is just the bare beginning of your flight test program. First flight should again be made under ideal weather conditions. The weight and CG position should be within the limited envelope for "first flight box". First flight is not intended to demonstrate the capability of your aircraft or of the pilot and should be flown very conservatively. Leave the gear down and give yourself one less thing to worry about. Limit your airspeed to a range of from 80 knots to 130 knots. Stay over the airport and resist the urge to buzz your observers. During your climb out, set your pitch and roll trims to trim the airplane for hands-off flight. This will be a handy reminder of trim direction, if the airplane needs adjustment. You will notice a small roll trim change when you reduce the power. The airplane will require more right trim with power off. Limit your first flight to feeling out roll, pitch and yaw responses and checking engine operation, temperatures, pressures, etc. Make your approach at 80 knots. Have a fast touch down (75-80 knots), leaving full stall landings for later in the test program. C. FLIGHT TEST 1. Start the engine and perform a normal preflight run-up in accordance with the engine operator's manual. 2. Take off at airframe recommended takeoff power, while monitoring RPM, fuel flow, oil pressure, oil temperature, and cylinder head temperatures. 3. As soon as possible, reduce to climb power specified in operator's manual. Assume a shallow climb angle to a suitable cruise altitude. Adjust mixture per pilot's operating handbook. 4. After establishing cruise altitude, reduce power to approximately 75% and continue flight for 2 hours. For the second hour, alternate power settings between 65%and 75% power per operator's manual. NOTE It will be necessary to cruise at the lower altitudes to obtain the required power levels. Density altitude in excess of 8,000 feet (5,000
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feet is recommended) will not allow the engine to develop sufficient cruise power for good break-in. 5. Increase engine power to maximum airframe recommendation and maintain for 30 minutes, provided engine and aircraft are performing within operating manual specifications. 6. Descend at low cruise power, while closely monitoring the engine instruments. Avoid long descents at low manifold pressure. Do not reduce altitude too rapidly or engine temperature may drop too quickly. CAUTION AVOID ANY CLOSED THROTTLE DESCENTS. CLOSED THROTTLE OPERATION DURING DESCENTS WILL CAUSE RING FLUTTER CAUSING DAMAGE TO THE CYLINDERS AND RINGS. 7. After landing and shutdown, check for leaks at fuel and oil fittings and at engine and accessory parting surfaces. Compute fuel and oil consumption and compare to the limits given in operator's manual. If consumption exceeds figures shown in manual, determine the cause before releasing aircraft for service. 8. Remove oil suction screen and oil pressure screen or oil filter to check again for contamination. NOTE To seat the piston rings in a newly overhauled engine, cruise the aircraft at 65% to 75% power for the first 50 hours, or until oil consumption stabilizes. After this first flight make a thorough systems check, clean and flush the fuel filter, electric fuel pump screen, and fuel injector screen. First 10 Hours after first flight Envelope Expansion With first flight completed and any squawks resolved, you are ready to expand your flight envelope. Do not promptly charge out and test fly your aircraft at the extreme CG position and weights. Expand your envelope in small increments. Remember, you have to spend 40 hours in your test area, so put the time to good use and do a professional job of flight testing. Before expanding the weight and CG range shown for initial testing, spend a few hours and become thoroughly comfortable in
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your piloting tasks. When you feel at home in the airplane, begin your expansion of the weight, CG position, load factor and airspeed ranges. Don't feel obliged to expand into the full ranges shown in the plans and in this handbook. Expand your limitations slowly, and if you reach a point that you feel uncomfortable, stop. The ranges shown are those demonstrated by the designer. Feel free to restrict your airplane as you determine in your own testing; just don't exceed the design limits shown. Do not assume that your aircraft will fly exactly the same as N81VA. Minor homebuilder construction tolerances can affect flying qualities and performance; for example, your aircraft may exhibit less or more stall margin. As with any aircraft, completely determine your stall characteristics at a safe altitude, then operate your aircraft accordingly. After you complete the expansion of the CG envelope on your aircraft, you may want to change the placarded minimum and maximum pilot weights to those in which you are comfortable. Second flight Objective: Re-affirm first flight findings. Repeat basic outline of first flight. Time of flight may be extended to not more than 1 hour. Third Flight Objective: Validate engine reliability. At 3000 ft, record engine oil pressure, oil temperature, CHT & EGT for following engine settings. Power setting 55% 60% 65% 75% RPM 2200 2300 2400 2500 Manifold pressure 22.0 23.0 24.0 25.0
Record fuel and oil consumption after landing.
Hours 4 through 10 Objectives: Build on data from first 3 hours. Expand flight envelope
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slowly. CLIMB PERFORMANCE Stabilize engine temps for 10 minutes at 3000 ft altitude. Climb at following speeds for 1 minute. 110 knots, 100 knots (Vy) 90 knots (Vx) DESCENT PERFORMANCE Stabilize engine temps for 10 minutes at 5000 ft AGL. Reduce engine speed to 1500 rpm and descend at following speed: 1.5 times stall speed (est. 49 knots x 1.5 = 74 knots) Record engine data and repeat descent.
AIRSPEED INDICATOR ACCURACY Set up measured course with GPS waypoints at least 2 miles apart. Carry out runs in each direction and time with stop watch. Speeds to begin at lowest safe airspeed and work up to 130 knots in 10 knot increments.
Hours 11 through 20 Carry out a “Condition Annual” inspection of engine and airframe. (See AC 90-89A page 45) Objective: General flight testing including stalls, best rate of climb, best angle of climb, slow flight. STALLS Decelerate aircraft at ½ knot / second. Determine 1g stall speed. Ensure ball stays in middle. Correct wing drop with top rudder. Repeat with 1 knot / second deceleration. Lower flaps and main gear. Repeat 1, 2 & 3. Carry out power on stalls. Increase power until stall is
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performed at full power. BEST RATE OF CLIMB 1. 2. 3. 4. Select altitude 1000 ft AGL as BASE altitude. Begin full throttle climb at 90 knots and below BASE altitude. Begin time check at BASE altitude. Climb for 1 minute and record altitude.
BEST GLIDE SPEED 1. 2. Descend and repeat at speeds of 85, 80, 75, 70, and 65, knots. down to 10 knots higher than stall speed. Determine Vx and Vy as shown in AC 90-89Al, pages 47 & 48.
Hours 21 through 35 Objective: Determine aircraft stability and range of control. Carry out a “Condition Annual” inspection of engine and airframe. (See AC 90-89A page 45). STATIC LONGITUDINAL STABILITY 1. Set up aircraft C of G to be in the flight test box i.e. 118.00 to 120.00 inches. 2. Climb to 6,000 feet AGL and trim for zero stick force in straight and level flight at low cruising speed. 3. Apply pull to establish airspeed at 10 % less than trimmed speed. 4. Pull further to establish airspeed 20 % less than trimmed speed. 5. Verify that greater pull is required to maintain the lower airspeed. This will confirm Positive Static Longitudinal Stability. 6. Apply push to establish airspeed at 10 % greater than trimmed speed. 7. Verify that push is required to maintain the higher airspeed. This will confirm Positive Static Longitudinal Stability. DYNAMIC LONGITUDINAL STABILITY (Short period) 1. Trim straight and level at cruise speed. 2. Push nose down fairly rapidly by a few degrees. 3. Quickly reverse input to nose up to bring pitch attitude back to trim attitude. 4. As pitch attitude reaches trim attitude, release stick. Aircraft with Positive dynamic longitudinal stability will oscillate briefly about trim attitude before stopping at trim attitude.
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DYNAMIC LONGITUDINAL STABILITY (Long period) 1. Trim for straight and level flight. 2. Pull stick to a speed 5 knots less than trim speed and release stick. 3. If amplitude damps out, this is Positive dynamic longitudinal stability. 4. If amplitude persists, this is Neutral dynamic longitudinal stability. 5. If amplitude increases, this is Negative dynamic longitudinal stability. LATERAL DIRECTIONAL STABILITY CONTROL 1. Trim straight and level at 5,000 feet AGL. 2. Enter sideslip, hold heading with at 10 degrees of bank or greater appropriate for full rudder deflection. 3. Check any overbalance of control forces. 4. Release ailerons. Check low wing returns to level. STATIC DIRECTIONAL STABILITY CONTROL 1. Trim at slow cruise speed at 5000 feet AGL. 2. Yaw left and right with rudder and maintain wings level with ailerons. 3. Aircraft should return to straight flight after release of rudder. SPIRAL STABILITY 1. Trim at slow cruise speed at 5000 feet AGL. 2. Apply 15 to 20 degrees of bank to left or right and release controls. 3. Stability is positive if bank angle decreases, neutral if bank angle stays same, negative if bank angle increases. FLUTTER TESTING This testing should be performed in smooth air only. The first time you exceed 130 knot (150 mph) it should be done wearing a parachute and at a height of at least 7000 ft AGL. You should expand the airspeed envelope in increments of not more than 5 knots. At each increment, assess the damping of the controls as follows: kick a rudder pedal, and jab the stick left, right, forward and aft. After each input the controls should immediately return to trim and any structural motion should damp within one cycle. This will require at least 3 or 4 dives, climbing back to altitude between dives. Do not expand airspeed in the dive when below 7000 ft AGL. Use care to not overspeed the engine RPM. If you have just increased speed and find lower damping (i.e.,
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the structure or controls shake more after the jab than at the 5-knot lower speed), do not continue to higher speeds. Recheck balance and weights of control surfaces. Solve any suspected cause of low damping before expanding airspeed. Expand speed to at least the red-line speed you desire to place on your aircraft, up to, but not exceeding 200 knots. Placard your airspeed indicator with your red line. Objective: To verify and confirm freedom from flutter. Note that the ailerons and elevators are mass balanced. Extend speed envelope in 5 knot increments checking for engine/propeller vibrations, temperatures and pressures, etc. 1. 2. 3. Trim to each new speed confirming sufficient trim and control. Note any out of trim condition. Carefully “tap” the control stick and rudder pedals to confirm freedom from vibration or flutter. IMPORTANT. If any vibration of flight controls is experienced discontinue the test immediately and report to Velocity Aircraft Inc.
SPIN TESTING Intentional spins are not permitted and the cockpit is placarded with “INTENTIONAL SPINS PROHIBITED”. The following procedure is copied from the Velocity Aircraft Owners Manual. Intentional spins have been attempted by holding full aft stick and using full rudder, with all combinations of aileron control, and at all cg positions. These controls were held through 360° of rotation. Full aft stick and full pull-up results in a lazy spiral, which ends up in a steep rolling dive at 3 + g and 100 knots. At any time, the spiral can be immediately stopped by removing rudder control and a completely straight forward recovery can be made. That maneuver is not a spin, since at no time is the aircraft departed from controlled flight. If the above maneuver is done at aft cg, the rotation rate is higher so the lazy spiral is more of a slow snap roll. However, even at aft cg the recovery is immediate when controls are neutralized.
ACCELERATED STALLS Objective: To further explore the stall characteristics of the aircraft. 1. Trim straight and level at 6000 feet AGL at slow cruise. 2. Enter 30 degree bank and reduce airspeed with constant bank angle
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3. 4. 5.
and ball in the center. Record airspeed at pre-stall buffet. Repeat in other direction. Repeat at 40, 50 and 60 degree bank angles.
Hours 36 to MAXIMUM GROSS WEIGHT TESTS Objective: To develop aircraft performance data across weight and CG ranges. IMPORTANT Ensure all ballast weights are positively secured and anchored. 1. 2. 3. 4. 5. Add 20 % of max payload to simulate passenger and baggage weight. Carefully weigh and secure. Calculate new weight and balance and CG location. Carry out stalls, rates of climb, stability, retraction tests, and slow flight and accelerated stall checks. Add weight in further steps of 20% of max payload. Calculate new weight and balance and CG location. Complete testing when max. gross weight (=2400 lbs) is reached.
SERVICE CEILING TESTS Objective: To determine the highest altitude at which aircraft can continue to climb at 100 ft/min. 1. Contact FSS and confirm time and place of test. 2. Install portable oxygen breathing equipment. 3. Maintain communications with ATC at all times. 4. Conduct step climbs and record engine data. 5. Terminate test and return if any engine performance or control problems are experienced. NAVIGATION, FUEL CONSUMPTION AND NIGHT FLYING Objective: To verify basic aspects of flight are reliable. COMPASS 1. Carry out compass swing calibration with engine running. Record details on compass correction card. 2. Repeat with all avionics, nav lights and strobe lights on. Record second correction card.
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VOR 1. Select landmark on selected radial from BZM VOR (110.8). 2. Note VOR bearing when over ground point. Max permitted variation is 6 degrees. IFR INSTRUMENTATION The objective is to verify that all instrumentation needed for flight under IMC is functioning properly: Note: At no time should the aircraft be flown under IMC conditions until all of the Initial Flight tests are completed and a log book entry is made certifying that the aircraft has met all initial flight test requirements. Verify attitude indicator remains erect and accurately indicates the artificial horizon agrees with the actual horizon. Verify that the turn indicator agrees with GPS track during no wind conditions Verify turn and bank indicator function properly. Time indicated bank for two minute turns. Verify that the GPS ILS system is functioning properly. Verify that the GPS will execute GPS automated approaches.
FUEL CONSUMPTION 1. Fly at 1000 ft AGL. Note fuel flow. Perform full throttle climb Note fuel flow. 2. Repeat climb to 6000, 7000, 8000, 9000 and 10,000 ft 3. At 3000 ft, Run 8 to 10 mile race track course at 55% power and record fuel consumption on fuel gauge. 4. Repeat at power settings below. 5. Repeat 3 and 4 at 4000, 6000, 8000, and 10,000 feet. Power setting 55% 60% 65% 70% 100% (do not exceed 2700 rpm) RPM 2200 2300 2400 2500 2700 Manifold pressure 22.0 23.0 24.0 25.0 27.0
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NIGHT FLYING 1. Perform with bright moon. Check flashlight available with fresh batteries. 2. Verify cockpit lighting adequacy. 3. Perform minimum of ½ hour of night taxiing. 4. Perform initial flight at dusk with low light level. 5. Transition to true night flying. Perform take offs and landings. Perform flight to selected way point and return. AEROBATICS Aerobatics are NOT APPROVED for the Velocity. FLIGHT TEST AREA The aircraft will be based at Lincoln County Airport for initial flight testing. Proposed flight test area shall be bounded by a radius of approximately 38 miles extending to Rutherford County (KFQD), Morganton - Lenoir (MRN), Wilkes County (UKF), Elkin (ZEF), and Rowan County (RUQ). Charlotte Class B airspace to the south will be out of bounds and altitudes will be limited to below the Class B airspace at and north of Lincoln County (IPJ).
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