3.13.1 The take-off sequence The full take-off sequence starts at pre-flight planning and concludes when: the aircraft is established in the climb configuration at an appropriate threshold height at the best rate of climb airspeed or a suitable enroute climb airspeed with the recommended power setting. The pre-flight planning, weather and airfield check, aircraft inspection, fuel quantity and quality check, engine warm-up and check, taxiing checks, pre-take-off checks and radio procedures are all part of the full pre-flight procedure and of good airmanship; and must be conducted for every take-off — even if you just contemplate doing a quick weather check flight. Take-off procedures and techniques vary according to aircraft type: seaplane or landplane, tailwheel configuration — tractor or pusher engine; nosewheel configuration — tractor or pusher; flap equipped; canard configuration; delta-winged; powered parachute; or weight-shift aircraft. Some procedures should be specified in the pilot's operating handbook for that aircraft. In this module, we will look at the common factors to be considered in the execution of the take-off for the normally configured, three-axis, nosewheel or tailwheel aeroplane. There are differing take-off procedures or techniques, or combinations thereof, applicable to particular airfield conditions: normal take-off short field take-off soft field take-off. The take-off sequence is varied according to prevailing conditions, but it usually has at least three parts: the initial ground roll, where the essentially landborne machine is accelerated to a lift-off speed selected according to the airfield conditions. Aerodynamic drag and rolling friction retard acceleration and the distance required to reach lift-off speed is dependent on atmospheric conditions. It is also inversely proportional to the achievable acceleration — i.e. a 20% increase in acceleration (×1.2) will decrease the distance to 83% (1/1.2=0.83) of the original. Conversely the ground roll is proportional to the lift-off speed squared — i.e. increasing the required lift-off speed by 10% (×1.1) will increase the distance 1.21 times. lift-off followed by a short transition period where the aircraft is accelerated by keeping induced drag to a reasonable level, possibly in ground effect (i.e. while held just above the surface), until either a minimum take-off safety speed (Vtoss) or the selected CAS for best rate of climb (Vy), or the best angle of climb (Vx), is reached. the climb-out, tracking the runway heading, to a safe threshold height where the pilot's options are less restricted, possibly 300–1000 feet above ground level [agl], and where airspeed can be increased to an appropriate enroute climb speed. Regulations forbid turns away from the extended runway line until the aircraft is 500 feet agl. However, at many smaller airfields, local custom may prescribe a climb-out path that provides greater safety in an engine failure event. 3.13.2 Factors affecting safe take-off performance Apart from the pilot's condition, experience and capability, take-off performance is limited by the following constraints, all of which should be assessed carefully within pre-take-off procedure to establish whether a safe take-off is viable. Aircraft weight and balance. The critical nature of aircraft weight and balance at take-off has been highlighted in the 'Weight and balance' module, and should be reviewed. Standard take-off distance [TOD]. TOD should always be expressed as the total distance required to accelerate from a standing start, and clear an imaginary screen 50 feet (15 m) high. The ground roll is that first part of the TOD where the aircraft's weight is partly or fully supported by the undercarriage; sometimes people incorrectly refer to the ground roll as the TOD, ignoring the fact that the distance covered from the lift-off point to climb to 50 feet may be longer than the ground roll. It is known for an under-powered aircraft to be able to lift-off but then be unable to climb out of ground effect. TOD is officially expressed as the take-off distance required [TODR] to clear the 50-foot screen. These standards require that the operating conditions associated with a particular TODR will be specified in approved aircraft take-off performance charts. These conditions are pressure altitude, temperature, runway slope and surface, and wind velocity. CAO 101.28, an airworthiness certification requirement for commercially supplied, amateur-built, kit ultralights states in part (at paragraph 3.6): "The take-off distance shall be established [by the manufacturer] and shall be the distance required to reach a screen height of 50 feet from a standing start, … appropriate to a short dry grass surface … [The] aeroplane [should reach] the screen height at a take-off safety speed [author's emphasis] not less than 1.2 Vs1 … Take-off charts … shall schedule distances established in accordance with the provisions of this paragraph, factored by 1.15." CAO 101.55 has much the same wording but specifies 1.3 Vs1 as the take-off safety speed and FAR Part 23 is similar. 'Short dry grass' means grass less than 100 mm long that is not wet. Unless the manufacturer's take-off performance figures are published as an approved performance chart within the aircraft's flight manual or comparable document, then such figures should be treated as unverified sales claims. In the absence of any specified conditions in an unapproved performance chart, assume that sea-level ISA, nil wind and smooth, dry runway are the basis for the published data. If the manufacturer's performance charts only provide data for the aircraft at maximum take-off weight then, for a recreational aircraft, a reduction of 10% in TODR for each 50 kg the aircraft's weight below MTOW is probably a reasonable estimate. Stopping distance required. The distance required to reach flight speed, and then bring the aircraft to a halt, should be known. It may be necessary to abandon the take-off soon after lift-off, due to doubtful engine performance or other event — this is particularly important in short field or 'hot and high' take-offs. If take-off and landing distance (over a 50-foot screen) charts are available then the total distance needed to take off, abandon take-off at 50 feet, land and bring the aircraft to a halt is the sum of the charted take-off and landing distances required. Airframe condition. An airframe in a battered or dirty condition, or which has unnecessary or non-standard accoutrements, will increase drag and retard acceleration, lengthen TODR and reduce climb performance. Engine age, condition and operating temperatures. An engine that is incapable of producing its rated power will reduce acceleration, lengthen TODR and reduce climb performance. The engine manufacturer's instructions regarding warm-up procedures should be followed, to ensure appropriate temperatures and pressures are established before the engine is subject to the stresses of take-off power; otherwise the potential for an engine failure after take-off is greatly increased. Check carefully for any warning signs or sounds during the full power ground roll. Never continue with the take-off if there are any doubts. Propeller condition and pitch. Chipped leading edges or scored blades, apart from being dangerous due to the possibility of delamination or fracture, will adversely affect thrust output. Blade pitch at a coarse setting — a cruise setting — will reduce acceleration and climb performance. Tyre pressure. Under-inflated tyres increase the rolling friction, decrease the acceleration and add perhaps 10% to the ground roll. Airfield dimensions and slope. The usable length of runways or strips must be known, as well as the degree of slope. Taking off upslope will reduce acceleration and lengthen the ground roll because thrust must also overcome a force equal to the aircraft weight × the sine of the angle of slope, in addition to the drag and rolling friction. The ground roll will increase by about 15% for each 2% of upslope. Runway slope can be measured by taking an altimeter reading at each end, dividing the elevation difference by the runway length (in feet) and multiplying by 100 to get the approximate slope percentage. Airfield surface and surrounds. A short. dry grass surface or rough gravel surface might add 10% to the ground roll compared to that for a smooth, sealed surface. Wet or long grass might add 50% to the ground roll. A soft or waterlogged surface might double the ground roll. Surface water and/or wet grass can lead to aquaplaning and loss of directional control; the effect of frost is similar. The height of obstructions and local terrain must be known. Airfield density altitude. The density altitude is a critical factor that is often not correctly assessed, and has a major effect on engine output, propeller performance and lift generated. Thus it affects acceleration, TODR and climb performance to such an extent that on 'hot and high' airstrips an aircraft may be incapable of safe take-off and climb-out. Read section 3.4 'High density altitude'. Wind velocity and turbulence. After weight and balance plus density altitude, the major considerations in take-off performance for a properly maintained aircraft are then wind strength, direction, gradient, downflow, gust intensity, surface turbulence and the potential for wind shear events. Please read 'Surface gusts or low level wind shear' in the 'Wind shear and turbulence' module. The diagram indicates possible cumulative effects of some take-off conditions on TODR. But as explained in section 11.6, the take-off distance required can be much greater. The pilot in command of an aircraft must assess all the foregoing factors and conditions to ascertain the cumulative total distance required for take-off and obstacle clearance, and then judge if the take-off can be conducted safely. The golden rule is "If you have ANY doubts, don't fly". The most favourable conditions for optimum take-off performance at MTOW are: a pilot who follows the rules and the recommended procedures a certificated aircraft in very good condition and fitted with a 'climb' or variable pitch propeller a surface that is dry, smooth and level — or with a slight downslope a low density altitude; i.e. low elevation and low temperature a smooth, full headwind at ground level of reasonable and constant velocity sufficient separation is maintained to avoid aircraft wake turbulence. You should not only be concerned that the take-off is conducted safely, it should also be accurately controlled — beginning with taxiing — so that alignments, headings, attitude and airspeeds — the 'numbers' — are properly maintained throughout. The take-off should take advantage of the aircraft's and engine's maximum rate of climb capability to reach the threshold height — and it should look well executed to an informed observer standing behind the aircraft's take-off point. In addition, you must have pre-established plans to safely cope with partial or total power loss, occurring at any stage of the take-off sequence. See 'Engine failure after take-off' and 'The turn back, possible or impossible — or just unwise?'. There are web versions of two CASA Advisory Circulars on this site: Operations at non-controlled airfields and Safety during take-off and landing. Both these documents should be read in conjunction with this module. 3.13.3 Engine/propeller effects and ground effect There are some engine effects, plus aerodynamic and inertia phenomena, which will be noticeable at take-off. However, both their existence and the extent of their effect are dependent on the configuration of the aircraft. Tailwheel aircraft are particularly subject to these phenomena, which can cause difficulties to any pilot who is inexperienced in the slow-speed handling of such aircraft. Ultralight aircraft also tend to have a much higher power-to-weight ratio than their general aviation counterparts. For example, at MTOW, the two-seat 110 hp Cessna 152 and Piper Tomahawk both weigh 1670 lb and have a power loading of 15 lb/hp; whereas a two-seat amateur built aircraft acceptance category ultralight equipped with an 80 hp engine will have a power loading of 12.5 lb/hp, and only 10 lb/hp if fitted with a 100 hp engine. A single-seat CAO 95.10 ultralight fitted with just a 60 hp engine will have a power loading of 11 lb/hp. The lower the power loading, or the higher the power-to-weight ratio, the greater and faster the reaction will be to the engine/propeller effects. The helical slipstream The propeller blades produce a rotating slipstream tube with a diameter equal to that of the propeller disc and a helical effect that increases as forward speed increases. If the propeller rotates clockwise, when viewed from behind the aircraft, the slipstream tube will also rotate clockwise. Where the engine is mounted in the nose (as with the Jabiru), then the slipstream will rotate clockwise around the fuselage; anything mounted below the fuselage will experience increased pressure on the right side (from the slipstream striking it at an angle) and anything mounted above the fuselage will experience higher pressure on the left side. The significant surfaces mounted above the fuselage are the fin and rudder, and the increased pressure on their left-hand side will tend to push the tail to the right; i.e. in nil wind conditions, the aircraft will want to swerve to the left — particularly in the early stages of the take-off run when the slipstream counts for practically all the airflow around the fin and rudder. The swing direction would be reversed for aircraft where the propeller rotates anti-clockwise. Full application of compensating rudder may be required at the start of the ground roll. The helical effect lessens as the aircraft accelerates (because the angle at which the slipstream meets the vertical surfaces lessens and also the rudder becomes increasingly effective), so rudder pressure should be decreased as the take-off roll progresses. Slipstream effect is not so apparent in the landing ground roll because normally the throttle is closed. However, if the engine is mounted above the fuselage, the rotating slipstream tube will be higher relative to the fin and rudder, and the swing effect may be lessened or reversed; aircraft with a pusher engine mounting are subject to the same effect. Before you fly any aircraft it is advisable to determine which way the aircraft will swing, and how to control the swing. The helical slipstream will also meet the horizontal stabiliser at an angle but the resulting effect is difficult to determine or distinguish. When a tailwheel aircraft has all wheels on the ground, as in the early part of the take-off ground roll, the slipstream may be deflected by the airfield surface so that the effect on the fin and rudder may vary between the tail-down and tail-up positions. Propeller torque effect The reaction torque of a propeller rotating under power attempts to rotate the aircraft about the propeller shaft. Of course, it is prevented by the resistance of the wings and undercarriage. However, at the beginning of the take-off run, the torque may be sufficient to increase the friction on one tyre and thus cause the aircraft to pull towards that side. The effect is there in the early stages of take-off but may not be apparent as such, because it reinforces the swing tendency initiated by the helical slipstream. (The propeller torque on some very high-powered, piston-engined fighter aircraft has been such that at full power the aircraft tended to hop sideways down the runway. In such aircraft, the engine was not opened up to full climb power until airborne, unless it was carrying a very heavy armament load.) Gyroscopic precession effect Any external force, which tends to alter the direction of the angular momentum axis of a spinning gyroscope, causes the direction of the axis to move (precess) 90° to the applied force and in the direction of rotation. A fast-rotating propeller disc acts as a gyroscope spinning in the lateral plane, its moment of inertia (the resistance to a change in angular velocity about the propeller shaft) is proportional to the propeller mass and the disc diameter squared. When the aircraft's attitude in pitch or yaw is changed rapidly the aircraft applies a torque to the propeller disc and the propeller's reaction is an equal and opposite moment or force applied to the aircraft. But the gyroscopic precession effect causes the direction of that moment to move (precess) 90° to the applied force and in the direction of propeller rotation. For example, if the aircraft's attitude is pitched up the upper rim of the propeller disc is forced back while the lower rim is pushed forward. The precession moment is moved 90° clockwise* to the applied force so the upper rim becomes the disc's right side (looking from the rear) and the reaction moment is directed to the rear tending to yaw the aircraft to the right, i.e. during the period the aircraft is being rotated about its lateral axis the gyroscopic precession effect is also trying to rotate the aircraft about its normal axis. Similarly if the aircraft is pitched down the precession effect prompts a yaw to the left. Conversely if the aircraft is strongly yawed to the left the nose tends to pitch up; if yawed to the right the nose tends to pitch down. There is no gyroscopic precession effect when the aircraft is rolled about the longitudinal axis. *Note: assuming a clockwise-rotating (viewed from behind the aircraft) tractor or pusher propeller. The magnitude of the gyroscopic moments induced by the rotating propeller are dependent on the rate of change in aircraft pitch or yaw, the rotational speed of the propeller and its moment of inertia. The precessive forces are transferred via the shaft to the propeller speed reduction unit or direct to the engine crankshaft, bearings, crankcase and mountings. Sport and recreational aircraft generally have a high power-to-weight ratio and the engines apply unusually high rpm to the propeller. The most prevalent example of the gyroscopic effect in such aircraft is in the early stages of a taildragger's take-off run should the pilot shove the control column forward to raise the tail and accelerate. At this stage airspeed is low so the aerodynamic forces generated by the airframe are also low and have a decreased ability to counter the gyroscopic effects. The pitch down causes the aircraft to yaw to the left so the pilot must anticipate this action by applying compensating rudder as the tail is lifted. Even ground manoeuvring may induce unfavourable gyroscopic effects – swinging the aircraft around with a burst of power plus rudder/brake places high loads on the propeller shaft. For an example of the possible longer term effects on the propeller shaft see 'The Fox story – gyroscopic loads' also see matching engine and propeller. You can read a little about gyroscopic effect in Spitfires and Seafires; the gyroscopic effect is also utilised in some advanced aerobatic manoeuvres in aircraft with powerful engines and large propellers, the Lomcevak end-over-end tumble and inverted spin was the first. P-factor P-factor, or asymmetric disc effect or asymmetric blade effect, occurs when the thrust line is not aligned with the flight path; i.e. when flying with a high angle of attack. As the propeller disc is then inclined to the relative airflow, a down-going propeller blade has a greater component of forward velocity than an up-going blade; thus, the down-going blade generates slightly more thrust than the up-going blade. For a clockwise rotation, more thrust is then generated on the right-hand side of the disc, which again reinforces the slipstream, torque and gyroscopic-induced tendencies for such aircraft to swing left during take-off. P-factor is dependent on thrust and is proportional to forward speed, so it is not a significant factor in the initial part of the ground roll for a tailwheel aircraft, even though the axis of the airscrew disc is inclined to the horizontal; it will become increasingly apparent as the ground roll progresses, if the aircraft's tail-down attitude is maintained. P-factor may also become apparent as higher velocities are reached — just before and after lift-off — if a high aoa is employed at those stages. P-factor may cause the aircraft to yaw when flying level using high power at high angles of attack. P-factor has little or no effect on a tailwheel aircraft during the landing ground roll because, normally, when the throttle is closed no thrust is produced — there is only propeller drag. However, should the throttle be opened suddenly during the ground roll while the tailwheel is on the ground, there may be a prompt P-factor reaction. Inertial effect of centre of gravity position relative to the longitudinal axis If the aircraft's cg is behind the main wheels, as it must be in a tailwheel undercarriage aircraft, then any ground swerve — initiated by the helical slipstream, gyroscopic effect, torque, crosswind, wind gust, deflating tyre or rough ground — will be reinforced by the inertia of the aircraft, applied through the cg position, and tend to pivot around the main wheels. When the cg of the loaded aircraft is in front of the main wheels — i.e. a tricycle undercarriage — the aircraft's inertia will lead to self-correction of the swing, as long as there is no excessive weight on the nosewheel. The cg inertial effect is usually much more likely to cause real difficulties when a tailwheel aircraft is slowing (i.e. on landing) rather than when accelerating. There are circumstances where the cg inertial effect also applies to nosewheel aircraft; see 'wheelbarrowing'. It is very important in such aircraft to identify any departure from the planned heading at a very early stage of the 'swing' and take prompt, corrective action — but not to the extent of over-correcting. The pilot must recognise the swing, stop it, correct the heading and then halt the correction. Over-correction is exacerbated by a hard, smooth runway surface. A groundloop is a swing that has been accentuated by the inertial effect into a very rapid 180° movement, which often causes wingtip and undercarriage damage, and occurs at speeds between 5 and 25 knots. At low speeds and/or in light winds, the inertial effect is stronger than any weathercocking action. There are occasions when it is necessary for a pilot to induce a groundloop, usually when aborting a take-off and nearing the boundary fence or something solid at speed — or after a misjudged approach and landing. The groundloop is induced by applying full rudder and brake on the appropriate side. The swing effect is exacerbated if a tailwheel aircraft is 'short-coupled'; i.e. the moment arm between the tailwheel and the main wheels (or the fin and the cg) is short, and thus the tailwheel friction moment is less than it might be. Such aircraft swing very rapidly. The inertial effect requires that taxiing techniques for tailwheel aircraft differ from those for nosewheel aircraft. A turn, initiated by rudder or brake in a nosewheel aircraft, will stop as soon as the pilot removes rudder or brake pressure, because the inertial effect is always trying to straighten up the ground path (wind conditions permitting). However, with a tailwheel aircraft, once a turn is initiated the inertial effect will keep the turn going — and possibly tightening — until the pilot takes definite action by using opposite rudder or brake to halt the turn. The inertial effect of the cg position relative to the main wheels is relevant when landing; see the rebound effect. Ground effect In the 'spanwise pressure gradient' section of the 'Aerofoils and wings' module we saw that induced drag was a consequence of lift generation, and the associated wingtip vortices increase the momentum imparted to the downwash. As the centre of each vortex is a little inboard of the wingtip, the vortices also have the effect of reducing the effective wing span, the effective wing area and probably the effective aspect ratio. When an aircraft is flying very close to the airfield surface during take-off and landing, the formation of the vortices is partly impeded by the proximity of the ground, so induced drag is less than normal and the centre of each vortex moves outboard a little with the potential for a little more lift. The phenomenon is ground effect and mainly — because of the drag reduction — produces faster acceleration on take-off (which can be very useful) and slower deceleration on landing (which generally is not useful). It can only occur when the lower surfaces of the wings are much less than one full wingspan distance from the surface. The closer the airborne aircraft is to the surface, the greater the reduction in induced drag. A light aircraft that maintains height with the wing under-surface about one-quarter wing span above the ground, might experience a 30–40% reduction; at low speeds, this would amount to a 15–20% reduction in total drag. A 50% reduction in induced drag might be achieved if the wing height is equivalent to one-tenth of wing span, which may be possible in a low-wing aircraft and if the pilot has a very steady hand. Induced drag is normally a much greater force than the wheel/tyre rolling friction on a smooth, dry surface. If flying in ground effect and utilising maximum available power, then when a disturbance causes the aircraft to lift further away from the ground, the induced drag will be restored immediately with a consequent decrease in airspeed, decrease in lift and substantial sink towards the ground. Similarly, if maintaining a constant low velocity in ground effect (i.e. not accelerating, which is poor energy management practice but can readily occur in an underpowered or overweight aircraft, or when attempting take-off in high density altitude conditions) the aircraft may not break out of the ground effect because as the control column is pulled back, the induced drag increases, velocity slows, lift decreases and the aircraft sinks back into ground effect. If the aircraft cannot be accelerated it may end up tripping over the boundary fence, unless the throttle is closed and the aircraft landed. The effective angle of attack of the horizontal stabiliser is also affected, mainly by the changing angle of the wing downflow. This might be evident as an uncommanded but slight pitch-up or down when leaving or entering ground effect. The same effect generally applies to seaplanes and amphibians for water take-offs and landings, so 'ground effect' should be more properly termed 'surface effect'. 3.13.4 Calculating density altitude The calculation of density altitude is fully explained in sections 3.3 and 3.4. However, we will run through an example for an airstrip — 'Olly's Folly' — located at an elevation of 2000 feet. Under ISA conditions, the standard temperature and pressure at that height is 11 °C and 942 hPa respectively. We will do density altitude calculations for a cold winter morning in a high pressure system, and a hot summer afternoon in a low pressure trough. Remember that each 1 °C variation from ISA is roughly equivalent to 120 feet variation in density altitude. (a) Cold winter morning: temperature is 0 °C and by setting 1013.2 on the altimeter pressure setting scale we read off the pressure altitude as 1600 feet. (We remember, of course, to then reset the scale to local or area QNH). The temperature of 0 °C is 11 °C less than ISA, so the density altitude variation due to temperature variation is: –11 × 120 = –1320 feet. So, density altitude = pressure altitude ± temperature variation = 1600 –1320 = 280 feet Thus, the aircraft should perform well at take-off — close to its rated sea-level capability. (b) Hot summer afternoon: temperature is 35 °C and by setting 1013.2 on the altimeter pressure setting scale we read off the pressure altitude as 2400 feet. The temperature of 35 °C is 24 °C greater than ISA so the density altitude variation due to temperature variation is +24 × 120 = +2880 feet. So, density altitude = 2400 + 2880 = 5280 feet Thus, the aircraft will perform poorly at take-off — probably at less than 70% of its rated sea-level capability. The following is an extract from an RA-Aus incident report: "I was attempting to take-off in a paddock approximately 140 metres in length. Due to the hot (35 °C) conditions the aircraft did not get enough lift which resulted in the main wheels catching the top wire of the boundary fence. The aircraft was slowed and struck the ground in a nose-down position. The wire snapped allowing the aircraft to bounce approximately 20 feet in the air. I cut the power and landed the aircraft to the left to miss another fence. This caused the left wingtip to strike the ground before coming to a stop. I walked away from the accident." The aircraft manufacturer provided the following information: "... the take-off distance to safely clear a 15 metre obstacle is 213 metres in ISA sea level conditions." Rule of Thumb #1 In the absence of manufacturer-supplied data the effect of density altitude on TODR (for a dry, smooth and level surface) can be estimated: "In nil wind conditions, for each 1000 feet that the pressure altitude exceeds sea level add 10% to TODR, then for each 10 °C that the airfield temperature exceeds 0 °C add a further 10%." e.g. in the 'Olly's Folly' hot day situation, the aircraft manufacturer's standard sea level TODR is 250 m. Pressure altitude is 2400 feet: 250 × 1.24 = 310 m. Temperature is 35 °C: 310 × 1.35 = 419 m TOD. Then add a further 10% margin for random events = 460 m estimated TODR. This is for a dry, smooth and level surface; if the surface is long grass with a 2% upslope then you might have to add another 50% to TODR, making it nearly three times the manufacturer's standard distance! Remember that all the factors mentioned above relating to surface, slope, pressure, temperature, airframe and engine condition are cumulative, and the runway length is finite. Rule of Thumb #2 In the absence of manufacturer-supplied data, the effect of density altitude on maximum rate of climb can be estimated: Let's say our aircraft's manufacturer states the initial Vy rate of climb at sea level in standard ISA conditions is 1000 feet per minute. However, manufacturers' standard sea level rates of climb are usually based on an aircraft in factory new condition, flown by a very accurate pilot in the most benign atmospheric conditions. The manufacturer's standard should be downgraded by a factor that represents an adjustment for general engine, propeller, airframe and other conditions — say 15% — thus the practical rate of climb at sea level in standard ISA conditions should be regarded as 850 feet per minute at Vy. "The practical rate of climb at Vy should be reduced by 10% for each 1000 feet of density altitude." e.g. At a density altitude of 5000 feet, there is a 50% reduction in the maximum rate of climb to 425 fpm. 3.13.5 Effect of wind Wind direction, strength and variability are usually assessed by observing the airfield windsocks — these indicate the direction and variability, and provide some idea of the surface speed. Indication of wind speed will vary with the type of windsock. The Bureau of Meteorology area forecast should provide an indication of the overlying gradient wind. Take-off into wind! There are several reasons why an aircraft, operating from reasonably flat terrain, should normally take-off directly into wind — or as close to that as possible when operating from defined runways or strips. If an into-wind take-off coincides with an upslope runway, then a little calculation should be done to ascertain whether a downslope tailwind take-off is preferable. You may find some 'one-way' airstrips where a combination of airfield slope and rising terrain at the high end mandates take-off in one direction only, no matter what the wind direction. If you intend operating into such strips, check the aircraft insurance policy carefully, because cover may be voided. The ground (rolling) speed for take-off is lower. The airspeed during the ground roll equals the ground speed plus/minus the headwind/tailwind component. Thus, if the aircraft is rolling at 30 knots into a 10 knot headwind, the airspeed = 30+10 = 40 knots. If rolling at 30 knots with a 10 knot following wind, the airspeed = 30 –10 = 20 knots. It is easier to keep straight because of the aircraft's increased directional stability, due to the higher airspeed. The take-off ground roll is shorter. The into-wind climb-out will be steeper and provide better obstacle clearance. (But the rate of climb — i.e. time to height — is not dependent on wind direction.) The vertical wind profile is such that the wind velocity changes encountered during the climb are likely to be an increase in headwind speed, thus providing a momentary increase in lift should any vertical shear be encountered. If the engine should fail after take-off, the aircraft can readily land into wind thus reducing impact force, because the ground speed is reduced quite significantly at light aircraft speeds. However, there are other factors involved; see 'Practice good energy management in the take-off!'. It is safer to conform to an accepted traffic pattern, which is always based on take-off into wind, or as near as runway direction allows. Estimating the crosswind component of the wind velocity When operating from defined airstrips or runways, the chances of the wind direction corresponding exactly with the strip alignment are low; thus, most take-offs have an element of crosswind. Also, local gusts and eddies usually alter the wind strength and direction during take-off. Taking off with a significant crosswind component makes it more difficult to keep aligned with the selected path — because the aircraft will try to weathercock into the crosswind — and increases the possibility of one wing lifting during the ground roll. Lateral forces may stress the undercarriage. All aircraft should have a demonstrated velocity limit for the 90° crosswind component in both take-off and landing. For a very light aircraft, the demonstrated crosswind component limit may be 10–12 knots, beyond which there is insufficient rudder authority to counter any adverse movement. If the crosswind limit is not known, you can assume that it is less than 25% of Vso. (FAR Part 23.233 requires that all aircraft have safe handling characteristics with a direct crosswind component not less than 0.2 Vso.) There are also various techniques to be learned for positioning the ailerons, elevators and rudder — depending on aircraft configuration, wind strength and wind direction — while taxiing and during the ground roll. While taxiing, the aircraft will always tend to weathercock into wind and there are techniques for taking advantage of that when turning in breezy conditions. Be aware that, due to the high cg and narrow wheel track, all light aircraft are fairly unstable when turning while taxiing. Turns made at speeds much above walking pace may result in a wingtip ground strike. Easy calculation to determine the crosswind component Having determined take-off direction and estimated the wind velocity: 1. Estimate the wind angle; i.e. if you intend taking off towards the north and the wind is coming from the north-east or north-west, then the wind angle is about 45°. 2. The crosswind component is the windspeed multiplied by the sine of the wind angle. However, a reasonable approximation of the crosswind component is made if you multiply the wind angle by 1.5 and apply the result as a percentage (to maximum 100%) of the wind speed. e.g. Wind speed 15 knots, wind angle 45°: Crosswind component = 45 × 1.5 = 67.5% of 15 = 10 knots If the angle was 30° the crosswind component would be about 7 knots. 3. If the wind angle is 60° or more, consider the full wind speed as the crosswind component; i.e. wind speed 15 knots, wind angle 60°, then crosswind component = 15 knots. Estimating the headwind or tailwind component In some crosswind take-offs, you may need to estimate the headwind or tailwind component of the wind velocity. The headwind or tailwind component of a crosswind is not the wind velocity minus the crosswind component — the square of the headwind or tailwind component equals the square of wind velocity minus the square of the crosswind component. Easy calculation to determine the headwind or tailwind component Having determined take-off direction and estimated the wind velocity: 1. Estimate the wind angle; i.e. if you intend taking off towards the north and the wind is coming from the north-east or north-west, then the wind angle is 45°. 2. The headwind component is the windspeed multiplied by the cosine of the wind angle. However, a reasonable approximation of the crosswind component is made if you deduct the wind angle from 115 and apply the result as a percentage (to maximum 100%) of the wind speed. e.g. Wind speed 15 knots, wind angle 45°: Headwind component = 115 –45 = 70% of 15 = 10 knots 3. If the wind angle is 30° or less, consider the full wind speed as the headwind component; i.e. wind speed 15 knots, wind angle 25°, then headwind component = 15 knots. If the wind angle exceeds 90° from your intended take-off direction then, of course, there is a tailwind component. In which case, use the acute angle that the wind subtends with your take-off direction; e.g. if the wind is from the south-east or south-west when taking off towards the north the acute angle is 45° and the same calculation as above is made to determine the tailwind component. Easy calculation to determine the headwind or tailwind effect on ground roll distance If you know the nil wind take-off ground roll for a particular aircraft, you can estimate the take-off ground roll for various headwind components, with the same airfield surface conditions. The take-off ground roll = the nil wind ground roll × ([lift-off speed –wind speed] /lift-off speed)² For example, if an aircraft has a ground roll of 100 m before reaching the normal lift-off speed of 40 knots, what would be the take-off ground roll into a headwind of 5 knots? The take-off ground roll = 100 × ([40 –5] / 40)² = 100 × 0.875² = 100 × 0.765 = 76 m. What would it be with a tailwind of 5 knots? The take-off ground roll = 100 × ([40 + 5] / 40) ² = 100 × 1.125 ² = 100 × 1.265 = 126 m. As you can see, there is a significant difference (50 m) in ground roll even in light winds. If the wind speed components involved were 10 knots, the ground roll would be 56 m into a headwind and 156 m with a tailwind. 3.13.6 Take-off procedure In a normal take-off the aim is to arrive at the 50 feet screen height, as quickly as possible, while maintaining optimum flight safety margins (including traffic separation) and without undue stress on the undercarriage. Normal take-off — nosewheel three-axis aircraft Let's imagine a nosewheel undercarriage aircraft (having lined up in the chosen direction and ensured that the nosewheel has trailed in the fore and aft position) just starting its take-off run, with the throttle being smoothly advanced to maximum power. The airframe will be in a level attitude and, if the wings have a 4° angle of incidence, the angle of attack will also be 4°. The aircraft's total weight is supported on the main wheels and the nosewheel. The rudder will be held deflected in a position to counter the initial slipstream and torque effects, with applied rudder pressure reducing as acceleration progresses. Ground roll. As the ground roll accelerates — because thrust is greater than the rolling friction plus total drag — the airflow velocity increases. At a speed perhaps 20% below Vs1 the elevators should have enough authority so that a little back pressure on the control column will provide sufficient up-elevator to raise the nosewheel from the surface, and increase the aoa by 2 or 3 degrees to 6 or 7°. This may slow the acceleration rate slightly but the reasons for getting the nosewheel off the ground earlier than really necessary — and holding it there — are: the nosewheel strut is the weakest part of the undercarriage and more susceptible to damage from a rough surface the support of the aircraft weight is then shared between the main wheels and the wings rolling friction, being proportional to weight on the wheels, is reducing as lift is increasing the ride is smoother on the main wheels only raising the nose a little reduces the possibility of stone or weed damage to the propeller without excessive deterioration of the view forward. Also, if on a smooth runway and you try to hold the nosewheel on the ground, by increasing forward pressure on the stick as the speed builds, you run the risk of wheelbarrowing. This is where the wings are generating sufficient lift (particularly if take-off flap is set or you are conducting a 'touch and go' landing and take-off) so that the weight on the main wheels is reduced (or they even lift-off slightly) and an abnormal part of the aircraft's weight is riding, and pivoting, on the nosewheel. Under these conditions, the moment arm between the nosewheel and the rudder is very long and the moment applied by the rudder, which is the most effective control at these speeds, is then much greater than normal. Any application of rudder will make the aircraft pivot about the nosewheel rather than the main wheels. The aircraft's cg is now behind the pivot point and the cg inertial effect will make the aircraft behave like a taildragger, but the possibility of a groundloop is greater and the consequences more drastic. On a slippery surface, the aircraft may slide sideways. Wheelbarrowing is a definite no-no on take-off and on landing. As rolling speed builds, so does airspeed and lift. If you allow the aoa to increase beyond 6–7°, a flight velocity may be prematurely reached and the aircraft will lift itself off at an airspeed slightly above stall speed. In this condition, any slight turbulence or mishandling will cause a loss in lift and the aircraft will settle back again, or maybe just one wing drops and it hops about on one wheel. Obviously not a tidy departure; you, not the aircraft, must be in command of the take-off — and you must maintain alignment with some selected reference point throughout the take-off. Rotation. Unless the aircraft manual, or flight school procedures for students specify otherwise, the usual technique is to hold the aircraft at 6–7° aoa until airspeed builds up to a lift-off speed [Vlof] 15–20% above Vs1, then apply further back pressure to rotate the airframe around the main wheels to an aoa of around 12°, and the aircraft will lift off smoothly and commence to climb away with sufficient airspeed in hand to deal with minor turbulence. Anticipate that P-factor effect will cause the aircraft to turn. Do not wait so long that the aircraft flies itself off; you, not the aircraft, should be in command. The increase in induced drag, which is greater than the removal of the rolling friction, will slow the acceleration rate. So, as the initial climb progresses, ease the stick forward until Vy is reached (at an aoa around 8°) and maintain maximum rate of climb at that speed until the planned threshold height is reached. For some aircraft it may be advisable to use Vtoss rather than Vy until a safe height is reached. In gusty wind conditions, it may be prudent to delay rotation until airspeed is perhaps 10% higher than normal. Some nosewheel aircraft may have a tendency to pitch up rather rapidly during rotation and the pilot must be ready to arrest this with forward pressure on the control column. Climb-out. Do not hold the aircraft down to build up speed beyond Vy and then pull up steeply — it displays poor airmanship and is extremely dangerous. Airspeed in a 'zoom' climb like that will drop off very quickly — possibly faster than the pilot can pitch the nose down — which may lead to an irrecoverable departure stall. Take-off procedure may vary a little if the aircraft is fitted with flaps that can be set to a position that provides increased lift without a significant increase in drag. There are other factors involved — see 'Practice good energy management in the take-off!'. Unless stated otherwise in the Pilot's Operating Handbook or engine notes, maintain full throttle until a safe height is reached. The initial climb speed maintained would normally be Vy but if a fixed-pitch cruise propeller is fitted then an airspeed higher than Vy may be more effective. After the initial climb a higher 'enroute climb' airspeed may be the optimum choice to reduce sector time and to maintain engine temperatures within the manufacturer's specified bounds; full power and low airspeed will 'cook' an aero-engine. Also, a lower pitch angle during climb improves forward visibility. Estimating the pitch angle It may be of interest to figure the pitch angle (the angle that the fuselage reference line subtends with the horizontal) during the climb-out. If the aoa is 8° and the angle of incidence is 4° then the fuselage reference line will be inclined at an angle of 4° above the aircraft's flight path. If the aircraft's practical rate of climb at sea level in standard ISA conditions is 850 feet per minute and Vy = 65 knots (or 6500 feet per minute) then the angle of climb (the flight path) is inclined about 8° to the horizontal, so adding the fuselage reference line inclination of 4°, the pitch angle in the climb will be 12°. One event, guaranteed to spoil your day, is the pilot's seat sliding back when the aircraft is rotated and accelerating after lift-off. If your aircraft is fitted with adjustable seats that slide on rails make doubly sure that your seat is locked in a comfortable position before take-off. Also ensure the passenger's seat is locked; she/he may grab at the controls if they find themselves sliding back — that will certainly ruin your day! Incidentally, when initially settling in to the cockpit, make sure that you can comfortably (i.e. without straightening your leg) apply FULL left and right rudder. If you cannot adjust the seat or rudder pedals to achieve this, do not fly that aircraft, because you will not have the full rudder authority provided by the designer. Also there is a danger that, should the aircraft come to a sudden halt with your knee joint locked while applying full rudder, impact forces may damage the knee and hip joint; so, you must be able to apply full rudder with the knee still bent. Normal take-off — tailwheel three-axis aircraft Tailwheel aircraft are subject to all the effects mentioned in section 11.3, and have a fairly predictable mode of behaviour at ground speeds between 5 and 25 knots. They will want to swing and gyrate, and these movements must be anticipated and promptly corrected by the pilot. Ground roll. At the start of the ground roll (again having lined up in the chosen direction and ensured that the tailwheel has trailed in the fore and aft position) the fuselage of a 'taildragger' is naturally pitched up at an angle of maybe 10–12°. Combined with the angle of incidence this means that the aoa at the start of the roll will be close to the stall aoa of about 15°; some aircraft with a high angle of incidence may be past the stall aoa. As the throttle is being smoothly and fully opened at the start of the ground roll, slipstream and torque effects will be at their greatest. Consequently, normal procedure is to start the ground roll with compensating rudder applied, and with the elevators held in the fully up position to put pressure on the tail wheel. The friction of the tailwheel will assist in taming the initial convolutions, particularly if the tailwheel is steerable. However, the high aoa implies consequent high drag and slow acceleration. The tailwheel is the weakest part of the undercarriage, so there is a need to relieve the loads on it as early as possible, particularly if the airfield surface is rough. Also the sooner the generation of lift begins to reduce tyre friction the faster the aircraft accelerates. Thus the requirement is to get the tailplane up reasonably soon so that, firstly, aoa is reduced to 6 or 7° or less; and thus the aircraft is able to pick up her skirts and run. Secondly, the lower the ground speed at which the aircraft's tail is raised, the gentler will be the swing from the ensuing gyroscopic effect. Thirdly, the sooner a near-level (i.e. slightly tail-down) attitude is achieved, the sooner the building P-factor effect is negated. However, remember that gyroscopic effect is also dependent on the rate of change of attitude in pitch, so ease the stick forward rather than shoving it forward. (Propeller surface clearance must be maintained so be careful on non-prepared strips.) Then, as lift-off speed is reached, rotation and climb-out proceeds as for a nosewheel aircraft. Taildragger enthusiasts sometimes refer to the appearance of the aircraft during take-off — when the pilot holds it in a level, minimum drag, maximum acceleration attitude — as being 'on the step'; the term is borrowed from seaplane pilots. Waterborne take-off Although the potential for tyres aquaplaning/hydroplaning — and thus affecting the landing roll — might be considered when landing on a wet runway, surface friction is rarely considered in runway take-offs; however, for seaplanes, water resistance [hydrodynamic drag] dictates the waterborne take-off routine. At rest the seaplane's centre of buoyancy is usually under the forward limit of the aircraft's centre of gravity, while the location of the vortex-creating transverse step in the hull or float/s is usually just to the rear of the centre of buoyancy. After water-taxying to the line-up position, the first part of a seaplane take-off involves getting the aircraft past the 'hump' speed where the aircraft is displacing the maximum amount of water, thereby creating the maximum hydrodynamic drag. (As with air resistance, water resistance also increases in proportion with the aircraft velocity squared.) The throttle is opened, while holding the control column right back, so that the thrust power (including the vertical component of the thrust line) combined with increasing lift from the high aoa quickly lifts the forward portion of the hull/floats above the surface and the hull or floats are 'ploughing' the water, i.e. pushing the water aside. The hump speed might be around 20–30 knots. The second part of the take-off is to to minimise hydrodynamic drag by getting the aircraft operating as a planing hull where it is supported by the hydrodynamic reaction of the water, rather than just pushing the water aside. After attaining hump speed the control column is eased forward to reduce aoa and induced drag and then some back-pressure is applied. So, rather than ploughing through the water and unable to accelerate due to the very high hydrodynamic drag, the aircraft is riding (hydroplaning/aquaplaning) on the deepest part of the hull forward of the step in the hull or floats, total drag (hydrodynamic plus aerodynamic) is greatly reduced allowing the aircraft to accelerate 'on the step' to a speed where wing lift can both break the adhesive action of the water and support total aircraft weight. When on the step the vortices induced by the step break up boundary layer flow and reduce water adhesion to the hull. The aircraft accelerates on the step until rotation speed is reached but unlike a runway take-off, hydrodynamic drag will increase during rotation because more of the hull/float surface is 'wetted' and the aircraft is pushing more water aside. Sufficient thrust must be available to overcome the increase in both the hydrodynamic drag and the induced drag at rotation, otherwise the aircraft can't lift off the water. The 'step-taxying' term describes fast taxying with less than lift-off power. 'Ground' effect is still pertinent in waterborne operations. Short-field take-off In a short-field take-off the aim is to accelerate as fast as possible, be airborne well before the boundary, clear obstacles near the boundary while climbing at the maximum angle of climb, and to maintain reasonable safety margins. Thus we are not so concerned with protecting the undercarriage. The procedure is to maintain a more or less level minimum drag attitude — i.e. 4–5° aoa (with a nosewheel held just above the bumps) throughout the ground roll until Vx is reached — rotate directly to a 12° aoa and climb away at Vx until obstacles are cleared, then reduce aoa to continue the climb at Vy or a higher speed. The ground roll is longer but the acceleration is greater, because rolling friction is normally less than induced drag at a low aoa. You reach Vx in a shorter distance and the TODR is less. The aircraft is subject to all the engine effects but an abnormal P-factor turning tendency should be anticipated after the lift-off rotation. As in normal take-off, the procedure may vary a little if the aircraft is fitted with flaps that can be set to a position that provides increased lift without a significant increase in drag. The recommended flap setting for a short-field take-off may vary from that for other take-off conditions, because the flap position that facilitates minimum ground roll may decrease climb performance. There are some suggestions that flaps should not be lowered to the take-off position until the aircraft is nearing lift-off speed (so the initial acceleration is faster), but the slight advantage provided by this can be dramatically offset by inadvertently lowering the flaps past the take-off position. It is better to set the flaps when doing the pre-take-off checks, when there is time to double-check the selected position. There may be a suggestion that an aircraft equipped with brakes is run up to full power at the start of take-off while holding on the brakes, but generally it is better to smoothly run up to full power while the aircraft is rolling. There is less chance of stone damage to the propeller, and it is easier to prevent a swing developing. Swings and swing correction reduce the acceleration, and it is better to allow time at the beginning of the ground roll to get the aircraft firmly under control. Obviously a take-off into wind is highly desirable, unless runway slope and rising terrain dictate otherwise, and the ground roll should be started as close to the boundary fence as reasonably possible. The procedure described above is for a hard, dry surface or for short dry grass. If the surface is soft or the grass is long and wet, then the rolling friction may exceed the induced drag at medium aoa or the slippery surface may make directional control difficult. In such cases it may be better to get the wheels off early and fly in ground effect until Vx is attained, as in the soft field technique. If there are any doubts about the take-off conditions, then stay on the ground. I suggest you read the article 'Tree's a crowd' in Flight Safety Australia September-October 2002 issue. Soft field take-off Soft field procedures may be applicable to muddy, waterlogged or long/wet grass surfaces. The prime aim in a soft field take-off is to reduce the extremely long ground roll, and become airborne with less than adequate initial airspeed safety margin while utilising ground effect for fast acceleration. The following procedure should not be used in turbulent or gusty conditions, as the possibility of a stall after lift-off is increased. In very soft conditions the usual technique is always to keep rolling; i.e. do not taxi to the take-off position and then stop to do the take-off checks — they should be completed beforehand. When lined up, open the throttle fully and smoothly while holding the control column back. Using a maximum lift flap setting is usually highly recommended. As the elevators become effective, the nose of a nosewheel aircraft will rise. With a taildragger, the elevator pressure should be relaxed sufficiently so that the tailwheel is held off the surface but the aircraft remains firmly in a tail-down attitude. As ground speed builds, start relaxing the back pressure and the aircraft will lift itself (or more likely lurch and stagger) from the surface at its minimum unstick speed [Vmu] and at an aoa very close to the stalling aoa — so, it is vulnerable to turbulence and mishandling. Also, P-factor and slipstream effect may come into play at this time, so it is important to keep the wings level with aileron and stop any turn with opposite rudder to negate any cross-controlled skid. The pilot must then smoothly reduce aoa to 5–6° and hold the aircraft just above the surface in ground effect, so that it accelerates at the maximum possible rate. Gyroscopic effect may be significant during the pitch down to the smaller aoa, which must be anticipated with rudder. The aircraft is rotated after Vy (or Vx if there are obstructions) is attained to break it out of ground effect, held for a few moments to ensure it will accelerate, and then climb-out is commenced. At the initial rotation. the aircraft will slow as induced drag increases substantially and rapidly; firstly because of the restoration of the normal induced drag as it pulls out of ground effect, and secondly because of the increased aoa. The aircraft is likely to sink back to the surface if rotation occurs before sufficient speed is built. The TODR for a soft field take-off will be considerably longer than that for a normal take-off. It is most unwise to attempt take-off from an airfield that is both short and soft. The following is an extract from an RA-Aus incident report: The pilot intended to conduct a trial instructional flight from a grass strip in excess of 250 metres in length. Due to recent rain the strip was soft and several solo take-offs had been carried out, each clearing the fence at the end of the strip by 25–30 m. After some test runs with the passenger on board the pilot's 'gut feeling' was to abandon the exercise but he elected to take-off using a short field technique. The aircraft accelerated until the nosewheel lifted off the ground and then slowed, with the nosewheel sinking back onto the ground. Because he still had what he believed to be sufficient speed in hand the pilot tried to make it over the fence — and didn't. The damage to occupants was minor but the aircraft was a write-off. The pilot identified the cause of the accident as lack of experience in operations from wet fields. In his words the aircraft was 'basically stuck to the field' Coping with significant crosswind During the initial stages of the ground roll in any type of take-off with a significant crosswind component, the aircraft will tend to weathercock into wind and pivot around the main wheels. There are lateral stresses on all wheels in contact with the ground during the roll. The lateral control of the aircraft is then very much dependent on adequate tyre contact with the surface, so if the surface is slippery a crosswind take-off may not be advisable. As the aircraft accelerates, the relative wind velocity (combining the ambient wind velocity, the aircraft's own forward speed and the slipstream velocity) over the tailplane surfaces will have an increasing headwind component and a (relatively) decreasing crosswind component. Thus, it is normal to start the ground roll with a large rudder deflection to counter weathercocking, and decrease the deflection as speed builds. It is usually advisable to also raise the into-wind aileron to prevent the into-wind wing from rising, particularly if gust-induced; the inclined lift vector, because of the rising wing, will tend to turn the aircraft away from the wind. Be aware that if the into-wind aileron is raised while you are countering the weathercocking with rudder, then you must be operating cross-controlled, which will cause the aircraft to sideslip into wind if you should get airborne in that condition. The aileron deflection is decreased as speed builds, but in strong crosswinds it may be advisable to lower the into-wind wing so that the aircraft is rolling just on the into-wind main wheel. The lift vector is then inclined from the vertical and has a lateral component that counteracts the effect of the crosswind; the aircraft line of roll is kept straight by the friction of that into-wind wheel. If the angle is correctly judged, there should be no stress on the wheel. As the aircraft is being lifted off, return the ailerons to neutral and level the wings. To provide an additional safety margin, hold the aircraft on the ground for a higher-than-normal lift-off speed. If conditions are gusty, add 50% of the wind gust speed in excess of the mean wind speed; e.g. if wind speed is 10 knots gusting to 20 knots, add 5 knots to the lift-off airspeed. If the aircraft does become prematurely airborne for any reason then, rather than let the wheels bump down again, hold the aircraft off the ground, accelerate in ground effect and use the soft field take-off technique. After becoming airborne, the aircraft will drift away from the heading, so to mark a tidy and controlled departure, gently turn the aircraft onto a new heading to compensate for the drift and the 'track made good' will follow the extended line of the ground roll — at least until the aircraft reaches 500 feet agl, at which height regulations allow a turn in the circuit direction. It can be that the crosswind either amplifies or reduces the slipstream and other effects. It may be wise to consider taking off in a direction that takes advantage of that counter-effect even if it means taking off with a tailwind component. Also, there is no rule that says you must always take-off aligned with the centre of the runway or strip; if crosswind conditions warrant it, plan your ground roll at an angle across the strip — edge to edge. Traffic separation and wake turbulence Do not commence the take-off roll should until any preceding aircraft using the same runway has crossed the upwind end or commenced a turn, or if the runway is longer than 1800 m the aircraft is airborne and at least 1800 m ahead. However, if both aircraft weigh less than 2000 kg, it is okay to start rolling when the preceding aircraft is airborne and at least 600 m ahead. The runway may be entered following an aircraft landing but the roll should not be started until that aircraft has turned off. The turbulence from the wingtip vortices of aircraft at high angles of attack is particularly strong and a function of aircraft weight. For aircraft taking off, a high aoa is initiated at the start of rotation and continues through climb-out. The wake vortices sink and drift with the wind, and may take several minutes to dissipate. Thus, light aircraft must practise caution when departing behind another aircraft of similar weight, more so if it is a significantly heavier aircraft, as the turbulence will readily roll the aircraft on to its back or worse. When following a very large aircraft note the runway position where the aircraft rotated, wait perhaps two minutes for the wake to dissipate a little, aim to be airborne well before the noted runway position and, where there is any crosswind component, maintain a line along the upwind side of the runway. For a little more information see Aircraft wake vortices in the 'Microscale meteorology and atmospheric hazards' module. Causes of take-off accidents One or more of the following factors commonly cause take-off accidents: exceeding weight and balance limitations failure to set elevator trim at the correct position for the airframe configuration over-controlling during the ground run and at lift-off premature lift-off climbing too steeply after lift-off failure to calculate the TODR to clear all obstacles/terrain and particularly neglecting the effects of high density altitude failure to observe power lines failure to abandon take-off early enough when it is apparent that airfield surface conditions preclude a safe departure using an excessive bank angle in a climbing turn running into the wake vortices from a heavier, previously departing aircraft. Engine failure after take-off [EFATO] Pilots should always be prepared for the possibility that the engine will lose partial or total power during the take-off and climb out; or, for that matter, at any other time during flight. When such an event occurs, the cardinal rule is to fly the aircraft, which initially implies quickly getting the nose down into the right attitude for an appropriate airspeed, either Vbg or Vmp depending on circumstances. Some say the second and third edicts should also be 'fly the aircraft' and 'fly the aircraft'. ( However, if a partial power loss is accompanied by extreme vibration or massive shaking of the aircraft then it is just as important to get the engine completely shut down.) For further information see 'Forced Landing Procedures' in the 'Coping with Emergencies Guide' and 'Engine failure after take-off' in the 'Decreasing your exposure to risk' series. 3.13.7 Precautions when taking off towards rising terrain Take-offs should always be planned so that they do not cause nuisance to others. But it is also prudent to avoid taking off in a direction that takes you close to structures, trees, masts and powerlines unless you are sure that the aircraft will clear them by whatever safety margin you consider acceptable within the existing atmospheric conditions. A take-off towards rising terrain is not something that should be undertaken without a thorough check of all conditions, even if such a take-off has previously been undertaken at a particular location without incident. Density altitude, wind and other conditions may be such that another take-off will result in a 'controlled flight into terrain' incident. Ascertaining terrain height The height of the terrain above the airfield — or more particularly the angle of climb needed to safely clear it — has to be ascertained by whatever means available, to confirm that the aircraft's rate of climb will more than outmatch both the increasing terrain height and the effect of air downflow from the slope. A simple way to judge the angle of climb needed is to extend your arm fully with the fingers bent so that your extended line of sight, including the bottom edge of your little finger, is horizontal. The width of each finger is around 2° and the width of the palm is around 10°. For an example, we will have another look at the 'Olly's Folly' airstrip on that hot summer afternoon. Here there is one grass strip, 1000 feet in length and oriented north-south. Northward, and starting near the end of the strip, the terrain has a 1 in 10 slope rising towards an extensive crescent ridge with an elevation 1000 feet above the airstrip. Using the 1-in-60 rule we can calculate that a 1 in 10 slope equates with an angle of slope of 6°. Ascertaining angle of climb needed We established our aircraft's practical rate of climb at sea level in standard ISA conditions as 850 feet per minute and Vy = 65 knots or 6500 feet per minute. (One knot is near enough to 100 ft/min so to convert knots into feet per minute just multiply by 100.) Then using the 1-in-60 rule we can estimate our aircraft's sea level angle of climb in nil wind conditions, thus: 850/6500 × 60 = 8°. Also note that the ratio of vertical speed to forward speed is about 1:8. But we are not operating in sea level ISA conditions and Vy is only an indicated airspeed, not a true airspeed. TAS is close to 1.5% greater than IAS for each 1000 feet of density altitude, so at our density altitude of 5280 feet TAS is (1.5 × 5.28) % = 8% greater = 65 × 1.08 = 70 knots or 7000 ft/min. Also, our practical rate of climb will be reduced by 10% per 1000 feet density altitude (= 52.8%) to 400 ft/min and the ratio of vertical speed to forward speed has been reduced to 1:18. Using the 1-in-60 rule the angle of climb in nil wind conditions is then: 400/7000 × 60 = 3.4°. Comparing the climb slope with the terrain slope of 6° we can see that it is impossible to outclimb the terrain; in fact the impact point will not be very far from the end of the strip. But what would be the climb angle if we chose to climb at Vx, which should provide a ratio of vertical speed to forward speed 10–15% better than Vy. If Vx, then provided a ratio of 1:15.5, the climb angle using 1-in-60 would be nearly 4°, which would extend the impact point a little further up the slope. Effect of wind on angle of climb A reasonably steady horizontal headwind makes some difference to the angle of climb. Let's say that headwind is 15 knots, which would have the effect of reducing the aircraft's Vy ground speed by 1500 ft/min to 5600 ft/min, so the angle of climb would be 400/5600 × 60 = 4.3°. However, winds that cross over slopes are not horizontal; they may have a substantial vertical component. So the gain, because of the reduction in forward ground speed, may be more than offset by a reduction in vertical speed. In fact, the downflow rate of sink can easily exceed the aircraft's rate of climb, in which case a 'controlled flight into terrain' is inevitable. Re-read lee side downflow in the meteorology section. 3.13.8 Limiting climbing turns during take-off In section 2.8 we discussed the accelerated stall, finding that the airspeed at which an aircraft will stall depends on the wing loading and, as a consequence of providing the centripetal force for the turn, wing loading increases as angle of bank increases. The table in section 2.8 shows that wing loading increases slowly up to a bank angle of 30° — where it is 15% greater than normal — after which it increases rather rapidly — where it is 41% greater at a 45° bank angle. We then concluded that turns involving bank angles exceeding 20–25° should not be made at low levels — including take-off and landing. The wing loading increase in the turn is provided by an increase in CL, which is brought about by an increase in aoa. We also know that the lift coefficient increases in direct relationship to increase in angle of attack. Now what will happen if we are climbing at Vx and decide to quickly turn away from rising terrain or an approaching aircraft, using a 45° bank angle, while still climbing? We know from the table that to maintain a 45° level or climbing turn, wing loading and thus aoa, must increase by 41% and that the aoa at Vx is probably around 12°, so that a 41% increase will take the aoa to 17° and the aircraft will stall. Full power stalls in a balanced climbing turn tend to result in the outer wing stalling first, because of the higher aoa of the outer wing. There will be a fairly fast wing and nose drop (particularly so if the propeller torque effect is such that it reinforces the roll away from the original direction of turn and the aircraft is a high wing configuration) and is likely to result in a stall/spin situation — which any pilot lacking spin recovery experience may find difficult to deal with. If the climbing turn is being made with excessive bottom rudder then the lower wing might stall first, with the consequent roll into the turn flicking the aircraft over. Recovery from a stall in a climbing turn is much the same as any other stall — ease the control column forward to about the neutral position, stop any yaw, level the wings and keep the power on. Even a 30° banked climbing turn at Vx will produce an aoa of 14°, very close to the stall aoa, and provide no margin for even minor turbulence or slight mishandling. The margin you should always have in hand to cope with such events is 3 or 4°. This indicates that when climbing at Vx, turns should not be contemplated. Even when climbing at the Vy aoa (around 8°), until a safe height has been gained, turns should be limited to about 20° to allow an additional margin should wind shear be encountered in the climb-out — and the nose lowered a little for the turn. Further reading The online version of CASA's magazine Flight Safety Australia contains articles relating to take-off that are recommended reading. Look under 'Take-off and landing' in the 'Further online reading' page. Things that are handy to know • The description taildragger is used as a generic term applied to all tailwheel aircraft. However, this is not strictly correct; a true taildragger is an aircraft equipped with a tail skid rather than a tailwheel. Aeroplanes so equipped are usually not fitted with main wheel brakes and they are designed for operation from grass airfields where all take-offs and landings can be made into wind. Such aircraft have little resistance to swinging if operated from a sealed, smooth surface. • Many tailwheel aircraft will have a steerable tailwheel, which improves the aircraft performance during crosswind operations and makes ground handling easier in windy conditions, particularly if not equipped with differential braking. The steerable tailwheel is usually linked to rudder movement and the rudder pedals in some way. But the tailwheel aircraft may have a disconnect feature that allows the tailwheel to fully castor, thereby improving manoeuvring when parking. The steering mechanism may automatically disconnect when weight is off the tailwheel, in which case a spring or other device returns the tail wheel to a low-drag fore and aft alignment. A nosewheel aircraft may be similarly equipped with a steerable nosewheel. Stuff you don't need to know • One of the most successful fighter aircraft of the 1914–18 war was the Sopwith Camel, fitted with a 130 hp rotary engine. The liquid-cooled engines of the day were very heavy and the rotary was designed to utilise air cooling of the cylinders, thus producing a lighter engine for fighter aircraft. The engine rotated around the crankshaft, which was fixed to the airframe. The propeller was bolted to the crankcase so that the engine and propeller rotated as a unit and, because of the flywheel effect, ran very smoothly at normal cruise settings around 1200–1300 rpm. However, as can be imagined, the torque and gyroscopic effects were extreme and such that the aircraft turned very sluggishly to the left but was lightning fast in a turn to the right. If a 90° turn to the left was required it was faster to initiate a 270° turn to the right. In a left turn the aircraft wanted to climb, while in a right turn the gyroscopic effect pushed the nose down. The aircraft was very unstable, hence very manoeuvrable. STRICT COPYRIGHT JOHN BRANDON AND RECREATIONAL FLYING (.com)
