AMC1 FSTD(H).200 Terminology and abbreviations

• ED Decision 2012/011/R found in: CS-FSTD(H) Initial issue - Helicopter Flight Simulation Training Devices (Jun 2012)

AMC1 FSTD(H).200 Terminology and abbreviations Decision 2012/011/R (a) Terminology (1) In addition to the principal terms defined in the requirement itself, additional terms used in the context of CS-FSTD(A) and CS-FSTD(H) have the following meanings: — ‘Acceptable change’ means a change to configuration, software etc., which qualifies as a potential candidate for alternative approach to validation. — ‘Aircraft performance data’ means performance data published by the aircraft manufacturer in documents such as the aircraft flight manual (AFM), operations manual, performance engineering manual, or equivalent. — ‘Airspeed’ means calibrated airspeed when relevant or other airspeed which is clearly annotated. — ‘Altitude’ means pressure altitude when relevant or other altitude which is clearly annotated. — ‘Audited engineering simulation’ means an aircraft manufacturer’s engineering simulation which has undergone a review by the appropriate competent authorities and been found to be an acceptable source of supplemental validation data. — ‘Automatic testing’ means FSTD testing wherein all stimuli are under computer control. — ‘Bank’ means the bank/roll angle (degrees). — ‘Baseline’ means a fully flight test validated production aircraft simulation. May represent a new aircraft type or a major derivative. — ‘Breakout’ means the force required at the pilot’s primary controls to achieve initial movement of the control position. — ‘Closed loop testing’ means a test method for which the input stimuli are generated by controllers which drive the FSTD to follow a pre-defined target response. — ‘Computer controlled aircraft’ means an aircraft where the pilot inputs to the control surfaces are transferred and augmented via computers. — ‘Control sweep’ means a movement of the appropriate pilot’s control from neutral to an extreme limit in one direction (forward, aft, right, or left), a continuous movement back through neutral to the opposite extreme position, and then a return to the neutral position. — ‘Convertible FSTD’ means an FSTD in which hardware and software can be changed so that the FSTD becomes a replica of a different model or variant, usually of the same type aircraft. The same FSTD platform, cockpit shell, motion system, visual system, computers, and necessary peripheral equipment can thus be used in more than one simulation. — ‘Critical engine parameter’ means the engine parameter which is the most appropriate measure of the engine power delivered. — ‘Damping (critical)’ means that minimum damping of a second order system such that no overshoot occurs in reaching a steady state value after being displaced from a position of equilibrium and released. This corresponds to a relative damping ratio of 1:0. — ‘Damping (over-damped)’: an ‘over-damped’ response is that damping of a second order system such that it has more damping than is required for critical damping, as described above. This corresponds to a relative damping ratio of more than 1:0. — ‘Damping (under-damped)’: an ‘under-damped’ response is that damping of a second order system such that a displacement from the equilibrium position and free release results in one or more overshoots or oscillations before reaching a steady state value. This corresponds to a relative damping ratio of less than 1:0. — ‘Daylight visual’ means a visual system capable of meeting, as a minimum, system brightness, contrast ratio requirements and performance criteria appropriate for the level of qualification sought. The system, when used in training, should provide full colour presentations and sufficient surfaces with appropriate textural cues to successfully conduct a visual approach, landing and airport movement (taxi). — ‘Deadband’ means the amount of movement of the input for a system for which there is no reaction in the output or state of the system observed. — ‘Driven’ means a state where the input stimulus or variable is ‘driven’ or deposited by automatic means, generally a computer input. The input stimulus or variable may not necessarily be an exact match to the flight test comparison data – but simply driven to certain predetermined values. — ‘Engineering simulation’ means an integrated set of mathematical models representing a specific aircraft configuration, which is typically used by the aircraft manufacturer for a wide range of engineering analysis tasks including engineering design, development and certification. It is also used to generate data for checkout, proof-of-match/validation and other training FSTD data documents. — ‘Engineering Simulator’ means the aircraft manufacturer’s simulator which typically includes a full-scale representation of the simulated aircraft flight deck/cockpit, operates in real time and can be flown by a pilot to subjectively evaluate the simulation. It contains the engineering simulation models, which are also released by the aircraft manufacturer to the industry for FSTDs. The engineering simulator may or may not include actual on-board system hardware in lieu of software models. — ‘Engineering simulator data’ means data generated by an engineering simulation or engineering simulator, depending on the aircraft manufacturer’s processes. — ‘Engineering simulator validation data’ means validation data generated by an engineering simulation or engineering simulator. — ‘Entry into service’ refers to the original state of the configuration and systems at the time a new or major derivative aircraft is first placed into commercial operation. — ‘Essential match’ means a comparison of two sets of computer-generated results for which the differences should be negligible because essentially the same simulation models have been used (also known as a virtual match). — ‘Flight test data’ means actual aircraft data obtained by the aircraft manufacturer (or other supplier of acceptable data) during an aircraft flight test programme. — ‘Free response’ means the response of the aircraft after completion of a control input or disturbance. — ‘Frozen/locked’ means a state where a variable is held constant with time. — ‘FSTD data’ means the various types of data used by the FSTD manufacturer and the applicant to design, manufacture, test and maintain the FSTD. — ‘FSTD evaluation’ means a detailed appraisal of an FSTD by the competent authority to ascertain whether or not the standard required for a specified qualification level is met. — ‘FSTD operator’ means that organisation directly responsible to the competent authority for requesting and maintaining the qualification of a particular FSTD. — ‘Fuel used’ means the mass of fuel used (kilos or pounds). — ‘Full sweep’ means the movement of the controller from neutral to a stop, usually the aft or right stop, to the opposite stop and then to the neutral position. — ‘Functional performance’ means an operation or performance that can be verified by objective data or other suitable reference material that may not necessarily be flight test data. — ‘Functions test’ means a quantitative and/or qualitative assessment of the operation and performance of an FSTD by a suitably qualified evaluator. The test can include verification of correct operation of controls, instruments, and systems of the simulated aircraft under normal and non-normal conditions. Functional performance is that operation or performance that can be verified by objective data or other suitable reference material which may not necessarily be flight test data. — ‘Grandfather rights’ means the right of an FSTD operator to retain the qualification level granted under a previous regulation of an EASA member state. Also the right of an FSTD user to retain the training and testing/checking credits which were gained under a previous regulation of an EASA Member State. — ‘Ground effect’ means the change in aerodynamic characteristics due to modification of the air flow past the aircraft caused by the presence of the ground. — ‘Hands-off manoeuvre’; means a test manoeuvre conducted or completed without pilot control inputs. — ‘Hands-on manoeuvre’ means a test manoeuvre conducted or completed with pilot control inputs as required. — ‘Heavy’ means with operational mass at or near maximum for the specified flight condition. — ‘Height’ means the height above ground (AGL) (meters or feet) — ‘Highlight brightness’ means the maximum displayed brightness, which satisfies the appropriate brightness test. — ‘Icing accountability’ means a demonstration of minimum required performance whilst operating in maximum and intermittent maximum icing conditions of the applicable airworthiness requirement. Refers to changes from normal (as applicable to the individual aircraft design) in take-off, climb (en-route, approach, landing) or landing operating procedures or performance data, in accordance with the AFM, for flight in icing conditions or with ice accumulation on unprotected surfaces. — ‘Integrated testing’ means testing of the FSTD such that all aircraft system models are active and contribute appropriately to the results. None of the aircraft system models should be substituted with models or other algorithms intended for testing only. This may be accomplished by using controller displacements as the input. These controllers should represent the displacement of the pilot’s controls and these controls should have been calibrated. — ‘Irreversible control system’ means a control system in which movement of the control surface will not backdrive the pilot’s control in the cockpit. — ‘Latency’ means the additional time beyond that of the basic perceivable response time of the aircraft due to the response time of the FSTD. — ‘Light’ means with operational mass at or near minimum for the specified flight condition. — ‘Line oriented flight training (LOFT)’ refers to flight crew training which involves full mission simulation of situations which are representative of line operations, with special emphasis on situations which involve communications, management and leadership. It means ‘real-time’, full-mission training. — ‘Manual testing’ means FSTD testing where the pilot conducts the test without computer inputs except for initial setup. All modules of the simulation should be active. — ‘Master qualification test guide (MQTG)’ means the competent authority-approved QTG which incorporates the results of tests witnessed by the competent authority. The MQTG serves as the reference for future evaluations. — ‘Medium’ means the normal operational weight for flight segment. — ‘Night visual’ means a visual system capable of meeting, as a minimum, the system brightness and contrast ratio requirements and performance criteria appropriate for the level of qualification sought. The system, when used in training, should provide, as a minimum, all features applicable to the twilight scene, as defined below, with the exception of the need to portray reduced ambient intensity that removes ground cues that are not self-illuminating or illuminated by own ship lights (e.g. landing lights). — ‘Nominal’ means the normal operational weight, configuration, speed etc. for the flight segment specified. — ‘Non-normal control’ is a term used in reference to computer controlled aircraft. Non-normal control is the state where one or more of the intended control, augmentation or protection functions are not fully available. (Note: Specific terms such as ALTERNATE, DIRECT, SECONDARY, BACKUP, etc., may be used to define an actual level of degradation) — ‘Normal control’ is a term used in reference to computer controlled aircraft. Normal control is the state where the intended control, augmentation and protection functions are fully available. — ‘Objective test (objective testing)’ means a quantitative assessment based on comparison with data. — ‘One step’ refers to the degree of changes to an aircraft that would be allowed as an acceptable change, relative to a fully flight test validated simulation. The intention of the alternative approach is that changes would be limited to one, rather than a series, of steps away from the baseline configuration. It is understood, however, that those changes which support the primary change (e.g. weight, thrust rating and control system gain changes accompanying a body length change) are considered part of the ‘one step’. — ‘Power lever angle’ means the angle of the pilot's primary engine control lever(s) in the cockpit. This may also be referred to as PLA, THROTTLE, or POWER LEVER. — ‘Predicted data’ means data derived from sources other than type-specific aircraft flight tests. — ‘Primary reference document’ means any regulatory document which has been used by a competent authority to support the initial evaluation of an FSTD. — ‘Proof-of-match (POM)’ means a document that shows agreement within defined tolerances between model responses and flight test cases at identical test and atmospheric conditions. — ‘Protection functions’ means systems functions designed to protect an aircraft from exceeding its flight and manoeuvre limitations. — ‘Pulse input’ means an abrupt input to a control followed by an immediate return to the initial position. — ‘Reversible control system’ means a partially powered or unpowered control system in which movement of the control surface will backdrive the pilot’s control on the cockpit and/or affect its feel characteristics. — ‘Robotic test’ means a basic performance check of a system’s hardware and software components. Exact test conditions are defined to allow for repeatability. The components are tested in their normal operational configuration and may be tested independently of other system components. — ‘Snapshot’ means a presentation of one or more variables at a given instant of time. — ‘Statement of compliance (SOC)’ means a declaration that specific requirements have been met. — ‘Step input’ means an abrupt input held at a constant value. — ‘Subjective test (subjective testing)’ means a qualitative assessment based on established standards as interpreted by a suitably qualified person. — ‘Throttle lever angle (TLA)’ means the angle of the pilot’s primary engine control lever(s) on the cockpit. — ‘Time history’ means a presentation of the change of a variable with respect to time. — ‘Transport delay’ means the total FSTD system processing time required for an input signal from a pilot primary flight control until the motion system, visual system, or instrument response. It is the overall time delay incurred from signal input until output response. It does not include the characteristic delay of the aircraft simulated. — ‘Twilight (dusk/dawn) visual’ means a visual system capable of meeting, as a minimum, the system brightness and contrast ratio requirements and performance criteria appropriate for the level of qualification sought. The system, when used in training, should provide, as a minimum, full colour presentations of reduced ambient intensity (as compared with a daylight visual system), sufficient to conduct a visual approach, landing and airport movement (taxi). — ‘Update’ means the improvement or enhancement of an FSTD. — ‘Upgrade’ means the improvement or enhancement of an FSTD for the purpose of achieving a higher qualification. — ‘Validation data’ means data used to prove that the FSTD performance corresponds to that of the aircraft, class of aeroplane or type of helicopter — ‘Validation flight test data’ means performance, stability and control, and other necessary test parameters electrically or electronically recorded in an aircraft using a calibrated data acquisition system of sufficient resolution and verified as accurate by the organisation performing the test to establish a reference set of relevant parameters to which like FSTD parameters can be compared. — ‘Validation test’ means a test by which FSTD parameters can be compared with the relevant validation data. — ‘Vibration’ means a permanent effect resulting from airframe interaction with rotor, engine or transmission, as opposed to buffet which is a transient vibration effect resulting from either pilot action or aerodynamic effect on the airframe. — ‘Visual ground segment test’ means a test designed to assess items impacting the accuracy of the visual scene presented to the pilot at a decision height (DH) on an ILS approach. — ‘Visual system response time’ means the interval from an abrupt control input to the completion of the visual display scan of the first video field containing the resulting different information. — ‘Well-understood effect’ means an incremental change to a configuration or system which can be accurately modelled using proven predictive methods based on known characteristics of the change. (b) Abbreviations A = aeroplane AC = Advisory Circular ACJ = Advisory Circular Joint A/C = aircraft Ad = total initial displacement of pilot controller (initial displacement to final ADF = automatic direction finder resting amplitude) AFM = aircraft flight manual AFCS = automatic flight control system AGL = above ground level (metres or feet) An = sequential amplitude of overshoot after initial X axis crossing, e.g. A1 = 1st overshoot. AEO = all engines operating AOA = angle of attack (degrees) ARA = airborne radar approach ATO = approved training organisation BC = ILS localiser back course CAT I/II/III = landing category operations CCA = computer controlled aeroplane CCH = computer controlled helicopter cd/m2 = candela/metre2, 3·4263 candela/m2 = 1 ft-Lambert CG = centre of gravity cm(s) = centimetre, centimetres CS = Certification Specifications CT&M = correct trend and magnitude daN = decaNewtons dB = decibel deg(s) = degree, degrees DGPS = differential global positioning system DH = decision height DME = distance measuring equipment DPATO = defined point after take-off DPBL = define point before landing EPR = engine pressure ratio EW = empty weight FAA = United States Federal Aviation Administration FATO = final approach and take-off FD = flight director FOV = field of view FPM = feet per minute ft = feet, 1 foot = 0·304801 metres ft-Lambert = foot-Lambert, 1 ft-Lambert = 3·4263 candela/m2 g = acceleration due to gravity (m or ft/s2), 1g = 9·81 m/s2 or 32·2 ft/s2 G/S = glideslope GPS = global positioning system GPWS = ground proximity warning system H = helicopter HGS = head-up guidance system HSI = horizontal situation indicator IATA = International Air Transport Association ICAO = International Civil Aviation Organisation IGE = in ground effect ILS = instrument landing system IMC = instrument meteorological conditions in = inches, 1 in = 2·54 cm IOS = instructor operating station IPOM = integrated proof of match IQTG = International Qualification Test Guide (RAeS Document) km = kilometres, 1 km = 0·62137 statute miles kPa = kiloPascal (kiloNewton/metres2). 1 psi = 6·89476 kPa kts = knots calibrated airspeed unless otherwise specified, 1 knot = 0·5148 m/s or 1 689 ft/s lb = pounds LOC = localiser LOFT = line oriented flight training LOS = line oriented simulation LDP = landing decision point m = metres, 1 metre = 3.28083 ft MCC = multi-crew cooperation MCTM = maximum certificated take-off mass (kilos/pounds) MEH = multi-engined helicopter min = minutes MLG = main landing gear mm = millimetres MPa = megaPascals [1 psi = 6894·76 pascals] MQTG = master qualification test guide ms = millisecond(s) MTOW = maximum take-off weight n = sequential period of a full cycle of oscillation N = NORMAL CONTROL Used in reference to computer controlled aircraft N/A = not applicable N1 = engine low pressure rotor revolutions per minute expressed in per cent of maximum N1/Ng = gas generator speed N2 = engine high pressure rotor revolutions per minute expressed in per cent of maximum N2/Nf = free turbine speed NDB = non-directional beacon NM = nautical mile, 1 nautical mile = 6 080 ft = 1 852 m NN = non-normal control a state referring to computer controlled aircraft NR = main rotor speed NWA = nosewheel angle (degrees) OEI = one-engine-inoperative OGE = out of ground effect OM-B = operations manual – Part B (AFM) OTD = other training device P0 = time from pilot controller release until initial X axis crossing (X axis defined by the resting amplitude) P1 = first full cycle of oscillation after the initial X axis crossing P2 = second full cycle of oscillation after the initial X axis crossing PANS = procedure for air navigation services PAPI = precision approach path indicator system PAR = precision approach radar Pf = impact or feel pressure PLA = power lever angle PLF = power for level flight Pn = sequential period of oscillation POM = proof-of-match PSD = power spectral density psi = pounds per square inch. (1 psi = 6.89476 kPa) PTT = part-task trainer QTG = qualification test guide R/C = rate of climb (m/s or ft/min) R/D = rate of descent (metres/s or ft/min) RAE = Royal Aerospace Establishment RAeS = Royal Aeronautical Society REIL = runway end identifier lights RNAV = radio navigation RVR = runway visual range (m or ft) s = second(s) sec(s) = second, seconds sm = statute mile, 1 statute mile = 5 280 ft = 1 609 m SOC = Statement of Compliance SUPPS = Supplementary procedures referring to regional supplementary procedures TCAS = traffic alert and collision avoidance system T(A) = tolerance applied to amplitude T(p) = tolerance applied to period T/O = take-off Tf = total time of the flare manoeuvre duration Ti = total time from initial throttle movement until a 10 % response of a critical engine parameter TLA = throttle lever angle TLOF = touch down and lift-off TDP = take-off decision point Tt = total time from Ti to a 90 % increase or decrease in the power level specified VASI = visual approach slope indicator system VDR = validation data roadmap VFR = visual flight rules VGS = visual ground segment Vmca = minimum control speed (air) Vmcg = minimum control speed (ground) Vmcl = minimum control speed (landing) VOR = VHF omni-directional range Vr = rotate speed VS = stall speed or minimum speed in the stall V1 = critical decision speed VTOSS = take-off safety speed VY = optimum climbing speed Vw = wind velocity WAT = weight, altitude, temperature