CAPÍTULO II: LA LETRA DE CAMBIO, EL PAGARÉ A LA ORDEN Y LA FACTURA COMERCIAL
2.1 La Letra de Cambio
2.1.3 Funciones de la Letra de Cambio
2.1.3.2 Función Jurídica
(a) Instruments and instrument lines
(1) Each powerplant instrument line must meet the requirements of CS LURS.961 and 993 . (2) Each line carrying flammable fluids under pressure must -
(i) Have restricting orifices or other safety devices at the source of pressure to prevent the escape of excessive fluid if the line fails; and (ii) Be installed and located so that the escape of fluids would not create a hazard.
(3) Each powerplant instrument sensing device that utilises flammable fluids must be installed and located so that the escape of fluid would not create a hazard. (b) Fuel flow meter system. If a fuel flow meter system is installed, each metering component must have a means for bypassing the fuel supply if malfunction of that
component severely restricts fuel flow.
(c) Oil quantity indicator. There must be means to indicate the quantity of oil in each tank on the ground (including during the filling of each tank).
(d) Rotor drive system transmissions and gearboxes utilizing ferromagnetic materials must be equipped with chip detectors designed to indicate or reveal the presence of ferromagnetic particles resulting from damage or excessive wear. Chip detectors must be removable for inspection of the magnetic poles for metallic chips
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CS-LURS.1351 General
(a) Electrical system capacity. Electrical equipment must be adequate for its intended use. In addition-
(1) Electric power sources, their transmission cables, and their associated control and protective devices must be able to furnish the required power at the proper voltage to each load circuit essential for safe operation; and
(2) Compliance with sub-paragraph (a)(1) must be shown by an electrical load analysis, or by electrical measurements that take into account the electrical loads applied to the electrical system in probable combinations and for probable durations.
(b) Function. For each electrical system, the following apply: (1) Each system when installed, must be -
(i) Free from hazards in itself, in its method of operation, and in its effects on other parts of the rotorcraft; and (ii) Protected from fuel, oil, water other detrimental substances, and mechanical damage.
(2) Electric power sources must function properly when connected in combination or independently, except that alternators may depend on a battery for initial excitation or for stabilization.
(3) No failure or malfunction of any source may impair the ability of any remaining source to supply load circuits essential for safe operation, except that the operation of an alternator that depends on a battery for initial excitation or for stabilization may be stopped by failure of that battery
(4) Each electric power source control must allow the independent operation of each source, except that controls associated with alternators that depend on a battery for initial excitation or for stabilization need not break connection between the alternator and its battery.
(c) Generating system, if installed. There must be at least one generator if the system supplies power to load circuits essential for safe operation. In addition- (1) Each generator must be able to deliver its continuous rated power;
(2) Generator voltage control equipment must be able to dependably regulate each generator output within rated limits;
(3) Each generator must have a reverse current cutout designed to disconnect the generator from the battery and from the other generators when enough reverse current exists to damage that generator.
(4) Each generator must have an overvoltage control designed and installed to prevent damage to the electrical system, or to equipment supplied by the electrical system, that could result if that generator were to develop an overvoltage condition; and
(5) There must be a means to give immediate warning to the UA Pilot of a failure of any generator. (d) NA
(e) Fire resistance. Electrical equipment must be so designed and installed that in the event of a fire in the engine compartment, during which the surface of the firewall adjacent to the fire is heated to 1100°C for 5 minutes or to a lesser temperature substantiated by the applicant, the equipment essential to continued safe operation and located behind the firewall will function satisfactorily and will not create and additional fire hazard. This may be shown by test or analysis.
(f) External power. If provisions are made for connecting external power to the rotorcraft, and that external power can be electrically connected to equipment other than that used for engine starting, means must be provided to ensure that no external power supply having a reverse polarity, or reverse phase sequence, can supply power to the rotorcraft's electrical system.
(g) It must be shown by analysis, tests or both, that the UAS (UAV + Ground Station) can be operated safely in the approved operational envelope according CS- LURS.23, for a period required to perform the emergency recovery procedure according CS-LURS.1412 in case of normal (main) electrical power inoperative
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CS-LURS.1353 Storage battery design and installation
(a) Each storage battery must be designed and installed as prescribed in this paragraph.
(b) Safe cell temperatures and pressures must be maintained during any probable charging and discharging condition. No uncontrolled increase in cell temperature may result when the battery is recharged (after previous complete discharge) -
(1) At maximum regulated voltage or power; (2) During a flight of maximum duration; and
(3) Under the most adverse cooling condition likely to occur in service.
(c) Compliance with sub-paragraph (b) must be shown by test or experience with similar batteries and installations.
(d) No explosive or toxic gases emitted by any battery in normal operation, or as the result of any probable malfunction in the charging system or battery installation, may accumulate in hazardous quantities within the rotorcraft.
(e) No corrosive fluids or gases that may escape from the battery may damage surrounding structures or adjacent essential equipment.
(f) Each battery installation capable of being used to start an engine or auxiliary power unit must have provisions to prevent any hazardous effect on structure of essential systems that may be caused by the maximum amount of heat the battery can generate during a short circuit of the battery or its individual cells.
(g) Battery installations capable of being used to start an engine or auxiliary power unit must have -
(1) A system to control the charging rate of the battery automatically so as to prevent battery overheating;
(2) A battery temperature sensing and over temperature warning system with means for disconnecting the battery from its charging source in the event of an over- temperature condition; or
(3) A battery failure sensing and warning system with a means for disconnecting the battery from its charging source in the event of battery failure.
CS-LURS.1357 Circuit protective devices
(a) Protective devices, such as circuit breakers, must be installed in each electrical circuit other than- (1) The main circuits of starter motors; and
(2) Circuits in which no hazard is presented by their omission.
(b) A protective device for a circuit essential to flight safety may not be used to protect any other circuit.
(c) Where installed, each remotely resettable circuit protective device (“trip free” device in which the tripping mechanism cannot be over-ridden by the operating control) must be designed so that
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(2) If an overload or circuit fault exists, the device will open the circuit regardless of the position of the operating control.
(3) Where automatic resettable circuit protection devices are used they must be designed so they comply with (c) (2) and restore circuit integrity on removal of fault condition.
(d) If the ability to reset a circuit breaker is essential to safety in flight, that circuit must be located and identified so that it can be readily remotely reset in flight.
CS-LURS.1359 Electrical system fire protection
(a) Components of the electrical system must meet the applicable fire protection requirements of CS-LURS.861 and CS-LURS.1183.
(b) Electrical cables, terminals and equipment in designated fire zones, that are used during emergency procedures, must be at least fire-resistant.
(c) Insulation on electrical wire and cable must be self-extinguishing when tested at an angle of 60° in accordance with approved methods. The average burn length must not exceed 76 mm (3 in) and the average flame time after removal of the flame source must not exceed 30 seconds. Drippings from the test specimen must not continue to flame for more than an average of 3 seconds after falling.
CS-LURS.1361 UA Electrical Load Shedding
(a) There must be an easily discernible and accessible means to allow ready shedding of electrical loads on the UA.
(b) Load shedding must be achieved by disconnection of all electric power sources on the UA from the power distribution systems except load circuits that are required for continued safe flight and landing
(c) The point of disconnection must be adjacent to the power sources controlled.
CS-LURS.1365 Electric cables
(a) Each electric connecting cable must be of adequate capacity and correctly routed, attached and connected so as to minimize the probability of short circuits and fire hazards.
(b) Each cable and associated equipment that would overheat in the event of circuit overload or fault must be at least flame resistant and may not emit dangerous quantities of toxic fumes.
CS-LURS.1367 Switches
Each switch must be
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(b) Constructed with enough distance or insulating material between current carrying parts and the housing so that vibration in flight will not cause shorting; (c) Accessible to appropriate maintenance staff ; and
(d) Labeled as to operation and the circuit controlled
LIGHTS CS-LURS.1384 External lights
a) If external lights are installed for see & avoid purpose, then they must comply with paragraphs 27.1385 to 27.1401 of CS-27 as appropriate. b) For RPA where a) is impractical, a special condition applies.
SAFETY EQUIPMENT
CS-LURS 1412 Flight Termination System (FTS)
CS-LURS.1412 Emergency recovery capability
(see AMC CS-LURS.1412)
(a) The UAS must integrate an emergency recovery capability to prevent third party risk that consists of : (1) a flight termination system, procedure or function that aims to immediately end the flight, or,
(2) an emergency recovery procedure that is implemented through UA crew command or by the onboard systems. This may include automatic pre-programmed course of action to reach a predefined and unpopulated forced landing area, or,
(3) any combination of CS-LURS.1412 (a) (1) and CS-LURS.1412 (a) (2).
(b) The emergency recovery capability must be achievable in the whole flight envelope under the most adverse combination of environmental and operating conditions (c) The emergency recovery capability must be safeguarded from interference leading to inadvertent or unauthorized operation.
(d) The emergency recovery capability must receives its electrical power, if needed, from the bus that provides the maximum reliability for operation.. (e) The emergency recovery capability must be achievable after loss of the primary electrical system.
(f) Use of explosives to perform in-flight destruction of the air vehicle is not an acceptable means of compliance to this requirement
CS-LURS.1413 Contingency procedures
See AMC CS-LURS.1413