Publication: Magyar Közlöny
Issue: MK-2007-70 (Year: 2007, Number: 70)
Era: 2004-2010
Section: Melléklet a 2007. évi XLVI. törvényhez
Paragraph Index: 3109

a) b) and c) Note uidance material on the testing of ND s is contained in of Attachment C 3 Specification for HF distance measuring e uipment D E Note In the following section provision is made for two types of DME facility DME N for application as outlined in Chapter and DME P as outlined in Note In the following paragraphs those denoted by are applicable to e uipment first installed after anuary (Chapter ) 3.5.1 Definitions Control motion noise (C ) That portion of the guidance signal error which causes control surface, wheel and column motion and could affect aircraft attitude angle during coupled flight, but does not cause aircraft displacement from the desired course and/or glide path. (See 3.11.) dead time A period immediately following the decoding of a valid interrogation during which a received interrogation will not cause a reply to be generated. Note Dead time is intended to prevent the transponder from replying to echoes resulting from multipath effects Distance measuring equipment, primarily serving operational needs of en-route or TMA navigation, where the “N” stands for narrow spectrum characteristics. The distance measuring element of the MLS, where the “P” stands for precise distance measurement. The spectrum characteristics are those of DME/N. uivalent isotro icall radiated ower (e i r ) The product of the power supplied to the antenna and the antenna gain in a given direction relative to an isotropic antenna (absolute or isotropic gain). Final a roac (FA) mode The condition of DME/P operation which supports flight operations in the final approach and runway regions. Initial a roac (IA) mode The condition of DME/P operation which supports those flight operations outside the final approach region and which is interoperable with DME/N. e down time The time during which a dot or dash of a Morse character is being transmitted. a roac re erence datum A point on the minimum glide path at a specified height above the threshold. (See 3.11.) datum oint The point on the runway centre line closest to the phase centre of the approach elevation antenna. (See 3.11.) 2007/70/II. szám C a ter Annex 10 — Aeronautical Communications 3 3 23/11/06 ode A method of coding the DME transmissions by time spacing pulses of a pulse pair, so that each frequency can be used more than once. artial rise time The time as measured between the 5 and 30 per cent amplitude points on the leading edge of the pulse envelope, i.e. between points h and i on Figures 3-1 and 3-2. at ollowin error ( F ) That portion of the guidance signal error which could cause aircraft displacement from the desired course and/or glide path. (See 3.11.) ulse am litude The maximum voltage of the pulse envelope, i.e. A in Figure 3-1. ulse deca time The time as measured between the 90 and 10 per cent amplitude points on the trailing edge of the pulse envelope, i.e. between points e and g on Figure 3-1. ulse code The method of differentiating between W, X, Y and modes and between FA and IA modes. ulse duration The time interval between the 50 per cent amplitude point on leading and trailing edges of the pulse envelope, i.e. between points b and f on Figure 3-1. ulse rise time The time as measured between the 10 and 90 per cent amplitude points on the leading edge of the pulse envelope, i.e. between points a and c on Figure 3-1. e l e icienc The ratio of replies transmitted by the transponder to the total of received valid interrogations. earc The condition which exists when the DME interrogator is attempting to acquire and lock onto the response to its own interrogations from the selected transponder. stem e icienc The ratio of valid replies processed by the interrogator to the total of its own interrogations. rac The condition which exists when the DME interrogator has locked onto replies in response to its own interrogations, and is continuously providing a distance measurement. ransmission rate The average number of pulse pairs transmitted from the transponder per second. Virtual ori in The point at which the straight line through the 30 per cent and 5 per cent amplitude points on the pulse leading edge intersects the 0 per cent amplitude axis (see Figure 3-2). 3.5.2 General 3.5.2.1 The DME system shall provide for continuous and accurate indication in the cockpit of the slant range distance of an equipped aircraft from an equipped ground reference point. 3.5.2.2 The system shall comprise two basic components, one fitted in the aircraft, the other installed on the ground. The aircraft component shall be referred to as the interrogator and the ground component as the transponder. 3.5.2.3 In operation, interrogators shall interrogate transponders which shall, in turn, transmit to the interrogator replies synchronized with the interrogations, thus providing means for accurate measurement of distance. 3.5.2.4 DME/P shall have two operating modes, IA and FA. 2007/70/II. szám Annex 10 — Aeronautical Communications Volume I 23/11/06 3 3 Figure 3 1 Figure 3 2 c e b d i f g h 0,05A 0,1A a 0,3A 0,5A Voltage amplitude (A) Time Pulse envelope A 0,9A 0,3A 0,05A Voltage amplitude (A) h i Partial rise time Time Virtual origin 2007/70/II. szám C a ter Annex 10 — Aeronautical Communications 3 3 23/11/06 3.5.2.5 When a DME function is combined with either an ILS, MLS or VOR for the purpose of constituting a single facility, they shall be considered to be associated in a manner complying with Chapter 2, 2.2.2, only when:

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