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Antenna pattern loss, dB –4 –2 –5 –5
Path loss, dB –125 –115 –107 –103
Monitor loss, dB –1 –1 –1 –1
Polarization and rain loss, dB –1 –1 0 0
Received signal at aircraft, dBm –81 –67 –62 –71
Power density at aircraft, dBW/m2 –89 –75 –70 –79
Aircraft antenna gain, dB 0 0 0 0
Aircraft cable loss, dB –4 –4 –4 –4
Received signal at interrogator, dBm –85 –71 –66 –75
Receiver noise video, dBm
(Noise factor (NF) = 9 dB)
IF BW: 3.5 MHz
IF BW: 0.8 MHz –109
–103
–103
–103
Signal-to-noise ratio (video), dB 24 32 37 28
Table C-8. CTOL air-to-ground power budget
Power budget items
41 km
(22 NM)
13 km
(7 NM)
Ref.
datum Roll-out
Interrogator transmitter power, dBm 57 57 57 57
Aircraft antenna gain, dB 0 0 0 0
Aircraft cable loss, dB –4 –4 –4 –4
Peak effective radiated power, dBm 53 53 53 53
Ground multipath loss, dB –5 –3 –4 –17
Path loss, dB –125 –115 –107 –103
Polarization and rain loss, dB –1 –1 0 0
Received signal at transponder antenna, dBm –78 –66 –58 –67
Ground antenna gain, dB 8 8 8 8
Pattern loss, dB –4 –2 –5 –5
Cable loss, dB –3 –3 –3 –3
Received signal at transponder, dBm –77 –63 –58 –67
Receiver noise video, dBm
(Noise factor (NF) = 9 dB)
IF BW: 3.5 MHz
IF BW: 0.8 MHz –112
–106
–106
–106
Signal-to-noise ratio (video), dB 35 43 48 39
ATT C-81 23/11/06
Annex 10 — Aeronautical Communications Volume I
7.3.8.2 In the power budget calculations, it is assumed that the aircraft antenna is not shielded by the aircraft structure
including the landing gear when extended.
7.3.8.3 The video power signal-to-noise ratio is related to the IF power signal-to-noise ratio in the following manner:
IF noise bandwidth
S/N (video) = S/N (IF) + 10 log
video noise bandwidth
Note 1.— The distances are measured from the transponder antenna.
Note 2.— Frequency dependent parameters were calculated for 1 088 MHz.
7.3.9 DME/P monitor time delay measurement
The required time delay measurement can be accomplished by measuring the output of a PFE filter and making a control
decision within 1 second. However, since the transponder PFE is a slowly varying error component, an equivalent
measurement is to average the unfiltered time delay samples for 1 second.
8. Material concerning power supply switch-over times
8.1 Power supply switch-over times for ground-based radio aids used in the vicinity of aerodromes
The power supply switch-over times for radio navigation aids and ground elements of communications systems are
dependent on the type of runway and aircraft operations to be supported. Table C-9 indicates representative switch-over times
which may be met by power supply systems currently available.
Table C-9. Power supply switch-over times for ground-based radio aids used at aerodromes
Type of runway Aids requiring power
Maximum
switch-over times
(seconds)
Instrument approach SRE
VOR
NDB
D/F facility
15
15
15
15
Precision approach, Category I ILS localizer
ILS glide path
ILS middle marker
ILS outer marker
PAR
10
10
10
10
10
Precision approach, Category II ILS localizer
ILS glide path
ILS inner marker
ILS middle marker
ILS outer marker
0
0
1
1
10
Precision approach, Category III (same as Category II)
___________________
23/11/06 ATT C-82
ATTACHMENT D. INFORMATION AND MATERIAL
FOR GUIDANCE IN THE APPLICATION OF THE
GNSS STANDARDS AND RECOMMENDED PRACTICES
1. Definitions
Bi-binary. Bi-binary is known as “Manchester Encoding”. It is sometimes referred to as “Differential Manchester Encoding”.
Using this system, it is the transition of the edge that determines the bit.
Chip. A single digital bit of the output of a pseudo-random bit sequence.
Gold code. A class of unique codes used by GPS, which exhibit bounded cross-correlation and off-peak auto-correlation
values.
Selective availability (SA). A set of techniques for denying the full accuracy and selecting the level of positioning, velocity
and time accuracy of GPS available to users of the standard positioning service signal.
　
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