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Frequency
Maximum level of undesired signals
at the receiver input (dBm)
88 MHz ≤ f ≤ 104 MHz 15
106 MHz 10
107 MHz 5
107.9 MHz 0
Note.— The relationship is linear between single adjacent points designated by the above
frequencies.
use a ranging source in the differential navigation solution if the time of
ount in the Type 1 or Type 101 message containing the ephemeris decorrelation
ara
ubsystem for Category I precision approach or
PV guidance only if the GCID indicates 1, 2, 3 or 4 prior to initiating the final stages of an approach.
the final stages of an approach.
3.6.8.3.1.8.4 The receiver shall not provide approach vertical guidance based on a particular FAS data block
L received prior to initiating the final stages of the approach is set to “1111
3.6.8.3.1.8.5 The receiver shall not provide approach guidance based on a particular FAS data block transmitted in a
Type 4 message if the FASLAL received prior to initiating the final stages of the approach is set to “1111 1111”.
3.6.8.3.1.8.6 Changes in the values of FASLAL and FASVAL data transmitted in a Type 4 message during the final
stages of an approach shall be ignored by the receiver.
3.6.8.3.1.8.7 The receiver shall use FAS data only if the FAS CRC for that data has been verified.
3.6.8.3.1.8.8 The receiver shall only use messages for which the GBAS ID (in the message block header) matches the
GBAS ID in the header of the Type 4 message which contains the selected FAS data or the Type 2 message which contains
the selected RSDS.
3.6.8.3.1.8.9 Use of FAS data
3.6.8.3.1.8.9.1 The receiver shall use the Type 4 messages to determine the FAS for precision approach.
3.6.8.3.1. r shall use the Type 4 messages to determine the FAS for APV associated with a channel
number between 20 001 and 39 999.
3.6.8.3.1.7 The receiver shall only
applicability indicated by the modified Z-c
p meter for that ranging source is less than 120 seconds old.
3.6.8.3.1.8 Conditions for use of data to support Category I precision approach and APV
3.6.8.3.1.8.1 During the final stages of a Category I or APV approach, the receiver shall use only measurement blocks
from Type 1 or Type 101 messages that were received within the last 3.5 seconds.
3.6.8.3.1.8.2 The receiver shall use message data from a GBAS ground s
A
3.6.8.3.1.8.3 The receiver shall ignore any changes in GCID during
transmitted in a Type 4 message if the FASVA
1111”.
8.9.2 The receive
23/11/06 APP B-118
Appendix B Annex 10 — Aeronautical Communications
3.6.8.3.1.8.9.3 The receiver shall use the FAS held within the on-board database for APV associated with a channel
number between 40 000 and 99 999.
irborne database, the receiver shall only use messages from the intended GBAS ground
bsystem.
ositioning service
3.6.8.3.1.9.1 The receiver shall only use measurement blocks from Type 1 messages that were received within the last
.5 seconds.
e containing additional data block 1 has been
received and the RSDS parameter in this bloc ng service is provided.
3.6.8.3.1.9.4 The receiver shall only u (in the message block header) matches the
BAS ID in the header of the Type 2 message .
.6.8.3.2 Integrity
3.6.8.3.2.1 Bounding of aircraft errors. For each satellite use navigation ion, the receiver shall compute a
σreceiver such that a normal distri nd a standard deviat al to σreceiver bounds the receiver
ontribution to the corrected pseudo-range error as follows:
3.6.8.3.1.8.10 When the GBAS ground subsystem does not broadcast the Type 4 message and the selected FAS data
are available to the receiver from an a
su
.6.8.3.1.9 3 Conditions for use of data to provide the GBAS p
7
3.6.8.3.1.9.2 The receiver shall only use measurement blocks from Type 101 messages that were received within the
last 5 seconds.
3.6.8.3.1.9.3 The receiver shall only use message data if a Type 2 messag
k indicates that the GBAS positioni
se messages for which the GBAS ID
G which contains the selected RSDS
3
d in the solut
bution with zero mean a ion equ
c
y
f (x) dx Qy for all y 0 and
∞ ∫ ≤ ⎛⎜ ⎞⎟ ≥
⎝σ⎠ σ
y f (x) dx Qy for all y 0
−
−∞
≤ ⎛⎜σ⎞⎟ σ ≥
he
⎝ ⎠ ∫
w re
f(x) = probability density function of the residual aircraft pseudo-range error and
1 ∞ − t2
3.6.8.3.2.2 Use of GBAS integrity parameters. The aircraft element shall compute and apply the vertical, lateral and
rizontal protection levels described , σvert_iono_gradient, and B parameters as
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