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ell as the σpr_air parameter. If a Bi,j dicating that the measurement is not
ume that Bi,j has a value of zero. For Category I precision approach and APV, the
computed vertical and lateral protection levels are smaller than the corresponding vertical
nd lateral alert limits defined in 3.6.5.6.
2
x
Q(x) e dt.
2
=
π ∫
ho in 3.6.5.5 using the GBAS broadcast σpr_gnd, σN, h0
w parameter is set to the bit pattern “1000 0000” in
available, the aircraft element shall ass
ircraft element shall verify that the aa APP B-119 23/11/06
Annex 10 — Aeronautical Communications Volume I
3.6.8.3.3 Use of satellite ephemeris data
3.6.8.3.3.1 IOD check. The receiver shall only use satellites for which the IOD broadcast by GBAS in the Type 1 or
Type 101 message matches the core satellite constellation IOD for the clock and ephemeris data used by the receiver.
C values fail to match.
initial acquisition of the VHF data broadcast, the receiver may incorporate a satellite into the position
adcast ephemeris CRC for that satellite.
emeris error position bounds (VEBj or LEBj) are larger than the corresponding
ertical and lateral alert limits defined in 3.6.5.6.
Note.— During initial acquisition of the VHF data broadcast, the receiver may incorporate a satellite into the position
solution before receivin hemeris error position
bounds.
3.6.8.3.3.3.2 Epheme n bound for the GBAS posit lement shall compute and
apply the horizontal ephemeris error position bound (HEB ) defined in 3.6.5.8.2 for each core satellite constellation’s ranging
source used in the position solution.
3.6.8.3.4 Message loss
3.6.8.3.4.1 For Category I precision approach, the pe 1 or Type 101
message was received during the last 3.5 seconds.
3.6.8.3.4.2 For APV, the receiver shall provide essage was
received during the last 3.5 seconds.
3.6.8.3.4 eceiver shall provide an appropriate alert if
o Type 1 message was received during the last 7.5 seconds.
3.6.8.3.4.4 For the GBAS positioning service using Type 101 messages, the receiver shall provide an appropriate alert
no Type 101 message was received
3.6.8.3.5 Airborne pseudo-range measurements. Pseudo-range m oothed using
the carrier measurement a filter which deviates less th ter initialization,
relative to the steady-state respo e of the filter defined in 3.6.5.1 in the presence of drift between the code phase and
integrated carrier phase of up to 0.01 metre per second.
3.6.8.3.3.2 CRC check. The receiver shall compute the ephemeris CRC for each core satellite constellation’s ranging
source used in the position solution. The computed CRC shall be validated against the ephemeris CRC broadcast in the Type
1 or Type 101 messages within one second of receiving a new broadcast CRC. The receiver shall immediately cease using
any satellite for which the computed and broadcast CR
Note.— During
solution before receiving the bro
3.6.8.3.3.3 Ephemeris error position bounds
3.6.8.3.3.3.1 Ephemeris error position bounds for Category I precision approach and APV. If the ground subsystem
provides additional data block 1 in the Type 2 messages, the aircraft element shall compute the ephemeris error position
bounds defined in 3.6.5.8.1 for each core satellite constellation’s ranging source used in the position solution within 1s of
receiving the necessary broadcast parameters. The aircraft element shall exclude from the position solution satellites for
hich the computed vertical or lateral eph wv
g the necessary broadcast parameters for that satellite to compute the ep
ris error positio ioning service. The aircraft e
j
receiver shall provide an appropriate alert if no Ty
an appropriate alert if no Type 1 and no Type 101 m
.3 For the GBAS positioning service using Type 1 messages, the r
n
if during the last 5 seconds.
easurement for each satellite shall be sm
nd a smoothing an 0.1 metre within 200 seconds af
ns
23/11/06 APP B-120
Appendix B Annex 10 — Aeronautical Communications
3.7 Resistance to interference
3.7.1 PERFOR CTIVES
Note 1.— For unaugmented GPS and GLONASS receiv respect to the
following performance parameters:
GP
MANCE OBJE
ers the resistance to interference is measured with
S GLONASS
Tracking error (1 sigma) 0.4 m 0.8 m
Note 2.— This tracking error neither includes contribu ropospheric
and ionospheric effects nor ephemeris and GPS and GLONASS satellite clock errors.
No to parameters specified in
3.5.8.2.1 and 3.5.8.4.1.
Note 4.— For GBAS receivers, the resistance to interference is measured with respect to parameters specified in
　
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