Publication: Magyar Közlöny
Issue: MK-2007-70 (Year: 2007, Number: 70)
Era: 2004-2010
Section: Melléklet a 2007. évi XLVI. törvényhez
Paragraph Index: 3513

b) 46 dB abov 3.6.8.2.2.7 Re ith no on-channel data broadcast signal present, the VHF data broadcast receiver shall not output data from an undesired VHF data roadcast signal on any other assignable channel. 3.6.8.2.2.8 Rejection of signals from sources outside the M band 3.6.8.2.2.8.2 Desensiti ation. The VHF data broadcast receiver shall meet the requirements specified in 3.6.8.2.2.3 in the presence of VHF FM broadcast signals with signal levels shown in Tables B-80 and B-81. 3.6.8.2.2.8.3 F dat st receiver shall meet the requirements specified in 3.6 ntermodulation products of two VHF FM broadcast signals having levels in accordance with the following: 2N1 N2 72  0 for VHF FM soun the range 107.7 108.0 MHz an signal is another VHF data broa me slot(s); e the desired signal power when the undesired signal is VOR. jection of off channel signals from sources inside the M band W VHF b 3.6.8.2.2.8.1 F data broadcast interference immunity The VHF data broadcast receiver shall meet the requirements specified in 3.6.8.2.2.3 in the presence of one or more signals having the frequency and total interference levels specified in Table B-79. a broadcast FM intermodulation immunity. The VHF data broadca .8.2.2.3 in the presence of interference from two-signal, third-order i d broadcasting signals in d f 2N N 3 24 20 log 0.4 ' § ·    d ¨ ¸ © ¹ below 107.7 MHz for VHF FM sound broadcasting signals where the frequencies VHF FM sound broadcasting signals produce, within the receiver, a two signal, third-order termodulation product on the desired VDB frequency. 1 and N2 are the levels (dBm) of the two VHF FM sound broadcasting signals at the VHF data broadcast receiver input. und broadcasting signal closer to 108.1 MHz. ata broadcast channel operating below M hence fre uencies below M are not intended for general assignments Additional information is en verified. 3.6.8.3.1.3 The receiver shall use only ranging source measurement blocks with matching modified -counts. of the two in N Neither level shall exceed the desensitization criteria set forth in 3.6.8.2.2.8.2. ǻf 108.1 f1, where f1 is the frequency of N1, the VHF FM so Note The FM intermodulation immunity re uirements are not applied to a F d provided in Attachment D 3.6.8.3 AIRCRAFT FUNCTI NA RE UIREMENTS .6.8.3.1 Conditions for use of data 3.6.8.3.1.1 The receiver shall use data from a GBAS message only if the CRC of that message has be 3.6.8.3.1.2 The receiver shall use message data only if the message block identifier is set to the bit pattern “1010 1010”. 23/11/06 A 2007/70/II. szám A endix Annex 10 — Aeronautical Communications able aximum le els of undesired signals Frequency the receiver input (dBm) Maximum level of undesired signals at 50 kHz up to 88 MHz 108.000 MHz 117.975 MHz excluded 18.050 MHz up to 1 660.5 MHz Notes ship is linear between single adjacent points designated by the above fre uencies These interference immunity re uirements may not be ade uate to ensure compatibility between F vertically polari ed component of the F data broadcast ithout coordination between C M and have to be implemented The final compatibility will have to be assured when e uipment is installed on the aircraft 88 MHz 107.900 MHz (see 3.6.8.2.2.8.2) 118.000 MHz 118.025 MHz The relation data broadcast receivers and F communication systems particularly for aircraft that use the NA fre uencies assignments or respect of a guard band at the top end of the M band the maximum levels uoted at the lowest C M F channels ( ) may be exceeded at the input of the D receivers In that case some means to attenuate the C M signals at the input of the D receivers (e g antenna separation) will able 0 Desensiti ation fre uency and po er re uirements t at apply for D fre uencies from 10 02 to 111 H Maximum level of undesired signals Frequency at the receiver input (dBm) 88 MHz  f  102 MHz 106 MHz 107.9 MHz 104 MHz Notes The relationship is linear between single adjacent points designated by the above fre uencies This desensiti ation re uirement is not applied for FM carriers above M and D channels at or M See Attachment D max is broadcast by the ground subsystem, the receiver shall only apply pseudo-range corrections when th AS reference point is less than Dmax. 3.6.8.3.1.5 The receiver shall only apply pseudo-range corrections from the most recently received set of corrections for a given measurement type. If the number of measurement fields in the most recently received Type 1 or Type 101 essage indicates that there are no measurement blocks, then the receiver shall not apply GBAS corrections for that easurement type. 3.6.8.3.1.6 The receiver shall exclude from the differential navigation solution any ranging sources for which ıpr_gnd is set to the bit pattern “1111 1111”. 3.6.8.3.1.4 If D e distance to the GB m m A 23/11/06 2007/70/II. szám Annex 10 — Aeronautical Communications Volume I able 1 Desensiti ation fre uency and po er re uirements t at apply for D fre uencies from 112 000 to 11 H Frequency Maximum level of undesired signals at the receiver input (dBm) 88 MHz  f  104 MHz 106 MHz 107 MHz 107.9 MHz Note The relationship is linear between single adjacent points designated by the above fre uencies 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 -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 AP 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 A 2007/70/II. szám A endix 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 ounding of aircraft errors For each satellite use navigation ion, the receiver shall compute a ıreceiver such that a normal distri nd a standard deviat al to ıreceiver 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 Conditions for use of data to provide the AS p 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 which contains the selected RSDS G d in the solut bution with zero mean a ion equ c y y y f(x) dx Q for all 0 and f § · d t ¨ ¸ ³ V V © ¹ y y y f(x) dx Q for all  f § · d t ¨ ¸ V V he © ¹ ³ w re f(x) probability density function of the residual aircraft pseudo-range error and 2t f  3.6.8.3.2.2 Use of AS integrity parameters. The aircraft element shall compute and apply the vertical, lateral and rizontal protection levels described , ıvert_iono_gradient, and B parameters as ell as the ıpr_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. x Q(x) e dt. S ³ ho in 3.6.5.5 using the GBAS broadcast ıpr_gnd, ıN, h0 parameter is set to the bit pattern “1000 0000” in w available, the aircraft element shall ass ircraft element shall verify that the a a A 23/11/06 2007/70/II. szám Annex 10 — Aeronautical Communications Volume I 3.6.8.3.3 Use of satellite ephemeris data 3.6.8.3.3.1 I D chec 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 ac uisition of the F 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 ac uisition of the F 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 AS 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 chec . 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 AP . 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 w v 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 an 0 ds af nd a smoothing .1 metre within 200 secon ns 23/11/06 A 2007/70/II. szám A endix Annex 10 — Aeronautical Communications Resistance to interference 3.7.1 PERFOR CTIVES Note For unaugmented PS and NASS receiv respect to the following performance parameters P MANCE OBJE ers the resistance to interference is measured with S NASS Trac ing error ( sigma) m m Note This trac ing error neither includes contribu ropospheric and ionospheric effects nor ephemeris and PS and NASS satellite cloc errors No to parameters specified in and Note For AS receivers the resistance to interference is measured with respect to parameters specified in and Note The signal levels specified in this section include a minimum standard antenna gain above degree elevation mum aircraft antenna gain in the lower hemisphere is d ic For non standard antennas with a different minimum gain above degree elevation angle the signal interference levels can be adjusted accordingly as long as the relative interference to signal level is maintained Note The performance re uirements are to be met in the interference environments defined below for various phases of flight 3.7.2 CONTINUOUS WAVE (CW) INTERFERENCE wer level at the o the interference thresholds specified in Table B-82 and shown in Figure B-15 and with a desired signal na port. 3.7.2.1.2 GPS and SBAS receivers used for non-precision approach shall meet the performance objectives with interference thresholds 3 dB less than specified in Table B-82. For terminal area and en-route steady-state navigation operations and for initial acquisition of the GPS and SBAS signals prior to steady-state navigation, the interference thresholds shall be 6 dB less than those specified in Table B-82. .7.2.2 NASS RECEI ERS 3.7.2.2.1 GLONASS receivers used for the precision approach phase of flight or used on aircraft with on-board satellite communications shall meet the performance objectives with CW interfering signals present with a power level at the antenna port equal to the interference thresholds specified in Table B-83 and shown in Figure B-16 and with a desired signal level of 165.5 dBW at the antenna port. tions due to signal propagation such as multipath t te For S AS receivers the resistance to interference is measured with respect angle of d ic Assumed maxi 3.7.2.1 PS AND S AS RECEI ERS 3.7.2.1.1 GPS and SBAS receivers used for the precision approach phase of flight or used on aircraft with on-board satellite communications shall meet the performance objectives with CW interfering signals present with a po antenna port equal t level of 164.5 dBW at the anten A 23/11/06 2007/70/II. szám Annex 10 — Aeronautical Communications Volume I 3.7.2.2.2 GLONASS receivers used for non-precision approach shall meet the performance objectives with interference thresholds 3 dB less than specified in Table B-83. For terminal area and en-route steady-state navigation operations and for itial acquisition of the GLONASS signals prior to steady-state navigation, the interference thresholds shall be 6 dB less an rference t res olds for S and S AS recei ers interference signal s for receivers used for precision approach phase of flight in th those specified in Table B-83. able 2 CW inte Frequency range fi of the Interference threshold fi  1 315 MHz 1 315 MHz fi  1 525 MHz Linearly decreasing from 4.5 dBW to 42 dBW Hz fi  1 610 MHz Linearly increasing from 150.5 dBW to 60 dBW 1 610 MHz fi  1 618 MHz Linearly increasing from 60 dBW to 42 dBW* 000 MHz 8.5 dBW * Applies to aircraft installations where there are no on-board satellite communications. ** Applies to aircraft installations where 4.5 dBW 1 525 MHz fi  1 565.42 MHz Linearly decreasing from 42 dBW to 150.5 dBW 1 565.42 MHz fi  1 585.42 MHz 150.5 dBW 1 585.42 M 1 618 MHz fi  2 000 MHz Linearly increasing from 42 dBW to 8.5 dBW* 1 610 MHz fi  1 626.5 MHz Linearly increasing from 60 dBW to 22 dBW** 1 626.5 MHz fi  2 000 MHz Linearly increasing from 22 dBW to 8.5 dBW** fi there is on-board satellite communications. able nterference t res old for O ASS recei ers Frequency range fi of the interference signal Interference thresholds for receivers used for precision approach phase of flight fi  1 315 MHz 4.5 dBW MHz f 1 315 562.15625 MHz Linearly decreasing from 4.5 dBW to 42 dBW reasing from 42 dBW to 80 dBW z Linearly decreasing from 80 dBW to 149 dBW dBW 1 609.36 MHz fi  1 613.65625 MHz Linearly increasing from 149 dBW to 80 dBW 1 613.65625 MHz fi  1 635.15625 MHz Linearly increasing from 80 dBW to 42 dBW* 1 613.65625 MHz fi  1 626.15625 MHz Linearly increasing from 80 dBW to 22 dBW** 1 635.15625 MHz fi  2 000 MHz Linearly increasing from 42 dBW to 8.5 dBW* 1 626.15625 MHz fi  2 000 MHz Linearly increasing from 22 dBW to 8.5 dBW** fi 2 000 MHz * Applies to aircraft re no on-board satellite communi ** Applies to aircraft s on-board satellite communicatio i  1 1 562.15625 MHz fi  1 583.6525 MHz Linearly dec 1 583.65625 MHz fi  1 592.9525 MH 1 592.9525 MHz fi  1 609.36 MHz 8.5 dBW installations where there a installations where there i cations. ns. 23/11/06 A 2007/70/II. szám A endix Annex 10 — Aeronautical Communications 3.7.3 BAND-LIMITED NOISE-LIKE INTERFERENCE 3.7.3.1 PS AND S AS RECEI ERS 3.7.3.1.1 After steady-state navigation has been precision approach phase of flight or used on aircraft with on-board satellite communications shall meet the performance objectives with noiselike interfering signals present in the frequency range of 1 575.42 MHz Bwi/2 and with power levels at the antenna port equal to the inte al level of 164.5 dBW t the antenna port. Note wi is the e uivalent noise bandwidth of the interference signal 3.7.3.1.2 GPS and SBAS re eir performance objectives with interference thresholds for band-limited noise-like signals 3 dB less than specified in Table B-84. For terminal area and en-route steady-state navigation op al acquisition of the GPS a ior to steady-state navigation, the interference thresholds for band-lim se-like signals shall be 6 dB less than those specified in Table B-84. 3.7.3.2 NASS RECEI ERS 3.7.3.2.1 After steady-state navigation has been established, GLONASS receivers used for the precision approach phase of flight or used on aircraft with on-board sa unications shall meet the performance objectives while receiving noise-like interferin the antenna port equal to the interference thresholds defined i he antenna port. Note f is the centre fre uency of a NASS channel M M and to as defined in Table and wi is the e uivalent noise b e s ONASS receivers used for non-prec hall meet their pe objectives with inte s for band-limited noise-like signals cified in Table B-84. minal area and enrou igation operations, and for initial acquisiti e GLONASS signals prior y-state navigation, the ited noise-like signals shall be 6 dB less than those specified in Table B-85. Note For the approach phase of flight it is assumed that the receiver operates in trac ing mode and ac uires no new tellites 3.7.3.3 Pulsed interference. After steady-state navigation has been established, the receiver shall meet the performance objectives while receiving pulsed int th characteristics according to Table B-86 where the interference threshold is defined at the antenna por 3.7.3.4 SBAS and GBAS receivers shall output misleading information in the presence of interference including interference levels above those specified in 3.7 Note uidance material on this re uirement is given in Attachment D SS aircraft satellite recei er antenna 3.8.1 Antenna coverage. The GNSS antenna shall meet the performance requirements for the reception of GNSS satellite signals from 0 to 360 degrees in azimuth and from 0 to 90 degrees in elevation relative to the horizontal plane of an aircraft in level flight. 3.8.2 Antenna gain The minimum antenna gain shall not be less than that shown in Table B-87 for the specified elevation angle above the horizon. The maximum antenna gain shall not exceed 7 dBic for elevation angles above 5 degrees. established, GPS and SBAS receivers used for the rference thresholds specified in Table B-84 and Figure B-17 and with the desired sign a ceivers used for non-precision approach shall meet th erations and for initi nd SBAS signals pr ited noi tellite comm g signals in the frequency band fk Bwi/2, with power levels at n Table B-85 and with a desired signal level of 165.5 dBW at t with f andwidth of the interferenc ignal 3.7.3.2.2 GL ision approach s 3 dB an spe rf e ormanc rference threshold e steady-state nav less th on of th For ter to stead t interference thresholds for band-lim sa erference signals wi t. not . A 23/11/06 2007/70/II. szám Annex 10 — Aeronautical Communications Volume I 3.8.3 Polari ation. The GNSS antenna polarization shall be right-hand circular (clockwise with respect to the direction of propagation). Cyclic redundancy c eck Each CRC shall be calculated as the remainder, R(x), of the Modulo-2 division of two binary polynomials as follows: k mod2 x M(x) R(x) Q(x) G(x) G(x) ­ ½  ® ¾ ¯ ¿ where k the number of bits in the particular CRC; M(x) the information field, which consists of the data items to be protected by the particular CRC represented as a polynomial; G(x) the generator polynomial specified for the particular CRC; Q(x) the quotient of the division; and R(x) the remainder of the division, contains the CRC: k able n ke interference to S and S AS recei ers for precision approac Interference bandwidth Interference threshold k k i k 1 k 2 i i 1 R(x) r x r x r x r x       ¦ ! terference t res old for band limited noise li used 0 H 0 Hz 50.5 dBW 10 k dBW ) dBW  1 M 1 M 20 MHz e 20 MH 30 MHz Line * 30 M  40 MH Linear * The interference threshold is not to exceed 140.5 dBW Hz in the frequency range 1 575.42 10 MHz. z Bwi  70 Hz Bwi  Hz .5 6 log10(BW/700) kHz Bwi  kHz Hz .5 3 log10(BW/10000 kHz Bwi Hz Bw  .5 dBW arly increasing from 140.5 to 127.5 dBW* arly increasing from 127.5 to 121.1 dBW i Lin z Bwi  Hz Bwi MH z ly increasing from 121.1 to 119.5 dBW* .5 dBW* z Bwi /M able nterference t res old for band limited noise like interference to O ASS recei ers used for precision approac Interference bandwidth Interference threshold 0 Hz Bwi  1 kHz 149 dBW 1 kHz Bwi  10 kHz Linearly increasing from 149 to 143 dBW 10 kHz Bwi  0.5 MHz 143 dBW 0.5 MHz Bwi  10 MHz Linearly increasing from 143 to 130 dBW 10 MHz Bwi 130 dBW 23/11/06 A 2007/70/II. szám A endix Annex 10 — Aeronautical Communications able nterference t res olds for pulsed interference GPS and SBAS GLONASS Frequency range 1 575.4 10 MHz 1 592.9525 MHz to 1 609.36 MHz Interference threshold (Pulse peak power) 10 dBW Pulse width 125 s, 1 ms* 1 ms Pulse duty cycle 10 10 * Applies to GPS receivers without SBAS. 2 MHz 10 dBW able inimum antenna gain S/S AS and O ASS Elevation angle degrees Minimum gain dBic 7.5 4.5 15 to 90 A 23/11/06 2007/70/II. szám Annex 10 — Aeronautical Communications Volume I Figure C/A code timing relations ips SUBFRAME 1 TLM HOW GPS week number, SV accuracy and health SUBFRAME 2 TLM HOW Ephemeris parameters SUBFRAME 3 TLM HOW Ephemeris parameters SUBFRAME 4 (25 pages) TLM HOW Almanac and health for satellites 25–32, special messages, satellite configuration, flags, ionospheric and UTC SUBFRAME 5 (25 pages) TLM HOW Almanac and health for satellites 1–24 and almanac reference time and GPS week number Figure Frame structure 20 ms X1 Epoch 2/3 bps 1 023 1 023 1 023 1 023 etc. Gold Code Epochs (1 000 per second) 1 023-bit Gold Code (1 023 Kbps) Data (50 cps) 1 ms 23/11/06 A 2007/70/II. szám A endix Annex 10 — Aeronautical Communications Preamble Reserved Parity MSB LSB 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 27 28 29 30 Figure ord format Figure HOW format End/start of week ĺ ĸ1.5 s 403 192 403 196 Decimal equivalent of actual TOW counts ĺ Subframe epochs ĸ ĺ 6 s ĸ 100 799 Decimal equivalent of HOW message TOW count Notes: 1. To aid in rapid ground lock-on, the HOW of each subframe contains a truncated TOW count. 2. The HOW is the second word in each subframe. 3. The HOW message TOW count consists of the 17 MSBs of the actual TOW count at the start of the next subframe. 4. To convert from the HOW message TOW count to the actual count at the start of the next subframe, multiply by four. 5. The first subframe starts synchronously with the end/start of each epoch. Figure ime line relations ip of HOW Parity Subframe ID TOW count message 11 12 13 14 15 18 19 20 21 22 23 24 25 26 27 28 29 A 23/11/06 2007/70/II. szám Annex 10 — Aeronautical Communications Volume I *** RESERVED P = 6 PARITY BITS t = 2 NON-INFORMATION BEARING BITS USED FOR PARITY COMPUTATION C = TLM BITS 23 AND 24 WHICH ARE RESERVED WN BITS C/A OR P ON L2 — 2 BITS URA INDEX — 4 BITS SV HEALTH — 6 BITS 2 MSBs IODC — 10 BITS TOTAL L2 P DATA FLAG — 1 BIT 24 BITS*** 24 BITS*** P P P P P BITS*** TGD 8 BITS 8 LSBs IODC — 10 BITS TOTAL toc 16 BITS af2 8 BITS af1 16 BITS af0 22 BITS t SUBFRAME NO. PAGE NO. N/A N/A P P P P P C TLM 22 BITS t HOW 22 BITS 23 BITS*** DIRECTION OF DATA FLOW FROM SV MSB FIRST 150 BITS 3 SECONDS WORD 1 WORD 2 WORD 3 WORD 4 WORD 5 DIRECTION OF DATA FLOW FROM SV MSB FIRST 150 BITS 3 SECONDS WORD 6 WORD 7 WORD 8 WORD 9 WORD 10 Figure Data format (1 of 11) 23/11/06 A 2007/70/II. szám A endix Annex 10 — Aeronautical Communications Figure Data format (2 of 11) P = 6 PARITY BITS t = 2 NON-INFORMATION BEARING BITS USED FOR PARITY COMPUTATION C = TLM BITS 23 AND 24 WHICH ARE RESERVED P P P P P TLM 22 BITS HOW 22 BITS t IODE BITS Crs 16 BITS 16 BITS BITS 24 BITS MSBs LSBs M0 — 32 BITS TOTAL P P P P P MSBs LSBs e — 32 BITS TOTAL Cuc 16 BITS BITS 24 BITS Cus 16 BITS BITS MSBs LSBs — 32 BITS TOTAL 24 BITS toe 16 BITS t FIT INTERVAL FLAG — 1 BIT AODO — 5 BITS A SUBFRAME NO. PAGE NO. N/A N/A DIRECTION OF DATA FLOW FROM SV MSB FIRST 150 BITS 3 SECONDS WORD 6 WORD 7 WORD 8 WORD 9 WORD 10 DIRECTION OF DATA FLOW FROM SV MSB FIRST 150 BITS 3 SECONDS WORD 1 WORD 2 WORD 3 WORD 4 WORD 5 'n A 23/11/06 2007/70/II. szám Annex 10 — Aeronautical Communications Volume I Figure Data format (3 of 11) P = 6 PARITY BITS C = TLM BITS 23 AND 24 WHICH ARE RESERVED t = 2 NON-INFORMATION BEARING BITS USED FOR PARITY COMPUTATION DIRECTION OF DATA FLOW FROM SV MSB FIRST 150 BITS 3 SECONDS WORD 1 WORD 2 WORD 3 WORD 4 WORD 5 SUBFRAME NO. PAGE NO. N/A P P P P P C TLM 22 BITS t HOW 22 BITS Cic 16 BITS BITS 24 BITS Cis 16 BITS BITS MSBs LSBs 0 — 32 BITS TOTAL i0 — 32 BITS TOTAL • DIRECTION OF DATA FLOW FROM SV MSB FIRST 150 BITS 3 SECONDS WORD 6 WORD 7 WORD 8 WORD 9 WORD 10 N/A P P P P P 24 BITS Crc 16 BITS BITS 24 BITS 24 BITS t IODE BITS IDOT BITS LSBs i0 — 32 BITS TOTAL MSBs LSBs MSBs Z — 32 BITS TOTAL 23/11/06 A 2007/70/II. szám A endix Annex 10 — Aeronautical Communications Figure Data format (4 of 11) P = 6 PARITY BITS t = 2 NON-INFORMATION BEARING BITS USED FOR PARITY COMPUTATION C = TLM BITS 23 AND 24 WHICH ARE RESERVED Note.— Pages 2, 3, 4, 5, 7, 8, 9 and 10 of subframe 4 have the same format as pages 1 through 24 of subframe 5. DIRECTION OF DATA FLOW FROM SV MSB FIRST 150 BITS 3 SECONDS WORD 1 WORD 2 WORD 3 WORD 4 WORD 5 SUBFRAME NO. PAGE NO. P P P P P C TLM 22 BITS t HOW 22 BITS e 16 BITS toa 8 BITS I 16 BITS 16 BITS 8 BITS SV HEALTH DATA ID — 2 BITS SV ID — 6 BITS DIRECTION OF DATA FLOW FROM SV MSB FIRST 150 BITS 3 SECONDS WORD 6 WORD 7 WORD 8 WORD 9 WORD 10 THRU THRU P P P P P 24 BITS 24 BITS 24 BITS M0 24 BITS t 8 MSBs 3 LSBs af0 — 11 BITS TOTAL af1 — 11 BITS TOTAL $ Z G :. :0 A 23/11/06 2007/70/II. szám Annex 10 — Aeronautical Communications Volume I ** RESERVED FOR SYSTEM USE *** RESERVED P = 6 PARITY BITS t = 2 NON-INFORMATION BEARING BITS USED FOR PARITY COMPUTATION C = TLM BITS 23 AND 24 WHICH ARE RESERVED SUBFRAME NO. PAGE NO. P P P P P TLM 22 BITS C HOW 22 BITS t 63 69 DATA ID — 2 BITS SV (PAGE) ID — 6 BITS toa WNa 8 BITS 8 BITS SV HEALTH 6 BITS/SV SV SV SV SV SV HEALTH 6 BITS/SV SV SV SV SV P P P P P SV HEALTH 6 BITS/SV SV SV SV SV SV HEALTH 6 BITS/SV SV SV SV SV SV HEALTH 6 BITS/SV SV SV SV SV SV HEALTH 6 BITS/SV SV SV SV SV 3 BITS *** 19 BITS** t DIRECTION OF DATA FLOW FROM SV MSB FIRST 150 BITS 3 SECONDS WORD 1 WORD 2 WORD 3 WORD 4 WORD 5 DIRECTION OF DATA FLOW FROM SV MSB FIRST 150 BITS 3 SECONDS WORD 6 WORD 7 WORD 8 WORD 9 WORD 10 Figure Data format (5 of 11) 23/11/06 A 2007/70/II. szám A endix Annex 10 — Aeronautical Communications Figure Data format (6 of 11) SUBFRAME NO. PAGE NO. ** RESERVED FOR SYSTEM USE *** RESERVED P = 6 PARITY BITS t = 2 NON-INFORMATION BEARING BITS USED FOR PARITY COMPUTATION C = TLM BITS 23 AND 24 WHICH ARE RESERVED P P P P P 24 BITS*** 24 BITS*** 24 BITS*** 8*** BITS BITS*** t 22 BITS** 1, 6, 11, 16 & 21 1, 6, 11, 16 & 21 P P P P P C TLM 22 BITS HOW 22 BITS t 63 69 BITS*** 24 BITS*** 24 BITS*** DATA ID — 2 BITS SV (PAGE) ID — 6 BITS DIRECTION OF DATA FLOW FROM SV MSB FIRST 150 BITS 3 SECONDS WORD 1 WORD 2 WORD 3 WORD 4 WORD 5 DIRECTION OF DATA FLOW FROM SV MSB FIRST 150 BITS 3 SECONDS WORD 6 WORD 7 WORD 8 WORD 9 WORD 10 A 23/11/06 2007/70/II. szám Annex 10 — Aeronautical Communications Volume I Figure Data format (7 of 11) SUBFRAME NO. PAGE NO. ** RESERVED FOR SYSTEM USE *** RESERVED P = 6 PARITY BITS t =2 NON-INFORMATION BEARING BITS USED FOR PARITY COMPUTATION C = TLM BITS 23 AND 24 WHICH ARE RESERVED P P P P P 24 BITS*** 24 BITS*** 24 BITS*** 8*** BITS BITS** t 22 BITS** 12, 19, 20, 22, 23 & 24 12, 19, 20, 22, 23 & 24 P P P P P C TLM 22 BITS HOW 22 BITS t 63 69 BITS*** 24 BITS*** 24 BITS*** DATA ID — 2 BITS SV (PAGE) ID — 6 BITS DIRECTION OF DATA FLOW FROM SV MSB FIRST 150 BITS 3 SECONDS WORD 1 WORD 2 WORD 3 WORD 4 WORD 5 DIRECTION OF DATA FLOW FROM SV MSB FIRST 150 BITS 3 SECONDS WORD 6 WORD 7 WORD 8 WORD 9 WORD 10 23/11/06 A 2007/70/II. szám A endix Annex 10 — Aeronautical Communications Figure Data format (8 of 11) ** RESERVED FOR SYSTEM USE P = 6 PARITY BITS t = 2 NON-INFORMATION BEARING BITS USED FOR PARITY COMPUTATION C = TLM BITS 23 AND 24 WHICH ARE RESERVED P P P P P A1 24 BITS 24 BITS BITS tot BITS WNt BITS tLS BITS BITS DN BITS tLSF BITS t BITS** WNLSF MSBs LSBs A0 — 32 BITS TOTAL SUBFRAME NO. PAGE NO. P P P P P TLM 22 BITS HOW 22 BITS C t 63 69 BITS BITS BITS BITS BITS BITS BITS BITS DATA ID — 2 BITS SV (PAGE) ID — 6 BITS DIRECTION OF DATA FLOW FROM SV MSB FIRST 150 BITS 3 SECONDS WORD 1 WORD 2 WORD 3 WORD 4 WORD 5 DIRECTION OF DATA FLOW FROM SV MSB FIRST 150 BITS 3 SECONDS WORD 6 WORD 7 WORD 8 WORD 9 WORD 10 D0 D0 D1 E1 D2 E2 D3 E3 A 23/11/06 2007/70/II. szám Annex 10 — Aeronautical Communications Volume I SUBFRAME NO. PAGE NO. P P P P P TLM 22 BITS HOW 22 BITS C t 63 69 DATA ID — 2 BITS SV (PAGE) ID — 6 BITS A-SPOOF & SV CONFIG SV SV SV SV SV SV SV SV SV SV A-SPOOF & SV CONFIG SV SV SV SV SV SV A-SPOOF & SV CONFIG P P P P P SV SV SV SV SV SV A-SPOOF & SV CONFIG SV SV SV SV SV SV A-SPOOF & SV CONFIG A-SPOOF & SV CONFIG SV SV SV SV SV 2 BITS ** SV SV SV SV SV HEALTH 6 BITS/SV t SV HEALTH 6 BITS/SV SV SV SV SV HEALTH — 6 BITS 4 BITS ** 29 30 DIRECTION OF DATA FLOW FROM SV MSB FIRST 150 BITS 3 SECONDS WORD 1 WORD 2 WORD 3 WORD 4 WORD 5 DIRECTION OF DATA FLOW FROM SV MSB FIRST 150 BITS 3 SECONDS WORD 6 WORD 7 WORD 8 WORD 9 WORD 10 Figure Data format (9 of 11) ** RESERVED FOR SYSTEM USE P = 6 PARITY BITS t = 2 NON-INFORMATION BEARING BITS USED FOR PARITY CO UTATION C = TLM BITS 23 AND 24 WHICH ARE RESERVED MP 23/11/06 A 2007/70/II. szám A endix Annex 10 — Aeronautical Communications Figure Data format (10 of 11) SUBFRAME NO. PAGE NO. P P P P P C TLM 22 BITS HOW 22 BITS t DATA ID — 2 BITS SV (PAGE) ID — 6 BITS P P P P P E R D L S B S E R D B I T S AVAILABILITY INDICATOR — 2 BITS E R D B I T S E R D B I T S E R D M S B S E R D L S B S E R D B I T S E R D B I T S E R D B I T S E R D M S B S E R D B I T S E R D B I T S E R D M S B S E R D L S B S E R D B I T S E R D B I T S E R D B I T S E R D L S B S E R D B I T S E R D B I T S E R D B I T S E R D M S B S E R D L S B S E R D B I T S E R D B I T S E R D B I T S E R D M S B S t E R D L S B S E R D B I T S E R D B I T S E R D B I T S E R D M S B S E R D L S B S E R D B I T S E R D B I T S E R D B I T S E R D M S B S P = 6 PARITY BITS t = 2 NON-INFORMATION BEARING BITS USED FOR PARITY COMPUTATION C = TLM BITS 23 AND 24 WHICH ARE RESERVED DIRECTION OF DATA FLOW FROM SV MSB FIRST 150 BITS 3 SECONDS WORD 1 WORD 2 WORD 3 WORD 4 WORD 5 DIRECTION OF DATA FLOW FROM SV MSB FIRST 150 BITS 3 SECONDS WORD 6 WORD 7 WORD 8 WORD 9 WORD 10 A 23/11/06 2007/70/II. szám Annex 10 — Aeronautical Communications Volume I Figure Data format (11 of 11) P = 6 PARITY BITS t = 2 NON-INFORMATION BEARING BITS USED FOR PARITY COMPUTATION C = TLM BITS 23 AND 24 WHICH ARE RESERVED SUBFRAME NO. PAGE NO. 14, 15 & 17** P P P P P C TLM 22 BITS HOW 22 BITS t 63 69 BITS** 24 BITS** 24 BITS** DATA ID — 2 BITS SV (PAGE) ID — 6 BITS P P P P P 14, 15 & 17** 24 BITS** 24 BITS** 24 BITS** 24 BITS** 22 BITS** t DIRECTION OF DATA FLOW FROM SV MSB FIRST 150 BITS 3 SECONDS WORD 1 WORD 2 WORD 3 WORD 4 WORD 5 DIRECTION OF DATA FLOW FROM SV MSB FIRST 150 BITS 3 SECONDS WORD 6 WORD 7 WORD 8 WORD 9 WORD 10 ** THE INDICATED PORTIONS OF WORDS 3 THROUGH 10 OF PAGES 14 AND 15 ARE RESERVED FOR SYSTEM USE, WHILE THOSE OF PAGE 17 ARE RESERVED FOR SPECIAL MESSAGES 23/11/06 A 2007/70/II. szám A endix Annex 10 — Aeronautical Communications Figure Superframe structure Frame number String number KX KX KX KX MB MB MB MB KX MB Reserved bits KX MB Reserved bits KX MB Non-immediate data (almanac) for four satellites Non-immediate data (almanac) for five satellites Non-immediate data (almanac) for five satellites Non-immediate data (almanac) for five satellites Non-immediate data (almanac) for five satellites I II III IV V 0.3 s 1.7 s 30 s Bit number within string Data bits in relative bi-binary code Hamming code bits in relative bi-binary code 2 s KX KX KX KX MB MB MB MB KX MB KX KX KX KX MB MB MB MB KX MB KX KX KX KX MB MB MB MB KX MB Immediate data for transmitting satellite Immediate data for transmitting satellite Immediate data for transmitting satellite Immediate data for transmitting satellite Immediate data for transmitting satellite KX KX KX MB MB MB KX MB 30 s × 5 = 2.5 minutes A 23/11/06 2007/70/II. szám Annex 10 — Aeronautical Communications Volume I 23/11/06 A 1 0 1n .&0% .&0% .&0% .&0% .&0% .&0% .&0% .&0% .&0% .&0% .&0% .&0% .&0% .&0% .&0% x (t ) n b x (t ) s b n x (t ) c b n y (t ) n b y (t ) n b s y (t ) n b c Jn b (t ) tb tk z (t ) n b z (t ) n b s z (t ) n b c 'i A n 'i A n '7 A n '7 A n '7 A n H A n H A n H A n H A n H A n + A n + A n 'i A n '7 A n 'i A n '7 A n 'i A n '7 A n '7 A n + A n + A n + A n . . '7 A n . '7 A n . '7 A n . 1n 1n 1n 1n 1n 1n 1n m m m m m m m m m m m m m m m (P2) (P3) (C ) n W$ On W$ On W$ On W$ On W$ On O $ n O $ n O $ n O $ n O $ n Wn b (t ) 'Wn Wc (n NA MA n MA n MA n MA n MA n nA nA nA nA nA ZA n ZA n ZA n ZA n ZA n WO$n WO$n WO$n WO $ n WO$n P1 P Bn * Reserved bits within frame Note Data content definitions and explanations of parameters are given in and Additional data tran smitted by NASS M are highlighted in this figure Figure Frame structure (frames 1 to 4) WGPS String No. FT P4 n M N4 NT * * * * * * 2007/70/II. szám A endix Annex 10 — Aeronautical Communications A 1 1 23/11/06 .&0% .&0% .&0% .&0% .&0% .&0% .&0% .&0% .&0% .&0% .&0% .&0% .&0% .&0% .&0% x (t ) n b x (t ) s b n x (t ) c b n y (t ) n b y (t ) n b s y (t ) n b c Jn b (t ) tb tk z (t ) n b z (t ) n b s z (t ) n b c 'i A n 'i A n '7 A n '7 A n '7 A n H A n H A n H A n H A n + A n + A n 'i A n '7 A n 'i A n '7 A n '7 A n + A n + A n . . '7 A n . '7 A n . 1n m m m m m m m m m m m m m m m (P2) (P3) (C ) n W$ On W$ On W$ On W$ On O $ n O $ n O $ n O $ n Wn b (t ) 'Wn Wc W (n NA MA n MA n MA n MA n nA nA nA nA ZA n ZA n ZA n ZA n WO$n WO $ n WO $ n WO$n P1 Bn * Reserved bits within frame Note Data content definitions and explanations of parameters are given in and Additional data transmitted by NASS M are highlighted in this figure Figure Frame structure (frame 5) 1n 1n 1n 1n 1n 1n B1 B2 KP P M n NT FT P4 N4 GPS String No. * * * * * * * * 2007/70/II. szám Annex 10 — Aeronautical Communications Volume I Figure Data string structure Figure Con olutional encoding Figure Data block format 2.0 s 1.7 s Data bits and check bits in bi-binary code (Tc = 10 ms) Time mark (Tc = 10 ms) 1111100 ... 110 Data bits in relative bi-binary code 0.3 s Hamming code check bits (1–8) in relative bi-binary code Character/numbers within string Note.— Tc = time duration for each chip Data input (250 bits/s) G4 (1011011) G3 (1111001) Symbol clock Output symbols 500 symbols/s (Alternating G3/G4) + + + + + + + + 212-BIT DATA FIELD 250 BITS/SECOND 24-BIT CRC DIRECTION OF DATA FLOW FROM SATELLITE; MOST SIGNIFICANT BIT (MSB) TRANSMITTED FIRST 6-BIT MESSAGE TYPE IDENTIFIER (0–63) 8-BIT PREAMBLE OF 24 BITS TOTAL IN 3 CONTIGUOUS BLOCKS 23/11/06 A 1 2 2007/70/II. szám A endix Annex 10 — Aeronautical Communications Figure numbering con ention (four IGPs) Figure numbering con ention (three IGPs) USER S IPP A 1 3 23/11/06 2007/70/II. szám Annex 10 — Aeronautical Communications Volume I Figure CW interference t res olds for S and S AS recei ers used for precision approac Figure CW interference t res for O ASS recei ers used for (2 000, -8.5) -8.5 (1 315, -4.5) -4.5 (1 626.5, -22) without Satcom with Satcom (1 500, -38) (1 525, -42) (1 618, -42) (1 610, -60) (1 565.42, -150.5) (1 585.42, -150.5) 1 300 1 400 1 500 1 600 1 700 1 800 1 900 2 000 -160 -140 -120 -100 -80 -60 -40 -20 Frequency [MHz] Interference Threshold [dBW] (2 000, -8.5) -8.5 (1 315, -4.5) -4.5 (1 626.15625, -22) without Satcom with Satcom (1 562.15625, -42) (1 583.65625, -80) (1 635.15625, -42) (1 613.65625, -80) (1 592.9525, -149) (1 609.36, -149) 1 300 1 400 1 500 1 600 1 700 1 800 1 900 2 000 -160 -140 -120 -100 -80 -60 -40 -20 Frequency [MHz] Interference Threshold [dBW] olds precision approac 23/11/06 A 2007/70/II. szám Appendix B Annex 10 — Aeronautical Communications Figure B-17. Interference thresholds versus bandwidth for GPS and SBAS receivers Figure B-18. Interference thresholds versus bandwidth for GLONASS ___________________ Interference Bandwidth (kHz) Interference Threshold [dBW] Terminal area, en-route and acquisition for all Non-precision approach Precision approach and Satcom equipped 0.01 0.1 1 000 1·10 1·10 –110 –120 –119.5 –130 –140 -140.5 –150 –150.5 –160 3dB 6dB –130 -143 –149 6dB 3dB –130 –135 –140 –145 –150 –155 –160 0.01 0.1 1·103 1·104 1·105 Terminal area, en-route and acquisition for all Non-precision approach Precision approach and Satcom equipped Interference Bandwidth [kHz] Interference Threshold [dBW] APP B-145 23/11/06 2007/70/II. szám ATTACHMENT A. DETERMINATION OF INTEGRITY AND CONTINUITY OF SERVICE OB ECTIVES USING THE RISK TREE METHOD 1. The risk tree method is a graphical method of expressing the logical relationship between a particular failure condition and the causes or failures leading to this condition. It is an application of fault tree analysis being used in the aerospace industry. 1.1 The method employs a set of logic symbols to show the relationship between the various causes of failure. The following symbols are used in this guidance material. The “AND” gate describes the logical operation whereby the coexistence of all input events is required to produce the output event. The “OR” gate defines a situation whereby the output event will exist if one or more of the input events exist. The rectangle identifies an event that results from the combination of fault or failure events through the input logic gate. The circle describes a primary failure event that requires no further development. Frequency and mode of failure of items so identified are derived from empirical data. 1.2 The method gives a visual representation of sequences and combinations of events leading to the top failure event. The method can also be used to determine the probability of the top event occurring, provided that the probabilities of the individual events are known or can be estimated. In the case of simple fault trees probabilities can be directly calculated, but care must be taken if the primary failure events are not independent, i.e. if failure events are common to more than one path. 1.3 In this guidance material the acceptable probability of the top level event occurring is determined by the risk allocation and the fault tree is used to further partition the risk into integrity and continuity of service risks. Therefore, the term “risk tree” is used rather than “fault tree”. 2. A generic risk tree for aircraft landing operations is given in Figure A-1. The top event for this tree is taken to be the loss of the aircraft due to a failure of the non-aircraft guidance system. The causes of this event are either an integrity failure of the primary non-aircraft guidance equipment or a continuity of service (COS) failure of the non-aircraft guidance system (i.e. both the primary system and any secondary system used to support a discontinued approach/missed approach). The primary non-aircraft guidance system is considered to have a number of elements, 1 to N, for example azimuth, elevation and DME/P in the case of MLS. The secondary guidance system may be an alternative non-aircraft system, or in some cases an aircraft navigation system such as an inertial reference system. 2.1 The following probabilities can be defined: Pa = Probability of aircraft loss due to a failure of the non-aircraft guidance system. Pb = Probability of aircraft loss due to primary guidance integrity failure. Pc = Probability of aircraft loss due to COS failure. ANNEX 10 — VOLUME I ATT A-1 23/11/06 2007/70/II. szám Annex 10 — Aeronautical Communications Volume I Aircraft loss due to non-aircraft guidance system failure = 3 x 10 Pa -9 Aircraft loss due to primary guidance integrity failure Pb Aircraft loss due to continuity of service failure Pc Primary guidance integrity failure Pi Pilot risk reduction Px Discontinued procedure practice Pd Secondary guidance failure (see Note 1) Ps Primary guidance continuity of service failure Pp Integrity failure nav element 1 Pi1 COS failure nav element 1 Pp1 COS failure nav element 2 Pp2 COS failure nav element N PpN COS failure Ps1 Integrity failure Ps2 Integrity failure nav element 2 Pi2 Integrity failure nav element N PiN Pilot risk reduction Pu Ppn = Exposure time MTBON Note 1: Secondary guidance may be aircraft or non-aircraft guidance system. Figure A-1. Generic risk tree 23/11/06 ATT A-2 2007/70/II. szám Attac ment A Annex 10 — Aeronautical Communications Px = Probability that the pilot is unable to detect and intervene successfully following a primary guidance integrity failure. This risk reduction factor is only relevant in those cases where an integrity failure of the guidance system may be detected by the pilot, e.g. at decision height in a Category I ILS approach. Pp = Probability of primary guidance COS failure. Pd = Probability of aircraft loss during a discontinued approach/missed approach procedure. Pi = Probability of primary guidance integrity failure. PiN = Probability of integrity failure in Nav element N. PpN = Probability of COS failure in Nav element N. Ps = Probability of aircraft loss during a discontinued approach/missed approach with secondary guidance. Ps1 = Probability of secondary guidance COS failure. Ps2 = Probability of secondary guidance integrity failure. Pu = Probability that the pilot is unable to intervene successfully following primary guidance COS failure with no secondary guidance available. Where: Pa = Pb + Pc Pb = Pi × Px Pi = Pi1 + Pi2 + ... PiN Pc = Pp × Pd Pp = Pp1 + Pp2 + ... PpN Pd = Ps × Pu Ps = Ps1 + Ps2 2.2 The acceptable probability of the top event, Pa, can be determined by partitioning the global risk factor for the approach and landing operation to the various classes of accident. Using this method an acceptable value for Pa of 3 × 10–9 has been determined. This is consistent with the smallest probability that can be assigned to each ground navigation element, which is 1 × 10–9 (normally divided equally between integrity and COS failures). 2.3 The risk analysis above assumes no equipment design errors. 3. Example of the use of the risk tree — MLS Category III basic operations (Figure A-2). 3.1 In this case there are only two navigation elements involved (e.g. azimuth and elevation). It is assumed that no secondary guidance is available following a COS failure of the primary guidance, the normal procedure being to maintain heading and climb. ATT A-3 23/11/06 2007/70/II. szám Annex 10 — Aeronautical Communications Volume I Aircraft loss due to non-aircraft guidance system failure = 3 x 10 Pa -9 Calculated = 2 x 10 Pa -9 1 x 10 -9 1 x 10 -9 2.5 x 10 -4 4 x 10 -6 1 x 10 -9 0.5 x 10 -9 2 x 10 -6 0.5 x 10 -9 2 x 10 -6 2.5 x 10 -4 Aircraft loss due to primary guidance integrity failure Pb Aircraft loss due to continuity of service failure Pc Primary guidance integrity failure Pi Pilot risk reduction Px Discontinued procedure failure Pd Secondary guidance failure (see Note 1) Ps Primary guidance continuity of service failure Pp Integrity failure, azimuth Pi1 COS failure, azimuth Pp1 COS failure, elevation Pp2 COS failure Ps1 Integrity failure Ps2 Integrity failure, elevation Pi2 Pilot risk reduction Pu Note 1: Secondary guidance not applicable Azimuth: 4 000 hours MTBO 30 seconds exposure time Elevation: 2 000 hours MTBO 15 seconds exposure Figure A-2. MLS Category III landing risk tree 23/11/06 ATT A-4 2007/70/II. szám Attac ment A Annex 10 — Aeronautical Communications Pi1 = Pi2 = 0.5 × 10–9 Pp1 = Pp2 = 2 × 10–6 Note.— These figures are from Attachment G, Table G-15, Level 4 and assume exposure times of 30 and 15 seconds, and MTBOs of 4 000 and 2 000 hours for the azimuth and elevation elements respectively. Ps = 1.0 Note.— Since there is no guided discontinued approach/missed approach procedure using secondary guidance, the probability of an accident during the procedure is taken to be 1. Px = 1.0 Note.— It is assumed in this example that in a Category III operation the pilot is unable to intervene in the event of an integrity failure in the ground system. The risk reduction factor is therefore equal to 1. Pu = 2.5 x 10-4 Note.— The pilot risk reduction factor is estimated at 1 in 4 000 based on a study of accidents to aircraft conducting approaches to land using ground guidance systems. This is the risk reduction factor assumed due to pilot intervention following a continuity of service failure. Therefore: Pi = 1 × 10–9 Pp = 4 × 10–6 Pd = 2.5 × 10–4 Pc = 4 × 10–6 × 2.5 × 10–4 = 1 × 10–9 Pb = 1 × 10–9 × 1 and: calculated Pa = 2 × 10–9. 3.2 There is therefore a margin of 1 × 10–9 on the generic requirement. 4. Application of the risk tree to an MLS/RNAV approach in an obstacle rich environment (Figure A-3). 4.1 In this case there are three navigation elements (i.e. azimuth, elevation and DME/P) and all are assumed to meet the integrity and COS requirements for Level 4 azimuth equipment; i.e integrity = 1 – 0.5 × 10–9 and MTBO = 4 000 hours. Pi1 = Pi2 = Pi3 = 0.5 × 10–9 Px = 1.0 Note.— It is assumed that the pilot is unable to intervene in the event of an integrity failure in the ground system. ATT A-5 23/11/06 2007/70/II. szám Annex 10 — Aeronautical Communications Volume I Aircraft loss due to non-aircraft guidance system failure = 3x10 Pa -9 Aircraft loss due to primary guidance integrity failure Pb Aircraft loss due to continuity of service failure Pc Primary guidance integrity failure Pi Pilot risk reduction Px Discontinued procedure practice Pd Secondary guidance failure Ps Primary guidance continuity of service failure Pp Integrity failure, azimuth Pi1 COS Pp1 failure, azimuth COS Pp2 failure, elevation COS Pp3 failure, DME/P COS failure Ps1 Integrity failure Ps2 Integrity failure, elevation Pi2 Integrity failure, DME/P Pi3 Pilot risk reduction Pu Calculated = 3 x 10 Pa -9 1.5 x 10 -9 1.25 x 10 -4 1.25 x 10 -4 12 x 10 -6 1.5 x 10 -9 1.5 x 10 -9 0.5 x 10 -9 0.5 x 10 -9 0.5 x 10 -9 4 x 10 -6 4 x 10 -6 4 x 10 -6 7.5 x 10 -5 5 x 10 -5 4 000 hours MTBO 1 000 hours MTBO Figure A-3. MLS/RNAV obstacle rich risk tree 23/11/06 ATT A-6 2007/70/II. szám Attac ment A Annex 10 — Aeronautical Communications Pp1 = Pp2 = Pp3 = 4 × 10–6 Note.— This assumes an obstacle exposure time (OET) of 60 seconds, and an MTBO of 4 000 for all ground elements. Pu = 1.0 Note.— It is assumed that an unguided discontinued approach/missed approach procedure is unacceptable. The probability of an accident during such a procedure is therefore taken to be 1. 4.2 In the case of an MLS/RNAV procedure in an obstacle rich environment, it is assumed that secondary guidance will be essential to execute a safe discontinued approach/missed approach procedure during the period of exposure to the obstacles. Ps1 = 7.5 × 10–5 Note.— This is the probability of a COS failure of the secondary guidance ground equipment. It is assumed here that the secondary guidance system has a MTBO of 1 000 hours and that the exposure time is 270 seconds. The exposure time to a failure of the secondary guidance is dependent on the point in the procedure at which the availability of secondary guidance is confirmed. Assuming that this would be prior to the commencement of the MLS/RNAV procedure, and that the pilot would not be required to reconfirm the availability of secondary guidance before commencing the critical obstacle rich part of the procedure, the exposure time could be several minutes. Ps2 = 5 × 10–5 Note.— This is the integrity required by the secondary guidance system. Therefore: Pi = 1.5 × 10–9 Pb = 1.5 × 10–9 Pp = 12 × 10–6 Ps = 7.5 × 10–5 + 5 × 10–5 = 1.25 × 10–4 Pd = 1.25 × 10–4 Pc = 12 × 10–6 × 1.25 × 10–4 = 1.5 × 10–9 and: calculated Pa = 3 × 10–9, as required. Note.— For obstacle exposure times greater than 60 seconds, it will be necessary to either increase the MTBOs of the primary guidance or to increase the risk reduction factor due to the secondary guidance. For example, if the exposure time is increased to 90 seconds, the MTBOs of the primary guidance must be increased to 6 000 hours or the MTBO of the secondary guidance increased to 2 250 hours. There are clearly trade-offs between the reliability of the primary guidance, the exposure time, and the reliability and integrity of the secondary guidance. The risk tree method can be used to examine individual MLS/RNAV procedures and determine the appropriate reliability and integrity requirements for the primary and secondary guidance. ___________________ ATT A-7 23/11/06 2007/70/II. szám ANNEX 10 — VOLUME I ATT B-1 23/11/06 ATTACHMENT B. STRATEGY FOR INTRODUCTION AND APPLICATION OF NON-VISUAL AIDS TO APPROACH AND LANDING (see Chapter 2, 2.1)

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