Appendix 4
A4-5. Horizontal Velocity Figure of Merit Pass/Fail Determination.
The receiver velocity data and the horizontal figure of merit - velocity (HFOMV) data shall be used to determine the percentage of samples bounded by the HFOMV as shown below. The test passes if TSh,b is greater than or equal to 0.95.
Vi Vi i h N i i hbh HFOM h HFOM hb N bNTS 0 1 samples of number 1 , 1 ,,
A4-6. Vertical Velocity Accuracy Test Conditions Commensurate with NACV = 1.
a. Ensure the simulator scenario has enough GPS satellites to provide a vertical dilution of precision (VDOP) of 3.0 or less.
b. One satellite shall be set at maximum power (including maximum combined satellite and aircraft antenna gain), and the other satellites shall be set at minimum power (including minimum antenna gain).
c. Broadband GNSS test noise (IGNSS,Test) of spectral density as defined in RTCA/DO-229D, paragraph 2.5.8, broadband external interference (Iext,test) and thermal noise contribution from the sky and the antenna (Nsky,antenna) shall be simulated.
Note: In RTCA/DO-229D, paragraph 2.5.8.2 step 2, replace -173.0 dBm/Hz with -172.8 dBm/Hz for total GNSS noise (IGNSS) when running separate GPS/SBAS testing for accuracy verification and/or GPS/SBAS message loss rate data.
d. The airborne equipment shall be initialized with the appropriate position and time.
It is assumed that the receiver has obtained a valid almanac for the simulator scenario to be tested prior to conducting the test.
e. Platform dynamics for the vertical velocity accuracy test shall be as defined in table 13 below.
A4- 4
Appendix 4
Time (s) Start Jerk (g/s) End Jerk (g/s) From To Dynamics North East Down Total North East Down Total 0 T Static 0 0 0 0 0 0 0 0 T+1 T+71 0.58g longitudinal acceleration to 411 m/s
0.xx Note 1
0.xx Note 1 0 0.25 0.xx Note 1
0.xx Note 1 0 0.25 T+72 T+130 Straight and level un-accelerated flight 0 0 0 0 0 0 0 0 T+131 T+131+X Climb, increasing the vertical climb rate from 0 to 21 m/s, then decrease the rate back to 0 m/s and repeat this increasing and decreasing pattern until the time out.
0 0 0.xx Note 1
0.25 0 0 0.xx Note 1
0.25 T+132+X T+192+X Straight and level un-accelerated flight 0 0 0 0 0 0 0 0 T+193+X T+193+2X Descend, increasing the vertical descent rate from 0 to 21 m/s, then decrease the rate back to 0 m/s and repeat this increasing and decreasing pattern until the time out.
0 0 0.xx Note 1
0.25 0 0 0.xx Note 1
0.25 T+194+2X T+274+2X Straight and level un-accelerated flight 0 0 0 0 0 0 0 0 Table 13. Platform Dynamics for Vertical Velocity Accuracy Test
Note 1: The components of the jerk in the north and east direction depends on the heading chosen in the scenario.
The total jerk is not to exceed the vector combination of north, east, and down jerk components. The maximum total jerk to quickly achieve the desired dynamics should be used, but the jerk should not exceed the normal maneuver total jerk requirement of 0.25 g/s.
Note 2: The actual times may vary based on the simulator scenario control settings.
Note 3: The value of X must be at least 63 seconds to have enough samples during vertical acceleration.
f. Signal and RFI conditions can be modified during the static period to aid acquisition. Ensure the receiver enters the desired operation mode before dynamics and A4-5
Appendix 4
appropriate signal and interference conditions are applied.
g. Use the simulator velocity truth data ( truthvertical iV _ ) and the GNSS receiver velocity data ( vertical iV ) to determine the vertical velocity error ( iv ) after the GNSS receiver has entered the desired navigation mode with the specified signal and RFI conditions:
vertical i truthvertical ii VVv _
A4-7. Vertical Velocity Accuracy Pass/Fail Determination.
a. The 95% vertical velocity accuracy statistic shall be computed using the formula given below. The equipment shall be considered pass only if the statistic is less than or equal to 50-LSB ft/s.
N i i N i VDOP v 1 2 3 *2
Where:
vi = vertical velocity error (ft/sec).
VDOPi = vertical dilution of precision at epoch i.
N = number of sample points used.
b. For this test, the number of samples shall include all samples where the receiver is in the desired navigation mode.
Note: The minimum number of samples is 420 for a 1 Hz solution and 2100 for a 5 Hz solution.
A4-8. Vertical Velocity Figure of Merit Pass/Fail Determination.
The receiver velocity data and the vertical figure of merit - velocity (VFOMV) data shall be used to determine the percentage of samples bounded by the VFOMV as shown below. The test passes if bvTS , is greater than or equal to 0.95.
Vi Vi iv N i ivbv VFOMv VFOMvb N bNTS 0 1 samples ofnumber 1 , 1 ,,
A4-6
Appendix 4
A4-7
A4-9. Additional Tests to Demonstrate Accuracy Commensurate with NACV = 2.
The following procedure is one acceptable means for equipment capable of better accuracy performance to demonstrate compliance with the horizontal velocity error requirement of less than 3 m/s.
a. Run the scenario in table 13 with all satellites set at high power and no RFI.
b. This accuracy evaluation shall only include those data samples collected during the acceleration period.
c. Find the particular ih (noted as accT ) so that 95% of ih samples are less than or equal to accT .
d. Re-run the scenario in table 13 with the same satellite and RFI conditions as the 10 m/s (NACV=1) test.
e. This time only the data samples during the non-acceleration period with the specified signal and RFI conditions are used.
f. Compute:
accnon N i accnoni accnoni accnon N HDOP h T accnon _ 1 2 __ __ _ _ 5.1 *2
Where:
accnoniHDOP __ and accnonN _ are the HDOP values for each sample i and the total number of samples (non-acceleration period), respectively.
g. The test passes only if accnonacc TT _ is less than or equal to 3-LSB m/s.
h. The velocity figure of merit is evaluated in the same way as for the 10 m/s test, i.e., the samples during acceleration and non-acceleration periods of the above 2 runs are evaluated together against the 0.95 threshold.
i. The vertical velocity requirement of 15 ft/s should be tested using the exact same philosophy as the test of 3 m/s above but with the scenario in table 13.
Appendix 5
Appendix 5. Sample Airplane/Rotorcraft Flight Manual Supplement.
A5-1. Introduction.
The intent of this appendix is to provide general guidance for creating an AFMS/RFMS.
The information and structure below are not intended to cover all possible aircraft integrations or equipment capabilities and should not be construed to limit the content included in an AFMS/RFMS. Actual AFMS/RFMS language and structure must be tailored to the actual installation, equipment capabilities, and limitations.
A5-8
Appendix 5
Installation Center/Repair Station Model XXX GPS 123 Fourth Street Navigation System Anytown, USA
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
ABC MODEL XXX GPS NAVIGATION SYSTEM
AIRPLANE MAKE:
AIRPLANE MODEL:
AIRPLANE SERIAL NO.:
REGISTRATION NO.:
This document must be carried in the airplane at all times. It describes the operating procedures for the ABC Model XXX GPS navigation system when it has been installed in accordance with <manufacturer's installation manual number and date>.
For airplanes with an FAA approved airplane flight manual, this document serves as the FAA approved ABC Model XXX GPS flight manual supplement. For airplanes that do not have an approved flight manual, this document serves as the FAA approved ABC Model XXX GPS supplemental flight manual.
The information contained herein supplements or supersedes the basic airplane flight manual dated <insert date> only in those areas listed herein. For limitations, procedures, and performance information not contained in this document, consult the basic airplane flight manual.
FAA APPROVED
_____________________ Title Office Federal Aviation Administration City, State F A A A p p r o v e d P a g e < > o f < > Date: ________ A5-9
Appendix 5
Sample Airplane/Rotorcraft Flight Manual (Continued)
Installation Center/Repair Station Model XXX GPS 123 Fourth Street Navigation System Anytown, USA
Table of Contents
SectionPage
1 General.............................................< >
2 Limitations........................................< >
3 Emergency/Abnormal Procedures....< >
4 Normal Procedures...........................< >
5 Performance......................................< >
6 Weight and Balance..........................< >
7 System Description...........................< >
FAA Approved Page <> of <> Date: ________ A5-10
Appendix 5
Sample Airplane/Rotorcraft Flight Manual (Continued)
Installation Center/Repair Station Model XXX GPS 123 Fourth Street Navigation System Anytown, USA
SECTION 1 - GENERAL <Include the appropriate statement to describe the equipment capability:>
GPS TSO-C129<appropriate revision>: The installed ABC system complies with AC 20-138B for IFR navigation using GPS for enroute, terminal area, and non-precision approach operations. Non-precision approach operations include those based on conventional navigation aids with “or GPS” in the title and those with “GPS” and “RNAV(GPS)” in the title to “LNAV” minimums.
GPS/SBAS TSO-C145 or C146<appropriate revision> Class 3: The installed ABC equipment complies with AC 20-138B for navigation using GPS and GPS/SBAS (within the coverage of a satellite-based augmentation system complying with ICAO Annex 10) for enroute, terminal area, non-precision approach, and approach procedures with vertical guidance operations.
Non-precision approach operations include those based on conventional navigation aids with “or GPS” in the title and those with “GPS” and “RNAV(GPS)” in the title to “LNAV” and “LP” minimums. Approach procedures with vertical guidance includes “RNAV(GPS) to “LNAV/VNAV” and “LPV” minimums.
Note 1: TSO-C145a/C146a Class 3 equipment is not required to perform LP approaches.
Note 2: Functional Class Delta equipment is an “ILS look-alike” that only provides LP/LPV capability on the final approach segment.
GPS/SBAS TSO-C145 or C146<appropriate revision> Class 2: The installed ABC equipment complies with AC 20-138B for navigation using GPS and GPS/SBAS (within the coverage of a satellite-based augmentation system complying with ICAO Annex 10) for enroute, terminal area, non-precision approach, and approach procedures with vertical guidance operations.
Non-precision approach operations include those based on conventional navigation aids with “or GPS” in the title and those with “GPS” and “RNAV(GPS)” in the title to “LNAV” minimums. Approach procedures with vertical guidance includes “RNAV(GPS) to “LNAV/VNAV” minimums.
FAA Approved Page <> of <> Date: ________ Sample Airplane/Rotorcraft Flight Manual (Continued) A5-11
Appendix 5
Installation Center/Repair Station Model XXX GPS 123 Fourth Street Navigation System Anytown, USA
GPS/SBAS TSO-C145 or C146<appropriate revision Class 1: The installed ABC equipment complies with AC 20-138B for navigation using GPS and GPS/SBAS (within the coverage of a satellite-based augmentation system complying with ICAO Annex 10) for enroute, terminal area, and non-precision approach operations. Non-precision approach operations include those based on conventional navigation aids with “or GPS” in the title and those with “GPS” and “RNAV(GPS)” in the title to “LNAV” minimums.
GPS/GBAS TSO-C161a<appropriate revision>: The installed ABC system complies with AC 20-138B for navigation using GPS and GPS/GBAS (within the coverage of a ground-based augmentation system complying with ICAO Annex 10) for GPS/GBAS precision approach procedures to “GLS” minimums.
GPS TSO-C196: The installed ABC system complies with AC 20-138B for IFR navigation using GPS for enroute, terminal area, and non-precision approach operations. Non-precision approach operations include those based on conventional navigation aids with “or GPS” in the title and those with “GPS” and “RNAV(GPS)” in the title to “LNAV” minimums.
<The following statement applies to all types of GNSS stand-alone equipment>:
Navigation information is referenced to the WGS-84 reference system, and should only be used where the Aeronautical Information Publication (including electronic data and aeronautical charts) conform to WGS-84 or equivalent.
<For TSO-C129(AR), TSO-C145/C146(AR), and TSO-C196 equipment that complies with the requirements in appendix 1 of this AC:> The ABC equipment as installed has been found to comply with the requirements for GPS oceanic/remote navigation, when used in conjunction with the ABC prediction program. This does not constitute an operational approval.
FAA Approved Page <> of <> Date: ________ A5-12
Appendix 5
Sample Airplane/Rotorcraft Flight Manual (Continued)
Installation Center/Repair Station Model XXX GPS 123 Fourth Street Navigation System Anytown, USA
SECTION 2 - LIMITATIONS
1. The ABC Model XXX GPS Quick Reference Guide, P/N <insert part number>, dated <insert date> (or later appropriate revision) must be immediately available to the flight crew whenever navigation is predicated on the use of the system.
2. The system must use at least software version <insert version identification> as the minimum version.
3. A valid and compatible database must be installed and contain current data.
<Limitation for TSO-C129(AR) and TSO-C196 equipment:>
4. The aircraft must have other operational, approved navigation equipment installed appropriate to the operation.
<Limitation for all GNSS equipment:>
5. The TSO-C<insert number and revision> equipment has an alternate airport flight planning limitation. Refer to section 1-1-19 in the Airman’s Information Manual.
6. <Specify any additional limitations applicable to the particular installation.>
SECTION 3 - EMERGENCY/ABNORMAL PROCEDURES
EMERGENCY PROCEDURES No Change
ABNORMAL PROCEDURES
1. If ABC Model XXX GPS navigation information is not available or invalid, use remaining operational navigation equipment as appropriate.
2. If loss of integrity monitoring message is displayed, revert to an alternate means of navigation appropriate to the route and phase of flight or periodically cross-check the GPS guidance to other, approved means of navigation.
SECTION 4 - NORMAL PROCEDURES
1. Normal operating procedures are outlined in the ABC Model XXX GPS Pilot's Guide.
FAA Approved Page <> of <> Date: ________ A5-13
Appendix 5
A5-14 Sample Airplane/Rotorcraft Flight Manual (Continued)
Installation Center/Repair Station Model XXX GPS 123 Fourth Street Navigation System Anytown, USA
2. <Describe approach mode sequencing.>
3. System Annunciators <applicable to installations with external annunciators>
a. Waypoint - <describe each annunciator>
b. Message - <describe each annunciator>
c. Approach - <describe each annunciator>
d. <describe any other annunciators>
4. System Switches <applicable to installations with external switches>
a. Nav/GPS - <describe switch use and function>
b. RMI Switch - <describe switch use and function>
c. <describe any other switches>
5. Pilot's Display <describe the pilot's GPS display(s)>
6. Flight Director/Autopilot Coupled Operation <describe the procedures for coupling GPS to the flight director and/or autopilot system(s)>
7. <include any other normal operating procedures necessary>
SECTION 5 - PERFORMANCE No Change
SECTION 6 - WEIGHT AND BALANCE <Refer to revised weight and balance data, if applicable.>
SECTION 7 - SYSTEM DESCRIPTION <Provide a brief description of the system, its operation, installation, etc.>
FAA Approved Page <> of <> Date: ________
Appendix 6
Appendix 6. Installation of GNSS Equipment for VFR Use Only.
A6-1. Introduction.
This appendix provides guidelines for the installation of stand-alone GNSS systems used for VFR navigation only.
A6-2. General.
GNSS equipment may be installed on a no-hazard basis as a supplement to VFR navigation.
Such installations need only to verify that the GNSS installation does not introduce a hazard to the aircraft (e.g., properly secured for crashworthiness, not combustible, etc) including EMI/EMC. Loss of or misleading VFR navigation information is considered a minor hazard failure condition; therefore, it is acceptable to have development assurance level D for software per RTCA/DO-178B, and electronic hardware, per RTCA/DO-254. A readable placard must be installed in clear view of the pilot stating that the equipment is only to be used for VFR operations, unless the equipment automatically displays this message on start-up and pilot action is required to clear the message. An AFMS/RFMS is not required since the placard or display contains the equipment limitation.
A6-3. Applicability.
This appendix applies to all un-pressurized aircraft less than 6000 pounds where the modification is classified as a minor alteration.
A6-4. Technical Instructions.
Install the GPS as follows:
a. The GPS equipment should be located in a position which is viewable and accessible to the pilot from his/her normally seated position. The installed GPS equipment should not:
(1) Restrict access to or view of any control, display or indicator;
(2) Restrict movement of the flight controls;
(3) Interfere with the pilot’s vision along the flight path; or
(4) Restrict pilot/passenger egress.
b. The installation should be carried out in accordance with the equipment manufacturer’s installation manual/instructions, the aircraft maintenance manual and the guidelines in AC 43.13-2 (latest revision). The installation should conform to the following requirements:
(1) Equipment manufacturer-supplied or standard parts should be used.
A6-1