The file's text, extracted by GovTribe without its formatting.
MVP Requirements Matrix VOR Minimum Viable Product (MVP) Requirements Matrix
Please complete “Respondent Actions” section in the table below.
Notes:
· The relevant FAA-E-37012 paragraph reference is included at the end of each requirement statement in square brackets.
· Acronym definitions for the Compliance column (i.e., Compl.): FM=Fully Met; PM=Partially Met; NM=Not Met.
· For level of effort to comply, please indicate Low, Moderate, or High; Rough Order of Magnitude (ROM) estimates should address both cost and schedule.
· Acronym definitions for the Verification Method column (i.e., VM): T=Test; D=Demonstration; I=Inspection; A=Analysis.
Respondent Actions
| ID |
| MVP Requirement [Spec Ref.] |
| Compl. |
| Explanation of how the product complies |
| If PM or NM, provide level of effort and ROM to comply |
| VM |
| 1 |
| The CVOR System shall provide Amplitude modulation (AM) of the carrier signal by 9960 Hz ±480 Hz. [3.1.1.a.1] |
| 2 |
| The CVOR and DVOR System shall provide a 1020 Hz AM signal with identification keying to produce alphabetic characters. [3.1.1.a.2, 3.1.1.b.2] |
| 3 |
| The CVOR System shall provide two RF double sideband outputs that are 30 Hz removed from (30 Hz above and below) the carrier reference input. [3.1.1.a.4] |
| 4 |
| The CVOR System shall provide a 9960 Hz frequency modulated (FM) subcarrier signal for purposes of amplitude modulating the carrier output. [3.1.1.a.5] |
| 5 |
| The CVOR System shall provide a system configuration with four Alford loop antennas. [3.1.1.a.6] |
| 6 |
| The DVOR System shall provide AM of the carrier signal by 30 Hz. [3.1.1.b.1] |
| 7 |
| The DVOR System shall provide two RF sideband outputs that are 9960 Hz above, and two RF sideband outputs that are 9960 Hz below the carrier reference input. [3.1.1.b.4] |
| 8 |
| The DVOR System shall provide a distributor function that is synchronized to the 30 Hz AM and switches the sideband signals to the appropriate antennas. [3.1.1.b.5] |
| 9 |
| The DVOR System shall provide a system configuration with either 48 or 50 sideband antennas (FAA-E-37012, 3.2.5.2). [3.1.1.b.6] |
| 10 |
| The integrity of the signal, expressed as a probability of not transmitting false guidance signals (FAA-E-37012, 3.1.5), shall be equal to or greater than 0.9999999, which is equivalent to 1-(1 x 10‑7). [3.1.3.a] |
| 11 |
| The implemented system design shall ensure that no single event or failure causes an out-of-tolerance azimuth condition that persists beyond the monitor response time. [3.1.3.b] |
| 12 |
| The implemented system design shall provide mechanisms that prevent unintended changes to parameters that could result in an out-of-tolerance azimuth condition and/or unintended outage. [3.1.3.c] |
| 13 |
| The likelihood of transmitting on an unassigned frequency (±10 kHz or more from the assigned frequency) shall be less than 1 x 10‑7. [3.1.4.a] |
| 14 |
| The implemented system design shall ensure that no single event or failure causes transmission on an unassigned frequency that persists beyond the monitor response time. [3.1.4.b] |
| 15 |
| The implemented system design shall provide mechanisms that prevent unintended changes to parameters that could result in transmission on an unassigned frequency. [3.1.4.c] |
| 16 |
| The ground station contribution to the error in the bearing information conveyed by the horizontally polarized radiation from the VOR for all elevation angles between 0 degrees and 60 degrees, measured from the center of the VOR antenna system, shall be within ±2 degrees. [3.1.5] |
| 17 |
| The electronic equipment shall be provided with devices that protect against atmospheric electricity and transients from nearby lightning strikes in accordance with FAA-STD-019. [3.1.6.3] |
| 18 |
| The equipment manufacturer or supplier shall ensure the system meets the requirements of Federal Communication Commission (FCC) Rules and Regulations, Code of Federal Regulations (CFR) Title 47, Chapter 1: Subchapter A, Part 2 and Part 15; and Subchapter D, Part 87. [3.1.7.b] |
| 19 |
| All components of the Remote Maintenance Monitoring (RMM) subsystem and any other computing devices shall meet the requirements for Class A computing devices in accordance with FCC Rules and Regulations, CFR Title 47, Chapter 1, Subchapter A, Part 2, subpart J, (Frequency Allocations and Radio Treaty Matters; General Rules and Regulations). [3.1.7.c] |
| 20 |
| The system shall operate without modifications within the frequency band from 108 MHz to 118 MHz. [3.2.1.a] |
| 21 |
| The transmitter shall transmit on the frequency that corresponds to the assigned channel without physical equipment modification or special test equipment. See FAA-E-37012, Appendix A for current channelization. [3.2.1.b] |
| 22 |
| The transmitted frequency shall not vary by more than ±0.0005% from the assigned frequency under the initial (room temperature) conditions. [3.2.1.1.a] |
| 23 |
| Over the service conditions listed in FAA-E-37012, 3.1.6.2, the transmitted frequency shall not vary by more than ±0.001% from the assigned frequency. [3.2.1.1.b] |
| 24 |
| A sample of the unmodulated transmitter output signal shall be provided on a front panel connector as appropriate with the frequency of operation with a 50 Ω, removable termination. [3.2.1.1.c] |
| 25 |
| The transmitter shall be capable of providing at least 150 W carrier power output into a 50 Ω load as measured at the output of the transmitter cabinet. [3.2.2.1.a] |
| 26 |
| A sample of the modulated transmitter output signal shall be provided on a front panel connector as appropriate with the frequency of operation with a 50 Ω, removable termination. [3.2.2.1.c] |
| 27 |
| The power output shall be adjustable from at least 25 W through 150 W with the output automatically maintained within ±0.5 dB. [3.2.2.2.a] |
| 28 |
| The transmitter shall require no mechanical/hardware change to operate in the specified settings in FAA-E-37012, 3.2.2.2-a. [3.2.2.2.b] |
| 29 |
| After 1 minute of power being applied to the transmitter, and within 6 s of being switched to operational mode, the transmitter output power shall be at least 90% of the nominal output. [3.2.2.3] |
| 30 |
| The transmitter shall be capable of amplitude modulation to a depth of 80%. [3.2.2.4.3] |
| 31 |
| The transmitter shall be capable of amplitude modulation by the 9960 Hz FM subcarrier to a depth of 30% ±1%. [3.2.2.4.3.1.a] |
| 32 |
| The 9960 Hz FM shall be adjustable to achieve amplitude modulation from 20% to 40%. [3.2.2.4.3.1.b] |
| 33 |
| With the modulation level in FAA-E-37012, 3.2.2.4.3.1-a, the levels of the harmonics of the 9960 Hz shall not exceed the values indicated Frequency Band Level Below Fundamental: 9960 Hz (reference): 0 dB |
15 kHz through <18 kHz: 15 dB 18 kHz through <27 kHz: 32 dB 27 kHz through <37 kHz: 52 dB 37 kHz and above: 62 dB. [3.2.2.4.3.1.c]
| 34 |
| The mean frequency (see FAA-E-37012, 6.1.15) of the 9960 Hz FM subcarrier signal shall be 9960 Hz ±0.1%. [3.2.2.4.3.1.1] |
| 35 |
| A phase shift control shall be provided in the 30 Hz reference signal of the 9960 Hz FM subcarrier generator. [3.2.2.4.3.1.2.a] |
| 36 |
| This control (FAA-E-37012, 3.2.2.4.3.1.2-a) shall provide a range of 0.00 degrees to 359.99 degrees of phase shift between the 30 Hz reference signal and the 30 Hz zero crossover(s) of the RF sideband(s). [3.2.2.4.3.1.2.b] |
| 37 |
| The phase shift control shall be in increments of 0.01 degrees or less. [3.2.2.4.3.1.2.c] |
| 38 |
| Once the phase shift control is set, the phase stability between the 30 Hz reference signal and the 30 Hz zero crossover point(s) of the RF sideband(s) shall remain within ±0.1 degrees of the 30 Hz signal. [3.2.2.4.3.1.2.d] |
| 39 |
| The 9960 Hz generator shall be frequency modulated by the 30 Hz audio signal (30 Hz reference signal). [3.2.2.4.3.1.3.a] |
| 40 |
| The 30 Hz reference signal shall cause the 9960 Hz generator to deviate by ±480 Hz (deviation ratio of 16). [3.2.2.4.3.1.3.b] |
| 41 |
| This deviation (FAA-E-37012, 3.2.2.4.3.1.3-b) shall be constant within ±15 Hz. [3.2.2.4.3.1.3.c] |
| 42 |
| The transmitter shall be capable of amplitude modulation by a 30 Hz signal to a depth of 30% ±1%. [3.2.2.4.3.2.a] |
| 43 |
| The 30 Hz AM shall be adjustable to achieve amplitude modulation from 20% to 40%. [3.2.2.4.3.2.b] |
| 44 |
| With this modulation level (FAA-E-37012, 3.2.2.4.3.2-b), the levels of the harmonics of the 30 Hz shall not exceed the values indicated: Frequency Level Below Fundamental |
30 Hz (reference): 0 dB 60 Hz: 32 dB 90 Hz: 50 dB 120 Hz: 60 dB Beyond 120 Hz: 60 dB [3.2.2.4.3.2.c]
| 45 |
| The mean frequency (see FAA-E-37012, 6.1.15) of the 30 Hz AM signal shall be 30 Hz ±0.01%. [3.2.2.4.3.2.1] |
| 46 |
| An adjustable phase control shall be provided to permit setting of the zero crossover of the 30 Hz signal with respect to the center of the interval of time during which the upper sideband (USB) signal is fed to the first antenna output (No. 1) of the distributor. [3.2.2.4.3.2.2.a] |
| 47 |
| This control (FAA-E-37012, 3.2.2.4.3.2.2-a) shall provide a range of 0.00 degrees to 359.99 degrees of phase shift to the 30 Hz signal. [3.2.2.4.3.2.2.b] |
| 48 |
| The phase shift shall be in increments of 0.01 degrees or less. [3.2.2.4.3.2.2.c] |
| 49 |
| For any initial setting of the phase adjust control in FAA-E-37012, 3.2.2.4.3.2.2-a, the variation of the zero crossover of the 30 Hz amplitude modulated carrier signal with respect to the distributor switching sequence described in FAA-E-37012, 3.2.4.1 shall not exceed ±0.2 degrees of the 30 Hz signal. [3.2.2.4.3.2.2.d] |
| 50 |
| The identification audio signal generator shall provide a sinusoidal 1020 Hz output signal for keyed or continuous tone to amplitude modulate the carrier output signal. [3.2.2.4.4.a] |
| 51 |
| Output for keying a Distance Measuring Equipment (DME) shall be provided that employs an isolated, solid state relay with contact resistance lower than 250 Ω, capable of sinking a current of 20 mA and withstanding an open circuit voltage of 50 VDC. [3.2.2.4.4.b] |
| 52 |
| Alternately to the Morse Code keying, the DME keying output shall be selectable to provide a Morse Code synchronization signal to initiate operation of the DME’s internal identification keyer [3.2.2.4.4.c]. |
| 53 |
| The stability of 1020 Hz frequency shall be within ±0.5%. [3.2.2.4.4.1] |
| 54 |
| The total harmonic distortion of the 1020 Hz audio signal (continuous tone output) shall not exceed 3.0%. [3.2.2.4.4.2] |
| 55 |
| The oscillator/keyer shall provide adjustable levels sufficient to amplitude modulate the carrier output from 3 to 8%. [3.2.2.4.4.3.a] |
| 56 |
| The identification amplitude modulation of the carrier output shall be maintained to within ±1%. [3.2.2.4.4.3.b] |
| 57 |
| The keyer shall operate to key the 1020 Hz audio signal into the dot-dash characters of International Morse Code representing any three-letter combination of the alphabet and the four-letter code of “T-E-S-T”. [3.2.2.4.4.4.1.a] |
| 58 |
| The transmitter shall provide controls to: Enable/disable identification keying. |
Program the keyer to operate in association with Tactical Air Navigation (TACAN)/DME equipment such that:
Every fourth identification cycle causes keying pulses to be provided to the TACAN/DME.
The other identification cycles shall be for the VOR.
Enable/disable continuous transmission of identification signal pulse groups.
Select three-letter alphabetic Morse Code characters in normal operation.
Select a mode in which the identification code is set to “T-E-S-T”. and Automatically generate a maintenance alert when the identification code is selected as “T-E-S-T”. [3.2.2.4.4.4.2]
| 59 |
| The repetition rate for the three- or four-letter identification code group shall be eight times per minute, except as noted in FAA-E-37012, 3.2.2.4.4.4.2-b. [3.2.2.4.4.4.3.b] |
| 60 |
| The maximum key down time shall not exceed 5 s per identification code group. [3.2.2.4.4.4.3.c] |
| 61 |
| The dots shall have a time duration of 0.1 s to 0.125 s. [3.2.2.4.4.4.3.d] |
| 62 |
| The dashes shall be three times the duration of the dots ±5%. [3.2.2.4.4.4.3.e] |
| 63 |
| The duration between dots and/or dashes shall be equal to that of one dot ±5%. [3.2.2.4.4.4.3.f] |
| 64 |
| The time duration between letters shall be equal to the duration of three dots within ±5%. [3.2.2.4.4.4.3.g] |
| 65 |
| The two RF sideband outputs shall contain 30 Hz components that are at audio phase quadrature (90 degrees) with each other. |
Note: These RF double sidebands are combined in the VOR antenna system in a manner such that a 30 Hz amplitude modulated carrier signal is produced (nominal amplitude modulation is 30%). [3.2.3.1.b]
| 66 |
| The total harmonic distortion of the 30 Hz envelope shall not exceed 1.0%. [3.2.3.1.3] |
| 67 |
| Spurious signal components within the bands of frequencies from 300 Hz to 9000 Hz above and below the carrier frequency shall not exceed a level which is 50 dB below the level of either 30 Hz sideband component as measured at the sideband output connector. [3.2.3.1.4.a] |
| 68 |
| Signals more than 9000 Hz removed from the carrier signal shall not exceed a level of 60 dB below the level of either 30 Hz sideband component as measured at the sideband output connector. [3.2.3.1.4.b] |
| 69 |
| The levels of the harmonics of the 30 Hz shall not exceed the values indicated below: Upper sideband 0 dB (reference) |
(fc +30 Hz) Lower sideband 0 dB (±0.1 dB) (fc -30 Hz) Carrier (fc) 30 dB (3.2.3.1.2) Second harmonic (fc ±60 Hz) 30 dB (balanced within 1 dB) Third harmonic (fc ±90 Hz) 30 dB (balanced within 2 dB) Fourth harmonic 40 dB (balanced within 2 dB) (fc ±120 Hz) Fifth harmonic 40 dB (balanced within 2 dB) (fc ±150 Hz) All higher order harmonics of 30 Hz 50 dB. [3.2.3.1.4.c]
| 70 |
| The audio phase relationship of the two outputs shall be in phase quadrature, 90 ±2 degrees. |
Note: The correct separation of the zero points of both output envelopes will address 3.2.3.1.4 carrier (fc) suppression requirement. [3.2.3.1.5]
| 71 |
| The RF phase relationship of the two sideband outputs shall reverse at 90 degree intervals of the 30 Hz audio modulating signal. [3.2.3.1.6.a] |
| 72 |
| At the phase reversal in FAA-E-37012, 3.2.3.1.6-a, the phase accuracy shall be alternately 0 ±3 degrees and 180 ±3 degrees, referenced to the carrier output phase in FAA-E-37012, 3.2.3.1.6-c. [3.2.3.1.6.b] |
| 73 |
| The RF phase of the two sideband outputs shall be maintained to within ±3 degrees referenced to the carrier output phase. [3.2.3.1.6.c] |
| 74 |
| Controls shall be provided to adjust the phase of the two sideband outputs individually, relative to the carrier output phase by at least +/-45 degrees in increments of 1 degree. [3.2.3.1.6.d] |
| 75 |
| For one complete period of the 30 Hz modulation signal, any individual maximum envelope amplitude, at both the outputs, shall not deviate by more than 0.5% from the average of all such maximums (averaged over a period of at least five complete cycles of 30 Hz). [3.2.3.1.7] |
| 76 |
| After one minute of power being applied to the transmitter, and within 6 s of being switched to operational mode, the sideband output power shall be at least 90% of the nominal output. [3.2.3.1.9] |
| 77 |
| Directional couplers and detectors shall be incorporated at each sideband output for measurement of forward and reverse power and VSWR, for display locally and remotely. [3.2.3.1.10, 3.2.3.2.9] |
| 78 |
| The DVOR sideband transmitter shall be capable of providing at least 10 W of continuous wave (CW) power at each sideband output. [3.2.3.2.1.a] |
| 79 |
| The DVOR sideband output power shall be adjustable from at least 2.5 W to 10 W, in 0.5 W increments. [3.2.3.2.1.b] |
| 80 |
| After initial DVOR setup, sideband power outputs shall automatically track the carrier output power with an accuracy of within ±0.25 dB for carrier transmitter power changes of +1.0 dB to -3.0 dB. [3.2.3.2.1.c] |
| 81 |
| Provisions shall be provided such that the four DVOR sideband outputs can be adjusted simultaneously to achieve amplitude modulations from 20% to 40%. [3.2.3.2.1.d] |
| 82 |
| The USB transmitter frequency shall be fc + (9960 Hz ±10.0 Hz). [3.2.3.2.2.a] |
| 83 |
| The LSB transmitter frequency shall be fc – (9960 Hz ± 10.0 Hz). [3.2.3.2.2.b] |
| 84 |
| After one minute of power being applied to the transmitter, and within 6 s of being switched to operational mode: the transmitter output frequency and phase shall meet the requirements in FAA-E-37012, 3.2.3.2.2 and FAA-E-37012, 3.2.3.2.3 and the sideband output power shall be at least 90% of the nominal output. [3.2.3.2.4] |
| 85 |
| The sideband RF voltage, as referenced to peak sideband power, shall vary as cos0.836 (θ) within a tolerance of ± (0.09cos0.836 (θ) + 0.009). [3.2.3.2.5.a] |
| 86 |
| The LSB zero amplitude point shall be within ± 75 µs from the 0 degree reference point of the 30 Hz waveform. |
Note: The modulation may be applied in the sideband transmitters. [3.2.3.2.5.b]
| 87 |
| Spurious radiation components within specified frequency bands on either side of the fundamental shall not exceed the following levels: Frequency Band Level Below Fundamental |
15 kHz through <18 kHz 15 dB 18 kHz through <27 kHz 32 dB 27 kHz through <37 kHz 52 dB 37 kHz and above 62 dB [3.2.3.2.6]
| 88 |
| The level of the carrier reference frequency in the output of either sideband output signal shall be at least 34 dB below the level of the sideband output signal. [3.2.3.2.7] |
| 89 |
| The level of the USB signal present in the output of the LSB signal shall be at least 40 dB below the output level of the USB signal. [3.2.3.2.8.a] |
| 90 |
| The level of the LSB signal present in the output of the USB signal shall be at least 40 dB below the output level of the LSB signal. [3.2.3.2.8.b] |
| 91 |
| The distributor shall operate with two USB signals and two LSB signals from the sideband transmitters. [3.2.4.1.a] |
| 92 |
| Separate switching channels for each sideband signal shall provide two separate modulated pulse trains of complementary waveforms (E1 and E2) – one for subsequent application to odd numbered antennas and the other to even numbered antennas. [3.2.4.1.b] |
| 93 |
| For a DVOR utilizing 50 sideband antennas in normal operation, each sideband output shall be applied to one antenna at a time by electronic switching for 1/750 second in the following repeating sequence:1.E1 (USB) Antenna No. 1, 3, 5, 7, 9 --- 47, 49, 1 --- |
2.E1 (LSB) Antenna No. 26, 28, 30, 32, 34 --- 22, 24, 26 --- (and 1/1500 second delayed with respect to the above) 3.E2 (USB) Antenna No. 2, 4, 6, 8, 10 --- 48, 50, 2 --- 4.E2 (LSB) Antenna No. 27, 29, 31, 33, 35 --- 23, 25, 27 [3.2.4.1.c]
| 94 |
| For a DVOR utilizing 48 sideband antennas in normal operation, each sideband output shall be applied to one antenna at a time by electronic switching for 1/720 second in the following repeating sequence:1.E1 (USB) Antenna No. 1, 3, 5, 7, 9 --- 45, 47, 1 --- |
2.E1 (LSB) Antenna No. 24, 26, 28, 30, 32 --- 20, 22, 24 --- (and 1/1440 second delayed with respect to the above) 3.E2 (USB) Antenna No. 2, 4, 6, 8, 10 --- 46, 48, 2 --- 4.E2 (LSB) Antenna No. 25, 27, 29, 31, 33 --- 21, 23, 25 [3.2.4.1.d]
| 95 |
| Means shall be provided through the MDT to disable the normal switching sequence and to cause the sideband outputs to be applied continuously to any selected pair of diametrically opposite antennas, or to remove the output to all antennas. [3.2.4.1.e] |
| 96 |
| The monitor shall accept RF signals from the monitor antennas, and simulated VOR signals from built-in test equipment as described in FAA-E-37012, 3.3-g. |
Note: In the event that more than one independent monitor is used, the requirements in FAA-E-37012, 3.3 apply to each independent monitor. [3.3.a]
| 97 |
| The monitor shall provide for the application of audio signals to other external equipment (GFE). [3.3.b] |
| 98 |
| The monitor shall measure the following system parameters: FM subcarrier. |
30 Hz AM signals.
Identification keying.
Radiated power level.
FM deviation ratio.
Azimuth determined at the monitor antenna.
Transmitter output power. and Transmitter frequency. [3.3.c]
| 99 |
| The monitor shall indicate whether the measured signals (FAA-E-37012, 3.3.c) are within, or exceed, established alarm limits. [3.3.d] |
| 100 |
| The monitor shall initiate an alarm action when the established alarm limits are exceeded, as specified in FAA-E-37012, 3.3.2.1. [3.3.e] |
| 101 |
| The monitor shall not affect or interrupt the VOR service, except as stated in FAA-E-37012, 3.3-e. [3.3.f] |
| 102 |
| The monitor shall provide for self-testing of monitor alarm limits through the use of built-in test equipment internal to the monitor as specified FAA-E-37012, 3.3.2.3 and FAA-E-37012, 3.3.2.5. [3.3.g] |
| 103 |
| The capability of the monitor to detect and respond to Hazardously Misleading Information (HMI) shall not be affected by the failure of other system functions. [3.3.h] |
| 104 |
| The VOR monitor shall provide adequate immunity to interference from two-signal, third-order intermodulation products caused by VHF FM broadcast signals having levels in accordance with the following: 2N1 + N2 + 72 ≤ 0 for VHF FM sound broadcasting signals in the range 107.7 – 108.0 MHz. and 2N1 + N2 + 3 (24 – 20 log (Δf/0.4) ≤ 0 for VHF FM sound broadcasting signals below 107.7 MHz |
Where:
N1 and N2 are the levels (dBm) of the two VHF FM sound broadcasting signals at the VOR receiver input that produce, within the receiver, a two-signal, third-order intermodulation product on the desired VOR frequency; and Δf = (108.1 – f1), where f1 is the frequency of the signal that has the level N1, the VHF FM sound broadcasting signal closer to 108.1 MHz. [3.3.1.5.a]
| 105 |
| The levels for N1 and N2 in FAA-E-37012, 3.3.1.5-a shall not exceed the desensitization criteria set forth in FAA-E-37012, 3.3.1.5-c. [3.3.1.5.b] |
| 106 |
| The VOR monitor system shall not be desensitized in the presence of VHF FM broadcast signals having levels in accordance with the following: Frequency (MHz) Maximum level of unwanted signal at receiver input (dBm) |
88 – 102: 15 104: 10 106: 5 107.9: -10. [3.3.1.5.c]
| 107 |
| The VOR monitor system shall not be desensitized in the presence of VHF Data Broadcast (VDB) adjacent channel signals (±25 kHz removed from the assigned VOR frequency) having a level of +15 dBm. |
Note: The relationship is linear between adjacent points designated by the frequencies in FAA-E-37012, 3.3.1.5-c. [3.3.1.5.d]
| 108 |
| Execution of monitor control actions and fault annunciation shall occur within 10 s of the commencement of an out-of-tolerance condition, except for identification alarms. For identification alarms refer to FAA-E-37012, 3.3.2.2.9. [3.3.2.1.a] |
| 109 |
| The monitor shall provide two separate alarm actions for purposes of automatic control and remote monitoring of the transmitter: one designated “primary parameter alarm” and the other designated “secondary parameter alert.” [3.3.2.1.b] |
| 110 |
| The alarm condition shall remain until it clears, or a reset is performed. [3.3.2.1.c] |
| 111 |
| If any primary parameter (FAA-E-37012, 3.3.2.2.1), or if any parameter listed in FAA-E-37012, 3.3.2.2.2 that is selected as primary, produces an out-of-tolerance condition, the monitor will cause the following actions to take place: |
a . A positive visual and aural indication (FAA-E-37012, 3.4.1.2) of the alarm condition shall be provided.
b. The main transmitter shall be automatically switched off.
c. The standby transmitter, if provided, shall be automatically switched into operation within 5 s of the main transmitter shutdown.
d. If any out-of-tolerance conditions occur for the standby transmitter, a positive visual and aural indication of the alarm condition shall be provided and
e. The standby transmitter shall be automatically switched off. [3.3.2.1.1]
| 112 |
| If any of the monitored parameters set to secondary (FAA-E-37012, 3.3.2.2.2) produces an out-of-tolerance condition, the monitor shall cause a positive visual and aural indication of the alert condition (FAA-E-37012, 3.4.1.2). [3.3.2.1.2] |
| 113 |
| The monitor delay time (FAA-E-37012, 6.1.18) for all parameters selected as primary (See FAA-E-37012, 3.3.2.2.1 and FAA-E-37012, 3.3.2.2.2) except for identification, shall be adjustable from 4 s to 10 s. For identification alarms see FAA-E-37012, 3.3.2.2.9. [3.3.2.1.5.a] |
| 114 |
| The adjustable value selected from the MDT shall be the total monitor delay as defined in FAA-E-37012, 6.1.18. [3.3.2.1.5.b] |
| 115 |
| The requirement FAA-E-37012, 3.3.2.1.6-b shall be met under conditions in which any faults have been sensed for a continuous period of 10 s or longer. [3.3.2.1.6.a] |
| 116 |
| Within 3 s after the application of transmitter output signals, which have characteristics that are all within a range prescribed for non-fault conditions, all sensed faults and alarm indications shall end. [3.3.2.1.6.b] |
| 117 |
| Each monitored parameter shall have an adjustable nominal value with adjustable alarm and pre-alarm limits, except as stated in FAA-E-37012, 3.3.2.2.9 and FAA-E-37012, 3.3.2.2.11-e. |
| 118 |
| The pre-alarm limits shall be adjustable to any value between the associated nominal and alarm limit values. [3.3.2.2.b] |
| 119 |
| The following parameters shall be monitored as primary alarms: Azimuth indication (FAA-E-37012, 3.3.2.2.3). |
DVOR sideband signal accuracy (FAA-E-37012, 3.3.2.2.12). and CVOR ground check azimuth alarm condition (FAA-E-37012, 3.3.2.6.4-c). [3.3.2.2.1]
| 120 |
| The following parameters shall be monitored and selectable as either primary parameter alarms or secondary parameter alerts: |
30 Hz modulation (FAA-E-37012, 3.3.2.2.4) FM subcarrier modulation (FAA-E-37012, 3.3.2.2.5) FM subcarrier frequency deviation (FAA-E-37012, 3.3.2.2.6) Transmitter power output (FAA-E-37012, 3.3.2.2.7) Radiated power level (FAA-E-37012, 3.3.2.2.8) Identification keying (FAA-E-37012, 3.3.2.2.9) Identification modulation (FAA-E-37012, 3.3.2.2.10) and Transmitter frequency stability (FAA-E-37012, 3.3.2.2.11-c). [3.3.2.2.2]
| 121 |
| The azimuth indication shall be within ±0.05 degrees, readable to 0.01 degrees for all azimuthal inputs. [3.3.2.2.3.a] |
| 122 |
| The azimuth indication shall remain within ±0.1 degrees when the frequency of the 30 Hz input signal components varies by ±0.02%. [3.3.2.2.3.b] |
| 123 |
| The azimuth indication shall remain within ±0.1 degrees with changes in AC line voltage (FAA-E-37012, 3.7.12.9-a). [3.3.2.2.3.c] |
| 124 |
| The azimuth indication shall remain within ±0.1 degrees when any signals within the frequency range of 300 Hz to 3000 Hz are applied to the monitor simultaneously with the 30 Hz input signal components. [3.3.2.2.3.d] |
| 125 |
| The azimuth low and high alarm limit shall be adjustable between 0.1 degrees and 1.9 degrees from the reference azimuth (FAA-E-37012, 6.1.22), in 0.1-degree increments, via the MDT interface. [3.3.2.2.3.e] |
| 126 |
| The default alarm limit shall be set to ±1 degree from the reference azimuth. [3.3.2.2.3.f] |
| 127 |
| The reference azimuth shall be settable between 000.0 degrees and 359.9 degrees, in 0.1 degree increments, via the MDT interface. [3.3.2.2.3.g] |
| 128 |
| The monitor shall measure the azimuth determined at the monitor antenna(s). [3.3.2.2.3.h] |
| 129 |
| The 30 Hz AM nominal value shall be adjustable between 20% and 40%. [3.3.2.2.4.a] |
| 130 |
| The 30 Hz AM alarm limit shall be adjustable between ±2% and ±8%. [3.3.2.2.4.b] |
| 131 |
| The default alarm limit shall be set to ±2%. [3.3.2.2.4.c]] |
| 132 |
| The alarm limit shall have a tolerance of ±1%. [3.3.2.2.4.d] |
| 133 |
| The default nominal value shall be 30%. [3.3.2.2.4.e] |
| 134 |
| For a CVOR, the 30 Hz modulation shall be measured at the monitor antennas. [3.3.2.2.4.f] |
| 135 |
| The FM subcarrier modulation nominal value shall be adjustable between 20% and 40%. [3.3.2.2.5.a] |
| 136 |
| The FM subcarrier modulation alarm limit shall be adjustable between ±2% and ±8%. [3.3.2.2.5.b] |
| 137 |
| The default alarm limit shall be set to ±2%. [3.3.2.2.5.c] |
| 138 |
| The alarm limit shall have a tolerance of ±1%. [3.3.2.2.5.d] |
| 139 |
| The default nominal value shall be 30%. [3.3.2.2.5.e] |
| 140 |
| For a DVOR, the FM subcarrier modulation shall be measured at the field monitor antenna. [3.3.2.2.5.g] |
| 141 |
| The default nominal value of the 9960 Hz FM subcarrier frequency deviation ratio shall be 16. [3.3.2.2.6.a] |
| 142 |
| The 9960 Hz FM subcarrier nominal frequency deviation ratio shall be adjustable between 14.0 and 18.0. [3.3.2.2.6.b] |
| 143 |
| The FM subcarrier frequency deviation alarm limit shall be adjustable between ±0.2 and ±1.4, in 0.1 steps (or smaller). [3.3.2.2.6.c] |
| 144 |
| The default alarm limit shall be set to ±0.6. [3.3.2.2.6.d] |
| 145 |
| The alarm limit shall have an accuracy within ±0.166. [3.3.2.2.6.e] |
| 146 |
| For a DVOR, the FM subcarrier frequency deviation shall be measured at the field monitor antenna. [3.3.2.2.6.g] |
| 147 |
| The monitor shall measure the carrier transmitter frequency. [3.3.2.2.11.a] |
| 148 |
| The pre-alarm limit shall be stated as a percentage of the nominal frequency and adjustable in increments of 0.0001%. [3.3.2.2.11.b] |
| 149 |
| The measured frequency shall be within ±0.0002% across the operational service conditions. [3.3.2.2.11.c] |
| 150 |
| The pre-alarm limit shall be adjustable between ±0.0001% and ±0.002%. [3.3.2.2.11.d] |
| 151 |
| The monitor shall detect faults that affect accuracy along any azimuth radial [3.3.2.2.12.a]. |
| 152 |
| Accuracy monitoring shall report an azimuth accuracy fault for the out-of-tolerance condition listed in FAA-E-37012, 3.1.5. [3.3.2.2.12.b] |
| 153 |
| Means shall be provided within the monitor to test the following parameters generated by the transmitter: |
Azimuth indication (FAA-E-37012, 3.3.2.2.3) 30 Hz AM modulation level (FAA-E-37012, 3.3.2.2.4) 9960 Hz AM modulation level (FAA-E-37012, 3.3.2.2.5) 9960 Hz FM deviation ratio (FAA-E-37012, 3.3.2.2.6) Power output (FAA-E-37012, 3.3.2.2.7) Identification keying code (FAA-E-37012, 3.3.2.2.9) Identification modulation level (FAA-E-37012, 3.3.2.2.10), and Transmitter frequency (FAA-E-37012, 3.3.2.2.11). [3.3.2.3.1.a]
| 154 |
| The certification tests shall run periodically and upon command. [3.3.2.3.1.b] |
| 155 |
| The period in which the certification tests run shall be adjustable, with a minimum period of as low as practicable and a maximum period of at least 24 hours. [3.3.2.3.1.c] |
| 156 |
| The certification tests shall be selectively enabled/disabled. [3.3.2.3.1.d] |
| 157 |
| Execution of the certification tests shall not affect or interrupt the VOR service. [3.3.2.3.1.e] |
| 158 |
| The latest certification test results shall be available through the MDT and the RMLS interface. [3.3.2.3.1.f] |
| 159 |
| Failure of any of the tests shall cause a maintenance alert. [3.3.2.3.1.g] |
| 160 |
| The maintenance alert in FAA-E-37012, 3.3.2.3.1-g shall be reset upon the next in-tolerance test. [3.3.2.3.1.h] |
| 161 |
| The transmitter certification test limits shall be adjustable and independent of the monitor alarm limits. [3.3.2.3.1.i] |
| 162 |
| Means shall be provided to test and validate alarm limits. [3.3.2.3.2.a] |
| 163 |
| The values used for the testing shall be adjustable through the MDT. [3.3.2.3.2.b] |
| 164 |
| The certification tests shall run periodically and upon command. [3.3.2.3.2.c] |
| 165 |
| The period in which the certification tests run shall be adjustable with a minimum period of at least 5 minutes and a maximum period of at least 24 hours. [3.3.2.3.2.d] |
| 166 |
| The certification tests shall be selectively enabled/disabled. [3.3.2.3.2.e] |
| 167 |
| Execution of the certification tests shall not affect or interrupt the VOR service. [3.3.2.3.2.f] |
| 168 |
| The test results with measured data, and monitor status for the parameter under measurement, shall be available through the MDT and the RMLS interface. [3.3.2.3.2.g] |
| 169 |
| Failure of any primary parameter (FAA-E-37012, 3.3.2.2.1 or FAA-E-37012, 3.3.2.2.2) test shall result in a primary alarm (FAA-E-37012, 3.3.2.1.1). [3.3.2.3.2.h] |
| 170 |
| Failure of any other test shall result in a maintenance alert. [3.3.2.3.2.i] |
| 171 |
| The maintenance alert in FAA-E-37012, 3.3.2.3.2-i shall be reset upon the next in-tolerance test. [3.3.2.3.2.j] |
| 172 |
| The low and high alarm limits each shall be tested for outside alarm limit (out-of-tolerance) and within alarm limit (within tolerance) conditions by injection of test signals for the following: |
Azimuth indication (FAA-E-37012, 3.3.2.2.3) 30 Hz modulation (FAA-E-37012, 3.3.2.2.4) FM subcarrier modulation (FAA-E-37012, 3.3.2.2.5) FM subcarrier frequency deviation (FAA-E-37012, 3.3.2.2.6) Identification modulation (FAA-E-37012, 3.3.2.2.10) and Transmitter frequency (FAA-E-37012, 3.3.2.2.11). [3.3.2.3.2.k]
| 173 |
| The low alarm limit shall be tested for outside alarm limit (out-of-tolerance) and within alarm limit (within tolerance) conditions by injection of test signals for the following: Transmitter power output (FAA-E-37012, 3.3.2.2.7). and |
Radiated power (FAA-E-37012, 3.3.2.2.8). [3.3.2.3.2.l]
| 174 |
| The monitor shall be failsafe such that failure of any part of the monitor subsystem, including any associated control action (transmitter shutdown), either results directly in an alarm condition, or does not alter any alarm limit to allow an out-of-tolerance condition to occur without detection. [3.3.2.4] |
| 175 |
| The nominal frequency of the FM subcarrier signal shall be 9960 Hz, frequency modulated ±480 (±8 Hz) by a 30 Hz sinusoid. |
Note: The increasing 9960 Hz frequency represents the positive going 30 Hz excursion. [3.3.2.5.1.1.a]
| 176 |
| The frequency deviation shall be adjustable to 9960 ±360 Hz through 9960 ±600 Hz, as a minimum, in increments of 10 Hz or less and with stability of ±4 Hz once set. |
Note: The increasing 9960 Hz frequency represents the positive going 30 Hz excursion. [3.3.2.5.1.1.b]
| 177 |
| The sinusoidal signal which frequency modulates the 9960 Hz FM signal shall be 30 Hz ±0.05%. [3.3.2.5.1.2.a] |
| 178 |
| The phase of the 30 Hz FM signal shall be in accordance with FAA-E-37012, 3.3.2.5.2.1 [3.3.2.5.1.2.b] |
| 179 |
| The total harmonic distortion of the 30 Hz FM signal shall be less than 0.5% [3.3.2.5.1.3]. |
| 180 |
| The FM subcarrier signal output level shall be adjustable in steps of 0.5% amplitude modulation over the range of 15% to 45% modulation. [3.3.2.5.1.4] |
| 181 |
| The output level shall not vary by more than ±0.2% for any setting of the output level (FAA-E-37012, 3.3.2.5.1.4). [3.3.2.5.1.5] |
| 182 |
| The root mean square (rms) of all hum distortion frequencies shall not exceed a value corresponding to 65 dB below the specified minimum output level (FAA-E-37012, 3.3.2.5.1.4). [3.3.2.5.1.6] |
| 183 |
| The nominal phase of the sinusoidal 30 Hz AM signal shall be within ±0.05 degrees of the phase of the 30 Hz FM signal (FAA-E-37012, 3.3.2.5.1.2) at any azimuth setting. [3.3.2.5.2.1] |
| 184 |
| The 30 Hz AM signal output level shall be adjustable in steps of 0.5% modulation, from 15% to 45% modulation. [3.3.2.5.2.1.1] |
| 185 |
| The amplitude distortion of the 9960 Hz FM signal shall be less than 2% when all other modulation is removed. [3.3.2.5.2.1.2] |
| 186 |
| The VOR test generator shall provide a connector as appropriate for the frequency of operation for connection to external test equipment (GFE). [3.3.2.5.3] |
| 187 |
| The ground check system shall consist of 16 equally spaced monitor antennas (FAA-E-37012, 3.3.2.6.5). [3.3.2.6.2.a] |
| 188 |
| The ground check system shall measure the azimuth error of the radiated signal with a resolution of 0.01 degrees. [3.3.2.6.2.b] |
| 189 |
| The ground check routine shall run periodically and upon command from the MDT. [3.3.2.6.2.c] |
| 190 |
| The ground check routine frequency shall be adjustable. |
Note: The nominal routine frequency and range of adjustability will be determined by the outcome of the system safety assessment. [3.3.2.6.2.d]
| 191 |
| The ground check routine shall be selectively enabled/disabled. [3.3.2.6.2.e] |
| 192 |
| A maintenance alert shall be generated when the ground check routine is disabled. [3.3.2.6.2.f] |
| 193 |
| The reference ground check, consisting of the average of six consecutive ground check measurements, shall be initiated from the MDT. [3.3.2.6.2.g] |
| 194 |
| Execution of the ground check routine shall not affect or interrupt the VOR service (except as stated in FAA-E-37012, 3.3.2.6.4). [3.3.2.6.2.h] |
| 195 |
| The system shall calculate and provide the difference between the reference ground check (FAA-E-37012, 6.1.23) azimuth error readings and subsequent routine ground check azimuth error readings. [3.3.2.6.3.a] |
| 196 |
| The ground check system shall perform the VOR course error analysis whenever the ground check routine is performed. [3.3.2.6.3.b] |
| 197 |
| The VOR course error analysis shall provide the following parameters: 1. DC bias. |
2. Duantal phase and azimuth error.
3. Quadrantal phase and azimuth error.
4. Octantal phase and azimuth error. and
5. Calculated azimuth error spread. [3.3.2.6.3.c]
| 198 |
| The phase reading resolution in FAA-E-37012, 3.3.2.6.3.c-2, FAA-E-37012, 3.3.2.6.3.c-3, and FAA-E-37012, 3.3.2.6.3.c-4 shall be at least 0.1 degree of phase angle. [3.3.2.6.3.d] |
| 199 |
| The azimuth error resolution in FAA-E-37012, 3.3.2.6.3.c-2, FAA-E-37012, 3.3.2.6.3.c-3, and FAA-E-37012, 3.3.2.6.3.c-4 shall be at least 0.01 degrees. [3.3.2.6.3.e] |
| 200 |
| The ground check results data shall be accessible from the MDT and from the RMLS interface. [3.3.2.6.3.f] |
| 201 |
| The most recent ground check error curve shall be provided graphically at the MDT, including date and time, and selectively include: Reference ground check error curve, including date, time, and applicable tolerances. |
Duantal error sinusoid.
Quadrantal error sinusoid. and Octantal error sinusoid. [3.3.2.6.3.g]
| 202 |
| All ground check data and analysis results, including reference ground check results, shall be stored in non-volatile memory. [3.3.2.6.3.h] |
| 203 |
| The stored ground check data and analysis results shall be identified as either periodic or commanded (FAA-E-37012, 3.3.2.6.2-c). [3.3.2.6.3.i] |
| 204 |
| The ground check azimuth error low and high alarm limit shall be adjustable between 0.1 degrees and 1.9 degrees, in 0.1-degree increments, via the MDT interface. [3.3.2.6.4.a] |
| 205 |
| The default ground check azimuth error limit shall be set to ±1.5 degrees. [3.3.2.6.4.b] |
| 206 |
| If the ground check azimuth error calculations (FAA-E-37012, 3.3.2.6.3-a) yield an error in excess of the ground check azimuth alarm limit value in FAA-E-37012, 3.3.2.6.4-a, at any of the 16 azimuth points, the monitor shall initiate action in accordance with FAA-E-37012, 3.3.2.1. [3.3.2.6.4.c] |
| 207 |
| If the calculated ground check azimuth error spread (FAA-E-37012, 3.3.2.6.3.c-5) exceeds the selected limit, then a maintenance alert (FAA-E-37012, 3.3.2.1.4) shall be generated. [3.3.2.6.4.d] |
| 208 |
| The ground check error spread low and high alarm limits shall be adjustable between 1.0 degree and 3.8 degrees, in 0.1-degree increments, via the MDT interface. [3.3.2.6.4.e] |
| 209 |
| The default ground check error spread limit shall be set to 2.0 degrees. [3.3.2.6.4.f] |
| 210 |
| The monitor antennas shall have broadband characteristics such that the performance requirements of FAA-E-37012 are met over the specified frequency range without requiring readjustment of the dimensions of the antenna elements. [3.3.2.6.5.1.a] |
| 211 |
| Each monitor antenna shall have an output impedance such that the VSWR does not exceed 2.5:1 at 113 MHz. [3.3.2.6.5.1.b] |
| 212 |
| The measured azimuth from the monitor antenna output shall not differ by more than 0.1 degrees when installed in the standard position and rotated 180 degrees from standard. [3.3.2.6.5.2] |
| 213 |
| The antennas shall be horizontally polarized. [3.3.2.6.5.3.a] |
| 214 |
| Vertically polarized radiation shall be at least 12 dB below horizontally polarized signals within the 108 MHz to 118 MHz frequency band. [3.3.2.6.5.3.b] |
| 215 |
| The antenna masts shall be constructed to extend 48 to 50 inches from the antenna base to the counterpoise surface. [3.3.2.6.5.4.b] |
| 216 |
| Radomes to protect the antenna elements from snow and ice accumulation shall be provided. [3.3.2.6.5.5.a] |
| 217 |
| The radomes shall be fabricated from a material which is resistant to heat, cold, fungus growth, bird droppings, and ultraviolet (solar) radiation. [3.3.2.6.5.5.b] |
| 218 |
| As a minimum, the following visual indicator functions shall be provided on the equipment front panel: Transmitter ON/OFF status. |
Monitor alarm condition.
Mode of operation (monitor bypass) defined in FAA-E-37012, 3.4.1.1-c.
Transmitter status (Main/Standby).
AC power failure.
On battery operation. and Remote control enabled/disabled. [3.4.1.2.a]
| 219 |
| The following colors shall be used for indicators: Green for normal operation/remote control enabled, Amber/Yellow for an alert condition/remote control disabled, and Red for an alarm condition. [3.4.1.2.b] |
| 220 |
| An aural alarm shall be provided to indicate an alarm condition. [3.4.1.2.c] |
| 221 |
| An aural representation of the detected identification transmission from the monitor shall be provided. [3.4.1.2.d] |
| 222 |
| The MDT, running vendor provided software, shall: Display any changes to the VOR System status. |
Display current values for all monitored parameters including environmental sensors (e.g., smoke, intrusion, temperature), and certification test results (FAA-E-37012, 3.3.2.3.1 and FAA-E-37012, 3.3.2.3.2).
Display the fault history (FAA-E-37012, 3.4.4).
Display the results from fault diagnostics (FAA-E-37012, 3.4.5).
Display the results from the most recent CVOR ground check (FAA-E-37012, 3.3.2.6.3).
Determine and report the logical, physical, and software configuration of the VOR System to the extent practicable.
Provide for a printable (to file) reference data display that includes selectable operational and certification parameters.
Display the current CVOR ground check results, to a resolution of 0.01 degrees, for the 16 antenna positions along with reference ground check values.
Provide CVOR ground check error analysis graphical display(s) sufficient to determine the duantal, the quadrantal and the octantal error to within 0.01 degrees of resolution.
Determine and report system resource utilization (such as Central Processing Unit (CPU) utilization, and Random-Access Memory (RAM), Programmable Read-Only Memory (PROM), and Non-Volatile RAM (NVRAM) memory usage and availability).
Display all users logged onto the VOR System.
Acknowledge and indicate either successful command execution or failure, including communication faults. and Display the elapsed time for all commands that take more than 5 s to complete. [3.4.2.b]
| 223 |
| At the MDT and RMLS interface, there shall be access to fault history data that provides a means to quickly display individual records associated with at least the 50 most recent alarms, pre-alarms, maintenance alerts, or other out-of-tolerance conditions that are brief or transient (i.e., less than alarm delay). Note: this includes retention of a minimum of 50 automatic ground checks. [3.4.4.a] |
| 224 |
| Fault diagnostics shall provide diagnostics and system verification to facilitate fault isolation to the Line Replaceable Unit (LRU) level, including the remote maintenance monitoring subsystem(s). Note: The automated diagnostics routine will identify the failed LRU or LRUs to the specified level of accuracy independently and without additional human input or need to reference flow charts, tables, etc. The diagnostics routine will ensure that any failed test results on a particular LRU were caused by a failure within that LRU, and not the result of a failure on a different LRU. [3.4.5.a] |
| 225 |
| The diagnostic routine shall be able to localize 85% of all failures to a single faulty LRU, and 95% of all failure occurrences to no more than two candidate LRUs, one of which contains the fault. Note: The automated diagnostics routine will identify the failed LRU or LRUs to the specified level of accuracy independently and without additional human input or need to reference flow charts, tables, etc. The diagnostics routine will ensure that any failed test results on a particular LRU were caused by a failure within that LRU, and not the result of a failure on a different LRU. [3.4.5.b] |
| 226 |
| Fault diagnostics shall run per FAA-E-37012, 3.4.7-f, and either continually or on command from the MDT. Note: The automated diagnostics routine will identify the failed LRU or LRUs to the specified level of accuracy independently and without additional human input or need to reference flow charts, tables, etc. The diagnostics routine will ensure that any failed test results on a particular LRU were caused by a failure within that LRU, and not the result of a failure on a different LRU. [3.4.5.c] |
| 227 |
| If fault diagnostics run upon command, then provisions shall be made to permit the operator to stop the test cycle at any time during the test sequence. Note: The automated diagnostics routine will identify the failed LRU or LRUs to the specified level of accuracy independently and without additional human input or need to reference flow charts, tables, etc. The diagnostics routine will ensure that any failed test results on a particular LRU were caused by a failure within that LRU, and not the result of a failure on a different LRU. [3.4.5.d] |
| 228 |
| All LRUs identified as failed by fault diagnostics shall be reported and listed in order of descending likelihood. Note: The automated diagnostics routine will identify the failed LRU or LRUs to the specified level of accuracy independently and without additional human input or need to reference flow charts, tables, etc. The diagnostics routine will ensure that any failed test results on a particular LRU were caused by a failure within that LRU, and not the result of a failure on a different LRU. [3.4.5.e] |
| 229 |
| Fault diagnostics that run continually shall not cause an out-of-tolerance condition of the radiated signals. Note: The automated diagnostics routine will identify the failed LRU or LRUs to the specified level of accuracy independently and without additional human input or need to reference flow charts, tables, etc. The diagnostics routine will ensure that any failed test results on a particular LRU were caused by a failure within that LRU, and not the result of a failure on a different LRU. [3.4.5.f] |
| 230 |
| Fault diagnostic data shall be stored in memory and accessible via the MDT or by RMLS request. Note: The automated diagnostics routine will identify the failed LRU or LRUs to the specified level of accuracy independently and without additional human input or need to reference flow charts, tables, etc. The diagnostics routine will ensure that any failed test results on a particular LRU were caused by a failure within that LRU, and not the result of a failure on a different LRU. [3.4.5.g] |
| 231 |
| The VOR shall record and store, in non-volatile memory, system status, alarms, pre-alarms, maintenance alerts, all monitored parameter values, all results of fault diagnostics, results of certification tests, CVOR 16-point ground check data and analysis, and any other system information or data that is required for corrective or preventive maintenance. [3.4.6.a] |
| 232 |
| The VOR transmitter automatic reset function shall: Return the VOR transmitter to normal operation when input power is restored after a power interruption. |
Reinitialize all VOR transmitter software in the event of a restart/reboot (i.e., a momentary loss of power) such that it is fully functional with the latest loaded software version.
Reset and restart the VOR transmitter at set intervals subsequent to a shutdown due to an alarm action, or protective actions in FAA-E-37012, 3.2.6 and FAA-E-37012, 3.2.7.
Be configurable to provide a minimum of three user-defined reset/restart time intervals.
Display the current status of the automatic reset timers on the MDT. and Initiate fault diagnostics after the third or final restart and subsequent shutdown. [3.4.7]
| 233 |
| The RMS shall be independent from the VOR monitor and shutdown control functions and circuits. [3.5.1.a] |
| 234 |
| The VOR RMS shall provide the following functions: |
a . Environmental monitoring as required in FAA-E-37012, 3.5.6.
b. Monitor each of the minimum set of performance parameters required to determine the operational status of the VOR.
c. Process the outputs of each of the monitoring devices as necessary to provide digital data in the appropriate engineering units for RMM.
d. Process the outputs of each of the monitoring devices to determine alert and pre-alert status by comparing the monitored outputs to user-defined limits.
e. Provide at least two limits for each monitored parameter, an alert (when the parameter reaches its established limit), and a pre-alert, which is typically 75% of the alert value.
f. In response to a poll (data request message) received from the RMLS, transmit the current value of each parameter in the group or groups of parameters indicated by the content of the request message.
g. Time stamping and local storage of the current status of alarms and alerts data values, alarm and alert limits, fault history (FAA-E-37012, 3.4.4), and trend analysis data (FAA-E-37012, 3.4.6).
h. Capability to provide 100% additional memory storage capacity of that required to meet the requirements specified herein.
i. The additional storage capacity required in FAA-E-37012, 3.5.1.1.h shall be provided in the initial design.
j. Capability to process RMM reset commands and
k. Capability to process RMM restart commands to restore VOR operation in the case of interrupted service. [3.5.1.1]
| 235 |
| An alarm message shall be generated and transmitted to the RMLS when a failure occurs within the VOR System that causes a loss of service to the user (shutdown) [3.5.2.1.a]. |
| 236 |
| An alert message shall be generated and transmitted to the RMLS when a failure occurs within the VOR System which does not cause a loss of service to the user [3.5.2.1.b]. |
| 237 |
| When the system is commanded off, or when the system is off as a normal state, alarm messages shall be inhibited. [3.5.2.1.c] |
| 238 |
| The interface from RMS to RMLS shall be compliant with selectively, either Internet Protocol (IP) v4 or IPv6. [3.5.10.a.3] |
| 239 |
| The VOR System shall contain features in its design and operation that prevent unauthorized and disruptive access to the system by implementing the following requirements as a minimum: Authorized user access verification. |
User password control.
Restriction of access to system/operating system (OS) files/data.
Denying access to direct OS functions/commands.
Limited access to specific functions based on job category.
While in the normal operating mode, prevent the loading of data from removable media or network connections. and Disable any unused ports during normal operation. [3.6.1]
| 240 |
| The CVOR System shall have a mean time between failures (MTBF) of not less than 7500 hours as a serial reliability model. [3.7.2.a] |
| 241 |
| The DVOR System shall have a MTBF of not less than 6500 hours as a serial reliability model. [3.7.2.b] |
| 242 |
| The mean time to isolate and replace a faulty LRU on the VOR System shall be less than or equal to 30 minutes. [3.7.6.a] |
| 243 |
| The maximum time to isolate and replace an LRU shall be less than or equal to 120 minutes. [3.7.6.b] |
| 244 |
| The ground reference for the equipment/ system shall be in accordance with FAA-STD-019, FAA-C-1217, NFPA 70 Article 250, and chapters 8 and 9 of IEEE 1100. [3.7.11.a] |
| 245 |
| Shielding and bonding shall be per FAA-STD-019. [3.7.11.b] |
| 246 |
| Any removable rack-mounted unit, assembly, or subassembly whose rack provides multi-point grounding shall have a flexible grounding strap, using bonding connections per FAA-STD-019. [3.7.11.c] |
This is the start of the file's text. The full file is on GovTribe.
