Operator´s Manual Supplement To Tm 55-1520-210-10.pdf

TECHNICAL MANUAL

OPERATOR’S MANUAL

SUPPLEMENT TO TM 55-1520-210-10

APPLICABLE TO HELICOPTER UH-1H FACH H-79, SN 66-16967 31 AUGUST 2016

EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

LIST OF EFFECTIVE PAGES

Page Number

Change Number

Cover ......................................................................0 A.............................................................................0 i a ii ........................................................................0 1-1 a 1-52 ...............................................................0

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EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH - 1H FACH H-79, SN 66-16967

TABLE OF CONTENTS Page SECTION I

GENERAL INFORMATION ......................................................................................... 1-1

SECTION II

COMMUNICATIONS ................................................................................................... 1-3

SECTION III

NAVIGATION ............................................................................................................ 1-11

SECTION IV

TRANSPONDER ...................................................................................................... 1-21

SECTION V

EQUIPMENT / FURNISHINGS ................................................................................. 1-45

SECTION VI

INSTRUMENTS ........................................................................................................ 1-47

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OPERATOR’S MANUAL SUPPLEMENT TO

LIST OF ILLUSTRATIONS Figure 1-1 1-2 1-3 1-4 1-5 1-6 1-7 1-8 1-9 1-10 1-11 1-12 1-13 1-14 1-15 1-15

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Title

Page

HF Control Display KCU 951 ...................................................................................................... 1-5 VHF Switches, Control and Display TFM-138B, (F10-B software) ............................................. 1-7 Switches, Control and Display TFM-403 .................................................................................... 1-9 GPS/NAV/COMM GARMIN GNS 430W .................................................................................... 1-13 Switches, Control and Display GNC 250 XL ............................................................................ 1-19 Switches, Control GTX 327 ...................................................................................................... 1-23 Switches, Control ADF KR 87 .................................................................................................. 1-27 Switches, Control EFD1000 PFD ............................................................................................. 1-42 Control Functions KNI 415 ....................................................................................................... 1-44 Cockpit Remote Switch ............................................................................................................. 1-46 Davtron M803 Digital Clock ....................................................................................................... 1-47 ADF Indicator KI 227 ................................................................................................................. 1-48 Instruments Panel ..................................................................................................................... 1-49 Central Console ........................................................................................................................ 1-50 Circuit Breakers Panel (Sheet 1 of 2) ........................................................................................ 1-51 Circuit Breakers Panel (Sheet 2 of 2) ........................................................................................ 1-52

EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

AVIONICS SECTION I. GENERAL INFORMATION 1.1. General. This Helicopter Flight Manual Supplement applies to New Avionics installations of the NAV and COM System as part of UH-1H FACH Number H-79, S/N 66-16967, Avionics Modication. This supplement includes a brief description of the elec-

Item

1

2

3

4

5

6

System Radio Altimeter Components: - Transceiver - Antennas - Indicator ADF Components: - Receiver - Antenna - Indicator HF Components: - Transceiver - Coupler - Control Display - Antenna VHF/FM Components: - Transceiver - Antenna UHF/FM Components: - Transceiver - Antenna COM/NAV/GPS Components: - Transceptor/Rcvr - Antennas

tronic equipment, technical characteristics, capabilities and location. 1.2

Avionics conguration.

The following is the list of equipment that are part of the new conguration of helicopter avionics:

Description

Model

Manufacturer

Qty.

- Radio Altimeter TX/RX - RA Antenna - RA Indicator

KRH 405B KA 54A KNI 416

Bendix/King

01 02 01

- ADF Receiver - ADF Antenna - ADF Indicator

KR 87 KA 44B KI 227

Bendix/King

01 01 01

- HF Transceiver RX/TX - Coupler Antenna - Control Display - Antenna

KTR 953 KAC 952 KCU 951 14379

- Transceiver TFM-138B - VHF Antenna

921012-1 CI 292-3

TECHNISONIC 01 COMANT 01

- Transceiver TFM-403 - UHF Serie

941059-1 CI 275

TECHNISONIC 01 COMANT 01

- GNS 430 COM/NAV/GPS - VHF Antenna - GS Antenna - GPS GA 35 Antenna

010-00412-01 DM C70-3 CI 215 013-00235-00

GARMIN DM COMANT GARMIN

Bendix/King

01 01 01 01

01 01 01 01

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EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

Item

System

Description

7

COM/NAV/GPS Components: - Transceptor/Rcvr - Antennas

8

TRANSPONDER Components: - Transmitter - Antenna

9

EFD1000H SCREEN Components: - Display - Display Assy - Cong. Module - Conf. Module Assy - Rem. Sen. Module - RSM

10

11

12

13

14

15

1-2

EFD500H SCREEN Components: - Display - Cong. Module RELOJ Components: - Clock - OAT Probe - Alarm

Model

Manufacturer

Qty.

- GNC 250XL COM/NAV/GPS - VHF Antenna - GPS GA 56 Antenna

011-00295-00 DM C70-3 011-00134-00

GARMIN DM GARMIN

01 01 01

- Transponder GTX 327 - Antenna

010-00188-00 CI 105

GARMIN COMANT

01 01

910-00001-101 910-00005-004 910-00003-001

ASPEN

ASPEN

02 02 02

- Display Assy - Conf. Module Assy

910-00001-102 910-00005-004

- Digital Clock - OAT Sensor - Alarm Horn

10-03344 AD590KH M800

DAVTRON

02 02 01

- ADI Indicator

H200ABM

SFENA

01

- ELT Transmitter, C406-N HM - Control Panel - ELT Antenna

453-5061 C 406 110-338

ARTEX

01 01 01

- Altitud Encoder

TRANS-CAL SSD120-30N-RS232 IND.

LIGHTS Components: - POS/NAV Lights - Anticollision Light

- Position / Navigation light - Anticollision Light

11-07360 23100-201

AVEOFLASHLP 02 PATRIOT 01 TAXIWAY

- Tail Pos. Light

- Tail Position light

01-0771011-02

WHELEN

ADI Stand By ELT Components: - ELT TX - Control Panel - Antenna ALTITUD Components: - Alt. Encoder

01 01

01

01

EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

SECTION II. COMMUNICATIONS 1.3. HF Radio System KHF 950 a. Description. The KHF 950 System is a solid state design with 150 PEP Watts out power, 28 VDC. Operation frecuency range between 2.0 to 29.9999 Mhz with 100Hz resolution. A fast oven warm-up controlled by a reference oscillator provides the precise frecuency reference required for the 100 Hz synthesizer. The system has two standard operation modes, USB (A3J) and AME (A3H). The use of Lower Sideband (LSB) is not permitted on HF radio transmitters operating under the jurisdiction of Federal Communication Commission with regard to Part 87 of the FCC code of regulations. Lower Sideband mode can be used in regions or applications where its use is authorized. A3A mode (reduced carrier AM) operation can be required in certain Locations when operating under part 83 of the FCC code. The system is capable of operating in a channel mode (frecuency preset) or direct frecuency mode. b. Control and functions. Refer to gure 1.1 c. Operations (1) System Power Up When power is rst applied (OFF/ON VOL CONTROL), the frecuency display is blanked and transmission is inhibited until the crystal oven be heated and synthesizer is locked. When the FREQ /CHAN button is in depressed position, the active channel will be displayed. The active channel would be the last channel used on transmission prior system turn off.The system is functioning as receiver connected directly to HF antenna. The receiver frecuency will appear on the display ( approximately 1-3 minutes after turn on), delay time will depend on the oven temperature. Depressing mic key button momentarily will initiate the coupler auto tune sequence. Frecuency will again be blanked during the auto tune

cycle, the TX message will also ash. Emmission mode and channel number will continue to be displayed. Active frecuency will reappear upon completion of coupler tune sequence. (2) Channel Operation Channel number, emission mode and active frequency will be displayed. When operating in the optional A3A mode the AM and USB messages are both illuminated. When transmitting in the channel mode, the transmission frequency and the added TX message will be displayed. Rotation of the inner control knob causes the channel number to be incremented or decremented. The coupler is switched to the bypass condition when a channel change occurs. Depressing the mic key will initiate the auto tune sequence. If a PA or coupler fault is detected, transmission is inhibited and the frequency digits will ash indicating the fault. All 99 preset channels may be programmed for semi duplex simplex or receive only operation, as desired. A “received only” channel may be programmed to allow only receive mode. When a receive only channel is detected, the coupler is bypassed and transmission is inhibited. (3) Frequency Mode The frequency mode operation is similar to channel mode except that the frequency is selected as desired rather than on a preprogram basis. Frequency selection is accomplished by means of cursor/digit increment/decrement switch. No RCV only condition applies. Only simplex operation is allowed. Transmission is therefore allowed on 100 Hz frequency increment in the 2-30 Mhz frequency range. In normal operation, frequency, emission mode and TX message when transmitting is displayed. No channel number is displayed. When the system is transferred from channelized operation to direct frecuency control, the initial frequency displayed is the last frequency

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EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

used for transmission purposes when operating in direct frequency mode. Previous emission mode is also saved and displayed. The cursor control is the outer concentric knob and works in a increment/decrement fashion. Cursor position is annunciated by ashing the active digit. The cursor occupies one of six positions and clockwise knob rotation moves it from Left to Right. The ashing digit can be incremented or decremented with the inner knob with rollover to 0 or 9 or borrow to those digits more signicant than the cursor digit. (4) Program Mode Operation Program mode is accessed by depressing the PGM switch. Program mode must be entered in the channel conguration (only channels can be programmed). Once in program mode, channel number, emission mode and transmission frecuency are displayed. Transmission is inhibited. The transmission frecuency however, may be examined by depressing the mic key. 1.4

VHF/FM Radio System TFM-138B

may also be entered via a PC computer and PC Up/ download cable. b. Control and functions. Refer to gure 1.2 c. Operations (1) Switch power on by turning the main volume clockwise. The last programmed frequencies will be displayed. The transceiver is now in normal operating mode. (2) Adjust the audio level by adjusting the main and guard volume knobs. (3) Pressing the squelch defeat button will open both receivers to conrm they are working. (4) The top display line will indicate which memory is selected followed by a “+” if the memory positions is in the scan list, an alphanumeric message, and the frequency of the main receiver. A small “n” before the frequency indicates 12.5 Khz narrowband channel spacing is in effect on this memory position.

a. Description.The TFM-138B Transceiver is a frequency agile, fully synthesized airbone transceiver capable of operating in the 138.000 MHz frequency range in 2.5 Khz increments with either 25 Khz or 12.5 Khz channel spacing. The transceiver can operate without restriction on any split frequency pair in the band and also incorporates a two channel synthesized guard receiver.

In the receive mode, the frequency is followed by an “RT” if a RX CTCSS tone is programmed, or an “RX” if no Receive tone is programmed.

The TFM-138B transceiver provides 100 operator accesible memory positions, each one is capable of storing a transmit frequency, receive frequency, transmit frequency CTCSS tone, receive frequency CTCSS tone, an alphanumeric identier for each channel and wideband (25 Khz) or narrowband (12.5 Khz) channel spacing assignment. Operating frequency and other related data are presented on a 48 character. Two line LED matrix display. Data entry and function control are performed via a 12 button keypad. Preset channels may also be scrolled and scanned through keypad function activation. Data

(5) Only TX CTCSS tones may be programmed for the guard receiver. At the beginning of each line, a LED indicates open squelch.

1-4

Similarly, in the transmit mode either a “TT” or “TX” is shown after the frequency. The bottom line indicates similar information about the guard receiver.

(6) Set the MN/GD switch to main or guard transmit frequency. (7) Set the G1/G2 switch to the desired guard channel. (8) Set the HI/LO switch to the desired RF output power.

EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

(9) Select the desired memory by using the M.UP and M.DN buttons, or the RCL button and a three digit number followed by ENTER.

(10) To transmit DTMF tones, use the keyboard keys while holding the PTT button on the microphone. The keyboard returns to its normal function when the PTT is released.

Figure 1-1 : HF Control Display KCU 951

CONTROL / INDICATOR (KCU 951) 1. ON / OFF/ VOLUME

2. SQUELCH

3. CLARIFIER

4. MODE

FUNCTION

Applies power to the unit and controls the audio output level. Squelch control – Provides variable squelch threshold control.

Clarier control – Provides up to 250 Hz of local oscillator adjustment during the receive mode of operation only. Means are provide to disengagge the clarier function by pushing the adjust knob in.

The emission mode switch is a momentary push button that selects LSB, AME, USB or optional A3A. Emissions mode selection is cyclic moving from left to right. This switch is active at all times except transmit. A3A is indicated by displaying the AM and USB messages simultaneously.

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EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

CONTROL/INDICATOR (KCU 951)

FUNCTION

5. FREQ/CHAN

This switch transfers the HF system from a direct frequency operation to a channelized form of operation. This switch operates as a two position switch. The depressed position establishes the channelized form of operation.

6. CHANNEL/FREQUENCY SELECT

This selector consists of two concentric knobs that controls the channel and frequency digits, plus the lateral position of the cursor. These switches function as increment – decrement switches. The outer knob is not functional when the FREQ/CHAN switch is in the CHAN position. The inner knob will provide channel control from 1 through 99.

7. PROGRAM (PGM) SWITCH

This switch enables channelized data to be modied. The PGM message will be displayed whenever this switch is depressed.

8. STORE (STO) SWITCH

This switch is used to store the displayed data when programming the preset channels.

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EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

Figure 1-2 : VHF Switches, Control and Display TFM-138B, (F10-B software)

CONTROL/INDICATOR (TFM-138B)

FUNCTION

1. MAIN ON/OFF/VOLUME

Volume control for main receiver, also incorporates main power switch.

2. GUARD VOLUME

Volume control for guard receiver.

3. SQUELCH BUTTON

Squelch override test push button.

4. TX/RX DISPLAY

Indicates receive or transmit.

5.CTCSS/DPL INDICATOR

Indicates when CTCSS tones or DPL codes in use.

6.MN/GD SELECTOR

MN/GD switch sets the transmitter to operate on either the main or guard transmit frequency.

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EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

CONTROL/INDICATOR (TFM-138B)

FUNCTION

7. G1/G2 SELECTOR

G1/G2 switch selects one of two guard channels.

8. HI/LO POWER SELECTOR

HI/LO switch selects between 1 Watt and 10 Watts transmitter output power.

9. KEY PAD

Key pad for entering new information or editing, etc.

10. MAIN MEMORY CHAN DISPLAY

Indicates which memory channel is selected (main receiver).

11. GUARD CHAN DISPLAY

Indicates which channel is selected on guard receiver.

12. CURRENT FREQ.DESCRIPTION

Alpha numerical message describing the current frequency.

13. RX/TX DISPLAY

Indicates receiver or transmit.

1.5

UHF/FM Radio System TFM-403

a. Description. The TFM-403, UHF/FM Transceiver is a frequency agile, fully synthesized airborne transceiver capable of operating in the 403.000 MHz to 512.000 MHz frequency range in 2.5 KH increments with either 25 KHz or 12.5 KHz channel spacing. The Transceiver can operate without restriction on any split frequency pair in the band and also incorporates a two channel synthesized guard receiver. The TFM-403 Transceiver provides 120 operator accessible memory positions, each one is capable of storing a transmit frequency, receive frequency, (in the TFM-403 s/n J0200 and up only) wideband (25 KHz) or narrowband (12.5 KHz) channel spacing assignment, transmission frequency CTCSS tone or DPL code, receive frequency and an alphanumeric identier for each channel. Operating frequency and 1-8

other related data are presented on a 48 character, two line LED matrix display. Data entry and function control are performed via a 12 button keypad. Preset channels may also be scrolled and scanned through keypad function activation. Data may also be entered via an MS-DOS based computer with the provided software and optional PC download cable. b. Control and functions. Refer to gure 1.3 c. Operations (1) Switch power on by turning the main volume clockwise. Depending how the radio is congured, either the last programmed or last displayed frequency will appear on the screen. The transceiver is now in normal operating mode. (2) Adjust the audio level by adjusting the main and guard volume knobs.

EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

(3) Pressing the squelch defeat button will open both receivers to conrm that both are working.

beginning of each line, an LED indicates open squelch.

(4) Read the display. The top line will indicate memory selected followed by a "+" if the memory position is included in the scan list, an alphanumeric message, and the frequency of the main receiver. A small "n" before the frequency indicates 12.5 Khz narrowband channel spacing is in effect on this memory position. In the receive mode, the frequency is followed by an "RT" if a RX CTCSS tone or RX DPL code is programmed, or an "RX" if no Receive tone/ code is programmed. Similarily, in the transmission mode either a "TT" or "TX" is shown after the frequency. The bottom line indicates similar information about the guard receiver.

(6) Set the MN/GD switch to main or guard transmit frequency.

(5) Only TX CTCSS tones or TX DPL codes may be programmed for the guard receiver. At the

(7) Set the G1/G2 switch to the desired guard channel. (8) Set the HI/LO switch to the desired RF output power. (9) Select the desired memory by using the M.UP and M.DN buttons, or the RCL button and a three digit number followed by ENTER. (10) To transmit DTMF tones, use the keyboard keys while holding the PTT button on the microphone. The keyboard returns to its normal function when the PTT is released.

Figure 1-3 : Switches, Control and Display TFM-403 1-9

EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

CONTROL/INDICATOR (TFM-403)

FUNCTION

1. MAIN ON/OFF/VOLUME

Volume control for main receiver, also incorporates main power switch.

2. GUARD VOLUME

Volume control for guard receiver.

3. SQUELCH BUTTON

Squelch override test push button.

4. TX/RX DISPLAY

Indicates receive or transmit and tone or no tone.

5.CTCSS/DPL INDICATOR

Indicates when CTCSS tones or DPL codes in use.

6.MN/GD SELECTOR

MN/GD switch sets the transmitter to operate on either the main or guard transmit frequency.

7. G1/G2 SELECTOR

G1/G2 switch selects one of two guard channels.

8. HI/LO POWER SELECTOR

HI/LO switch selects between 1 Watt and 10 Watts transmitter output power.

9. KEY PAD

Key pad for entering new information or editing, etc.

10. MAIN MEMORY CHAN DISPLAY

Indicates which memory channel is selected (main receiver).

11. GUARD CHAN DISPLAY

Indicates which channel is selected on guard receiver.

12. CURRENT FREQ.DESCRIPTION

Alpha numerical message describing the current frequency.

13. RX/TX DISPLAY

1-10

Displays receive frequency during receive and transmit frequency during transmit.

EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

SECTION III. NAVIGATION 1.6

GPS/NAV/COMM Garmin GNS 430W

a. Description. The GNS 430W is an all-in-one GPS/ Nav/Comm solution. It features a WAAS-certied GPS, 2280-channel capacity comm and 200-channel ILS/VOR with localizer and glideslope. Traditionally it would take a host of components to provide the capabilities of this one smart box. High-speed 5 Hz processing makes navigation calculations and map redraw rates ve times faster than earlier GNS series navigators. GNS 430W comes with built-in WAAS navigation capabilities. It is approved to y LPV glideslope approaches without reference to ground-based navaids of any kind. Featuring an advanced 15-channel receiver capable of ve position updates per second, GNS 430W meets the FAA's stringent TSO C146a standards for WAAS "sole means" navigation providing vertical and lateral approach guidance into airports previously inaccessible in IFR conditions. GNS 430W's 4-inch high-contrast display with brilliant colors makes it easy to read and interpret pilotcritical information. Effective use of color makes it easy to see your position relative to ground features, chart data, navaids, ight plan routings, approach procedures and more. Conveniently scan information from wide viewing angles, even in direct sunlight. b. Control and functions. Refer to gure 1.4. c. Operations. This is a quick reference for VFR functions of these units, the Garmin 400W Series Pilots Guide, must be inmediately available for the ight crew whenever navigation is predicated on the use of the 400W Series Unit. Remember to always Keep Your Head Up when using your GPS in visual conditions.Pilots are always responsible for a safe ight, including avoiding midair collisions.

(I) POWER ON (1) The COM power/volume turns the unit on and sets the desired radio volume. The self test screen will display briey. (2) Database Conrmation - Database current? Press ENT. (3) Instrument Panel Self Test - Compare the GPS screen with panel instruments. Everything OK? Press ENT. (4) Map Page - When the GPS has acquired enough satellites for navigation, the Map page shows your present position. (II) USING THE VHF COMM (1) All COMM controls and indicators are located on the left. The active frequencies are on top, standby on the bottom. Only the standby frequency can be tuned directly. Once tuned, it is transfered to the active position. (2) Position Entry Cursor - If the tuning cursor is not currently in the COMM window, press the small left knob momentarily. (3) Enter Frequency - The large left knob tunes MHz. Think “big number, big knob”. The small left knob tunes kHz. (4) Activate Frequency - The COMM ip-op key activates the tuned frequency. The standby frequency becomes active, and the active frequency becomes standby. (5) Adjust Volume - using the power/volume knob. Press it momentarily to disable the automatic squelch.

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EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

(6) Using Emergency Frequency- Press and hold the COMM ip-op key for two seconds to quickly tune 121.5.

(2) SELECT DIRECT-TO the Direct-To key Press. The direct-to page appears, with the cursor on the waypoint identier.

(III) USING VLOC

(3) GPS Data Entry - Entering waypoints and other data into the GPS is a three step process.

(1) VLOC refers to tuning and navigating with VOR and localizer (LOC) signals. All VLOC controls and indicators are located on the left. The active frequencies are on top, standby on the bottom. (2) Position Entry Cursor - If the tuning cursor is not currently in the VLOC window, press the small left knob momentarily. (3) Enter Frequency - The large left knob tunes MHz. Think “big number, big knob”. The small left knob tunes kHz. (4) Activate Frequency - The VLOC ip-op key activates the tuned frequency. The standby frequency becomes active, and the active frequency becomes standby. (5) Adjust Volume - using the VLOC volume knob. Press it momentarily to enable and disable the navigation aids ident tone. (IV) SELECT NAV SOURCE (1) The CDI key toggles between GPS and VLOC outputs for the CDI or HSI. The selected navigation source is displayed just above the CDI key.

Selecting the wrong CDI source is a common but serious problem. (V) ABOUT GPS (1) The most frequently used features of any GPS are direct-to, map display, and nearest airport. All the controls and indicators for the GPS are located on the right side of the panel.

1-12

a. Enter identier letters and numbers. b. Conrm it is the correct waypoint. c. Activate the waypoint for navigation. (4) Enter Waypoint Identier - The large right knob moves the cursor about the page. The small right knob selects individual characters. If you don’t see the cursor, press the small right knob momentarily. The cursor allows you to enter data and/or make a selection from a list of options. (5) Conrm Waypoint - Press ENT. (6) Activate Waypoint - Press ENT again. The selected course is displayed as a magenta line, and the CDI indicates the direct course to the waypoint. (VI) GPS MAPS

(1) Display Default NAV Page - On the GNS 430, press and hold the CLR key for two seconds. The default NAV page is displayed. The default NAV page shows the bearing and distance to the active waypoint, ground speed, and estimated time of arrival at the active waypoint. (2) Display Map Page - Turn the small right knob one click clockwise. The Map page is displayed. It is the second in the NAV page group as indicated below the map. The Map page shows the active waypoint identier, track and distance, and ground speed. (3) Adjust Range- Use the RNG key to change the map scale . The up arrow zooms out, the down arrow zooms in. The current map scale is shown at lower left corner of map.

EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

(VII) NEAREST PAGES (1) Display Nearest Airport Page - Press and hold CLR to display the default NAV page.Turn the large right knob to select the NRST page group. NRST will appear in the lower right corner of the screen. The nearest airport page displays airport identier, bearing, distance, and other information. To scroll through nearby airports, press the small right knob to activate the cursor, then use the large right knob to scroll through the list.

(2) Go DIRECT-TO a nearby airport- With the cursor on the desired airport, press the Direct-To key to display the “select direct-to waypoint” page. The identier for the previously selected nearby airport should already be entered. (3) Go DIRECT-TO the Selected Airport - Press ENT to accept the selected airport’s identier. Press ENT again (with “Activate?” highlighted) to navigate to that airport. The Map page will be displayed.

Figure 1-4 : GPS/NAV/COMM GARMIN GNS 430W 1-13

EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

CONTROL/INDICATOR (GNS 430W) 1. POWER AND COMM VOLUME/SQUELCH

2. NAV RADIO VOLUME

FUNCTION Controls unit power and COM volume. Pressing it momentarily disables automatic squelch control. Controls volume for the VOR/Localizer (VLOC). Pressing it momentarily enables or disables the ident tone.

3. LARGE KNOB COMM/VLOC FREQ (MHZ)

Tunes Megahertz (Mhz) values for the standby COM or VLOC frequency.

4. SMALL KNOB COMM/VLOC FREQ (KHZ)

Tunes the Kilohertz (Khz) values for the COM or VLOC frequency. Pressing the small knob momentarily also toggles the tuning cursor between the COM and VLOC frequency elds.

5. COM FLIP-FLOP KEY

Swaps the active and standby COM frequencies. Press and hold it to automatically tune the emergency frequency (121.5).

6. VLOC FLIP-FLOP

Swaps the active and standby VLOC frequencies.

7. CDI KEY

Toggles the navigation source (GPS or VLOC) going to the external CDI or HSI.

8. OBS KEY

Used to select manual or automatic sequencing of waypoints.Pressing the OBS Key selects OBS mode, which will retain the current “active to” waypoint as your navigation reference even after passing the waypoint.Pressing the OBS key again will return to normal operation.

9. MESSAGE KEY

Used to view system messages and important warnings and requirements.

10. FLIGHT PLAN KEY

This key allows you to create, edit, activate and invert ight plans, as well as acces approaches,departures and arrivals.

11. PROCEDURE KEY

This key allows you to select and remove approaches, departures and arrivals from your ight plan.

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EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

CONTROL/INDICATOR (GNS 430W)

FUNCTION

12. SMALL RIGHT KNOB (GPS)

Selects pages within a group listed above. Pressing it momentarily displays the cursor.

13. LARGE RIGHT KNOB (GPS)

Selects between the displayed page groups: NAV, WPT, AUX or NRST. It also allows you to move the cursor about the page.

14. ENTER KEY

Approves an operation or completes data entry. It also conrms information, like during power on.

15. CLEAR KEY

Erases information or cancel an entry. Press and hold CLR to display the Default Navigation Page.

16. MENU KEY

Displays a context-sensitive list of options. This options list allows you to access additional features or make settings changes which relate to the currently displayed page.

17. DIRECT-TO KEY

Provides access to the direct-to function, which allows you to enter a destination waypoint and establishes a direct course to the selected destination.

18. RANGE KEY

Allows you to select the desired map scale. Use the up arrow side of the key to zoom out to a larger area, or the down arrow side to zoom in to a smaller area.

19. MAP DISPLAY AND NAV INFO

The default NAV, map and NAVCOM pages will be the primary pages used for navigation. The default NAV page displays a graphic course deviation indicator (CDI), the active leg of your ight plan (as dened by the current “from” and “to” waypoints),and six userselectable data elds. The default settings for these elds are distance to waypoint (DIS), desired track (DTK), bearing to waypoint (BRG), ground speed (GS), ground track (TRK) and estimated time en route (ETE).

20. COMM FREQ. WINDOW

21. NAV FREQ. WINDOW

This display is divided into separate “windows” (or screen areas), the upper section, shows the active Comm frequency, the bottom section shows the standby Comm frequency. This display is divided into separate “windows” (or screen areas), the upper section, shows the active Comm frequency, the bottom section shows the standby Comm frequency.

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EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

CONTROL/INDICATOR (GNS 430W)

22. PHOTOCELL FOR AUTO-DIMMING

23. CAM LOCK

FUNCTION The unit can automatically adjust for ambient lighting based on this photocell sensor. To install or remove the unit, insert the special

wrench exa throught this hole and turn to corresponding direction.

24. ALERT DISPLAY

Waypoint and arrival alerts, turn advisories, function and page numbers.

25. ANNUNCIATOR

Displays a advice of terrain, Flight Phase and GPS Integrity annunciator.

26. OUTER SLOT

Provides access to install a Aviation Database Card.

27. INNER SLOT

Provides access to install a Terrain Database Card.

28. NAV SOURCE INDICATOR

Show the Navigation Source that is being used: GPS, VLOC or GPS-PTK.

1.7. GNC 250XL Integrated GPS/NAV/COM System a. Description.This helicopter is equipped with a GNC 250XL integrated GPS navigator and COM receiver. The GPS navigator consists of a GPS receiver and a Jeppesen Nav Data database all contained in the GNC 250XL control unit mounted in the center console. Also integrated into the GNC 250XL control unit is a VHF communications receiver. All tuning and display controls for the GPS and COM are located in the GNC 250XL control/display in the center console. b. Control and functions. Refer to gure 1.5. c. Operations.

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NOTE

This is a quick reference for VFR functions of these unit, the Garmin GNC 250 XL Pilots Guide and Reference, must be inmediately available for the ight crew whenever navigation is predicated on the use of the GNC 250 XL Unit. (I) POWER ON (1) Insert data card in card slot (2) The GNC 250 XL power and volume are controlled using the power/volume knob at the bottom left of the unit. Rotating it clockwise will turn

EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

the unit on and increase the radio volume, a welcome page will be displayed while the unit performs a self test.

by leaving the cursor on the standby frequency, or remove the cursor by pressing the CRSR key twice.

(3) The Database page will appear, showing the current database information on the Nav Data card. To acknowledge the database information. Press ENT key.

(6) To override the automatic squelch, press the SQ key. Press SQ again to return to automatic squelch.

(4) Once the database has been acknowledge, the satellite status page will appear, and the GNC 250 XL will begin to collect satellite information. An “Acquiring” status will be displayed on the satellite status page, and the signal values on the bottom line of the page will begin displaying numeric values. (5) When the GPS is acquiring a position, let´s take a minute to dial in the active and standby frequencies you´ll be using for the rst phase of your ight. The GNC 250 XL display can be broken down into two separate “windows” The COMM window and the GPS window. (II) USING THE VHF COM (1) The CRSR key is used to activate the cursor in a particular window to provide access to various comm and navigation features. To select the active frequency, you must rst enter the frequency in the standby eld, and use the arrows key to move it to the active eld. (2) To change the standby communication frequency, press CRSR key once to active the cursor in the comm window. (3) Rotate the outer knob to select the Mhz, and the inner knob to select the Khz of desired frequency. (4) To place the standby frequency in the active eld, press the arrow key. (5) Once you entered the active frequency, simply repeat steps 1 and 2 to enter the standby frequency. After both frequencies have been entered, you may elect to keep the comm window “hot”

(7) To auto-tune a frequency displayed in the GPS Database, press ENT key with the cursor off to select the frequency as the standby frequency. (8) To auto-tune a frequency from a list in the GPS database, press CRSR twice to active the cursor in the GPS window, rotate the outer knob to highlight the desired frequency, then press ENT to place the frequency in the standby eld. (9) To automatically tune for emergency transmission, press and hold the arrows key for more than two seconds. (III) USING NAVIGATION PAGES The GNC 250 XL features seven navigation pages to provide various position, course, speed, status and planning information. The pages may be viewed by pressing the NAV key and rotating the outer knob, or by pressing the NAV key repeatedly. (1) The CDI Page: provides with important information needed to navigate directly to destination. (2) To change any of the selectable elds on the CDI page, press CRSR twice to activate the cursor in the GPS window, rotate the outer knob to highlight the eld you would like to change, rotate the inner knob to change the eld to display the desired information, rotate the outer knob to highlight another eld, or CRSR to nish. (3) The Map Page: displays the present position, using an airplane symbol (in track up mode) or a position diamond (in other orientation modes), along with nearby airports, VORs, NDBs, intersections, user waypoints and airspace boundaries.

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EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

(4) The Map display can be set to 14 different scale settings from 0.5 to 300 (nautical miles, statute miles or kilometers) the scale represents the topto-bottom distance covered by the map display. (5) To select a map scale, rotate the inner knob clockwise to increase the map scale and show a larger area, rotate the inner knob counter clockwise to decrease the map scale and show a smaller area. (6) The Nav Comm Page: provides a list of the airport frequencies at the departure and arrival airports, allowing convenient selection of frequencies you´ll need along your ight path. (7) To scroll through the list of frequencies, rotate the inner knob in the direction of arrow prompts at the bottom left of the page. (8) To make any of the frequencies on the Nav Comm page the standby frequency, press CRSR twice to activate the cursor in the GPS window, rotate the outer knob until the desired frequency is highlighted, press ENT to make the highlighted frequency the standby frequency, the curso will automatically advance to the next frequency on the list. (9) The Position Page: displays the present latitude and longitude, altitude and reference waypoint eld. The altitude and reference waypoint elds are selectable to congure the page preferred and current navigation needs. (10) To change the altitude eld, press CRSR twice to obtain a cursor in the GPS window, rotate the outer knob until the alt/ESA/MSA eld is highlighted, rotate the inner knob to display the desired data. Press CRSR to return to normal navigation. (11) The position page also features a reference waypoint eld. Located at the bottom of the page, to indicate the bearing and distance from a selected waypoint.

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(12) The Satellite Status Page: provide satellite information to monitor GPS coverage and receiver perfomance, this helpful when you may be experiencing low signal levels due to poor coverage or installation problems. (13) To view the satellite status page, press NAV key and rotate the outer knob until the satellite status page appears. (14) In addition to the other pages, the GNC 250 XL features two menu pages to perform a host planing and navigation functions. Nav menu 1 provides acces to the following functions: Trip planing, Fuel Planning, VNAV planing, Density altitude/true airspeed calc., Winds aloft calculations and Checklists. (15) To display NAV Menu 1, press NAV and rotate the outer knob until NAV Menu 1 is displayed. (16) The NAV Menu 2 provides acces to various timer and planning functions, including: approach timer, trip timer, schedule messages, clock (data and time), rain prediction and sunrise and sunset calculations. (17) To display NAV Menu 2, press NAV, and rotate the outer knob until NAV Menu 2 is displayed. (IV) ABOUT GPS (1) The most frequently used features of any GPS are direct-to, map display, and nearest airport. All the controls and indicators for the GPS are located on the botton of the panel. (2) SELECT DIRECT-TO. Press the Direct-To key. The direct-to page appears, enter the identier of the destination waypoint, press ENT to accept the identier, and ENT again to accept the direct-to conrmation page. (3) To enter a new course from the CDI Page, press CRSR twice to active the cursor in the GPS

EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

window, rotate the outer knob to highlight the course select eld, use the inner and outer knobs to enter the desired course, press ENT to conrm and CRSR to remove the cursor.

(4) To view Nearest APT Information, Press the NRST key. The nearest airport will be displayed, subject to the runway surface type and minimum runway length currently selected.

Figure 1-5 : Switches, Control and Display GNC 250 XL . CONTROL/INDICATOR (GNC 250 XL)

FUNCTION

1. POWER/VOLUME KNOB

The power/volume knob controls unit power and COM volume.

2. SQ BUTTON

The squelch button activates automatic squelch control.

3. DIRECT-TO KEY

The direct-to key performs an instant direct-to, allows you to enter a waypoint, and sets a direct course to the destination.

4. NRST KEY

The nearest key is used to obtain information on the 9 nearest airport, VORs, NDBs, intersections, user waypoint and 2 nearest FSS/ARTCC points of comunication. The nearest key also accesses any active SUA information.

5. RTE KEY

The route key enables to create, edit, activate and invert routes. Search and resue, parallel offset and closest point of approach functions are also performed using the route key.

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EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

CONTROL/INDICATOR (GNC 250 XL)

FUNCTION

6. WPT KEY

The waypoint key is used to view information such as runway, frequencies, position and comments on airports, VORs, NDBs, intersections and used waypoints.

7. NAV KEY

The navigation key is used to view navigation and position information. Planning operations are also performed using this key.

8. MSG KEY

The message key is used to view system messages. This key is also used to access the GNC 250 XL unit settings.

9. ◄ ► ARROW KEY

The transfer key ip-ops the active and standby frequencies.

10. CLR KEY

The clear key is used to erase information or cancel an entry.

11. ENT KEY

The enter key is used to approve an operation or complete data entry. It is also used to conrm information, such as during power on.

12. CRSR KEY

The cursor key is used to activate or deactivate the cursor in the separate areas of the GNC 250 XL. Pressing once will activate the cursor in the “COMM” window and enable the pilot to change frequencies. Pressing twice will activate the cursor in the GPS window. It is used to hightlight elds for data entry, changing information or cycling through available options.

13. ☼ OUTER KNOB

The outer knob is used to advance through pages, advance the cursor or move through data elds.

14. ● INNER KNOB

The inner knob is used to change data or scroll through information that cannot t on the screen all at once.

15. CARD SLOT

Used to insert the Nav Data Card.

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EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

SECTION IV. TRANSPONDER 1.8

TRANSPONDER Garmin GTX 327

a. Description. The GTX 327 is a panel-mounted transponder with the addition of altitude reporting and timing functions. The transponder is a radio transmitter and receiver that operates on radar frequencies, receiving ground radar or TCAS interrogations at 1030 Mhz and transmitting a coded response of pulses to ground-based radar on a frequency of 1090 Mhz. As with other Mode A/Mode C transponder, the GTX 327 replies with any one of 4.096 codes, which differ in the position and number of pulses transmitted. By replying to ground transmissions or TCAS interrogations, the GTX 327 enables ATC to display aircraft identication, altitude and ground speed on ATC radar screens or TCAS trafc indicators. The GTX 327 is equipped with IDENT capability that activates the Special Position Identication (SPI) pulse for 18 seconds. The GTX 327 is congured with all key controls. The Layout of the front panel keys and displays segregates the transpoder´s primary functions from the secondary timing functions. The unit can be congured so the aircraft avionics master bus can turn the unit on.

(I) POWER ON

NOTE

Any time the function switch is in the ON or ALT position the transponder becomes an active part of the Air Trafc Control Radar Beacon System (ATCRBS). The transponder also responds to interrogations from TCAS equipped aircraft. (1) The GTX 327 transponder is powered on by pressing the STBY, ON, or ALT key powers on the transponder displaying the last active identication code. (2) After power ON, a start-up page is displayed while the unit performs a self test. (3) If the GTX 327 is congured with Automated Airborne Determination, ight operation is automatic and not dependent on user mode selection.Whether STBY, ON or ALT is selected on the ground, the transponder annunciation continues to indicate STBY and does not respond to radar or TCAS interrogations. When lift-off is sensed, the unit automatically selects the ALT mode.

b. Control and functions. Refer to gure 1.6.

(II) CODE SELECTION

c. Operations.

(1) Code selection is done with eight keys (0-7) that provide 4,096 active identication codes. Pushing one of these keys begins the code selection sequence. The new code is not activated until the fourth digit is entered.

NOTE

This is a quick reference for VFR functions of these units, the Garmin GTX 327 Pilots Guide, must be inmediately available for the ight crew whenever navigation is predicated on the use of the GTX 327 Unit.

NOTE

The GTX 327 should be turned off before aircraft engine starting.

(2) Pressing the CLR key moves the cursor back to the previous digit. Pressing the CLR key when the cursor is on the rst digit of the code, or pressing the CRSR key during code entry, removes the cursor and cancel the data entry, restoring the previous code. (3) You may press the CLR key up to ve seconds after code entry is complete to return the cursor to the fourth digit.

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EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

(4) The numbers 8 and 9 are not used for code entry, only for entering a Count Down time, contrast and display brightness, and data selection in the Conguration Mode.

NOTE

The selected identication code should be entered carefully, either one assigned by air trafc control for IFR ight or an applicable VFR transponder code. (III) TIMER OPERATION. (1) To operate the Flight Timer: Press the FUNC key until FLIGHT TIME is displayed, If the GTX 327 Flight Timer is congured as ACCUMULATE or CLEAR, the timer will begin automatically when the unit senses that the aircraft has become airborne, the timer may be reset to zero at every lift-off (CLEAR), continue accumulating time at lift-off (ACCUMULATE), or may be controlled manually (MANUAL). (2) If desired, press START/STOP to pause or restart the timer, press CLR to reset the timer to zero. If the timer is congured to start automatically it will pause when the Automated

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Airborne Determination senses that the aircraft is on the ground. (3) To operate the Count Up timer: Press the FUNC key until COUNT UP is displayed, if is necessary, press CLR to reset the Count Up timer to zero. (4) Press START/STOP to begin counting up, press START/STOP again to pause the timer. (5) Press CLR to reset the timer to zero. (6) To operate the Count Down timer: Press the FUNC key until COUNTDOWN is displayed, press CRSR and use the 0 – 9 keys to set the initial time. All digits must be entered (use the 0 key to enter leading zeros). (7) Press START/STOP begin to counting down, press START/STOP again to pause the timer. (8) When the Count Down timer expires, the COUNT DOWN banner is replaced with a ashing EXPIRED, and the times begins counting up. (9) Press CLR to reset the timer to the initial time value.

EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

Figure 1-6 : Switches, Control GTX 327

CONTROL/INDICATOR (GTX 327)

FUNCTION

1. OFF BUTTON

Powers off the GTX 327. Pressing STBY, ON, or ALT key powers on the transponder displaying the last active identication code.

2. STBY BUTTON

Selects the standby mode. When in standby mode, the transponder will not reply to any interrogations.

3. ON BUTTON

Selects Mode A. In this mode, the transponder replies to interrogations, as indicated by the Reply Symbol ( R ). Replies do not include altitude information.

4. ALT BUTTON

Selects Mode A and Mode C. In ALT mode, the transponder replies to identication and altitude interrogations as indicated by the Reply Symbol (R ). Replies to altitude interrogations include the standard pressure altitude received from an external altitude source.

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EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

CONTROL/INDICATOR (GTX 327)

5. IDENT KEY

6. VFR KEY

FUNCTION Pressing the IDENT key activates the Special Position Identication (SPI) Pulse for 18 seconds, identifying your transponder return from others on the air trafc controller´s screen. The word IDENT will appear in the upper left corner of the display during this time. Sets the transponder code to the pre-programmed VFR code selected during installation conguration (this is set at 1200 at the factory). Pressing the VFR key again restores the previous identication code. If the VFR key is pressed when disabled (dependent upon installation conguration) a VFR key Disabled message appears, to indicate that no operation took place.

7. FUNC KEY

Changes the page show on the right side of the display. Display includes Pressure Altitude, Flight Time, Count Up, and Count Down timers.

8. START/STOP KEY

Starts and stops the Count Up, Count Down and Flight timers.

9. CRSR KEY

Initiates starting time entry for the Count Down timer and cancels transponder code entry.

10. CLR KEY

Resets the Count Up, Count Down and ight timers. Cancels the previous key press during code selection and Count Down entry. Returns cursor to the fourth code digit within ve seconds after entry.

11. 8 KEY

Reduces Contrast and Display Brightness when the respective elds are displayed and enters the number eight into the Count Down timer.

12. 9 KEY

Increases Contrast and Display Brightness when respective elds are displayed and enters the number nine into the Count Down timer.

13. DIGIT KEY ( 0 - 7)

Code selection is done with eight keys (0-7),pushing one of this key begins the code selection sequence.

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EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

1.9.

AUTOMATIC DIRECTION FINDER KR 87

a. Description. The KR 87 Automatic Direction Finder is a digitally tuned solid state receiver which provides bearing information to stations in the 200 KHz to 1799 KHz frequency band and which also provides audio reception to enable the pilot to identify stations and listen to transcribed weather broadcasts or commercial radio stations in the AM broadcast band. The unit features a gas discharge display that displays the active ADF frequency in the left window. The right window will display either the standby frequency (which can be transferred to the active window) or a ight timer or programmable elapsed timer. The ight timer will keep track of the total ight time, while the independent programmable elapsed timer can be reset to count up from zero or preset to a value and count down to zero. This feature will prove especially valuable for non-precision timed approaches, fuel management, dead reckoning navigation, etc. An automatic dimming circuit adjusts the brightness of the display to compensate for changes in ambient light level. A single-chip microprocessor is used to control the display, provide the timer functions, control the tuning circuitry, and provide timing reference signals. A non-volatile electrically alterable memory (EAROM) is used to store the active and standby frequencies even after the unit is turned off. The tuning circuitry utilizes a single reference frequency crystal and a large scale integrated circuit (LSI). The KR 87 is an extremely compact ADF, requiring only 1.3 inches of panel height. Power consumption is only 12 watts at any input voltage, therefore, forced air cooling is not required. The KI 227 is a single needle ADF Indicator and is the basic indicator used with the KR 87. b. Control and functions. Refer to gure 1.7. c. Operations. It is recommended that the KR 87 unit be turned off during engine starting in order to prevent possible voltage transient damage to the radio. The unit is

turned on by rotating volume control clockwise past the detent. The volume control is used to adjust the audio output for a comfortable listening level.

NOTE

The audio muting feature of the KR 87 will cause the audio output to be muted unless the receiver is locked onto a valid station. This reduces interstation noise and aids to pilot in identifying usable stations. (I) POWER ON. (1) Rotate the ON/OFF/VOL knob clockwise from the detented “OFF” position, the unit will be activated and will be ready to operate, rotation of this control also adjusts audio volume. (2) The KR 87 has “audio muting” which causes the audio output to be muted unless the receiver is locked on a valid station. (II) FREQUENCY SELECTION (1) The active frequency (to which the ADF is tuned) is displayed in the left side of the window at all times. (2) The standby frequency is displayed in the right side when “FRQ” is annunciated, the standby frequency is placed in “blind” memory when either FLT (Flight Time) or ET (Elapsed Time) mode is selected. (3) With “FRQ” annunciated, the standby frequency is selected using the frequency select knobs which may be rotated either clockwise or counterclockwise. (4) Pull small inner knob out to tune 1´s. (5) Push small inner knob in to tune 10´s. (6) Outer knob tunes the 100´s and the 1000´s up to 1799.

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EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

(7) The stanby frequency selected may then be put into the active window by pressing the “FRQ” button. (8) The standby and active frequencies will be exchanged (ip-opped), the new frequency will become active, and the former active frequency will go into standby. (III) OPERATION MODES The KR 87 Automatic Direction Finder has two operational modes. In the ANT (Antenna) mode (ADF button out) the loop antenna is disabled, and the unit simply acts as a receiver, allowing audio reception through the speaker or headphones. The indicator needle will remain parked at the 90º relative position and the ANT message on the left side of the display will be lighted. This mode provides slightly clearer audio reception, and is used for station identication. In various parts of the world, some L/MF stations use an interrupted carrier for identication purposes. A Beat Frequency Oscillator (BFO) function is provided to permit these stations to be more easily identied pushing the BFO switch will cause a 1000Hz tone to be heard whenever there is a radio carrier signal present at the selected frequency. It will also light the BFO message in the center of the display.

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(3) The bearing pointer in the KI 227 indicator will be deactivated and immediately turn to the 90º relative position and remain there during ANT reception. (4) The ADF mode is selected and annunciate when the “ADF” button is in the depressed position. (5) ADF activates the bearing pointer in the KI 227 indicator, causing it to move without hesitation to point in the direction of the station relative to the aircraft heading. (6) The compass card on the KI 227 may be rotated as desired by using the heading knob. (IV)TIMER OPERATION (1) Flight time or elapsed time are displayed and annunciated alternatively by depressing the FLT/ET button. (2) The ight timer continues to count up until the unit is turned off or stopped with an external switch. (3) The elapsed timer may be reset back to :00 by pressing the SET/RST button.It will then start counting up again.

(1) Antenna (ANT) mode is selected and annunciated when the “ADF” button is in the “out” position.

(4) The elapsed timer also has a “count down” mode. To enter the countdown mode, the SET/ RST button is depressed about two seconds, or until the “ET” annunciation begins to ash.

(2) ANT provides improved audio reception from the station tuned and is usually used for identication.

(5) In this ET mode, a time up to 59 minutes, 59 seconds may be preset into the elapsed timer with the concentric knobs.

EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

Figure 1-7 : Switches, Control ADF KR 87

CONTROL / INDICATOR (ADF KR 87) 1. POWER/VOLUME SWITCH

FUNCTION This knob controls ON/OFF/VOL.

2. FREQUENCY SELECT KNOBS

The active frequency is displayed in the left side of the window, with a standby frequency displayed in the right side when “FRQ” is annunciated. Pull the small inner knob out to tune 1´s, push in to tune 10´s. The outer knob tunes the 100´s and the 1000´s up to 1799.

3. ADF BUTTOM

Use the ADF mode (“in” position) for navigation. Use the ANT (Antenna) mode (“out” position) for improved audio reception.

4. BFO BUTTON

This is used in some countries other than U.S. to allow the Morse code identier to be heard on unmodulated stations.

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EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

CONTROL/INDICATOR (ADF KR 87)

5. FRQ BUTTON

6. FLT/ET BUTTON

FUNCTION Pressing this button “ip-ops” frequency displays, switching between preselected “standby” and “active” frequencies. It´s also used to retrieve the “standby” frequency in the timer modes. Use this button to select ight time (FLT) or elapsed time (ET).

7. SET/RST BUTTON

Use this button to set and reset the Elapsed Timer.

8. ANT/ADF INDICATOR

Show the frequency in used.

9. FREQUENCY IN USE

Show the frequency in use.

10. FREQUENCY STANDBY

11. FT/ET ANNUNCIATION

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Show The standby frequency. Reduces Contrast and Display Brightness when the respective elds are displayed and enters the number eight into the Count Down timer.

EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

1.10 PRIMARY FLIGHT DISPLAY ASPEN EFD 1000H / MFD EFD 500H SYSTEM a. Description.The system installed on the helicopter, combines two EFD1000H PFD (pilot´s and copilot´s) and one EFD500 MFD to provide a glass cockpit solution. The EFD1000H is a highly capable Electronic Flight Instrument System (EFIS) with integral Micro Electromechanical Systems (MEMS)-based Air Data Attitude and Heading Reference System (ADAHRS) with an internal backup battery. The system offers two Primary Flight Displays (PFD) with Attitude Indicator , HSI, and two pointer RMI. The standard internal battery in the EFD1000H Pro PFD is capable of providing 30 minutes of operation at typical cockpit temperatures if aircraft power fails. The EFD500H MFD Navigation Map VIEW is a pilot congurable moving map which can be rendered as either a VFR or IFR style map. The map consists of symbols depicting the location of Navaids, intersections, airports, topographic information, boundaries, and GPS ight plan and waypoints. Various information overlays are accessible via Hot Keys.The EFD500H MFD display is similar to the EFD1000H PFD display, but excludes the ADAHRS, RSM, Secondary HSI. The EFD500 can only be used as a Multi Function Display (MFD). b. Control and functions. Refer to gure 1.8. c. Operations. (I) LIMITATIONS (1) Pilots Guide:The Aspen Avionics EFD1000/500 MFD Pilots Guide, Document number 09100006-001 Rev. (B) or later approved revision, must be immediately available to the crew at all times. (2) Software:The EFD1000H must use software version 2.0 or later approved version. (3) RSM GPS usage (PFD 1000H Only):The RSM (Remote Sensor Module) GPS is limited to EMERGENCY USE ONLY. Position data from the RSM GPS will ONLY be presented following the loss or failure of a certied external GPS navigator.

NOTE

When the RSM GPS is in use, magnetic variation data used by the base map is not updated. This can result in misaligned base map symbology whenever the external GPS position source is lost and the aircraft travels far enough to produce a signicant change in the local magnetic variation. (4) Geographic Limitation: Like all compass systems, the magnetometer used in the EFD1000H system will experience degraded performance in the vicinity of the magnetic poles. When the horizontal component of the earth's magnetic eld is no longer strong enough to provide reliable heading data, the EFD1000H system will present a “CROSS CHECK ATTITUDE” annunciation and will subsequently ag the magnetometer data as invalid, resulting in the annunciated loss of heading and attitude. Depending on the aircraft latitude and longitude, this effect could be observed as far away as 750 nm from the magnetic pole (approximately 77- North or South latitude). (5) Operation on internal battery:Takeoff with rotorcraft voltage (as indicated on the EFD1000H PFD System) below 24.6V is NOT AUTHORIZED. (II) POWER ON Refer to Aspen Avionics document 091-00006001 Rev. (B) EFD1000/500 MFD Pilot's Guide for detailed operating instructions of the EFD1000H/MFD EFD500 System. (1) Exterior inspection: (a) RSM(s) - Check condition and security. (b) RSM Vent Hole - Check clear of obstructions. (c) RSM Lightning Tape - Check condition and security.

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EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

NOTE

It is recommended that the EFD1000H/ MFD500 System units be turned off during engine starting in order to prevent possible voltage transient damage to the units.

(III) BEFORE TAKE-OFF (1) Avionics and Instruments: - Set as desired. (2) PFD and MFD - Congure for departure. (3) Before Take-off checks:

(2) Once the pre-ight inspections and check lists are complete, start the engine, after the engine start, turn ON the system,The units are turned on by setting ON the Circuit Breakers identicated as “ASPEN PFD 1”, “ ASPEN MFD”, on pilot´s circuit breakers panel and “ASPEN PFD 2” on copilot´s circuit breakers panel. (3) When the EFD1000/500 MFD powers up the rst screen you see is the Initializing Screen which displays the system conguration and any status annunciations.

NOTE

The AHRS will perform an internal test and alignment during EFD1000H power up (typically less than ve (5) minutes). The aircraft should remain stationary during the AHRS power up and alignment sequence. If the aircraft is moved during AHRS alignment it will take longer for accurate attitude and heading information to be presented to the pilot. Attitude and heading information is presented once the AHRS completes the alignment process.

(b) EXT PWR: (Aircraft Input Voltage) - Check >24.6V. (c) BAT - Verify battery status is not shown as FAIL (normally shows CHARGING or READY).

Takeoff with the indicated aircraft voltage (as displayed in the EF01000H PDF Power Settings Menu) below 24.6V is NOT AUTHORIZED.

NOTE

If the EFIS input voltage is below 25.0 V ± 0.6V (28V Electrical System) then the EFD1000H PFD will transition to internal battery as soon as the indicated airspeed exceeds 30 KIAS. Indicated voltages below these thresholds indicative an aircraft electrical system charging problem that must be resolved before ight.

(4) After the Initializing Screen, the EFD1000/500 MFD presents the Jeppesen Database Conrmation Screen, overlaid on lower half of EFD1000/500 MFD display. The conrmation screen displays validity dates currently loaded Jeppesen Database and the terrain awareness message.

(IV) BEFORE APPROACH CHECKS

(5) Press either the Left or Right Knob to acknowledge and accept the information and display the rst PAGE of the EFD1000/500 MFD.

(V) SHUTDOWN CHECKS

The validity and expiration date of all databases is displayed in the Main Menu, on the Database Menu Page.

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(a) MENU - POWER SETTINGS Page

(1) Avionics and Instruments - SET as desired. (2) PFD/MFD - Congure for arrival.

(1) EFD1000H PFD Circuit Breaker/Switches OFF. (2) MFD500H Circuit Breaker/Switches - OFF.

EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

NOTE

Each EFD1000H PFD (2)/MFD500H (1) includes an internal battery. On the ground, all three displays will initiate a shut down sequence when aircraft power is removed. If this sequence is interrupted, the electronics displays will continue to operate from battery until the battery is depleted. To avoid inadvertently discharging of the each (3) EFD battery, conrm that each EFD is completely powered down before leaving the rotorcraft. (VI) EMERGENCY/MALFUNCTION PROCEDURES (1) IN-FLIGHT AHRS RESET. (a) ATTITUDE - Maintain straight and level ight. FLY BY VISUAL REFERENCE OR BY STANDBY INSTRUMENTS. (b) MENU Button - Press to activate menu. (c) Right Knob - Rotate as needed to select GENERAL SETTINGS page. (d) "AHRS: RESET?" Line Select Key - Press. The following conrmation message will appear: “PRESS AGAIN TO CONFIRM AHRS RESET. ACTIVATE ANY OTHER CONTROL TO CANCEL RESET.” (e) "AHRS: RESET?" Line Select Key - Press again to conrm AHRS reset.

NOTE

When EFD1000H PFD System AHRS is reset in ight, it performs an abbreviated initialization. (f) During the initialization, the aircraft should not be subjected to excessive turn rates. Typical in-ight initialization will take approximately 30 seconds, but can take longer if the reset is initiated while banked or maneuvering.

(g) AHRS reset is considered complete when EFD1000H attitude and heading is once again displayed, stable, and correct with respect to horizon or standby indicator. (2) PITOT/STATIC SYSTEM BLOCKAGE.

The helicopter has only a single pitot and static system available for ight instrument use. As such, the pitot and static lines used by the EFD1000H PFD System are shared with those lines used by the mechanical airspeed indicator and altimeter. Should these lines become blocked, such as might occur due to inadvertent icing encounter, both the mechanical indicators and the EFD1000H PFD System indicators will display erroneous information. Because the EFD1000H PFD uses pitot and static pressures as part of the ADAHRS solution, loss or corruption of this data, such as from a line blockage, will impact the accuracy of data output by the ADAHRS. Affected parameters can include the airspeed, altitude and attitude information displayed by the EFD1000H PFD. If erroneous pitot or static inputs are detected by the EFD1000H PFD System, it will present a "CROSS CHECK ATTITUDE" annunciation. (a) If a blocked pitot is suspected: PITOT HEAT - ON (3) PERSISTENT OR FREQUENT CROSS CHECK ATTITUDE MESSAGE: Persistent or frequent CROSS CHECK ATTITUDE annunciations during normal maneuvers are indicative of a degraded ADAHRS solution. (a) ATTITUDE - Maintain by reference to visual cues or mechanical instruments.

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EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

NOTE

The CROSS CHECK ATTITUDE message indicates that the statistical condence in the ADAHRS solution is degraded. Momentary annunciations during aggressive maneuvers such as 60 degree angle of bank turns are normal. (4) ADAHRS ATTITUDE DISAGREEMENT. Should differences be observed between the EFD1000H PFD System and visual cues or mechanical instruments, monitor all available attitude, airspeed, and altitude information to diagnose faulty indicator(s) and perform inight ADAHRS reset: (a) ATTITUDE - Maintain straight and level ight. (b) If an EFD1000H ADAHRS is suspected as faulty, proceed as follows: ● MENU Button - Press to activate menu. ● Right Knob - Rotate as needed to select GENERAL SETTINGS page.

placed with red "X"s and the annunciations, "ATTITUDE FAIL" and "DIRECTION INDICATOR FAIL are presented. Minimal maneuvering during the initialization is permitted. (d) The ADAHRS reset is considered complete when the EFD1000H attitude and heading are once again displayed and the attitude display is stable and correct with respect to other sources of attitude information. (5) LOSS OF EXTERNAL POWER. In the event that external power to the unit is degraded or fails, the EFD1000H PFD/MFD 500H System will automatically switch to its internal battery. (a) When operating on internal battery, the display backlight intensity is capped at a value of 70. (b) An annunciation of this operating state and the estimated battery charge remaining is displayed in the lower portion of the attitude indicator.

● "AHRS: RESET?" Line Select Key - Press. The following conrmation message will appear: “PRESS AGAIN TO CONFIRM AHRS RESET. ACTIVATE ANY OTHERCONTROL TO CANCEL RESET.” ● "AHRS: RESET?" Line Select Key - Press again to conrm AHRS reset.

NOTE

When an EFD1000H PFD System ADAHRS is manually reset in ight, it performs an abbreviated initialization that usually takes less than 30 seconds. (c) During the initialization, the attitude and direction information are removed and re-

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If the aircraft alternator or generator fails and the EFD1000H PFD System is operated until its internal battery is exhausted, the screen may fade to solid white for several seconds before blanking. To avoid this condition at night, manually turn off the EFD1000H PFD System once the display shows 0% battery remaining.

EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

During situations where a high electrical demand is placed on the aircraft electrical system, electrical transients that cause aircraft voltage to momentarily drop below 25.0 ± 0.6 V (28V Electrical System) will cause the EFD1000H PFD System to automatically switch to its internal battery. This will be accompanied by an "ON BAT" annunciation. The "ON BAT" annunciation should extinguish shortly after the electric transient demand goes away. If the "ON BAT" annunciation does not extinguish, then an external power source failure has most likely occurred.

NOTE

When fully charged the EFD1000H PFD System internal battery will allow for operation of the AHRS, display and RSM emergency GPS for at least 30 minutes at typical aircraft temperatures. (6) POWER OVERRIDE.In the event that the pilot wishes to override the automatic power conguration of the equipment: (a) MENU Button - Press to activate menu. (b) Right Knob - Rotate as needed to select POWER SETTINGS page. (c) To switch from external power to battery: * “BATTERY” Line Select Key - Press: * “EXT PWR” Line Select Key - Press

NOTE

When airborne, if the EFIS input voltage is below the 25.0 ± 0.6 V (28V Electrical System) automatic battery transition threshold, and "EXT PWR" is selected the EFD1000H PFD/ MFD 500H will automatically transition back to its internal battery.

(7) ABNORMAL SHUTDOWN PROCEDURE. In the event of an EFD1000H PFD System malfunction requiring in-ight shut down of the equipment: (a) EFD1000H PFD Circuit Breaker / Switch – OFF. (b) REV Button - HOLD UNTIL DISPLAY BLANKS. (8) LOSS OF GPS INFORMATION CAUTION. In the event of complete GPS failure, the Nav Map stops moving and orients North Up, the aircraft symbol is removed and reverts to a stationary map with an accompanying "GPS POS FAILED" is annunciated. In this case, the Nav Map may be manually panned to correlate to the estimated rotorcraft position determined by other means. (a) Position and flight plan data for the EFD1000H PFD, and also mapping information for MFD500H are provided from aircraft GPS equipment GNS 430W (GPS1) or from GNC 250XL (GPS2). The EFD displays are congured to receive data from both external GPS systems. In addition, as an RSM is connected to the each EFD1000H PFD, (not on the MFD 500H), it includes an emergency GPS, this information may be used when the both aircraft GPS systems fail. (b) The Nav Map function in the EFD1000H PFD System follows an automatic position reversion scheme to determine which GPS is the position source for the map. The primary GPS1 is always the one selected by the pilot, either by the associated CDI nav source or via the menus. If selected GPS1 fails, EFD1000H PFD automatically switches to GPS2 , and will annunciate “GPS2 Reversion”, where 2 represents the GPS source providing position data. (c) If all external GPS systems fail, an RSM

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EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

GPS with GPS sensor is connected to each EFD1000H PFD, then both EFD1000H PFD (pilot´s and copilot´s) will use position data from RSM GPS and annunciate “RSM GPS REVERSION EMER USE ONLY”. In this case, the map data is approved for emergency use only. (d) Whenever the map has reverted to an alternate position source, all map features and capabilities are retained including the display of the ight plan from the selected GPS. However, when the GPS position source is different from the source that generated the ight plan, the ight plan is presented without showing an active (magenta) leg. The ight plan and map data from each external GPS is retained independently. Two

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external GPS were connected in the Navigation system, and if each had a different ight plan at the time of failure, then both of these ight plans are retained and can be viewed by the pilot. (e) In unlikely event that there is a complete loss of all GPS data to the MFD 500H, then the NAV map is retained, the ight plan is removed, and the map is no longer updated with aircraft position information. An annunciation of “GPS POS FAIL” is presented in the center of the map, the aircraft symbol is removed, the map changes to a North·Up orientation, and the map will no longer move with the aircraft. Manual panning is still possible and all map features that are not GPS position dependent continue to remain available.

EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

(VII) WARNING, CAUTION, AND ADVISORY SUMMARY

Annunciation

W

Description

Red annunciations presented whenever the EFD1000 is operating on the internal or EBB. The countdown timer appears rst, and then replaced by ON BAT and % charge annunciation.

Red annunciation presented whenever EFD1000 determines that the associated function is invalid or failed. On the EFD1000 MFD SAI and SHSI, only the “ATTITUDE FAIL” and DIRECTION INDICATOR FAIL” annunciations are presented. These indications are also presented when the ADAHRS system is re-initializing after a manual or automatic reset.

W

Fly by reference to standby sources of attitude, altitude and airspeed, such as the EFD1000 MFD, standby instruments, or the visible horizon. Note: In this circumstance GPSS operation is still possible. In addition, the LDI and VDI will continue to remain available and display either GPS approach lateral and vertical deviations, or localizer lateral deviation information, which may be manually own.

W

Red chevrons displayed on the Attitude Indicator’s pitch scale to indicate extreme pitch up and down attitudes and the appropriate y-to direction to restore level ight.

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EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

Annunciation

C

C

C

C

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Description

Amber annunciation centered in the upper half of the attitude indicator whenever the EFD1000 ADAHRS internal integrity monitor determines that attitude is potentially degraded. If a steady CROSS CHECK ATTITUDE annunciation is presented, cross check attitude, airspeed and altitude indications against alternate sources.

Amber annunciation displayed in the data bar of the EFD1000 MFD when its internal ADAHRS reports a failure (e.g. during ADAHRS Reset).

Amber annunciation presented on the EFD1000 MFD when its internal ADAHRS reports a “CROSS CHECK ATTITUDE” condition.

Amber annunciation presented in the EFD1000 MFD Data Bar when it loses communication with the PFD, and in the EFD500 MFD data bar when it loses communication with either the PFD or the EFD1000 MFD.

EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

Annunciation

Description

C

Amber annunciation accompanied by an “ATTITUDE FAIL” annunciation. Presented when the software detects an obstruction in the pitot system that could potentially degrade the attitude solution This annunciation is removed when the detected condition is resolved, which would be followed by an automatic ADAHRS reset. A GPS system is required for this monitor to be enabled.

C

Amber annunciations presented when a connected GPS is invalid or not available. GPS# or RSM REVERSION (optional) annunciations indicate the current GPS basemap source. Note: the EFD500 MFD cannot revert to RSM GPS since it is not congured with an RSM. *GPS2 is not applicable to the PFD Pilot. “GPS1”, “RSM GPS” and “RSM GPS REVERSION” are the only annunciations of this type that apply to the PFD Pilot.

C

Amber annunciation presented in the center of the NAV Map when all GPS sources have failed. When presented, the map changes to a North-up orientation and the map no longer moves with the aircraft. Manual panning is still possible and all map features that are not GPS position dependent continue to remain available,including relative terrain overlays.

C

Amber annunciation presented whenever the selected GPS source indicates that GPS integrity is degraded. See the applicable GPS AFMS for more information.

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EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

Annunciation

C

Description

Amber annunciation presented when the aircraft reaches, or is below the set MINIMUMS. Will be accompanied by a one-second stuttered tone when the optional tone generator is installed. Not applicable to the PFD Pilot.

C

Amber ag presented to indicate the aircraft is reaching (steady) or deviating (ashing) the selected altitude. Will be accompanied by a one-second steady tone when the optional tone generator is installed. *The tone is not available on the PFD Pilot.

C

Amber “DH” annunciation presented when a connected radar altimeter indicates the aircraft has reached the radar altitude set by the pilot. See the radar altimeter’s AFMS for more information. Not applicable to the PFD Pilot.

C

GPSS annunciation that indicates the previously selected GPSS source is invalid (e.g. the ight plan was deleted) or a different GPSS has been selected by pilot. Commands the autopilot to roll the aircraft to wings level until GPSS is reengaged, or a valid GPSS signal is available. Not applicable to the PFD Pilot.

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EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

Annunciation

C

C

C

A

Description

Amber annunciation presented on the dedicated terrain display when any of the information needed to render the map (position, altitude, or heading) is detected as invalid.

A “TRAFFIC” Advisory annunciation is presented in the data bar whenever a connected trafc system generates a Trafc Advisory and a dedicated trafc view is not being displayed. “TRFC” legend above the lower center button is presented to inform the pilot of the single pilot action needed show a dedicated trafc display.

Annunciation presented on the PFD HSI whenever the HSI compass card is no longer receiving magnetic corrections. After 6 minutes of free gyro operation the attitude and heading solutions will be removed.

Annunciation presented when the EFD1000 PFD’s or EFD500 MFD’s “REV” button is pressed.

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EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

Annunciation

A

A

A

A

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Description

Annunciation presented when the EFD1000 MFD’s “REV” button is pressed.

Green annunciations provided whenever GPSS is enabled and the GPS source is valid. Either “GPSS1” or “GPSS2” may be annunciated depending on aircraft conguration. Not applicable to the PFD Pilot.

GPS annunciations provided by an active GPS source.TERM may also be displayed in the same location as APPR. See the GPS AFMS for additional information on the meaning of these annunciations.

A horizontal red line through the legend of selected data indicates that the data is invalid, unavailable, or for datalink products, that the data product is expired. Not applicable to the PFD Pilot.

EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

Annunciation

Description

A

A horizontal red line through the source legend of selected data indicates that the data is invalid or unavailable. Not applicable to the PFD Pilot.

A

A horizontal red line through the selected navigation source indicates that the data is invalid or unavailable. HSI and SHSI only. Not applicable to the PFD Pilot.

A

Annunciation presented at the bottom center of the Nav Map if the software is unable to access the data base stored to the micro SDHC memory card.

A

Annunciation presented at the bottom center of the Nav Map when data is being loaded from the micro SD card at start up. The current data type and total number of data types to be loaded is identied (i.e. “11/11”), along with an indication of the type of data that is currently being loaded (i.e., "AIRWAYS").

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EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

REVERSION AND POWER BUTTON 1

Reversion and Power Button

2

Range Button

3

Menu Button

4

Hot Key Menu

5

MIN - Minimums

3

6

360/ARC View

4

7

MAP - Map Declutter

5

8

GPSS - GPS Steering

6

9

Right Knob

7

10

Double–Line Bearing Pointer Source Sel

8

11

CDI Source Select

12

Single-Line Bearing Pointer Source Sel

13

Left Knob

14

Automatic Dimming Photocell

1 2

14

13 12

11

10

9

Figure 1-8 : Switches, Control EFD1000 PFD Controls The primary means for the pilot to control the EFD1000 are the two knobs and three buttons at the bottom of the display. The knobs control setting CRS and HDG, and additional bugs and altitude settings. The three buttons control selection of navigation sources for the CDI and bearing pointers. Additionally, ve Hot Keys to the right of the Navigation Display toggle various features on and off. The function of each one is indicated by the label on the screen to the left of each button. Three additional buttons above the Hot Keys control entering and exiting the Main Menu, setting the Map range, and reversion or manual power control.

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NOTE

For full details, refer to The Aspen Avionics EFD1000/500 MFD Pilots Guide, Document number 091-00006-001 Rev. (B) or later approved revision. 1.11 Radar Altimeter System KRA 405B a. Description.The KRA 405B Radar Altimeter System provides the pilot with dependable, accurate AGL (altitud above ground level) information during the approach phase of ight. The system has the capability of alerting the pilot when a predetermined altitude (decision height) is reached. The system also provides altitud information to the ight control system during the approach.

EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

The KRA 405B determines the altitude above ground level (AGL) by transmitting a signal to the ground then processing the reected signal. The altimeter outputs the altitude information as analog voltages and ARINC 429 digital format. The KRA 405B Radar Altimeter displays 2,000 ft. and provides analog and ARINC 429 outputs for increased interface capability including GPWS, TCAS, and autopilot. The KRA 405B Radar Altimeter system installed on helicopter UH1H includes the KRA 405B Receiver/ Transmitter, a KNI 415 Radar Altimeter Indicator and two KA 54A antennas. b. Control and functions. Refer to gure 1.9. c. Operations. (I) SYSTEM POWER UP AND TEST (1) Press the circuit breaker “KNI 415/RAD ALT” located on copilot´s circuit breakers panel. (2) Turn “ON” the togle switch “RAD ALT” on the right side of Central Console. (3) Adjust the DH knob on the KNI 415 Radar Altimeter Indicator to set the DH but to 25 feet. (4) Depress the TEST button on the indicator. The indicated altitude should be 50, ± 5 feet and the ag should come into view. The DH lamp should be out. (5) With the test button depressed, slowly increase the DH bug until the DH lamp lights. The bug should be 50, ± 5 feet. The lamp should be lit at all altitudes above 50 feet. (6) Release the test switch. The Warning ag should move out of view and the indicated altitude should be 0 feet, nominal.

(II) APPROACH When the approach plates are reviewed prior to beginning the actual approach, the pilot should set the DH but to the decision height altitude, and check altimeter operation as follows: (1) Depress the SELF TEST button and hold:1. 50 ±5 feet should be indicated. (2) The ag should come into view. (3) The DH lamp should light (if the DH setting is above 50 feet). (4) Verify that the pointer comes on scale at 2000 feet AGL by using the barometric altitude as a reference. (5) If altimeter does not operate as specied above, refer to the following section: Emergency Operation. During the actual approach, the Radar Altimeter System provides altitude and altitude trip information to the ight control system. When the decision height is reached, the DH lamp lights to alert the pilot that a decision is to be made. The DH lamp may then be turned off by pressing the lamp in. (III) EMERGENCY OPERATION (1) If the altimeter does not indicate 50 ± 5 feet when initiating self test, disregard radar altimeter system. (2) Should the ag not come into view but the indicated altitude is correct, the altimeter system may be used. Keep in mind that subsequent failures will not be indicated by the ag. (3) Failure of the DH lamp to light during self test means the pilot must watch the indicator closely since the decision height will not be annunciated.

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EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

Figure 1-9 : Control Functions KNI 415

CONTROL/INDICATOR (KNI 415)

FUNCTION

1. ALTITUDE SCALE

The KNI 415 scale gives accurate altitude indications from -20 to +2000 feet. From - 20 to 500 feet each mark on the scale represents 10 feet. From 500 to 2000 feet, each mark represents 100 feet.

2. INDICATOR NEEDLE

The AGL altitude in feet is displayed beneath this needle. Needle will be clockwise behind mask when above 2000 feet.

3. FLAG

Indicates invalid altitude information is being displayed or self test button is depressed.

4.SELF TEST BUTTON

This button is used to test the Radar Altimeter R/T and indicator. When the button is depressed, the ag will come into view and 50 +/-5 feet will be displayed.

5.DH KNOB

This knob controls the DH (Decision Height) bug. By turning it clockwise, the DH bug will increase in altitude; counterclockwise, the bug will decrease in altitude.

6.DH BUG

Indicates altitude during an approach at which the DH lamp will light.

7. DH LAMP

This lamp lights when the Decision Height is reached. The lamp can be turned off by pushing the lamp in.The lamp can be turned on again, when below the decision height, by depressing the lamp a second time. Once turned off, the DH lamp will be automatically armed upon climb out as the aircraft passes through the DH altitude. Pressing the self-test button will also turn on the DH lamp if the DH bug is set above 50 feet.

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EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

SECTION V. EQUIPMENT / FURNISHINGS 1.12 EMERGENCY LOCATOR TRANSMITTERS ARTEX 406 MHz a. Description. The Artex C406-N HM ELT is a single output ELT that incorporates the latitude/longitude information from the helicopter GPS Navigation System. All 3 emergency frequencies (121.5/243.0 and 406 MHz) utilize the same RF output, which requires only 1 coax cable to connect to the new series of Artex single input antennas. The ELT automatically activates during a crash and transmits the standard swept tone on 121.5 and 243.0 MHz. Every 50 seconds for 520 milliseconds (long message protocol), the 406 MHz transmitter turns on and transmits an encoded digital message to the Cospas/Sarsat satellite system. The Artex C406-N HM ELT, also consider a installation of a Remote Switch located on Helicopter´s Central Console, this remote control is designed for to inhibit the equipment from being automatically activated, deactivate the ELT after it has been activated (reset if the ELT is activated accidentally). The C406-N HM ELT was developed for helicopter installations and features an additional 5-axis GSwitch module, which allows the ELT to be activated in any of the six orthogonal axes. b. Control and functions. Refer to gure 1.10. c. Operations. One of the primary features of the C406-N series ELT is its simplicity of operation. As long as the ELT is

locked into its mounting tray and the remote switch harness is attached and the antenna is connected, it will activate in a crash and transmit a distress signal. Neither the cockpit switch nor the ELT unit switch can be positioned to prevent automatic activation once the unit is mounted property. (I) POWER ON + 28 VDC aircraft power is required to operate the navigation function of the C406-N. Aircraft power also provides power for the cockpit remote panel light functions but has no effect on the switch functions. The ELT will activate and transmit an emergency signal (less position data) without + 28 VDC. Should + 28 VDC aircraft power be lost in ight, prior to a crash, the ELT will retain the last known position from the ARINC 429 source for 36 seconds. The ELT power is wired via a circuit breaker identicated as “ELT” located on pilot´s circuit breaker panel, since the ELT circuitry will draw current whenever power is applied. (II) NORMAL OPERATION (1) The cockpit remote switch is in the “ARM” position (i.e., down). (2) The local switch on the ELT is in the “OFF” position (i.e., down). (3) Aircraft navigation system active.

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EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

NOTE

The aircraft GPS Navigation System must be active and sending position data to the ELT for the ELT to incorporate position data into the 406 MHz message. (III) MANUAL ACTIVATION (1) The ELT may be manually activated by placing either the remote switch or the ELT local switch in the “ON” position.

NOTE

As long as the cockpit remote switch and the ELT local switch are in the ARM/OFF positions respectively, the ELT will automatically activate on impact.

(IV) ELT RESET (1) If the ELT is activated accidently, it will need to be reset. (2) Reset the ELT from the cockpit by moving the remote switch to the “ON” position, waiting approximately one second, and then moving it back to the “ARM” position. If the switch is already in the “ON” position, move it to the “ARM” position. (3) Reset the ELT locally by moving the switch on the ELT to the “ON” position, waiting approximately one second, and then moving it back to the “OFF” position. If the switch is already in the “ON” position, move it to the “OFF” position.

NOTE

The ELT cannot be reset if either the cockpit remote switch or the ELT local switch is in the “ON” position. The cockpit-mounted remote switch assembly is comprised of an ELT status LED and control switch, which allows an operator to monitor ELT status and manually turn on the ELT (i.e., activating) for testing and resetting (i.e., deactivating) the ELT.

NOTE

The ELT CANNOT be disarmed or disabled from the cockpit. Cockpit operation is limited to deactivating or manually activating the ELT.

Figure 1-10 : Cockpit Remote Switch

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EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

SECTION VI. INSTRUMENTS 1.13 DAVTRON M803 DIGITAL CLOCK a. The upper display can be switched to Voltage, O.A.T. Fahrenheit and O.A.T. Centigrade. b. The actual mode is indicated by a letter beside the value. (I) E indicates Voltage (II) F indicates O.A.T. Fahrenheit (III) C indicates O.A.T. Centigrade c. On power up the Voltage mode is selected. d. The lower display shows time information and can

be switched to UT, local time, ight time and elapsed time. e. The selected mode is indicated in the left part of the clock display. (I) UT indicates "Universal Time", also known as GMT (Greenwich Mean Time) (II) LT indicates local time (III) FT indicates ight time (IV) ET indicates elapsed time f. The Timer Control Button starts and resets the timer in ET mode.

Figure 1-11 : Davtron M803 Digital Clock 1-47

EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

1.14 ADF INDICATOR KI 227 The KI 227-00 has a manually rotatable compass card which the pilot can set to a selected bearing reference with the Heading Knob.

Figure 1-12 : ADF INDICATOR KI 227 1-48

EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

1.15 INSTRUMENTS PANEL

Figure 1-13 : INSTRUMENTS PANEL 1-49

EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

1.16 CENTRAL CONSOLE

Figure 1-14 : CENTRAL CONSOLE 1-50

EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

1.17 CIRCUIT BREAKERS PANEL

Figure 1-15 : CIRCUIT BREAKERS PANEL (Sheet 1 of 2) 1-51

EMPRESA NACIONAL DE AERONÁUTICA OPERATOR’S MANUAL SUPPLEMENT TO TM 55-1520-210-10 HELICOPTER UH-1H FACH H-79, SN 66-16967

Figure 1-15 : CIRCUIT BREAKERS PANEL (Sheet 2 of 2) 1-52

AV. JOSÉ MIGUEL CARRERA 11087 PARADERO 36 1/2 COMUNA EL BOSQUE SANTIAGO - CHILE. FONO: 56(2) 23831831. 56(2) 23831958. FAX: 56(2) 23832699. Email: [email protected] www.enaer.cl