ACK! E-04 Istruzioni operative

MODEL E-04 ELT

INSTALLATION MANUAL

OPERATION MANUAL

IMPORTANT VISIT OUR WEBSITE WWW.ACKAVIONICS.COM FOR THE

LATEST SERVICE BULLETINS AND INSTALLATION INFORMATION BEFORE

STARTING THE INSTALLATION.

THE CONDITIONS AND TESTS REQUIRED FOR TSO APPROVAL OF THIS ARTICLE ARE

MINIMUM PERFORMANCE STANDARDS. IT IS THE RESPONSIBILITY OF THOSE DESIRING

TO INSTALL THIS ARTICLE ON A SPECIFIC TYPE OR CLASS OF AIRCRAFT TO

DETERMINE THAT THE AIRCRAFT INSTALLATION CONDITIONS ARE WITHIN THE TSO

STANDARDS. THE ARTICLE MAY BE INSTALLED ONLY IF FURTHER EVALUATION BY THE

APPLICANT DOCUMENTS AN ACCEPTABLE INSTALLATION AND IT IS APPROVED BY THE

ADMINISTRATOR.

P/N E04M REV DATE 12/02/2015

Rev 1.8 PRINTED IN THE USA

APPROVALS

FAA /TRANSPORT CANADA

TSO C-126b

TSO C-142a

TSO C-91a

EASA

ETSO 2C126

ETSO 2C91a

ETSO C142a

COSPAS/SARSAT

T.007

INDUSTRY CANADA

1863A-E04AF

Brazil ANAC

ANTEL

TABLE OF CONTENTS

Section 1 406 MHz ELT overview

Section 2 ELT installation

Section 3 Antenna installation

Section 4 Remote control installation

Section 5 Audio alert indicator installation

Section 6 GPS interface installation

Section 7 Final installation and checkout

Section 8 Registration

Section 9 Operation and self test

Section 10 Periodic maintenance / Continuing airworthiness

Section 11 Lithium battery replacement

Section 12 Programming

Section 13 Warranty procedure

Section 14 Canadian maintenance requirements

Section 15 Specifications

Section 16 Major parts

Section 17 Environmental qualifications DO-160F/ED-14F

Section 18 RS 232 data formats / Installation notes

Section 19 Trouble shooting / Miscellaneous notes

SECTION 1 406 MHz ELT OVERVIEW

The model E-04 121.5/406 MHz ELT is designed for use in aircraft used for general and

commercial aviation. Older generation ELT’s were very limited in their ability to rapidly

locate, and identify a downed aircraft. Often it took several passes of the orbiting satellites

to get an approximate fix on a downed aircraft. The older generation ELT’s gave rescuers

no information on type of aircraft, owner/operator, or contact information. The new

generation 406 MHz ELT’s provide much better, and faster location accuracy. Along with

providing information to search and rescue organizations about the aircraft type,

ownership, and emergency contact information. Location accuracy with older generation

ELT’s was limited to about a 15 - 20 mile radius, and could take several hours to provide

accurate location data. For new generation 406 MHz ELT’s without GPS position

information, the average time to process, and identify the aircraft location is 1-2 hours,

with a search radius of about 2 miles or less. With GPS information, the time to locate the

aircraft position is 10 minutes or less, with an accuracy of about 300 feet. The model E-04

ELT may be installed without interfacing it to the aircraft GPS system, however we strongly

recommend that when available the GPS data be supplied to the ELT. For aircraft which do

not have GPS data available, the unit can be interfaced with a low cost GPS data receiver,

such as the Garmin GPS 18PC which is available for less than $75.00. (Note: these

receivers require a 5V supply. One model has a cigarette lighter plug with a built in

regulator, or you can use a 5V switching power supply, such as Digi-Key P/N 811-1116-ND)

You must register this beacon before activating it. Failure to do so can result in monetary

fines, and other sanctions. See section 8 for registration instructions.

You must update your registration every two years.

SECTION 2 ELT INSTALLATION

Several problems associated with previous TSO C-91, and C-91a ELT installations, is the

result of poorly chosen mounting locations. Generally the most suitable location for fixed

wing aircraft, is to position the ELT transmitter in the fuselage as far aft as possible. Anten-

na location, and accessibility for maintenance, are factors that should be considered when

choosing a mounting location. The ELT must be mounted with the arrow printed on the

battery case pointing in the direction of flight. The ELT should be mounted with it’s longi-

tudinal axis aligned within 10 degrees of the longitudinal axis of the aircraft fuselage.

Avoid mounting the ELT near sources of strong EMI/RFI radiation.

RTCA document DO-204 paragraph 3.1.8. prescribes the mounting requirements which

must be met when installing this ELT, these requirements are as follows:

The ELT shall be mounted to primary load-carrying structures such as trusses, bulkheads,

longerons, spars, or floor beams. (not aircraft skin) The mounts shall have a maximum

static local deflection no greater than 2.5mm (0.1 inch) when a force of 450 newton's (100

lbs.) is applied to the mount in the most flexible direction. Deflection measurements shall

be made with reference to another part of the airframe not less than 0.3 meter (1 foot) nor

more than 1.0 meter (3 feet) from the mounting location.After selecting a suitable location

meeting all of the above requirements. Drill and mount the ELT tray assembly as shown in

Fig 3. A doubler plate may be required. Secure latches with tie wrap as shown.

IMPORTANT

The quick release retaining straps which secure the ELT to the tray are slightly different in

size. The strap that fits around the front of the ELT, (transmitter assembly) is marked

“front.” The strap that fits around the battery case end of the ELT, is marked “Battery.”

Helicopter installation

The model E-04 ELT is suitable for helicopter installation. The procedures for installation,

maintenance, and operation, are the same as for fixed wing aircraft, except for the orienta-

tion of the ELT in relation to the helicopter longitudinal axis. The arrow on the battery case

of the ELT should be pointed in the normal direction of forward flight. The longitudinal axis

should be aligned within +- 10 degrees of the longitudinal axis horizontally, and at a 45

degree downward angle as shown in Fig 2.

SECTION 3 ANTENNA INSTALLATION

In order to meet the requirements of COSPAS/SARSAT TSO C-126b,TSO C-91a, and FAR

91.207 an approved antenna must be used. The antenna supplied with the ELT P/N E-04.8 is

a monopole, dual frequency antenna design. It has a recommended operating speed of up

to 260 knots. We have a high speed blade antenna avalible, part number S65-1231-1 which

is rated to Mach 1.0. Other antennas may be used provided they meet the minimum VSWR

requirements as noted in the specifications section of this manual, (Section 15) and meet

COSPAS/SARSAT approval for use with the model E-04 ELT. The coaxial cable supplied is

RG-58, and is 5 feet long. A longer or shorter cable may be fabricated using RG-58 or

equivalent cable, and Amp 227079-5 connectors. The insertion loss of the cable assembly

at 406 MHz should not exceed 2 dB. At 121.5 MHz the insertion loss should not exceed 3

dB. The cable should be a minimum of 2 feet in length.

The antenna may be mounted internally in composite construction, and tubular fabric

covered aircraft, as long as the fabric or composite material is of a non conductive nature.

The antenna must be mounted externally, on airframes of metallic construction. The

antenna should be mounted as close to the ELT transmitter as practical. The coaxial cable

connecting the antenna to the ELT transmitter, should not run in close proximity to comm

radio coaxial cables, and should avoid crossing aircraft production breaks. (i.e. Riveted

fuselage sections) The antenna must be mounted within 30 degrees of vertical, when the

aircraft is in normal flight attitude. The installed antenna must be able to withstand a static

load of 100 (one hundred) times it’s weight (13 lbs.) applied to the base of the antenna,

along the longitudinal axis of the aircraft. The antenna should be mounted a minimum dis-

tance of three feet (1 meter) from any vertically polarized communication antennas. (i.e.

Antennas radiating in the 118-137 MHz band.)

MODEL E-04.8 WHIP ANTENNA

1.) Drill a ½" (13mm) diameter hole in the aircraft at the antenna mounting location (Fig. 4)

2.) Install the antenna, and determine if the antenna meets the static load requirements. If

not, a doubler plate should be fabricated.

3.) If the antenna is being mounted on a non conductive portion of the airframe, a

supplementary ground plane must be installed. The supplemental ground plane must have

a minimum diameter of 24" however 48” will provide maximum power at 121.5 MHz and is

recommended. The ground plane must be centered around the base of the antenna. This

may be fabricated out of copper, or aluminum tape. The tape should be cut into six ele-

ments 12" long, and the tape elements should be evenly spaced, radiating in a circular

pattern from the base mounting point of the antenna. (Fig. 4) Make sure all elements are

electrically bonded to the base of the antenna. The tape may follow the contour of the fuse-

lage. The metallic airframe of fabric covered aircraft may be used as the ground plane.

When installing the antenna, make sure the base of the antenna is electrically bonded to

the tubing frame. A static suppressor is supplied install as shown in (Fig 4)

4.) Assemble the antenna as shown in figure 4. Make sure the rubber washer that forms a

moisture seal between the antenna base, and aircraft structure, is in place before installing

the antenna. Also make sure the serrated locking washer is in place. If the aircraft skin at

the mounting point is less than .060” thick when installing the P/N E-04.8 whip antenna, a

2” diameter doubler plate must be fabricated using .040” thick 2024, or 7075 T6 aluminum.

ALL WIRE SUPPLIED WITH THE ELT MEETS THE REQUIREMENTS OF FAR 23.1359 AND

FAR 23.853 AND MAY BE INSTALLED IN ANY PART 23 CERTIFIED AIRCRAFT.

WARNING: Do not

install static suppressor

directly to ELT BNC

terminal.

SECTION 4 REMOTE CONTROL INSTALLATION

IMPORTANT YOU MUST INSTALL A BATTERY IN THE REMOTE.

The remote control panel indicator (RCPI) P/N E-04.5 is designed to be powered by a single

Duracell PX28L 6 volt Lithium battery, or equivalent. Alkaline batteries may be used such

as Eveready A 544, or equivalent. Under normal operating conditions, the Lithium battery

must be replaced every 10 years. The alkaline batteries must be replaced every 5 years. If

the ELT is activated for an unknown period of time, the battery must be replaced.

Equivalent cross reference batteries from other manufacturers are acceptable for use in

the remote control.

To install, or replace the RCPI battery follow these steps:

1.) Remove the three retaining screws which secure the top and bottom half of the RCPI

unit. (Fig. 5)

2.) Remove the two switch retaining nuts located on the face of the RCPI. There are two

placards supplied with the remote, (a horizontal, and a vertical) remove the protective

plastic film from the placard face, and install the vertical or horizontal placard. Caution:

The “ON“ position marking on the placard must be aligned with the red switch, the

“TEST/RESET” marking must be over the black switch (Fig. 5)

3.) Carefully remove the top half of the RCPI unit exposing the battery compartment. (Fig.

5) if replacing an old battery, carefully inspect the battery contacts for dirt or corrosion. If

the contacts need cleaning, use only non abrasive electrical contact cleaner and a stiff

brush. Abrasive cleaners will remove the nickel and gold plating from contacts.

4.) Insert the battery with the polarity as shown in figure 5. The polarity is also engraved on

the bottom of the battery compartment.

5.) Replace the top half of the RCPI, and replace the three retaining screws, and two

retaining nuts on the face of the RCPI.

6.) The next RCPI battery replacement date should be recorded in the aircraft log book with

a note indicating the battery expiration dates.

IMPORTANT: The RCPI must be mounted so that it can be seen, and operated by the pilot

of the aircraft from a normal operating position. We strongly recommend that the RCPI be

located within an area that is part of the pilots regular instrument scan.

5.) Mount the RCPI using four 4-40 screws, and nuts. Figure 6 shows the dimensions of the

cut out for the RCPI unit. If the unit is to be mounted in a location that does not have a

flush mounting surface (i.e. Beneath the panel glare shield.) an angle bracket should be

fabricated. (Fig. 6)

For a list of other approved antennas and other technical information visit our web site .

WWW.ACKAVIONICS.COM

SECTION 5 AUDIO ALERT INDICATOR INSTALLATION

IMPORTANT: THERE IS NO BATTERY INSTALLED IN THE AUDIO ALERT INDICATOR.

Remove the four screws that attach the top cover to the audio alert indicator P/N E-04.7.

Install a Duracell CR-2, 3 volt or equivalent battery. Make sure to observe the battery

polarity (Fig. 7). Replace the top cover, making sure the grill portion of the indicator cover

is positioned over the buzzer. The battery must be replaced every 10 years. The expiration

date must be entered in the aircraft airframe log book.

SECTION 6 GPS INTERFACE INSTALLATION

The model E-04 ELT will interface and recognize EIA standard RS 232 data at 1200, 2400,

4800, and 9600 baud from NMEA 0183 sources, Garmin panel mount, and handheld GPS’s

along with Bendix/King GPS’s. See section 18 for GPS data formats, and connection

information, along with other manufacturers GPS’s known to be compatible.

To change the baud rate, one or two jumpers are installed on the digital board of the ELT. To

accomplish this remove the four screws at the front of the ELT, and remove the battery pack.

(Fig. 9) Figure 10 shows how to position the jumper on the digital board for the various baud

rates. After selecting the desired baud rate, replace the battery pack, and torque the screws

to 3-4 in. lbs. The model E-04 ELT is interfaced to the aircraft source of navigation data

through a four pin mini din connector. Three of the pins are used for interfacing with the

aircraft systems, and the fourth pin is used to verify the ELT is receiving and processing the

data properly after installing the ELT. A three conductor shielded cable 24 AWG or heaver,

(Aircraft Spruce P/N 11-04478 or equivalent) should be used to connect the ELT RS 232 data

and power to the aircraft systems. Figure 11 shows the pin outs for RS 232, and power input.

1.) Disassemble the mini DIN connector, noting the position of the parts for reference when

reassembling the connector .

2.) Connect one conductor to pin 1 of the DIN connector, and to 10 - 30 volts DC from the

aircraft buss. Protect the circuit with a one amp fuse or circuit breaker. (Fig. 13)

3.) Connect one conductor to pin 3 (Fig. 12.1) and connect to aircraft ground at the cockpit.

connect the outer shield to ground, at the cockpit end only. (Fig. 13)

4.) Connect one conductor to pin 4 of the din connector, for the RS 232 output from the

navigation equipment providing data. Make sure this data conforms to one of our

recognized data formats, and baud rates. (Fig.13)

5.) Bring a short 4” 24 AWG wire out from pin 2 to be used later in verifying that the ELT is

receiving, and processing the GPS data properly. (Fig 12.4)

6.) Solder the connections, seal the back of the jack, and wire solder joints with silicon

RTV sealant. (Loctite 59530 or equivalent) (Fig. 12.2)

7.) Apply RTV sealant to the inside of the outer cover to seal the wire where it enters the

outer housing. (Fig. 12.3)

SECTION 7 FINAL INSTALLATION AND CHECK OUT

1.) After installing the ELT, antenna, and RCPI in the aircraft, install the coaxial cable

between the ELT transmitter, and antenna base. If possible the cable should not cross any

production breaks in the airframe, and must have a reasonable amount of slack at the

transmitter. The slack is necessary for easy removal of the coaxial cable during

maintenance. If a longer cable than the one supplied with the unit (5 foot) is needed, it may

be fabricated using RG-58 cable or equivalent, and Amp 227079-5 connectors or their

equivalent. Insertion loss of the cable at the 121.5 MHz frequency should not exceed 3dBm,

and at the 406 MHz frequency 2dbm. Secure the coaxial cable using tie wraps or other

appropriate methods. Make sure the cable is protected from abrasion.

2.) The RCPI unit is connected to the ELT transmitter via a RJ-11 standard type modular

connectors. A 15 foot connecting cable is included with each ELT. To install the cable

connect the modular plug on the ELT transmitter into the jack end of the interconnecting

cable. Run the plug end of the cable to the audio alert unit. Run the short audio alert cable

from the RCPI to the audio alert module (page 6 Fig. 8) avoid running this cable near

sources of strong EMI/RFI radiation. (i.e. Comm cables, strobe light power cables, starter

cables.) Secure the cable along its run using tie wraps, or other suitable methods. The

interconnecting cable may be shortened, or a longer cable of up to 150ft. may be used if

necessary. After connecting the mini DIN RS 232 jack and plug. Wrap electrical tape

around the joint at the center of the connection to secure the two parts together, and seal

the joint from moisture. (Page 8 Fig. 12.5)

3.) After installation, and wiring is complete, verify that the ELT is receiving and

processing GPS data correctly. Apply power to both the ELT, and the GPS equipment

supplying data. Make sure the GPS has a satellite fix, and is reporting position data.

Fabricate a GPS verification tool as shown in figure 14.

4.) Connect the test tool as shown in Fig 14. The main switch on the ELT should be in the

“armed” position.

5.) With power supplied both to the ELT, and the GPS, make sure the GPS has acquired the

satellites, and is transmitting valid position data. The LED should blink each time the ELT

receives a valid GPS data position. (Typically once per second) This test verifies that the

ELT is properly receiving, and processing position data from the GPS system. This is a

very short duration low intensity flash make sure the LED is shielded from bright light.

6.) After verifying that the ELT is receiving, and processing GPS data correctly. Seal the

end of the GPS verification test line using a adhesive lined end cap, (McMaster-Carr

72855k21) or other method to protect it from moisture. Secure the test wire to the shielded

cable with a tie wrap.

7.) Complete the steps in section 8 (registration) before you verify the installed operation

of the ELT. After you have registered the ELT, do the self test as described in section 9 to

verify the complete system is functioning properly.

8.) Record the ELT battery expiration date marked on the ELT battery case, the expiration

of the RCPI, and audio alert batteries in the airframe logbook.

SECTION 8 REGISTRATION

1.) Before completing the final check out of the ELT, YOU MUST FIRST REGISTER YOUR

BEACON FOLLOWING THE REGISTRATION REQUIREMENTS OF THE COUNTRY WHERE

THE AIRCRAFT IS BASED. YOU CAN ONLY REGISTER THE ELT IN THE COUNTRY THE

AIRCRAFT IS REGISTERED.

2.) There is a preprinted self adhesive label supplied with the ELT that has the hex code,

manufacturer, and model number on it which you should affix to the top of the registration

form. Or you can refer to this label when registering over the internet. You can download the

registration forms for your country from our website.

WWW.ACKAVIONICS.COM

3.) In the U.S. and Canada you can mail or fax the registration forms, however it is strongly

recommend that beacon registration be completed on line at the following sites:

UNITED STATES

www.beaconregistration.noaa.gov

CANADA

www.canadianbeaconregistry.forces.gc.ca

4.) For other countries contact the COSPAS/SARSAT regulating body for registration

instructions. If allowed by your regulating country you may register at the

COSPAS/SARSAT website. INTERNATIONAL

www.406registration.com

5.) When filling out the registration the hex code identifier may also be found on the front

right side of the ELT. (Fig 15)

6.) YOU MUST UPDATE YOUR BEACON REGISTRATION every two years, and any time the

beacon is used in a different aircraft.

SECTION 9 OPERATION AND SELF TEST

THERE ARE THREE MODES THAT THE ELT MAY BE ACTIVATED:

1.) The ELT automatically activates when in the “armed” position, and a crash level

deceleration force is applied to the ELT, in the forward direction as indicated by the arrow on

the top of the battery pack.

2.) The ELT also may be activated by pressing the “On” button on the cockpit remote control

(RCPI). (Page 11 Fig. 16)

3.) A third method of activating the ELT, is by means of placing the main on-off-armed

switch, on the front of the ELT in the “On” position. (Page 11 Fig. 17)

The red rubber cover, covering the main switch on the ELT SHOULD BE LEFT OFF AT ALL

TIMES, EXCEPT WHEN THE ELT IS IN THE ARMED POSITION. The cover has a center cone,

that projects down into the switch recess, and provides for positive retention of the switch in

the armed position.

There are two modes in which the ELT may be deactivated.

1.) Pressing the “Reset” button on the remote control (RCPI). (Page 11 Fig. 16)

2.) Placing the main switch on the ELT in the “Off” position. (Page 11 Fig. 17)

When the ELT is activated, and transmitting the 406 Mhz distress signal. The cockpit remote

will flash, and the audio alert indicator will emit a series of 9 beeps, approximately every 50

seconds to alert the crew that the ELT is operating. If there is no emergency, reset the ELT

using the “Reset” button on the remote, (Page 11 Fig. 16) and immediately notify the

appropriate search and rescue operations office, or ATC of the false activation.

SELF TESTS:

The ELT is capable of performing a self test to verify that major ELT systems are functioning

properly.

During the self test, the ELT transmits on 121.5 MHz for 1 second, (3 audio sweeps) then

transmits a 406 MHz test burst for 550ms, then returns to the armed mode.

There are two modes in which a self test can be initiated:

1.) When the ELT is in the “Armed” position, pressing the “Reset/Test” switch on the cockpit

remote control (RCPI) initiates a self test. (Page 11 Fig. 16)

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