PREPARED BY PAGE

Q. Phan AMERI-KING CORP. NO.

DATE: 10-22-08 2
SUBJECT
OPERATIONS AND
CHECKED BY INSTRUCTIONS FOR REPORT REV NO.
K. Van NO.
CONTINUED
DATE: 10-22-08 IM-451 NC-1
Document No. ICA-451 AIRWORTHINESS (ICA)
MANUAL

PREPARED BY: _______________________________________ DATE: 4/4/07

OPERATIONS AND INSTRUCTIONS FOR Quang Phan, Senior Design Engineer
CONTINUED AIRWORTHINESS (ICA) MANUAL APPROVED BY: _______________________________________ DATE: 4/8/07
Keith Van, Engineering Manager
APPROVED BY: _______________________________________ DATE: 4/10/07
FOR Victor Vu, General Manager

MODEL AK-451-( ) Series REVISION TABLE

CHANGED APPROVED
REVISION DESCRIPTION DATE
BY BY
406 MHz ELT Emergency Locator Transmitter with NC First Release Q.P. K. V. 10-22-
GPS/NAV position 2008
NC-1 Add Periodic
Maintenance Check List Q.P. K.V. 10-24-
with Compliance Cross 08
References

AMERI - KING CORPORATION

17881 Sampson Lane

Huntington Beach, CA 92648
Tel: (714) 842-8555
Fax: (714) 842-4235

2
 DOCUMENT NO.: IM-451 REV. NC TABLE OF CONTENTS

APPLICABILITY
Table of Contents............................................................................................ 4
Model/Part Fixed Whip Or Fixed Rod Or Fixed Portable Whip List of Figures................................................................................................. 6
No.: Antenna Antenna Blade Antenna Antenna
451017-1B 451017-2A 451017-3A 451017-4S
406/121.5 406/121.5/243 406/121.5/243 406/121.5/243 SECTION I
MHz MHz MHz MHz GENERAL INFORMATION &
BATTERY REPLACEMENT INSTRUCTIONS
AK- 451- S S S -
(AF) S S S M
AK- 451- - - - M 1.1 Scope ............................................................................................ 7
(AF)(AP) - - - M
AK - 451- 1.2 Overview .......................................................................................... 7
(AP) 1.2.1 Application and Equipment Limitation.............................. 7
AK - 451-(S) 1.2.2 Certification ....................................................................... 8

M: Mandatory. The respective model must be accompanied by this antenna. 1.3 Technical Characteristics.................................................................. 8
S: Selective. The respective model must be accompanied by at least 1 of these
antennas. 1.4 Battery replacement instructions ...................................................... 13
- : Not applicable 1.4.1 ELT main unit battery replacement instructions ................ 13
1.4.2 ELT remote unit battery replacement instructions ............. 15
4500010-1: Battery Package, Lithium, LiMnO2, 90 Hrs Lasting.

TS-451: Computer Test Set and ELT Coding Equipment for AK-451 SECTION II
OPERATIONS

2.1 General ........................................................................................ 16

2.2 Operation ........................................................................................ 17

2.3 Transmitter Functional Test ................................................................. 17

2.3.1 Main Switch ON/OFF/ARM Operation................................. 18
2.3.2 Transmitter ID Programming and Self-Test .......................... 18
2.3.3 System Integration Test ......................................................... 19
2.3.4 Green ON Lights and Buzzer Sound Functions..................... 22
2.3.5 Transmitter Functional Test for ELT-(S) only....................... 22

SECTION III
INSTRUCTIONS FOR CONTINUED AIRWORTHINESS (ICA)

3.1 Periodic Maintenance (Instructions for Continued Airworthiness).... 26

3.1.1 Secure Inspection................................................................... 26
3.1.2 Corrosion Inspection for Coaxial Cable................................. 26
3 4
 3.1.3 Corrosion Inspection for Remote Wiring Modular Cable ......26 List of Figures
3.1.4 Expiration Date Check............................................................26
3.1.5 Battery Leakage Check...........................................................26 Figure 1: Front view of ELT........................................................................... 15
3.1.6 Operational Test .....................................................................26 Figure 2: 3-D view of ELT ............................................................................. 15
3.1.7.1 G-Switch Check......................................................................26 Figure 3: ELT Front Panels-Main Unit and Remote Unit............................... 20
3.1.7.2 Antenna Check .......................................................................27 Figure 4: Battery Replacement for ELT Main Unit ........................................ 14
3.1.8 Verification of Digital Message..............................................27 Figure 5: Battery Replacement for ELT Main Unit (Actual View) ................ 14
3.1.9 Verification of Registration ....................................................29 Figure 6: Battery Replacement for ELT Remote Unit .................................... 15
3.1.10 Verification of ELT/GPS interface .........................................30 Figure 7: ELT-(S) complete assembly with antenna....................................... 24
3.1.10.1 ELT to GPS Interface Information ..................................30 Figure 8: Verify parameter setting.................................................................. 34
3.1.10.2 ELT/GPS Interface Communication Formats .................31
3.1.10.3 ELT/FMC Interface and Checkout Process.....................32
3.1.10.4 24-Bit Address Maintenance Check (mandatory for
Installations reprogramming
by Ameri-King’s authorized dealer)................................33
3.1.10.5 GPS Position Test............................................................33

3.2 Periodic Maintenance (Instructions for Continued Airworthiness) for

Canadian Installation ............................................................................35
3.2.1 Regular Periodic Maintenance Test........................................36
3.2.2 Power output test, Performance Testing .................................36
3.2.3 Frequency Test / Current Draw Test, Performance Testing ...38
3.2.4 Audio Modulation, Performance Testing ...............................40
3.2.5 Transmitter Functional Test…..……………………………..40
3.2.6 Performance Test Marking and Log Book Entry ...................40
3.2.7 Shipping..................................................................................40

Periodic Maintenance Check List With Compliance Cross References ..........41

5 6
 SECTION I • ELT Transmitter w/ integral battery
GENERAL INFORMATION • ELT Mounting Tray and Velcro Holder
• ELT Antenna and Coaxial Cable Assembly
• ELT Remote Switch and Remote Wiring Cable Assembly
• ELT Audible Buzzer Monitor unit and T-Adapter Connector
1.1 SCOPE
Note:
This manual contains information necessary for the Operations and Instructions for
Continued Airworthiness (ICA) of the model AK-451, Emergency Locator
Only Ameri-King approved system components may be used for a TSO approved
Transmitter, manufactured by Ameri-King Corporation, California, U.S.A.
system.
1.2 OVERVIEW
1.2.2 Certification:
. The Ameri-King AK-451-( ) Series is a FAA TSO C-126/91a approved, EASA
The AK-451 has been certified to the following:
ETSO approved, 406 MHz ELT Emergency Locator Transmitter, Types (AF)
Automatic Fixed, (AP) Automatic Portable, (S) Survival. It may transmit aircraft • FAA TSO-C126
GPS/NAV position data, immediately and accurately, on triple (406 Satellite /243 • FAA TSO-C91a
Military /121.5 Civilian) MHz frequencies. • ETSO-2C126 per European Aviation Safety Agency (EASA)
• FAR Part 91 – mandatory automatic ELT requirements
1.2.1 Application and Equipment Limitation. • Cospas-Sarsat T.001
47 CFR Part 87 (FCC requirements) Note: Per FCC regulations 47
This manual constitutes FAA approved data as described in AC 43.9-1E, paragraph CFR § 2.902, the ELT is tested per “Verification” method.
(h)(2) and AC 43-201, chapter 2, paragraph 201(a)(6) for major alterations. Not all
installations are “major”; consult your local FAA ACO for clarification. Note:
The AK-451 is certified to meet the requirements of FAA TSO-C126, TSO-C91a and
In Canada, Installation of an ELT in an aeronautical product is carried out under a EASA ETSO-2C126 per EUROCAE ED-62. For use outside the US or EASA
Supplemental Type Certificate (STC). This is a separate regulatory requirement and member states, contact your local civil aviation authority for ELT requirements.
should therefore be in a separate document manual for the Operations and Instructions
for Continued Airworthiness (ICA). Note:
There is no electronic connection between TCAS or Mode S systems and the ELT,
The conditions and tests required for TSO approval of this article are minimum only the ID number is common. The ELT may accept aircraft GPS/NAV Lat/Long
performance standards. It is the responsibility of those desiring to install this position data, then transmits the position data on the 406 MHz digital long messages..
article on a specific type or class of aircraft to determine that the aircraft
installation conditions are within the TSO standards. TSO articles must have 1.3 TECHNICAL CHARACTERISTICS
separate approval for installation in an aircraft. The article may be installed
only if further evaluation by the applicant documents an acceptable installation SPECIFICATIONS: CHARACTERISTICS:
and it is approved by the FAA Administrator. The article may be installed only APPROVALS: FAA TSO-C126 / C91a,
if performed under 14 CFR parts 43 or the applicable airworthiness and EASA ETSO-2C126/2C91a
requirement. For installations outside of the US, contact your local civil aviation
authority for guidance (Ref. TSO-C126 paragraph D). BATTERIES:

Lithium battery safety concerns include the possibility of fire, venting violently, 4500010-1: Battery Pack, Lithium, LiMnO2, 90 Hrs lasting, 4D cells
and venting of toxic gases (Ref. TSO-C126 paragraph 5.a.(2)).

The AK-451 ELT described in this manual was designed, tested and certified as a
complete system including the following components:

7 8
PHYSICAL CHARACTERISTICS: Equivalent Isotropic 100mW (-10dBW) @121.5/243.0 MHz
(min)
• SIZE AND WEIGHT:
Main Unit: (4.27”Wx2.95”Hx5.64”L) 1lbs 14oz Radiated Power (EIRP): 6dBW ± 4dB @406.028 MHz (max)
Remote Unit: (1.58”W x 0.65”H x 2.00”L) 1.0 oz
Transport Blade type, 451 017-3: 600 Knots airspeed, 1.4 lbs • BATTERY REQUIREMENTS:
Business Rod type, 451 017-2: 350 Knots airspeed, 0.5 lb Transmitter Main Unit: Battery Pack consists of 4 cells LiMnO2 or LiSO2
General Aviation whip type, “D” Size
451 017-1: 250 Knots airspeed, 0.25 lb Remote Unit: DURACELL DL 1/3 NB, Lithium Cell
Portable Antenna, 451 017-4: (17”L) 4.0 oz
Mounting Tray & Velcro holder: (4.51”W x 0.75”H x 5.87”L) 4.0 oz
• AUTOMATIC CRASH ACTIVATION:
• MOUNTING HOLE SPACING: Velocity Change of 2.3 ± 0.3 G (4.5 ± 0.5 FPS) per TSO C-126 (DO-
204A) and ETSO-2C126 (EUROCAE ED-62) requirement.
Mounting Tray: 4 Trapezoid Corners (L1=2.76”; L2=1.76”; H=2.01”)
Remote Unit: 4 Rectangular Corners (1.825”W x 0.490”H) • ANTENNA RADIATION CHARACTERISTICS:
Fixed Antenna: 7 / 5 / 1 Holes (0.500” Diameter) for Blade / Rod / Whip Radiation on 121.5, 243.0 MHz, and 406.028 MHz
respectively Vertically polarized & Omni directional in the Horizontal Plane.

• CASE AND COLOR: • CRASHWORTHINESS: 100g, 23 ms, 6 directions

No Sharp Edges, High Impact, Flame Retorted, Fire Resistant, Waterproof, High, • ACTIVATION MONITOR:
Temperature ABS Plastic. Safety International Orange Color.
Manual ON and RESET functions are located on both ELT Main Unit and Remote
• GENERAL SPECIFICATIONS (STANDARD CONDITIONS): Unit. The two Green ON lights flashing, located on the ELT Main Unit and Remote
Switch Unit and a buzzer are to indicate when the ELT is transmitting. Both ELT
• TRANSMITTER: Main Unit and Remote Unit are self-powered by their internal batteries. Automatic
Operating Frequencies: 406.028 MHz ± 0.001 MHz activation is remained, regardless whether the Cable Interconnect between the Main
121.500 MHz ± 0.0025 % Unit and the Remote Unit is open or shortened.
243.000 MHz ± 0.0025 %
−9 GPS INTERFACE PROTOCOL: Aviation RS-232
Short term stability ≤ 2 x 10 /100ms
−9 (Latitude/ Longititude Insert Messages) Baud Rate (fixed): 9600
Medium slope -1 to +1x10 /min Parity: None
−9
Medium Residual variant ≤ 3 x 10 Data Bits: 8
Modulation Stop Bits: 1
Characteristics: Audio Sweep Frequency: Download
Sweeping: (1600-300) Hz Garmin International Inc.:
Sweep Rate: 3 Hz ± 1 Hz
Modulation Factor: More than 0.85 • All Series: 150/ 250/ 400/420/430/ 500/520/530
Occupied Bandwidth: Less than 25 Hz
Voice Modulation: Included Honeywell Bendix-King Inc.:

Modulation Duty Cycle: (33-55) % Square Wave AM Continuous • KLN 88, KLN89, KLN89B, KLN 90, KLN90B, KLN94, KLN900.
Peak Effective Radiated50mW @ 121.5 MHz
RF Power (PERP): 50mW @ 125/243.0 MHz
5W @ 406.028 MHz

9 10
Arnav Systems Inc.:

• R50, R50i, STAR 5000, FMS 5000, MFD (Multi-Functional Display).

II Morrow:

• FLYBUDDY, 2001 NMS

Trimble Nav Inc.:

• NAV 1000, NAV 2000, TNL 2100, and TNL3100. The following Trimble systems
all require a RS-422 to RS-232 adapter: NAV 3000, TNL 1000, TNL 2000, TNL
2000A, TNL 3000, 2000 APPROACH, 2000 APPROACH PLUS, 2101
APPROACH, 2101 APPROACH
PLUS, 2101 I/O APPROACH, 2101 I/O APPROACH PLUS.

ENVIRONMENTAL TEST SPECIFICATIONS:

• RTCA DO-204A; DO-183

Figure 1: Front view of ELT
• TSO-C126/C91a, RTCA DO-160E ENV. CAT.: F1XBA (204/183)
(204/183)XR(204/183)XXSXXXXAC(204/183)BXXXX (204)

• TEMP. AND ALTITUDE: Category F1

Low Temperature: -20°C Operating; -55°C Storage.
High Temperature: +55°C Operating; +85°C Storage.

• OPERATING LIFE: 5W @ 406.208 MHz for 24 hrs @ 20°C

50mW @ 121.5 MHz
50mW @ 243.0 MHz
(Minimum Requirement throughout a 50
hour period at –20°C)
• TEMP VARIATION: Category B, 10°C minimum per minute
• HUMIDITY: Category A, 95% RH, 50 hours
operating
• SHOCK: 500G, 4 ± 1msec
• IMPACT: Penetration of 55 lbs mass, 6 drops, 4
surfaces
• CRUSH: 1000 lbs, 4 surfaces
• VIBRATION: 10G, Sinusoidal, (5-2000) Hz, 3 axes
• WATERPROOF: Category R, 15 minutes Spray, 6 sides
• IMMERSION SALT WATER: Category S, 24 hours Immersion, 160
hours at + 55°C Figure 2: 3-D view of ELT
• SALT SPRAY: Category S, 48 hours exposure to the
Salt Fog, and 48 hours drying

11 12
1.4 BATTERY REPLACEMENT INSTRUCTIONS 1. Using the 3/32” Hex Driver supplied with the ELT, remove the 4 retaining
1.4.1 ELT MAIN UNIT BATTERY REPLACEMENT INSTRUCTIONS screws and split lock washers that attach the battery case to the ELT Transmitter
Assembly (See Figure15).
All batteries are strongly advised to be serviced by Ameri-King or its authorized 2. Insure both battery connectors are locked-in properly by its tab.
service centers. End users may return the entire ELT for replacing the batteries Verify the battery pack voltage is 13 +/- 0.5 VDC
and post functional tests. Ensure that the gasket is in place (See Figure 4).
3. Place the Transmitter Assembly face down on a bench. Press down on the
The Ameri-King Corp. Model AK-451 ELT is designed to use only with Ameri-King battery case to compress the battery contact springs. Replace the four battery retaining
lithium battery packages which have been tested per TSO-C126, TSO-C91a screws and lock washers and evenly tighten until the battery case is pulled flat against
requirements. the Transmitter Assembly.
4. Remove any existing battery replacement date labels from the battery case and
The use of any other battery will void all warranties of the ELT by Ameri-King install the new label you prepared in step 3 above in a readily visible location on the
Corp. The ELT does not meet the requirements of TSO-C126, and TSO-C91a or ELT.
FAR 91.52 if used with any other type of battery. Using any other battery is not 5. After battery replacement, a transmitter function test must be performed as
allowed (forbidden). described in section 2.3 of this manual.

The Ameri-King Battery Pack has a 10 years shelf life and 5 years useful life. It will
last for 78 hours at -20 deg C, at end of 5 years battery life.
FAR 91.52 (d) (i) requires that ELT batteries be replaced when the transmitter has
been in use for more than one cumulative hour.

The label sticker for expiration date of the batteries must be affixed on the
outside of the ELT battery case and recorded in the aircraft logs.

””” WARNING ”””

USE ONLY DURING SITUATIONS OF GRAVE
AND IMMINENT DANGER!
LITHIUM BATTERY PACK – NON-RECHARGEABLE
P/N 4500010 -1 FOR USE ON Model AK-451-(AF)(AP)(S)
RTCA DO-160E Environmental Categories
F1XB(227)(227)(227)XXXXXXXXXXXXXXXXXX
””” WARNING ”””

Replace Main Batteries FOR AVIATION EMERGENCY USE ONLY.

Replace battery pack

UNLICENSED OPERATION UNLAWFUL

after one culmulative hour

of use or by date shown: By Date: _________
*Battery type: Lithium LiMn02

NEVER CHARGE, SHORT CIRCUIT, PUNCTURE,

DEFORM, INCINERATE, OR OPEN. DO NOT
Figure 3: Battery Replacement for ELT Main Unit
O
SUBMERGE IN WATER OR HEAT ABOVE 85 C.
REMOVE WHEN DISCHARGED Battery Box Silkscreen

The owner or operator may perform Battery replacement provided that the
accessibility, removal and reinstallation of the ELT can be considered “simple” as
prescribed in Advisory Circular 91-44A, Paragraph 8.a (See Appendix B).

The following is a step-by-step instruction for replacing ELT Battery Pack P/N
4500010-( ) Series: Figure 4: Battery Replacement for ELT Main Unit (Actual View)
13 14
1.4.2 ELT REMOTE UNIT BATTERY REPLACEMENT SECTION II
INSTRUCTIONS OPERATIONS
The ELT Remote Unit is designed to be powered by a Duracell DL1/3NB 3 Volt 2.1 GENERAL
Lithium Batteries. Under normal operating conditions, the Lithium battery must be
replaced every five years. If the ELT is activated for an unknown period of time, the This section describes the operation of the ELT, Emergency Locator Transmitter,
lithium battery must be replaced. model AK-451.
To install or replace the Remote Unit Battery, follow these steps: The following types are applicable for the model AK-451:
Remove the three Retaining Screws that secure the top and bottom half of the remote a. Automatic Fixed - Fixed ELT (AF):
unit (Figure 5). Loosen the two Switch Retaining nuts located on the front of the unit
(Figure 5). See paragraph 1.2.1 (a)
Carefully remove the top half of the Remote unit, exposing the battery compartment b. Automatic Portable - ELT (AF) (AP) with dual antennas:
(Figure 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 See paragraph 1.2.1 (b)
cleaner and a stiff brush. Badly corroded contacts should be replaced.
c. Automatic Portable - ELT (AP):
Insert the battery with the polarity as shown in Figure 5. The polarity is also engraved
on the bottom of the battery compartment. See paragraph 1.2.1 (c)
Replace the top half of the remote unit and replace the three retaining screws and d. Survival-ELT (S):
tighten the two switch retaining nuts.
See paragraph 1.2.1 (d)
The next remote battery replacement date should be recorded on one of the adhesive
labels supplied and affixed to the ELT in a readily visible location. The AK-451 is a "third generation ELT," transmitting on 406.028, 121.5 and 243.0
MHz. The ELT is designed to meet or exceed the requirements of TSO-C126 and
TSO-C91a and the mandatory automatic ELT requirements of FAR Part 91. The ELT
meets the requirements of DOT Aviation Regulations, Section 3, Chapter 3, Part 2.

The ELT automatically activates during a crash and transmits the standard swept tone.

The Green ON lights flashing located on both the ELT Main Unit and the Cockpit
Remote Switch unit and the buzzer sound periodically indicates when the ELT is
activated. The ON switch on the Remote Switch Unit allows you to turn on the ELT
for testing. The RESET Switch on the Remote Switch Unit enables to reset the ELT.
In normal operation, the Main Switch on the ELT Unit must be selected at “ARM"
position.

Note:
You cannot "disarm" or disable the unit from the cockpit; you can only deactivate the
ELT after it has been activated.

The ELT unit is able to withstand extremely harsh environments. Units exactly like
Figure 5: Battery Replacement for ELT Remote Unit yours have been subjected to numerous 500G shock pulses; 1000 pounds crash

15 16
weights and severe penetrator tests, and continue to operate normally. Continued
operation in a temperature range of -20 degrees Celsius to +55 degrees Celsius is WARNING
assured. Do not allow test duration to exceed 5 seconds. A false alarm may be generated.
Any time the ELT is activated, it is transmitting a 121.5 MHz and 243.0 MHz
2.2 OPERATION distress signal. If the ELT operates for approximately 50 seconds, a “live” 406
MHz distress signal is transmitted and is considered valid by the Cospas-Sarsat
The AK-451 ELT, Emergency Locator Transmitter, is a state of the art Micro satellite system.
controller technology, long lasting, solid state based equipment. It is an extremely Any time that the ELT Main Switch is lifted and flipped from “OFF” to “ARM”,
reliable, highest standard of quality, designed to meet TSO-C126 and TSO-C91a a 406 MHz self test signal is transmitted (after 25 seconds), however it is
requirements for critical application. specially coded as a “self test” signal that is ignored by the COSPAS-SARSAT
satellites.
Both ELT main unit and Remote Switch are self-powered by their own internal
batteries. Interface with aircraft electrical power system is not required. 2.3.1 Main Switch ON/OFF/ARM Operation:

With the main switch, located on the ELT main unit, set at "ARM" position, the AK-
451 ELT is automatically activated upon sensing a change of velocity of 4.5 ± 0.5 In normal operation, the Main Switch, located on the ELT main unit, must be in the
Feet/Second, along its longitudinal axis (Automatic Fixed-ELT (AF) Configuration). "ARM" position. In the event of a crash, an acceleration activated crash censor (G-
It is also designed to be removed from the aircraft and used as a personal locating switch) turns the ELT 'on' automatically when the ELT experiences a change in
device when it is necessary to leave the scene of the accident (Automatic Portable velocity (or deceleration) of 4.5 fps ± 0.5 fps. Activation is also accomplished by
ELT (AP) Configuration) and survival ELT(s) configuration. means of the cockpit mounted remote control unit or the "ON" switch on the ELT
main unit. To reset the ELT press either "RESET" switch on the remote control panel
In the event of a crash, the AK-451 activates automatically, and transmits the standard or on the main unit.
swept tone on 243/121.5 MHz lasting until battery power is gone. This 243/121.5
MHz signal is mainly used to pinpoint the beacon during search and rescue The ELT has an "OFF" position. This allows the beacon to be handled or shipped
operations. without 'nuisance' activation. Care should be taken when transporting or shipping the
ELT not to move the switch or to allow packing material to become lodged such as to
For the first 24 hours of operations, a 406 MHz signal is transmitted at 50-second toggle the switch.
intervals. This transmission lasts 520 ms and contains identification data programmed
into the beacon and is received by COSPAS-SARSAT satellites. The aircraft Main switch, alternate positions:
GPS/NAV latitude/longitude data position will also be transmitted (if GPS/NAV is
connected with the ELT). The transmitted data is referenced in a database (maintained • "ON:" ELT transmits immediately. Both Green ON lights on the main unit and
by the national authority responsible for ELT registration) and used to identify the remote switch unit flash and the buzzer sound, at rate of 1 second ON, 4 seconds
beacon and owner. OFF.

Accuracy: • "OFF:" The ELT is turned off.

Doppler positioning is employed using both 121.5 MHz and 406 MHz signals. • "ARM:" ELT self-test is confirmed after 24 seconds. If the self-test is passed,
Position accuracy of the 121.5 MHz signal is within an area of approximately 15-20 the 2 Green ON lights and the buzzer sound must be extinguished. The ELT system is
km radius about the transmitter. Due to the better signal integrity of the 406 MHz, its then in the "ARM" mode.
location accuracy is within about a 1-2 km radius. If the GPS/NAV position data is
transmitted, the accuracy of the AK-451 will narrow to 22 meters (typically). 2.3.2 Transmitter ID Programming and Self-Test:

2.3 TRANSMITTER FUNTIONAL TEST Turn the main switch from the "OFF" position to the "ARM" position. The
Buzzer sound and the 2 Green ON lights shall illuminate for 4 seconds, then
The ELT should be tested every month. extinguish. This is to allow coding programming during the next 20 seconds window
and self-test for 1 second thereafter.

17 18
 The ELT may be ID coding programming during the aforementioned 20
seconds window period. If no programming happened the ELT will then enter the Self
Test Mode for 1 second thereafter.

Self-test results (after 25 seconds), is:

If the self-test is passed: the Green ON lights are steadily extinguished and no
buzzer sound.

If the self-test is failed: the Green ON LIGHTS flashes as defined below:

1 flash: Internal Data stored in Memory at fault.

2 flashes: Distress ID stored in Memory at fault.
3 flashes: Battery voltage is low < Useful Life Battery Voltage setting.
4 flashes: Vcc supplies for F3, F2, or F1 at fault.
5 flashes: F3 RF power level < 33 dbm @ 406.028 MHz
7 flashes: F1/F2 VHF RF power level < 17 dbm @ 121.5/243 MHz.
9 flashes: PLL locked in F3 or F1 or F2 at fault.
Continuous flash: no F3/F2/F1 RF output power, ELT shuts down completely

Note:
The self-test mode that transmits a 406 MHz test code pulse monitors certain
system functions before returning to the ARM mode. The 406 MHz test pulse is
ignored by any satellite that receives the signal, but the ELT uses this output to check
output power and correct frequency.

• Self-test is 520 ms long message burst on the 406 MHz signal. Synchronization
pattern is 011 010 000.
• Self-test is then 121/243 MHz (VHF) Continuous Wave during 1s.

2.3.3 System Integration Test:

The test consists of turning the unit “ON” and then “resetting” it to verify that the
Transmitter, Latch Circuit, Batteries, and associated equipment are operating
properly. Regulations require that Transmitter tests only be done during the first 5
minutes of each hour and must not last for more than 3 Audio sweeps (1.5 seconds).
If you are at a location where there is an FAA Control Tower or other monitoring
facility, notify the facility before beginning the tests. Never activate the ELT while
airborne for any reason. See Figure 18 for the ELT Front Panels for both ELT
Main Unit and Remote Unit.

Figure 6: ELT Front Panels-Main Unit and Remote Unit.

19 20
2.3.3.1 Monitor 121.5 MHz using the Aircraft Com Receiver or Portable Hand Held Important:
Receiver. Turn the Squelch all the way up or ON.
If the ELT is accessible after the accident, place the Main Switch in the ON
2.3.3.2 Ensure that the main switch on the ELT is on ”ARM” position. position and monitor it on 121.5 MHz for proper operation if possible. If the
• Push the “ON” button on the Cockpit Remote Switch Unit. Verify that both the Antenna is broken off of the Aircraft, the ELT Unit should be removed and the
Green ON lights, located on the Main Unit and the Cockpit Remote Switch portable antenna to be used. If the ELT Unit is to remain at the Aircraft site, it should
Unit, are flashing. Verify the Buzzer sound periodically. Verify the ELT audio be placed on a large metallic portion of the airframe with its Antenna pointing
sweep tone can be heard on the Com Receiver. skyward. The Green ON lights should be flashing after the accident.

• Push the RESET button on the Remote Switch unit. Verify that the two Green If the ELT is to be taken along as the Portable Unit when leaving the scene of the
ON lights are extinguished. Verify the Buzzer sound ceased. Verify the ELT accident, place the Main switch in the ON position and keep the Antenna vertically
audio sweep tone ceased. oriented as much as possible. The ELT Green ON light should be flashing.

G Switch Check: Activate the G switch by using a rapid forward (throwing) motion 2.3.4 Green ON Lights and Buzzer Sound Functions:
coupled by a rapid reversing action. Verify that the ELT has been activated by use of
the Wattmeter, the Airplane’s VHF Radio Communications Receiver when tuned to Green ON lights, located on the ELT main unit and remote switch unit:
121.5 MHz, or other means (see Note 1). The ELT must then be reset by pressing
either the RESET push button located on the ELT main unit or the ELT Remote Unit. • In ON mode: Green ON LED flashes continuously (1 second ON, 4 second
OFF) and the Buzzer sound periodically. This is to indicate that the ELT has been
Note: manually activated.
This is not a measured check. It only indicates that the G-Switch is working.
• In ARM mode: Green ON light flashes continuously (1 second ON, 4 second
Note: OFF) and the Buzzer sound periodically. This is to indicate that the ELT has been
In normal configuration, the main switch on the ELT Main Unit must be selected to automatically activated by the G switch.
the “ARM” position. Whenever both the Green ON lights (located on the Main Unit
and the Remote Switch Unit) flash and the Buzzer sound periodically, they indicate 2.3.5 TRANSMITTER FUNTIONAL TEST FOR ELT-(S) ONLY:
the ELT is transmitting.
The ELT-(S) should be tested every month.
If the ELT be accidentally activated by turbulence, hard landing, etc., or if this occur
under any conditions other than an accident requiring immediate assistance, pressing 2.3.5.1 Main Switch ON / OFF / SELF TEST Operation:
the RESET button on the Remote Switch Unit.
The ELT-(S) has an "OFF" position. This allows the beacon to be handled or shipped
If the Aircraft is on the ground and the RESET button on the Remote Unit does not without 'nuisance' activation. Care should be taken when transporting or shipping the
cause the Green ON light to extinguish, the RESET button on the Main Unit should ELT-(S) not to move the switch or to allow packing material to become lodged such
be pressed. If airborne and the RESET button on the Remote unit does not cause the as to toggle the switch.
Green ON LIGHT to extinguish, the main switch on the ELT should be set to the OFF
position, if the ELT is accessible. Main Switch, alternate / alternate / momentary positions:

If the ELT is not accessible in flight, you should land at the nearest suitable airport • "ON:" Alternate position. ELT-(S) transmits immediately. Green ON light on
and set the Main Switch to the OFF position. In either case, the unit should be the main unit flashes, 1 second ON, 4 seconds OFF.
inspected by qualified facility as soon as possible.
• "OFF:" Alternate position. The ELT-(S) is turned off.
The Aircraft may be operated with the ELT removed for inspection or repair subject
to the conditions of FAR 91.52. • "SELF TEST:" Momentary position. ELT-(S) self-test is confirmed after the
switch is held for 25 seconds. If the self-test is passed, the Green ON light must be
In the event of an accident, ensure that the External Aircraft Antenna has no damage. extinguished. The ELT-(S) system is fully self-tested.

21 22
2.3.5.2 Transmitter Self-Test:

Turn and hold the main switch, from the "OFF" position to the "SELF TEST"
position. The Green ON light shall illuminate for 4 seconds then extinguish. This is to
allow coding programming during next 20 seconds window and self-test for 1 second
thereafter.
The ELT-(S) may be coding programming during the aforementioned 20 seconds
window period. If no programming happened the ELT will then enter the Self Test
Mode for 1 second thereafter.

Self-test results after (4+20+1) =25 seconds, is:

If the self-test is passed, the Green ON LIGHT is steadily extinguished.

If the self-test is failed, the Green ON LIGHT flashes as shown below:

ƒ
1 flash: Internal Data stored in Memory at fault.
2 flashes: Distress ID stored in Memory at fault.
3 flashes: Battery voltage is low < Useful Life Battery Voltage setting.
4 flashes: Vcc supplies for F3, F2, or F1 at fault.
5 flashes: F3 RF power level < 33 dbm @ 406.028 MHz ELT-(S) Top Label
7 flashes: F1/F2 VHF RF power level < 17 dbm @ 121.5/243 MHz.
9 flashes: PLL locked in F3 or F1 or F2 at fault.
Continuous flash: no F3/F2/F1 RF output power, ELT shuts down completely.

Note:
The self-test mode that transmits a 406 MHz test code pulse monitors certain system
functions before returning to the SELF TEST mode. The 406 MHz test pulse is
ignored by any satellite that receives the signal, but the ELT-(S) uses this output to
check output power and correct frequency.

• Self-test is 520 ms long message burst on the 406 MHz signal. Synchronization
pattern is 011 010 000.
• Self-test is then 121/243 MHz (VHF) Continuous Wave during 1s.

The ELT-(S) may accept GPS position input by connecting the external GPS to the
Remote connector

Figure 7: ELT-(S) complete assembly with antenna

23 24
 SECTION III
INSTRUCTIONS FOR CONTINUED AIRWORTHINESS (ICA):

FORWARD 3.1 PERIODIC MAINTENANCE (INSTRUCTIONS FOR CONTINUED

””” WARNING ””” AIRWORTHINESS):
FOR AVIATION EMERGENCY USE ONLY.
UNLICENSED OPERATION UNLAWFUL
REFERENCES: FAR Part 91.52, Part 91.169, Part 43 Appendix D (i).
To Activate: Lift & flip the switch to the “ON” position FAR Part 91.207 Paragraph (d)
Verify: The Green “ON” light flashes 1 sec on, 4 sec off FAR Part 91.407 Appendix D (i)
Self Test: Lift & flip the switch from “OFF” to “ARM” position.
Verify: The Green “ON” light must illuminate for 4 sec
then extinguishes. Wait for an additional 21 sec. PURPOSE:
Pass: The Green “ON” light must remain extinguished To insure continued reliability of your ELT, it must be inspected for damage and wear
Fail: The Green “ON” light flashes. Please see Operation which could be caused by age, exposed elements, vibrations, etc. Even the best
Manual for detail fault code analysis
designed equipment, if not properly maintained and cared for, will eventually fail.
This satellite ELT only floats w/ floating collar

IMPORTANT NOTES:
Front label
The following inspections must be performed, a minimum of one time every year:

3.1.1 Secure Inspection: Inspect the ELT Main Unit and Mounting Tray to insure
all fasteners and mechanical assemblies are secure.
””” WARNING ”””
USE ONLY DURING SITUATIONS OF GRAVE 3.1.2 Corrosion Inspection for Coaxial Cable: Inspect the Coaxial Cable
AND IMMINENT DANGER! connecting the ELT Main Unit to the Antenna for cuts or abrasions on its outer jacket.
LITHIUM BATTERY PACK – NON-RECHARGEABLE Disconnect the BNC connectors on each end. Examine both the BNC connectors and
P/N 4500010 -1 FOR USE ON Model AK-451-(AF)(AP)(S) the mating plug on the Antenna and the ELT Main Unit for any signs of corrosion.
RTCA DO-160E Environmental Categories
F1XB(227)(227)(227)XXXXXXXXXXXXXXXXXX
3.1.3 Corrosion Inspection for Remote Wiring Modular Cable: Inspect the
Replace Main Batteries Remote Wiring Modular Cable, connecting the ELT Main Unit to the Remote Unit of
Replace battery pack
after one culmulative hour signs of wear or abrasion on its outer jacket. Remove the Modular Connecting Cable
of use or by date shown: By Date: _________ and inspect and jack and plug assembly for corrosion.
*Battery type: Lithium LiMn02

3.1.4 Expiration Date Check: Check the expiration date of the ELT Main Unit
NEVER CHARGE, SHORT CIRCUIT, PUNCTURE, and the Remote Unit Batteries. Replace if necessary.
DEFORM, INCINERATE, OR OPEN. DO NOT
O
SUBMERGE IN WATER OR HEAT ABOVE 85 C.
REMOVE WHEN DISCHARGED 3.1.5 Battery Leakage Check: Disassemble the ELT to inspect the Battery
Compartment for signs of corrosion or battery leakage. If any battery leakage is
present, the battery Assembly must be replaced. The Battery useful life is 5 years.
Back label 3.1.6 Operational Test: After completing the above inspections, a Functional Test
as described in Paragraph 2.3 must be performed to verify proper operation.

3.1.7.1 G-Switch Check: Ensure that the Main Switch on the ELT main unit must
be selected at “ARM: position at all times. Activate the ELT using applied force. The
direction for mounting and force activation is indicated on the ELT. The AK-451-
(AF)(AP) ELT can be activated by using a rapid forward (throwing) motion coupled

25 26
by a rapid reversing action. Verify that the ELT has been activated by use of the The AMERI-KING AK-451 has a self-test feature, which is encoded such that it will
Wattmeter, the Airplane’s VHF Radio Communications Receiver when tuned to be ignored by the SAR satellite system. This 15-digit number is used to register the
121.5 MHz, or other means (see Note 1). The ELT must then be reset by pressing ELT with the appropriate 406 MHz ELT registration authority. In the US, the
either the RESET push button located on the ELT main unit or the ELT Remote National Oceanic and Atmospheric Administration (NOAA) maintain the database of
Unit. registered ELT's.

Note 1: Note:
This is not a measured check. It only indicates that the G-Switch is working. For the following example, the programming protocol is assumed to be Standard
Location Protocol, ELT with C/S type approval number and Serial Number (Long
3.1.7.2 Antenna Check: A low quality AM Broadcast Radio Receiver should be Message.) Other protocols are possible and the exact read-outs of the Computer Test
used to determine if energy is being transmitted from the Antenna. When the Set will vary. Refer to the applicable operation manual included with the Computer
Antenna of this Radio (tuning dial on any setting) is held about 6 inches from the Test Set or contact AMERI-KING for assistance.
activated ELT Antenna, the ELT Aural tone will be heard (see notes 2 and 3). The
ELT must be reset by pressing either the RESET push button located on the ELT To verify the digital message, perform the following steps:
Main unit or the ELT Remote Unit. Setup
Use provided cable to connect the ELT (RJ-12 port) to the PC (USB port)
Note 2:
This is not a measured check, but it does provide confidence that the Antenna is 3.1.8.1 ELT ID Reading
radiating with sufficient power to aid search and rescue. The Aircraft’s VHF
Receiver, tuned to 121.5 MHz, may also be used. This Receiver however is more Step1: Double-Click AK451 Icon to run the program. The programming window
sensitive and could pick up a weak signal even if the radiating ELT’s Antenna is appears as below:
disconnected. Thus, it does not check the integrity of the ELT System or provide the
same level of confidence as does an AM Radio.

Note 3:
Because the ELT radiates on the emergency frequency, the Federal Communications
Commission allows these tests to be conducted only within the first 5 minutes after
any hour and limits the tests to 3 sweeps of the Transmitter Audio Modulation.

IMPORTANT NOTE:
IN NORMAL CONFIGURATION, THE MAIN SWITCH, LOCATED ON THE
ELT MAIN UNIT, MUST BE SELECTED AT “ARM” POSITION AT ALL TIMES.

3.1.8 Verification of Digital Message

Note:
This test is not mandatory per FAR 91.207(d) however Ameri-King strongly Note: If you don’t see the window above, you may try the other USB port.
recommends that it be performed as part of periodic maintenance, at least every
year. Step 2: Set the ELT main switch to “ARM” position.
Step 3: Verify the LED ‘ON’ light illuminates for 4 seconds.
Verify the 406 MHz digital message using a Computer Test Set capable of receiving Step 4: At the “:>_” prompt, type: “Password” command then press “Enter” to go to
and decoding the message. Ameri-King suggests the Ameri-King ELT Computer Test main menu. Must type this command within next 20 seconds after the
Set P/N TS-451. Contact your local Ameri-King dealer for availability of the command prompt appears.
Computer Test Set or call Ameri-King. Follow instructions provided with the
computer test set.

27 28
Note: If there is no programming command input in this time window, the ELT will The Ameri-King website also contains information on registering beacons in other
enter the Self-Test mode, and you cannot program the ELT. In this case, set the ELT countries
switch to “OFF” position and start again from step 2.2. http://www.Ameri-King.com

NOTICE; FOR ELTS THAT HAVE A COUNTRY OF REGISTRATION OTHER

THAN THE USA, PLEASE CONTACT THE APPROPRIATE CIVIL AVIATION
AUTHORITY IN THAT COUNTRY FOR GUIDELINES AND
DOCUMENTATION NEEDED TO ASSURE PROPER REGISTRATION

Logbook Entry:

Enter the date the test technician's initials and whether the ELT passed or failed into
the aircraft's logbook.

3.1.10 Verification of ELT/GPS interface (if equipped)

Note:
This test is not mandatory per FAR 91.207(d) however Ameri-King strongly
recommends that it be performed as part of periodic maintenance, at least every
Step 5: To read ELT ID: Use command “ 03 “ year.
Step 6: View message, ensure that all applicable information is correct (country 3.1.10.1 ELT to GPS Interface Information
code, aircraft ID, etc.).
For details on the operation and use of the ELT Computer Test Set TS-451, please
Step 7: The 15 digit ID hex ID (for example "2E28598228FFBFF") should match contact Ameri-King Corporation to request the brochures and Operation Manual for
what is shown on the ELT product label. This is the 15 digit hex ID (Unique the ELT Computer Test Set.
Identification Number or "UIN") that is used to register the ELT.
When used with ELT's that are programmed for Standard Location 24 bit protocol,
3.1.9 Verification of Registration the ELT to be program itself to the aircraft's 24 bit address. This feature will allow the
ELT to be transferred between aircraft. This makes maintenance of the ELT a simple
Note: matter of replacing the ELT. Note: There is no electronic connection between TCAS
This verification is not mandatory per FAR 91.207(d) however Ameri-King or Mode S systems and the ELT, only the ID number is common.
strongly recommends that it be performed as part of periodic maintenance, at
least every year. The AK-451 receives position data (longitude and latitude) from the aircraft's on-
board GPS system. The ELT may be programmed with the aircraft's 24 bit address.
Check ELT for signs of registration. When used with ELT's that are programmed for long message 24 bit protocol, which
In the US, NOAA supplies a beacon registration label that is applied to the ELT when is set up to match the 24 bit address parity of the Mode S surveillance and
it is registered. The following address should be used to register and obtain communications system switch block.
information on how to register 406 MHz ELT's in the United States:
Note: There is no electronic connection between TCAS or Mode S systems and the
SARSAT BEACON REGISTRATION ELT, only the ID number is common. This feature was implemented in the ELT with
E/SP3, RM 3320, FB-4 fleet operators in mind. ELT's are programmed with either a serialized or 24 bit
NOAA/NESDIS protocol. The ELT transmits position data as part of the 406.025 MHz distress
5200 Auth Rd. message.
Suitland, MD 20746-4304
http://www.sarsat.noaa.gov/ In the event of a crash, the ELT will transmit the converted position information from
the navigation system, such as the GPS flight management computer, loran, etc.
Geostationary satellites constantly monitor the 406.025 MHz transmissions. The crash
29 30
site is instantly known due to the aircraft's navigation system position data The following manufacturer's navigation systems are known to interface with the AK-
communication with the ELT. Without the position data being transmitted, it is 451:
necessary for the polar orbiting satellites to pass overhead, using Doppler Shift
technology to determine position. In a worst case scenario this could be a 3 to 4 hour GARMIN INTERNATIONAL INC.:
wait for a polar orbiting satellite to pass over. In addition, the accuracy of the position • All Series: 150/ 250/ 400/420/430/ 500/520/530
fix is much better i.e. 22 meters (with GPS/Nav Position data) versus 1 to 2
kilometers for the standard 406.028 MHz system (without GPS/NAV Position data). HONEYWELL BENDIX-KING INC.:
• KLN 88, KLN89, KLN89B, KLN 90, KLN90B, KLN94, KLN900.
The ELT accept Aviation RS-232 data bus formats. By reprogramming the ELT with
the aircraft's 24 bit identification or serialized (long message format), this facilitates ARNAV SYSTEMS INC.:
moving the ELT from one aircraft to another when performing routine maintenance, • R50, R50i, STAR 5000, FMS 5000, MFD (Multi-Functional Display).
etc
II MORROW:
WARNING: The programming and labeling of the ELT must match the aircraft it is • FLYBUDDY, 2001 NMS
installed in. The product label will have to be re-marked to reflect the new
programming and/or country of registry if a 24-Bit address long message protocol TRIMBLE NAV INC.:
ELT is reprogrammed . • NAV 1000, NAV 2000, TNL 2100, and TNL3100. The following Trimble systems
Re-registration may not be required if the contact information does not change, all require a RS-422 to RS-232 adapter: NAV 3000, TNL 1000, TNL 2000, TNL
however, contact your local civil aviation or beacon registration authority when in 2000A, TNL 3000, 2000 APPROACH, 2000 APPROACH PLUS, 2101
doubt. APPROACH, 2101 APPROACH PLUS, 2101 I/O APPROACH, 2101 I/O
Both serialized long message and 24-Bit address long message, re-programmed APPROACH PLUS.
ELT, that is moved to another aircraft, shall need to be re-registered via On line
or via Post mail. For other equipment models contact that equipment manufacturer to determine if their
equipment supports the Aviation RS-232 format specified above.
The user must specify 24-bit long message programming when ordering the ELT.
Changing the programming protocol of the ELT can only be done at Ameri-King or 3.1.10.3 ELT/FMC Interface and Checkout Process
an authorized Ameri-King Repair Station.
All installation processes and interconnections to navigation systems should adhere to
3.1.10.2. ELT/GPS Interface Communication Formats the guidelines set forth in the FAA Advisory Circulars AC43.13-1A, 43.13-2A,20-
130A and 20-138, or later revisions of these documents. It is very important that the
The only Aviation RS-232 format which is supported is limited to the following Global Positioning System/Flight Management Computer (GPS/FMC) manufacturer's
conditions: installation instructions be consulted regarding installation details that may be specific
to the GPS/FMC. Refer to the installation instructions specific to the GPS/FMC that
Baud Rate (fixed): 9600 you are connecting the ELT for specific instructions.
Parity: None For all testing of the 406 MHz output, only the "test message" that is transmitted at
Data Bits: 8 turn off is required to verify the ELT and ELT/GPS Interface function.
Stop Bits: 1
Note: It is extremely important that the ELT/GPS Interface installation not be in
In addition the RS-232 format must have a Start of Text (STX): an "A" identifier for conflict with the GPS/FMC manufacturer's installation instructions in order to avoid
latitude; a "B" identifier for longitude and END of Text (ETX). The format expects an installation that may degrade the GPS/FMC performance. As a result, the Post
carriage returns but will not operate if there are line feeds. Installation checkout in the GPS/
FMC Installation Manual may be followed after installing the ELT.

31 32
3.1.10.4 24-Bit Address Installation Test (mandatory for Installations
reprogramming by Ameri-King’s authorized dealer):

Verify the 24 Bit Address by using the ELT Computer Test Set TS-451. The 15 digit
hex code shall be extracted by using the Computer Test Set or equivalent. Realize that
the AK-451 transmits a 406 MHz test message, which is encoded such that it will be
ignored by the SAR satellite system. This 15-digit number is used to register the ELT
with the appropriate 406 MHz ELT registration authority. In the US, the National
Oceanic and Atmospheric Administration (NOAA) maintains the database of
registered ELT's.

Note: Although a typical 15 digit hex code can contain position data, the 15-digit
ID used for registration purposes shall contain the "default' value of no position
data instead (this is indicated by the last 5 digits of the 15 digit hex code being
"FFBFF").

3.1.10.5 GPS Position Test, (if equipped)

(for using TS-451 Computer Test Set only) :

This test must be conducted inside a RF shielded room or an ELT RF shielded box.
Connect the AK-451 with ELT Computer Test Set TS-451.

Turn the switch of the ELT to “ON” position.

Verify the following setting (See Figure 20.) From the Hyper Terminal window (or
the equivalent RS-232 window), Click File -> Properties -> Settings tab. Click OK to
go back to Hyper Terminal window.
Figure 8: Verify parameter setting.

Waiting for 50s, verify the 36 Hex digits (ignore first 6 digits). The last 30 Hex digits
will be used for Cospas-Sarsat Decode program, in order to see the Latitude,
Longitude Position.

Note:
When used with ELT's that are programmed for Standard Location 24 bit protocol,
the ELT to be program itself to the aircraft's 24 bit address. This feature will allow
the ELT to be transferred between aircraft. Re-register the ELT with the Search and
Rescue authority is required. This makes maintenance of the ELT a simple matter of
replacing the ELT. Note: There is no electronic connection between TCAS or Mode S
systems and the ELT, only the ID number is common.

33 34
3.2 PERIODIC MAINTENANCE (INSTRUCTION FOR CONTINUED PERIODIC MAINTENANCE (at least every year)
AIRWORTHINESS FOR CANADIAN INSTALLATION: Note:
* These tests should be performed only within an RF Screen Room or Facility
REFERENCES: providing shielding of RF Emissions.
* Using of ELT Test set TS-451 or equivalent test equipment is acceptable
Canadian Aviation Regulations CAR Standards: Part V – Airworthiness
Manual AWM 571: Appendix G. 3.2.1 Regular Periodic Maintenance Test

PURPOSE: Perform Periodic Maintenance Test per paragraph 3.1 above, including all Test
paragraphs 3.1.1 through 3.1.10.
Instructions for continued airworthiness, which shall include as a minimum, details of
approved batteries and sources of supply; battery replacement or recharge In addition to the Periodic Maintenance requirements prescribed in Paragraph 3.1, the
instructions; battery capacity test procedures, if applicable; transmission or functional following Performance Testing must be performed, at least every year, to comply
test procedures; procedures necessary to accomplish the performance tests specified with Canadian Aviation Regulations CAR Standards: Part V – Airworthiness Manual
in Chapter 571 Appendix G ; and for 406 MHz ELTs, instructions to verify the 571: Appendix G.
aircraft 24 bit address or serialized protocol as applicable;
3.2.2 Power Output Test, Performance Testing
Appendix G
NOTE: Using of ELT Test set TS-451 or equivalent test equipment is acceptable
(a) Corrosion Inspection
(b) Operational Testing 3.2.2.1 121.5/243.0 MHz Power Output:
(c) Performance Testing
(d) Battery Replacement and Recharging Connect the equipment as shown below:
(e) Shipping
ELT BNC Applicable Spectrum
IMPORTANT NOTES:
The ELT must be “performance tested within the 12 month period preceding
(top) attenuator Analyzer
installation in an Aircraft and within 12 months intervals thereafter…” Connector

The following Supplemental Installation and Periodic Maintenance Note:

requirements must be complied with, when installing the Model AK-451 ELT in Use as fresh battery pack (12.5 ± 0.5 VDC nominal) or a 2 amp, 12.5 VDC power
Canadian Aircraft: supply as power source.

SUPPLEMENTAL INSTALLATION The test equipment specified in the following steps is only a recommendation. The
use of other manufacturer's models of test equipment capable of providing equivalent
Installation and maintenance of the ELT must comply with Transport Canada measurement results is acceptable.
Airworthiness Manual Chapter AWM 551.104 (f)(4) Transmitter Remote Control
Set the Spectrum Analyzer as follows:
A Placard shall be fabricated and installed near the Remote Unit which states: • Center freq: 121.5 MHz
• Span: 1 MHz
FOR AVIATION EMERGENCY USE ONLY UNAUTHORIZED • Resolution bandwidth: 1 MHz
OPERATION PROHIBITED • Vertical display: 10dB/Div
• Sweep: Auto
• Peak/Avg: Peak
• Reference level: 30 dBm
• Time/Div: 20ms
35 36
Adjust the reference amplitude to place the peak of the carrier slightly above the top 3.2.3 Frequency Test / Current Draw Test, Performance Testing:
graticule fine.
Enable the "fine" amplitude adjustment. Set the carrier peak to exactly the top of the NOTE: Using of ELT Test set TS-451 or equivalent test equipment is acceptable
reference line.
Read the displayed amplitude. The ELT Transmitter frequency may be measured as follows:

Repeat for the 243.0 MHz harmonic (change the "Center Frequency" to 243.0 MHz. 3.2.3.1 Connect the Frequency Counter as shown below:
All other settings remain the same).

The minimum allowed amplitude on 121.5 MHz and 243.0 MHz is 20 dBm, after 3
minutes of operation.

3.2.2.2 406.028 MHz Power Output:

Note:
The power output is approximately (35 – 39) dBm. Ensure adequate attenuation is
inserted in-line between the ELT's 406.028 MHz output and the input to the spectrum 3.2.3.2 Measure the 121.5 / 243.0 MHz frequency:
analyzer to protect the analyzer's input circuitry.
Select the Notch filter as appropriate, i.e. 243 notch when measuring 121.5 MHz.
Connect the equipment as shown below: The ELT should be within 50ppm (± 6.075 KHz) of 121,500,000 Hz.

Repeat with the 121.5 MHz Notch Filter. The ELT frequency should be within 50
ELT BNC Applicable Spectrum ppm (± 12.150 KHz) of 243,000,000 Hz, after 3 minutes of operation.
Connector attenuator Analyzer
3.2.3.3 Measure the 406.028 MHz frequency:

Set the Spectrum Analyzer as follows: Ensure that adequate attenuation rated for 406.028 MHz, 37 dBm and 5 Watts is
• Center freq: 406.028 MHz installed between the ELT's 406.028 MHz output and the input to the frequency
• Span: 1 MHz counter to prevent damaging the frequency counter's input circuitry.
• Resolution bandwidth: 1 MHz
• Vertical display: 10dB/Div Set up the equipment as shown below:
• Sweep: Auto
• Peak/Avg: Peak ELT BNC Applicable Spectrum
• Reference level: 30 dBm
Connector attenuator Analyzer
• Time/Div: 20ms
• Max hold: On
• Attenuator (as required) on Input
Verify an initial frequency of 406.028 MHz +/- 1 KHz, after 3 minutes of operation.
Turn the ELT on and wait approximately 50 seconds for the 406.028 MHz transmitter
to turn on (transmitter sends out first signal at 50 seconds then every 50 seconds
Note:
thereafter). Determine the power output from the stored waveform. Allow the unit to run 3 minutes, before making the measurement to allow the
oscillator to stabilize.
The 406.028 MHz power output should be (35-39) dBm (3.16 W min to 7.94 W
max), after 3 minutes of operation.

37 38
 3.2.3.4 Current draw tests: 3.2.4 AUDIO MODULATION, PERFORMANCE TESTING:

CAUTION: The following tests involve measurement of the lithium battery pack. Perform the transmitter tests by activating the ELT and listening on 121.5 MHz.
Exercise extreme caution to avoid causing a short circuit condition which will blow The audio swept tone should “sound” like an ELT.
the fuse in the battery cell. It is recommended that only an experience technician
perform these tests.
3.2.5 TRANSMITTER FUNCTIONAL TEST:
A test harness (P/N TS-451-HN-1) may be ordered from Ameri-King Corp. at 714-
842-8555 Perform Transmitter Functional Test per paragraph 2.3 above, including all Test
paragraphs 2.3.1 through 2.3.4.
All tests must be performed in an RF screen room or with the ELT in a shielded
container that will substantially attenuate the RF signal. Note: All ELT “ON” tests should be performed within the first five minutes of the
hour.
All "ON" state current measurements must be made with the RF outputs loaded with
50 ohms rated for 5 watts (either a resistive load or equipment with 50 ohm 3.2.6 PERFORMANCE TEST MARKING AND LOG BOOK ENTRY:
impedance padded with 10 dB / 5 Watt attenuator, i.e. a spectrum analyzer).
Following satisfactory completion of all of the above Performance Testing, the date
NOTE: the ELT may activate (turn "ON") when the various connections are initially on which the test was performed shall be marked on the external casing in a legible
made during the following current tests. This is normal. Press the RESET Switch, to and permanent manner.
Reset the unit.
Enter the test date and Technician Initials, as ELT Pass or Fail, into the aircraft Log
"OFF" Mode Current Measurement: Book.
• Remove the battery pack as described in Section 2.5.1
• Disconnect the 2-pin harness
3.2.7 SHIPPING:
• Install the test harness P/N TS-451-HN-1 and inline ammeter as shown in Figure 4-2
• Ensure the ELT is "OFF"
In order to prevent accidental activation of the ELT during transit, the ELT
• Measure the current with the ammeter. The measured current should be 0 microamps
ON/OFF/ARM Main Switch must be set in the “OFF” position.
(uA).
Note: The ON/OFF/ARM Switch is lever locked type.
"ARM" Mode Current Measurement:
• Measure the current with the ammeter. The measured current should be not more than
20 uA.

"ON" Mode Current Measurement:

Note:
Current draw during this test may exceed 2.0 Amps during the 406.028 MHz burst.
Ensure the ammeter is set on the appropriate range to accommodate this level of
current.
• Activate the ELT, allow to stabilize, by select ON.
• The measured steady state current should not exceed 150 milliamps (mA).
When the 406.028 MHz module is on (generating the 406.028 MHz burst)
the current may exceed 2.0 amps.
• Turn the ELT OFF
• Disconnect the test harness P/N TS-451-HN1
• Reconnect the 2-pin module power harness
• Reinstall the battery pack as described in Section 4.3.4
39 40
 PERIODIC MAINTENANCE CHECK LIST FAR 91.207(d); 91.409 and 43
Appendix D.
WITH COMPLIANCE CROSS REFERENCES
In the United States, minimum maintenance requirements for ELTs are stated in FAR Transport Canada Civil Aviation
91.207 paragraph (d): Each emergency locator transmitter required by paragraph (a) Part V Airworthiness Standards
of this section must be inspected within 12 calendar months after the last inspection Chapter 551.104 (d) (1) (VI)
Inspections are also to take place annually per FAR Part 91.409. FAR 43, Appendix 1.4.1 ELT Main
D(i) states in part that each person performing an annual or 100-hour inspection shall Battery replacement or recharge Battery Replacement … …
inspect the components of the ELT. instructions instructions

In Canada, The periodicity of operational checks is at the operator's discretion, but the (Checks are to be performed every 1.4.2 ELT Remote
check shall only be conducted during the first five minutes of any UTC. year) Unit Battery Replacement … …
instructions
NOTE 1: All references to maintenance requirements for the United States shall also
apply to all ELT users outside of the US unless otherwise required by the installer / 3.1.4 Expiration Date … …
aircraft maintenance procedures or the relevant national regulations. Check
NOTE 2: Ameri-King suggests Functional Testing of the ELT every 1 to 2 months. Note: The Batteries for
WARNING : Do not allow test duration to exceed 5 seconds. A false alarm may both Main ELT Unit and
be generated. Remote Switch Unit are
Any time the ELT is activated, it is transmitting a 121.5 MHz and 243.0 MHz distress not rechargeable
signal. If the ELT operates for approximately 50 seconds, a “live” 406 MHz distress
signal is transmitted and is considered valid by the Cospas-Sarsat satellite system.
Any time that the ELT Main Switch is lifted and flipped from “OFF” to “ARM”, a
406 MHz self test signal is transmitted (after 25 seconds), however it is specially
coded as a “self test” signal that is ignored by the COSPAS-SARSAT satellites.

TEST
TEST PROCEDURE
REQUIREMENTS RESULT
Paragraphs
PASS FAIL
FAR 91.207(d); 91.409 and 43
Appendix D.

Transport Canada Civil Aviation

Part V Airworthiness Standards
Chapter 551.104 (d) (1) (VI)
Approved Batteries: … …
Details of approved batteries and Main ELT Unit: Ameri-
sources of supply King P/N 4500010 -1
Remote Switch Unit:
(Checks are to be performed every Duracell DL1/3NB
year)
Source of Supply: … …
Ameri-King

41 42
FAR 91.207(d); 91.409 and 43 (B) Operational Testing 3.1.6 Operational Test … …
Appendix D.
Transport Canada Civil Aviation The periodicity of operational checks 3.1.7.1 G-Switch Check … …
Part V Airworthiness Standards is at the operator's discretion, but the
Chapter 551.104 (d) (1) (VI) check shall only be conducted during 3.1.7.2 Antenna Check … …
the first five minutes of any UTC.
Battery capacity test procedures 1.4.1 ELT Main Battery 3.1.8* Verification of Digital … …
These test procedures are
(Tests are to be performed every Replacement instructions, … … Message
recommended by Ameri-King to be
year) Step 2, Battery Voltage Test.
performed every
3.1.9 Verification of
(1-2) months … …
FAR 91.207(d); 91.409 and 43 Registration
Appendix D.
Transport Canada Civil Aviation 3.1.10* Verification of
Part V Airworthiness Standards ELT/GPS interface (if … …
Chapter 551.104 (d) (1) (VI) equipped)
2.3.1 Main Switch … …
Functional Test Procedures ON/OFF/ARM Operation:
These functional test procedures are (C) Performance Testing 3.2.1 Regular Periodic … …
recommended by Ameri-King to be 2.3.2 Transmitter ID … … Maintenance Test
performed every (1-2) months Programming and Self-Test These Tests are required for
Canadian compliance only 3.2.2** Power Output Test
2.3.3 System Integration Test … … (20 +/-3) dBm at
(Tests are to be performed every 121.5 & 243 MHz) … …
2.3.4 Green ON Lights and … … year) (35 +4/-0)dBm at 406.028 MHz)
Buzzer Sound Functions
3.2.3* Frequency Test
2.3.5 Transmitter Functional … … 121.5 MHz ± 6.075 KHz
Test For ELT-(S) only 243 MHz ± 12.150 KHz … …
406.028 MHz +/- 1 KHz
2.3.5.1 Main Switch ON / OFF / … …
SELF TEST Operation 3.2.3.4*** Current Draw Tests … …

2.3.5.2 Transmitter Self-Test … … 3.2.4 Audio Modulation … …

3.2.5 Transmitter Functional … …

FAR 91.207(d); 91.409 and 43 Test
Appendix D.
Procedures Necessary To Accomplish 3.2.6 Performance Test
The Performance Tests Specified In Marking and Log Book Entry … …
Chapter 571 Appendix G
3.1.2 Corrosion Inspection For … …
(A) Corrosion Inspection Coaxial Cable

(Inspections are to be performed 3.1.3 Corrosion Inspection For

every year) Remote Wiring Modular Cable … …

43 44
(D) Battery Replacement And 1.4.1 ELT Main Battery … …
Recharging Replacement Check

(Checks are to be performed every 1.4.2 ELT Remote Unit Battery … …

year) Replacement Check

3.1.4 Expiration Date Check … …

3.1.5 Battery Leakage Check … …

(E) Shipping 3.2.7 Shipping … …

Transport Canada Civil Aviation Part 3.1.8* Verification of … …

V Airworthiness Standards Chapter Digital Message
551.104 (d) (1) (VI)
3.1.10.4* 24-Bit Address … …
Verify the aircraft 24 bit address Maintenance Test

This Test is required for Canadian

compliance only

(Tests are to be performed every year)

* Test Equipment: Test Set TS-451 or equivalent

** Test Equipment: Spectrum Analyzer or equivalent
*** Test Equipment: DC Current Meter or equivalent

45