Home' RTCA Documents for Review : DO-204B, MOPS Aircraft ELT 406MHZ Contents © EUROCAE, 2018
220.127.116.11 The penetrator shall be dropped onto one surface of the ELT unit from a minimum height of 15
cm above the surface of the ELT unit; at least half of the penetrator shall impact within a 2.5
cm radius of the most vulnerable area of the surface of the ELT unit. (Impact velocity for an
object dropped from 15 cm is approximately 1.7 m s~1).
This procedure shall be repeated on each main surface of the ELT as described in
18.104.22.168 Upon completion of this test the ELT unit shall be operating.
The ELT unit shall meet the specifications of the aliveness test.
ensure that all mechanical devices operate satisfactorily
Antenna shall be shown to withstand a static load equal to 100 times the antenna’s
weight applied at the antenna mounting base along the longitudinal axis of the aircraft.
This strength can be demonstrated by either test or conservative analysis.
The ELT(AD) shall be subjected to an impact shock developed on contact with a hard
(unyielding) surface. The resulting impact velocity shall not be less than 25 m/s. The
ELT unit package shall be oriented in the most vulnerable impact attitude.
Upon completion of this test, the ELT unit shall be operating. The ELT system shall
meet the aliveness test.
This test shall be replaced by the test as described in ED-112A § 3-3.2.1 or ED-155 §
3-4.2.2 for an ELT(AD) installed in an ADFR.
Crush (ELT(AF), (AP), (S), (DT) with crash survivability, (AD)) (SPECIAL)
For an ELT(AD) integrated in ADFR compliant to ED-112A, the beacon should be
submitted to the test specified in ED-112A § 3-3.2.3. The ELT unit and its antenna
shall perform a successful transmission after being submitted to this test.
The ELT unit shall be placed on an unyielding surface and activated. ELT(S) units
need not be activated before this test. A rigid mass shall apply a crushing pressure of
690 kPa (100 psi), not to exceed a total load of 455 Kg (1,001 pd), successively over
each surface specified in FIGURE 4-3, for a period of five minutes. The size of the
mass shall be sufficient to cover each surface area.
Upon completion of this test, all mechanical devices of the ELT shall operate
satisfactorily. The ELT shall meet the aliveness test.
The ELT system, including antenna(s) and antenna cabling shall be subjected to the
following test (remote indicator not included)
Depending on the type of battery provided with the ELT, the possibility of
explosion makes this test potentially hazardous. Appropriate precautions
should be taken.
At the start of the flame test the ELT system shall have been allowed to stabilize in an
ambient room temperature.
The fire source shall be a tray, 1 meter (3.28 ft) square and 100 mm (4 in) deep,
containing water to a depth of 5 cm, (2 in), on which is floated 10 litres (2.64 U.S.
gallons) of Avgas (100 LL).
The Avgas shall be ignited and allowed to burn for 15 (±2) s, before carrying out the
following flame test.
The ELT system components shall be placed in a position directly over the
centre of the fire tray at a height of 1 meter, ±25 mm (39 in ±1 in), above the
b. The ELT system components under test shall remain in the flame for a
minimum period of 15 seconds.
The test shall be conducted in as near as practicable still air conditions.
After removal from the flame, the ELT system components under test shall be allowed
to cool naturally to ambient temperature before being tested.
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