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Appendix 1 to ETSO-2C517 - Minimum Operational Performance Standard (MOPS) for Automatic Deployable Flight Recorder (ADFR) Systems

Available versions for ERULES-1963177438-18308

ED Decision 2020/011/R found in: CS-ETSO Amdt 17 - European Technical Standard Orders (Oct 2026)

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###### Appendix 1 to ETSO-2C517 – Minimum Operational Performance Standard (MOPS) for Automatic Deployable Flight Recorder (ADFR) Systems

*ED
Decision
2020/011/R*

The
applicable standard is EUROCAE ED-112A, MOPS for Crash Protected
Airborne Recorder Systems, dated September 2013, and shall be
modified as per Table 1 below.

***Table
1 — Modification of EUROCAE ED-112A for ADFR systems***

<table bgcolor="#d9d9d9" cellpadding="7" cellspacing="0">
<col/>
<col/>
<col/>
<tr valign="top">
<td bgcolor="#808080">
Location
</td>
<td bgcolor="#808080">
Initial
			ED-112A text
</td>
<td bgcolor="#808080">
Amending
			text
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-1.1
</td>
<td bgcolor="#d9d9d9">
This
			section details the additional requirements and exceptions that
			are specific to deployable recorders. The requirements specified
			in this section shall be met in addition to the requirements of
			Sections 1 and 2, together with Sections 4 and 5 as applicable,
			and the appropriate recorder specific parts.

A
			deployable recorder is a recording medium housed in a
			crash-protected memory module that is automatically deployed
			(released) from the aircraft at the start of an accident sequence.
			Its characteristics have the objective of enabling it to land at
			low speeds clear of the main aircraft wreckage, or, in the event
			of an over-water accident, its flotation characteristics enable it
			to float on water. Since the recorder is no longer with the
			aircraft it should be equipped with a means to locate it.

This
			type of recorder is attached to the exterior of the airframe, and
			under normal conditions, functions in the same manner as a fixed
			recorder. The Recorder Memory Unit, Beacon Transmitters, Antennas,
			Battery Pack and the survival packaging for these units are all an
			integral part of the Automatic Deployable Package.
The
			deployable Package incorporates flight characteristics that enable
			it to deploy and rapidly establish a flight trajectory that clears
			the airframe.
</td>
<td bgcolor="#d9d9d9">
This
			section details the additional requirements and exceptions that
			are specific to deployable recorders. The requirements specified
			in this section shall be met in addition to the requirements of
			Sections 1 and 2, together with the requirements of Sections 4 and
			5 as applicable, and the appropriate recorder‑specific
			parts. 


A
			deployable recorder is a recording medium housed in a
			crash-protected memory module that is automatically deployed
			(released) from the aircraft at the start of an accident sequence.
			Its characteristics have the objective of enabling it to land at
			low speeds clear of the main aircraft wreckage or, in the event of
			an over-water accident, its flotation characteristics enable it to
			float on water. An ELT is embedded in the deployable recorder to
			permit determination of the location of the point of the end of
			flight, and to locate the recorder.

This
			type of recorder is attached to the exterior of the airframe, and
			under normal conditions, it functions in the same manner as a
			fixed recorder. The recorder memory unit, beacon transmitters,
			antennas, battery pack and the survival packaging for these units
			are all integral parts of the automatic deployable package. 

The
			deployable package incorporates flight characteristics that enable
			it to deploy and rapidly establish a flight trajectory that clears
			the airframe.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-1.2
</td>
<td bgcolor="#d9d9d9">
 

</td>
<td bgcolor="#d9d9d9">
Ignore
			3-1.2
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-1.3
</td>
<td bgcolor="#d9d9d9">
This
			section defines the minimum specification to be met for Deployable
			Recorder Systems. It is applicable to any crash-protected recorder
			that is designed to be deployed, its ancillary equipment and its
			installation in civil aircraft.
</td>
<td bgcolor="#d9d9d9">
This
			section defines the minimum specifications to be met for automatic
			deployable flight recorder systems. It is applicable to any
			crash‑protected recorder that is designed to be deployed
			from a large aeroplane, and to its ancillary equipment.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-1.4
</td>
<td bgcolor="#d9d9d9">
3-1.4
			APPLICATION
Compliance
			with this section will ensure that deployable systems will perform
			their function under the conditions encountered in aircraft
			operations.
</td>
<td bgcolor="#d9d9d9">
Replace
			by the following paragraph:

3-1.4
			DEFINITIONS

The
			following definitions are provided for the terms that are used in
			Section 3.

Activation
			depth: The nominal depth of the hydrostatic sensor at which it
			triggers the deployment of the automatic deployable
			package (3-1.7.2, 3-3.2.10 as defined in this appendix).

ADFR
			 Automatic deployable flight recorder

ADFR
			system The system composed of: 


the
			automatic deployable package; and 


the
			system components installed in the aircraft and that support the
			deployment (the deployment mechanism, sensors except those that
			detect the deformation of the aircraft, etc.) and the recording. 


Automatic
			deployable package The
			part of the system that is deployed, including the crash-protected
			memory module, the ELT (also named radio location beacon in
			ED-112A), its antenna and battery, contained in a floatable
			aerofoil.

Deployment
			case A deployment condition as defined in Appendix 2 to this
			ETSO.

Deployment
			time The time from a positive indication of a crash until the
			deployable recorder is released (ED-112A 3-1.7 f.).

Immersion
			depth The maximum depth of immersion in salt water at which
			the automatic deployable package has been tested (3-3.2.8).

Release
			point The point of the aircraft fuselage from which the
			automatic deployable package is released.
Tested
			impact speed The speed used in the impact shock test in
			Section 3-3.2.1 as amended by this appendix, which is declared by
			the equipment manufacturer.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-1.5.1
</td>
<td bgcolor="#d9d9d9">
In
			addition to the safety requirements specified in paragraph
			2-1.3.1, the following requirements shall apply to all deployable
			recorders:

a.	The
			exterior of the equipment shall have no sharp edges or projections
			that could damage inflatable survivable equipment or injure
			persons.

b.	The
			overall quantitative probability (per flight hour) of the failure
			event ‘non-commanded deployment’ shall be &lt; 10–7.
			This probability objective addresses such hardware and software
			components, which contribute directly to the deployment event.
</td>
<td bgcolor="#d9d9d9">
In
			addition to the safety requirements specified in Section 2-1.3.1,
			the exterior of the automatic deployable package shall have no
			sharp edges or projections that could damage inflatable survivable
			equipment or injure persons.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-1.5.2
</td>
<td bgcolor="#d9d9d9">
In
			addition to the certification documents specified in paragraph
			2-1.3.4, the following shall be provided.

a.
			Instructions shall be provided for safely removing deployable
			recorders from the aircraft for maintenance purposes.
b.
			The transmission frequency and modulation characteristics of the
			radio location beacon.
</td>
<td bgcolor="#d9d9d9">
In
			addition to the certification documents specified in Section
			2-1.3.4, the following shall be provided:

a.	The
			transmission frequency and modulation characteristics of the radio
			beacon.

b.	Installation
			instructions that contain:

1.	the
			tested impact speed (Impact shock test in Section 3-3.2.1);

2.	the
			deployment time as defined in 3-1.7.f;

3.	the
			distances required for the automatic deployable package to reduce
			its speed to the tested impact speed in the deployment cases as
			defined in Appendix 2 to this ETSO; 


4.	the
			activation depth at which the hydrostatic sensor triggers the
			deployment (3-1.7.2);

5.	the
			immersion depth that the automatic deployable package can
			withstand as tested in 3-3.2.8;

6.	other
			installation constraints ensuring that the automatic deployable
			package is released before the immersion can disable the system;

7.	the
			maximum ice thickness that can be permitted before de-icing action
			is necessary, as determined during the icing test in Table 2 of
			this ETSO;

8.	the
			recommended recorder orientation on the fuselage to ensure the
			performance of the deployment when installed; 


9.	instructions
			for safely removing deployable recorders from the aircraft for
			maintenance purposes;

10.	the
			kinetic energy of the automatic deployable package once deployed
			from a fixed position;

11.	other
			installation constraints.

The
			ADFR system installation manual shall state that the installer
			must verify that:

a.	the
			automatic deployable package is installed so that it may not be
			crushed or penetrated by aircraft parts when deployed and is
			located in an area limiting the exposure to fire before and after
			an accident;

b.	the
			hydrostatic sensor is installed in a fuselage section as close as
			possible as the one of the release mechanism;

c.	the
			installation is likely to result in an impact speed of the
			automatic deployable package that is less than the tested impact
			speed selected for the impact shock test of the crash‑protected
			recording medium (Section 3-3.2.1) for the deployment cases listed
			in Appendix 2 to this ETSO – this may be achieved by comparing
			the distances determined in 3-1.5.2 b. 3. to the distances between
			the release point and the aircraft nose for case 1 and between the
			release point and the lowest part of the fuselage for case 2;

d.	the
			installation minimises the risk that the deployment of the
			automatic deployable package in normal flight conditions affects
			the capability of continued safe flight and landing.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-1.6
</td>
<td bgcolor="#d9d9d9">
Refer
			to ED-112A
</td>
<td bgcolor="#d9d9d9">
Unchanged
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-1.6.1
</td>
<td bgcolor="#d9d9d9">
A
			visual method to alert the cockpit crew when the deployable
			recorder is no longer captive to the aircraft shall be provided.

The
			cockpit crew shall have an unobstructed view of the visual
			indicator when in the normal seated position.
The
			brilliance of any indicator may be adjustable to levels suitable
			for data interpretation under all cockpit ambient light conditions
			ranging from total darkness to reflected sunlight.
</td>
<td bgcolor="#d9d9d9">
The
			ADFR system shall provide a means to inform the flight crew that
			the recorder is no longer captive to the aircraft. 

</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-1.7.a
</td>
<td bgcolor="#d9d9d9">
Refer
			to ED-112A
</td>
<td bgcolor="#d9d9d9">
Unchanged
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-1.7.b
</td>
<td bgcolor="#d9d9d9">
Refer
			to ED-112A
</td>
<td bgcolor="#d9d9d9">
Unchanged
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-1.7.c
</td>
<td bgcolor="#d9d9d9">
Refer
			to ED-112A
</td>
<td bgcolor="#d9d9d9">
Unchanged
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-1.7.d.
</td>
<td bgcolor="#d9d9d9">
Refer
			to ED-112A
</td>
<td bgcolor="#d9d9d9">
Ignore
			3.1.7.d.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-1.7.e.
</td>
<td bgcolor="#d9d9d9">
Refer
			to ED-112A
</td>
<td bgcolor="#d9d9d9">
Ignore
			3.1.7.e.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-1.7.f
</td>
<td bgcolor="#d9d9d9">
Refer
			to ED-112A
</td>
<td bgcolor="#d9d9d9">
Unchanged
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-1.7.g
</td>
<td bgcolor="#d9d9d9">
Refer
			to ED-112A
</td>
<td bgcolor="#d9d9d9">
Unchanged
			

</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-1.7.h
</td>
<td bgcolor="#d9d9d9">
 

</td>
<td bgcolor="#d9d9d9">
h.	There
			shall be no means for manual deployment.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-1.7.i
</td>
<td bgcolor="#d9d9d9">
 

</td>
<td bgcolor="#d9d9d9">
i.	when
			deployed on the ground from a static position, the point of impact
			of the automatic deployable package shall be within 20 metres
			of the deployment mechanism in any direction over a horizontal
			plane one metre below the release point.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-1.7.
</td>
<td bgcolor="#d9d9d9">
The
			design characteristics of a deployable recorder should result in
			the recorder landing clear of the aircraft wreckage. 


The
			unit shall incorporate flight characteristics that enable it to
			rapidly establish a flight trajectory that clears the airframe.
The
			unit shall not be given sufficient initial momentum on deployment
			such that its release could endanger ground support personnel or
			the aircraft itself.
</td>
<td bgcolor="#d9d9d9">
The
			design characteristics of a deployable recorder should result in
			the recorder landing clear of the aircraft wreckage. 


The
			automatic deployable package shall incorporate flight
			characteristics that enable it to rapidly establish a flight
			trajectory that clears the airframe.

When
			the aircraft stands on the ground, the automatic deployable
			package shall not be given sufficient initial momentum on
			deployment such that its release could endanger ground support
			personnel or the aircraft itself.
The
			automatic deployable package shall be shown to satisfy the
			deceleration requirements detailed in Appendix 2 to this ETSO.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-1.7.1
</td>
<td bgcolor="#d9d9d9">
Refer
			to ED-112A
</td>
<td bgcolor="#d9d9d9">
Ignore
			3-1.7.1
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-1.7.2
</td>
<td bgcolor="#d9d9d9">
Sensor(s)
			shall be installed to activate deployment of the recorder at a
			depth of 3 m or more.
</td>
<td bgcolor="#d9d9d9">
The
			ADFR system shall deploy the automatic deployable package when it
			detects an immersion by measuring the water pressure. A pressure
			equivalent to a water activation depth between 1.5 and 2.5 m
			is recommended for the switching threshold of a hydrostatic
			pressure switch.

 


The
			system design shall be such that its progressive immersion does
			not affect the deployment of the automatic deployable package if
			installed as per the installation constraints.

Automatic
			deployment shall take place up to 15 minutes after the loss
			of external electrical power.
The
			installation manual shall contain the identification of all the
			component electronics, power sources, mechanisms and
			interconnecting cables, as well as any caution notes that are
			needed to ensure the activation and deployment of the ADFR system.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-1.8.1
</td>
<td bgcolor="#d9d9d9">
Refer
			to ED-112A
</td>
<td bgcolor="#d9d9d9">
Unchanged
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-1.8.2
</td>
<td bgcolor="#d9d9d9">
All
			deployable recorders shall be equipped with a Class 1 dual
			frequency 406 MHz and 121.5 MHz radio location beacon compliant
			with the requirements of ED-62A instead of the underwater locator
			beacon and its attachment as specified in paragraph 2-1.16.4.

The
			radio locating device shall be attached to the deployable recorder
			such that the aerodynamic properties of the recorder are not
			adversely affected and the risk of damage to, or separation of,
			the locating device is minimised.

In
			addition to meeting the endurance requirements specified by
			ED-62A, the 121.5MHz radio shall operate for an additional 102
			hours for a total minimum operational duration of 150 hours. For
			the operational duration in exceedance of ED-62A (between 48 hours
			and 150 hours of operation), the minimum Equivalent Isotropic
			Radiated Power (EIRP) for the 121.5MHz radio shall be 5mW.
NOTE:
			Other required characteristics of the radio location beacon are
			outside the scope of this MOPS. Reference should be made to the
			applicable equipment standard.
</td>
<td bgcolor="#d9d9d9">
The
			automatic deployable package shall be equipped with an ELT that is
			approved in accordance with ETSO-C126c, type ELT(AD) Class 0 or 1
			with capabilities C (crash resistance), H1 (121.5 MHz homing)
			and be of any generation (capability T.001 or T.018) instead of
			the underwater locator beacon and its attachment as specified in
			Section 2-1.16.4.

The
			ELT shall radiate nominal power levels (as required per
			ETSO-C126c) for any orientation of the deployable package that is
			stable when laid on a flat horizontal surface.

The
			radio locating device shall be attached to the deployable recorder
			such that the aerodynamic properties of the recorder are not
			adversely affected and the risk of damage to, or separation of,
			the locating device is minimised.
In
			addition to meeting the endurance requirements specified by
			ED-62A, the 121.5MHz radio shall operate for an additional 102
			hours for a total minimum operational duration of 150 hours. For
			the operational duration in exceedance of ED-62A (between 48 hours
			and 150 hours of operation), the minimum Equivalent Isotropic
			Radiated Power (EIRP) for the 121.5MHz radio shall be 5 mW.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-1.8.3
</td>
<td bgcolor="#d9d9d9">
Refer
			to ED-112A
</td>
<td bgcolor="#d9d9d9">
Add
			the following text:

If
			the automatic deployable package (ADP) is designed to be installed
			with one side exposed to the exterior of the aircraft and if its
			kinetic energy can reach 44 Joules within 0.5 metre from the
			release point when the aircraft is standing on the ground, that
			side of the ADP shall bear a conspicuous label. 


 

Note:
			This label is intended to provide a visual warning to maintenance
			and servicing crews, as well as to rescue or other personnel at
			the scene of an accident or incident in the event that the ADFR
			has not deployed.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-1.8.4
</td>
<td bgcolor="#d9d9d9">
Refer
			to ED-112A
</td>
<td bgcolor="#d9d9d9">
Unchanged
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-2.1
</td>
<td bgcolor="#d9d9d9">
CHAPTER
			2-3 defines the environmental tests to be performed on the
			recorder system.
Deployable
			recorders shall satisfy the functional requirements as detailed in
			Chapter 4 of the applicable function specific Part(s).
</td>
<td bgcolor="#d9d9d9">
Table
			2 of this ETSO defines the minimum environmental tests to be
			performed on the ADFR system.

During
			each test, an unintended deployment of the ADFR shall be
			considered to indicate that the test has been failed. Unless Table
			2 of this ETSO specifies that the deployment shall be performed
			during the tests, the successful deployment shall be verified
			after submission of the equipment to the test (this may be
			achieved by verifying the successful deployment only once after a
			group of tests has been performed on a single item of equipment).

The
			ADFR system shall satisfy the functional requirements as detailed
			in Chapter 4 of the applicable function-specific part(s).
The
			verification of deployment aspects may be performed using a dummy
			automatic deployable package.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-3.1
</td>
<td bgcolor="#d9d9d9">
Refer
			to ED-112A
</td>
<td bgcolor="#d9d9d9">
Unchanged
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-3.2.1
</td>
<td bgcolor="#d9d9d9">
The
			integrity of the crash-protected recording medium contents and the
			proper operation of the Radio Location Beacon are to be validated
			when subjected to the following impact shock test.

a.	Subject
			the deployable recorder package, to an impact shock applied to the
			most probable landing attitude in the most damage vulnerable
			direction. The shock shall be such a level as to simulate a
			landing velocity of 46.33 m/s (152 ft/s) onto a hard surface such
			as rock, concrete or steel.

NOTE:
			The definitions of ‘landing attitude’ and ‘most
			damage-vulnerable direction’ should not be limited to the three
			primary axes of the recorder.

b.	The
			deployable recorder containing the protected memory module shall
			impact or be impacted by a hard surface (50 mm thick steel plate
			of dimensions greater that the overall dimensions of the recorder)
			at a minimum impact velocity of 46.33 m/s (152 ft/s). Figure 3-3.1
			illustrates an acceptable impact shock test set-up for deployable
			recorders. Figure 3-3.2 illustrates an acceptable method and
			set-up for retrieval of the deployable after impact. The mass of
			the impact plate shall be greater than 10 times the mass of the
			deployable recorder and experience no yield when subjected to the
			impact.

c.	Apart
			from the test sequence specified in paragraph 3-1.8 a iii,
			electronic components external to the crash-protected memory may
			be removed and replaced with representative mass models prior to
			commencing the impact shock test. For test sequence iii, the radio
			location beacon shall be installed and the test carried out on the
			complete recorder.
</td>
<td bgcolor="#d9d9d9">
The
			integrity of the contents of the crash‑protected recording
			medium, the proper operation of the radio beacon and the
			seaworthiness of the automatic deployable package are to be
			validated when subjected to the following impact shock test.

a.	Subject
			the automatic deployable package to an impact shock that is
			applied to the most probable impact attitude in the most
			damage‑vulnerable direction. The shock shall be at such a
			level as to simulate an impact speed of at least 46.33 m/s (152
			ft/s) onto a hard surface such as a rock, concrete or steel.

The
			equipment manufacturer may demonstrate a higher impact speed for
			the crash-protected recording medium (that may be specified by the
			organisation installing the ADFR) and declare it in the
			installation manual and the declaration of design and performance
			(DDP). In this case, the proper operation of the radio beacon and
			the seaworthiness of the automatic deployable package are still
			required to be demonstrated for the impact speed of 46.33 m/s.

NOTE:
			The definitions of ‘impact attitude’ and ‘most
			damage-vulnerable direction’ should not be limited to the three
			primary axes of the recorder.

b.	The
			deployable recorder that contains the protected memory module
			shall impact or be impacted by a hard surface (a 50-mm-thick steel
			plate of dimensions greater than the overall dimensions of the
			recorder) at a minimum impact velocity of 46.33 m/s (or
			higher as declared by the manufacturer). Figure 3-3.1 illustrates
			an acceptable impact shock test set‑up for the automatic
			deployable package. Figure 3-3.2 illustrates an acceptable method
			and set-up for the retrieval of the deployable after impact. The
			mass of the impact plate shall be greater than 10 times the mass
			of the deployable recorder and shall not yield when it is
			subjected to the impact.

c.	Apart
			from the test sequence specified in paragraph 3-1.8.a.iii,
			electronic components that are external to the crash-protected
			memory may be removed and replaced with representative mass models
			prior to commencing the impact shock test. For test sequence iii,
			the radio beacon shall be installed and the test carried out on
			the complete automatic deployable package.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-3.2.2
(except
			note)
</td>
<td bgcolor="#d9d9d9">
Refer
			to ED-112A
</td>
<td bgcolor="#d9d9d9">
Unchanged
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-3.2.2
(note)
</td>
<td bgcolor="#d9d9d9">
NOTE:
			This test methodology is the same as the penetration test
			specified for Emergency Locator Transmitters (ELTs) in ED-62A.
</td>
<td bgcolor="#d9d9d9">
NOTE:
			This test methodology is the same as that for the impact test
			specified for emergency locator transmitters (ELTs) in ED-62B
			Section 4.5.10. Per ETSO-C126c, the ELT(AD)s fitted to the ADFR
			are required to pass the ED-62B impact test described in Section
			4.5.10.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-3.2.3
</td>
<td bgcolor="#d9d9d9">
Refer
			to ED-112A
</td>
<td bgcolor="#d9d9d9">
Add
			the following note to ED-112A Section 3‑3.2.3:
NOTE:
			Per ETSO-C126c, the ELT(AD)s fitted to the ADFR are required to
			pass the static crush test, as described in ED-62B Section 4.5.12.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-3.2.4
</td>
<td bgcolor="#d9d9d9">
Refer
			to ED-112A
</td>
<td bgcolor="#d9d9d9">
Add
			the following note to ED-112A Section 3‑3.2.4:
NOTE:
			Per ETSO-C126c, the ELT(AD)s fitted to the ADFR are required to
			pass the ED-62B Section 4.5.14 fire test.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-3.2.5
</td>
<td bgcolor="#d9d9d9">
Refer
			to ED-112A
</td>
<td bgcolor="#d9d9d9">
Add
			the following note to ED-112A Section 3‑3.2.5:
NOTE:
			Per ETSO-C126c, the ELT(AD)s fitted to the ADFR are required to
			pass the ED-62B Section 4.5.14 fire test.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-3.2.6
</td>
<td bgcolor="#d9d9d9">
Refer
			to ED-112A
</td>
<td bgcolor="#d9d9d9">
Unchanged
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-3.2.7
</td>
<td bgcolor="#d9d9d9">
Refer
			to ED-112A
</td>
<td bgcolor="#d9d9d9">
Unchanged
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-3.2.8
</td>
<td bgcolor="#d9d9d9">
The
			deployable recorder shall be buoyant and, when floating in fresh
			water or salt water, shall be self-righting and sufficiently
			stable to maintain the antenna substantially in its normal
			operating position and to transmit on its 406 MHz and 121.5 MHz
			frequencies. Transmission of the ELT frequencies shall be
			demonstrated by testing in fresh and then salt water and
			confirming the reception of the 406 MHz Alert frequency via COSPAS
			SARSAT Satellite, and the 121.5 MHz homing frequency via a SAR
			Homing receiver. This test shall be performed in water conditions
			that are representative of an open sea state 7 (equivalent to
			Beaufort Scale force 10).
</td>
<td bgcolor="#d9d9d9">
The
			automatic deployable package shall be buoyant and, when floating
			in fresh water or salt water, shall be self-righting and
			sufficiently stable to maintain the antenna substantially in its
			normal operating position, and to transmit on its 406-MHz and
			 
121.5-MHz frequencies.

The
			automatic deployable package shall be immersed at the immersion
			depth for 5 minutes and shall then return to the surface when
			released.
Transmission
			on the ELT frequencies shall then be demonstrated by conducting
			testing in fresh water and confirming the reception of the 406‑MHz
			alert frequency via the COSPAS SARSAT Satellite. The 121.5-MHz
			homing transmission shall be tested in the conditions described in
			ED-62B Section 5.5.6.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-3.2.9
a.
</td>
<td bgcolor="#d9d9d9">
Unless
			it can be shown that the recording medium can withstand the
			conditions associated with deep sea immersion and that it is
			unlikely to be damaged as a consequence of collapse of any
			protective armour, immerse the recorder in sea water at a pressure
			of 60 MPa (equivalent to a depth of 6 000 m (20 000 feet) for a
			period of 30 days.
</td>
<td bgcolor="#d9d9d9">
Ignore
			3-3.2.9.a.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-3.2.9
b.
</td>
<td bgcolor="#d9d9d9">
Unless
			it can be shown that the recording medium and the identification
			required by paragraph 2-1.16.3 are resistant to the corrosive
			effects of sea water, immerse the recorder in sea water at a depth
			of 3 m and nominal temperature of + 25°C for a period of 30 days.
			

</td>
<td bgcolor="#d9d9d9">
Unless
			it can be shown that the recording medium and the identification
			required by Section 2-1.16.3 are resistant to the corrosive
			effects of seawater, immerse the recorder in seawater at a depth
			of 3 m and a nominal temperature of at least + 25.0 °C
			for a period of 90 days.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
3-3.2.10
</td>
<td bgcolor="#d9d9d9">
 

</td>
<td bgcolor="#d9d9d9">
Add
			a section: Water immersion initiation test 


This
			test may be performed on an additional individual ADFR system that
			is not part of the test sequences defined in 3-1.8.1.

The
			geometry of test set-up (orientation, relative position of the
			release mechanism and of the hydrostatic sensor) shall be the
			least favourable one permitted by the installation constraints
			with regard to the risk of being disabled by immersion.

The
			ELT shall be activated and the system deprived of external power
			before the test for the duration defined in Section 3-1.7.2, as
			amended by this Appendix.

Submerge
			it in fresh water at a speed of not less than 1 m per minute.
			Verify that the ADFR deploys when the hydrostatic pressure sensor
			is at a depth of between 1.5 and 2.5 m. 

Perform
			an aliveness test of the ELT as defined in EUROCAE ED-62B Section
			4.3.1.
</td>
</tr>
</table>

***Table
2 — Environmental test for ADFR systems***

<table bgcolor="#d9d9d9" cellpadding="7" cellspacing="0">
<col/>
<col/>
<col/>
<tr valign="top">
<td bgcolor="#808080">
Test
			

</td>
<td bgcolor="#808080">
EUROCAE
			ED-14G/ RTCA DO-160G Section 

</td>
<td bgcolor="#808080">
Minimum
			category/Remarks 

</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
Temperature
			

</td>
<td bgcolor="#d9d9d9">
4.0
			

</td>
<td bgcolor="#d9d9d9">
Category
			to be defined by the manufacturer.
Deployment
			shall be tested at the short-time low and short-time high
			operating temperatures.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
Altitude
			

</td>
<td bgcolor="#d9d9d9">
4.0
			

</td>
<td bgcolor="#d9d9d9">
Category
			to be defined by the manufacturer.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
Temperature
			Variations 

</td>
<td bgcolor="#d9d9d9">
5.0
			

</td>
<td bgcolor="#d9d9d9">
A,
			S1 or S2
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
Humidity
			

</td>
<td bgcolor="#d9d9d9">
6.0
			

</td>
<td bgcolor="#d9d9d9">
C
			for the components and parts of the ADFR system that are exposed
			to the outside air, A for the rest of the system.
Deployment
			shall be tested at the end of exposure period, without draining
			off any condensed moisture.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
Operational
			Shock 

</td>
<td bgcolor="#d9d9d9">
7.0
			

</td>
<td bgcolor="#d9d9d9">
Category
			to be defined by the manufacturer.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
Crash
			Safety Shock 

</td>
<td bgcolor="#d9d9d9">
7.0
			

</td>
<td bgcolor="#d9d9d9">
Category
			to be defined by the manufacturer.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
Vibration
			

</td>
<td bgcolor="#d9d9d9">
8.0
			

</td>
<td bgcolor="#d9d9d9">
R,
			U or U2 and

H
			or Z
A
			deployment shall be performed during the test, at the most
			unfavourable vibration condition (e.g. the resonance frequency).
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
Explosion
			Proofness 

</td>
<td bgcolor="#d9d9d9">
9.0
			

</td>
<td bgcolor="#d9d9d9">
As
			required. 

</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
Waterproofness
			

</td>
<td bgcolor="#d9d9d9">
10.0
			

</td>
<td bgcolor="#d9d9d9">
S
			for the components and parts of the ADFR system that are exposed
			to the outside air, Y for the rest of the system including for the
			water sensor.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
Fluids
			Susceptibility 

</td>
<td bgcolor="#d9d9d9">
11.0
			

</td>
<td bgcolor="#d9d9d9">
F,
			with at least fuel, hydraulic fluids, lubricating oils, de-icing
			fluids and fire extinguishants.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
Sand
			and Dust 

</td>
<td bgcolor="#d9d9d9">
12.0
			

</td>
<td bgcolor="#d9d9d9">
S
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
Fungus
			Resistance 

</td>
<td bgcolor="#d9d9d9">
13.0
			

</td>
<td bgcolor="#d9d9d9">
F
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
Salt
			Spray 

</td>
<td bgcolor="#d9d9d9">
14.0
			

</td>
<td bgcolor="#d9d9d9">
T
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
Magnetic
			Effect 

</td>
<td bgcolor="#d9d9d9">
15.0
			

</td>
<td bgcolor="#d9d9d9">
Category
			to be defined by the manufacturer.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
Power
			Input 

</td>
<td bgcolor="#d9d9d9">
16.0
			

</td>
<td bgcolor="#d9d9d9">
Category
			to be defined by the manufacturer.
A
			deployment shall be performed under the most unfavourable testing
			conditions. The unit under test may encompass only the installed
			components of the ADFR system.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
Voltage
			Spike 

</td>
<td bgcolor="#d9d9d9">
17.0
			

</td>
<td bgcolor="#d9d9d9">
Category
			to be defined by the manufacturer.
The
			unit under test may encompass only the installed components of the
			ADFR system.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
AF
			Conducted Susceptibility 

</td>
<td bgcolor="#d9d9d9">
18.0
			

</td>
<td bgcolor="#d9d9d9">
Category
			to be defined by the manufacturer.

A
			deployment shall be performed during the test under the most
			unfavourable testing conditions.
The
			unit under test may encompass only the installed components of the
			ADFR system.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
Induced
			Signal Susceptibility 

</td>
<td bgcolor="#d9d9d9">
19.0
			

</td>
<td bgcolor="#d9d9d9">
Category
			to be defined by the manufacturer.
A
			deployment shall be performed during the test under the most
			unfavourable testing condition. The unit under test may encompass
			only the installed components of the ADFR system.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
RF
			Susceptibility 

</td>
<td bgcolor="#d9d9d9">
20.0
			

</td>
<td bgcolor="#d9d9d9">
Category
			to be defined by the manufacturer.
A
			deployment shall be performed during the test under the most
			unfavourable testing conditions.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
RF
			Emission 

</td>
<td bgcolor="#d9d9d9">
21.0
			

</td>
<td bgcolor="#d9d9d9">
Category
			to be defined by the manufacturer.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
Lightning-Induced
			Transient Susceptibility 

</td>
<td bgcolor="#d9d9d9">
22.0
			

</td>
<td bgcolor="#d9d9d9">
Category
			to be defined by the manufacturer.
 

</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
Lightning
			Direct Effects 

</td>
<td bgcolor="#d9d9d9">
23.0
			

</td>
<td bgcolor="#d9d9d9">
Category
			to be defined by the manufacturer.
The
			recorder is required to successfully deploy after a direct impact.
			No unintended deployment shall occur, and no part shall detach.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
Icing
			

</td>
<td bgcolor="#d9d9d9">
24.0
			

</td>
<td bgcolor="#d9d9d9">
The
			test shall be performed for Categories B and C. For Category B, 2
			cycles are required. The deployment of the recorder shall be
			tested at the end of first cycle and at the end of the
			low‑temperature phase for the second cycle. For Category C,
			the deployment shall be tested after the required ice thickness
			(as declared by the manufacturer) is met and the temperature is
			stabilised at its lowest value as required by the ED‑14G/DO-160G
			test.
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
Electrostatic
			Discharge 

</td>
<td bgcolor="#d9d9d9">
25.0
			

</td>
<td bgcolor="#d9d9d9">
A
</td>
</tr>
<tr valign="top">
<td bgcolor="#808080">
Fire
</td>
<td bgcolor="#d9d9d9">
26.0
</td>
<td bgcolor="#d9d9d9">
C
			+ ED-112A Sections 3-3.2.4 and 3-3.2.5.
</td>
</tr>
</table>

[Amdt ETSO/16]