ASTM F3310-18

This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the
Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.
Designation: F3310 −18
Standard Specification for
Non-Essential Ice Detectors for Aircraft
This standard is issued under the fixed designation F3310; the number immediately following the designation indicates the year of
original adoption or, in the case of revision, the year of last revision. A number in parentheses indicates the year of last reapproval. A
superscript epsilon (´) indicates an editorial change since the last revision or reapproval.
1. Scope for use is indicated. In all cases later document revisions are
acceptable if shown to be equivalent to the listed revision, or if
1.1 This specification covers international standards for
otherwise formally accepted by the governing civil aviation
non-essential ice detection system aspects of airworthiness and
authority; earlier revisions are not acceptable.
design for aeroplanes.
2.2 ASTM Standards:
1.2 The term “aeroplane” is utilized in this specification as
F3060 Terminology for Aircraft
it was originally conceived for normal category fixed wing
F3061/F3061M Specification for Systems and Equipment in
aircraft with a certified maximum takeoff weight (MTOW) of
Small Aircraft
19000lborlessandapassengerseatingconfigurationupto19
F3120/F3120M Specification for Ice Protection for General
as defined in the Rules. However, these standards may be more
Aviation Aircraft
broadly applicable and their usage should not be unnecessarily
2.3 Other Standards:
limited.
SAEAS 5498 Issued 2001-10 Minimum Operational Perfor-
1.3 The applicant for a design approval must seek the
mance Specification for Inflight Icing Detection System
individual guidance of their respective CAA body concerning
EUROCAE ED-103A Minimum Operational Performance
the use of this specification as part of a certification plan. For
Specification for Inflight Icing Detection Systems
information on which CAA regulatory bodies have accepted
RTCA DO-160E Environmental Conditions and Test Proce-
this specification (in whole or in part) as a means of compli-
dures for Airborne Equipment
ance to their Small Aircraft Airworthiness regulations (herein-
after referred to as “the Rules”), refer to ASTM F44 webpage
3. Terminology
(www.ASTM.org/COMMITTEE/F44.htm) which includes
3.1 Refer to Terminology F3060.
CAA website links. It is the responsibility of the Applicant to
3.2 Definitions:
validate any applicability beyond that identified in this speci-
fication and request acceptance from the applicable CAA. 3.2.1 FIDS—flight icing detection system.
1.4 This standard does not purport to address all of the 3.2.2 LWC—liquid water content.
safety concerns, if any, associated with its use. It is the
3.2.3 non-essential ice detector—an active or passive ice
responsibility of the user of this standard to establish appro-
detector that does not receive certification credit for its
priate safety, health, and environmental practices and deter-
installation.
mine the applicability of regulatory limitations prior to use.
1.5 This international standard was developed in accor-
4. Applicability
dance with internationally recognized principles on standard-
4.1 Aircraft Level/Category—The installation of a non-
ization established in the Decision on Principles for the
essentialicedetectorislimitedtolevel1,2,3and4Aeroplanes
Development of International Standards, Guides and Recom-
defined in Specification F3061/F3061M and normal, utility,
mendations issued by the World Trade Organization Technical
acrobatic, or commuter category Aeroplanes.
Barriers to Trade (TBT) Committee.
2. Referenced Documents
For referenced ASTM standards, visit the ASTM website, www.astm.org, or
contact ASTM Customer Service at service@astm.org. For Annual Book of ASTM
2.1 Following is a list of external standards referenced
Standards volume information, refer to the standard’s Document Summary page on
throughout this specification; the earliest revision acceptable
the ASTM website.
Available from SAE International (SAE), 400 Commonwealth Dr.,Warrendale,
PA 15096, http://www.sae.org.
1 4
ThisspecificationisunderthejurisdictionofASTMCommitteeF44onGeneral Available from The European Organisation for Civil Aviation Equipment
Aviation Aircraft and is the direct responsibility of Subcommittee F44.10 on (EUROCAE), 9-23 rue Paul Lafargue, “Le Triangle” building, 93200 Saint-Denis,
General. France, https://www.eurocae.net.
Current edition approved April 1, 2018. Published April 2018. DOI: 10.1520/ Available from Radio Technical Commission for Aeronautics (RTCA), 1150
F3310-18. 18th NW, Suite 910, Washington, DC 20036, https://www.rtca.org.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
F3310 − 18
4.2 Existing Ice Detection System—The installation of a 5.3.6 Instructions for Continued Airworthiness—The manu-
Non-essential ice detector as a replacement for or modification factureroftheNon-Essentialicedetectionsystemshallprovide
to an existing Primary or Advisory ice detection system is continued airworthiness procedures necessary to ensure safe
prohibited. and accurate operation (calibration, alignment to aircraft,
maintenance, etc.).
4.3 Aircraft Certification Basis—The aircraft icing certifi-
5.3.7 Anotice advising the installer that the icing indication
cation basis determines which portions of this specification are
must be placed within the pilot’s viewing area, but cannot
applicable for a specific project. The requirements are defined
obstruct the pilot’s view.
in Table 1.
5.3.8 Installation location of markings and placards must be
provided.
5. General Requirements
5.4 User’s Manual—The manufacturer of the non-essential
5.1 Product Identification—Oneofthemajorcomponentsof
ice detection system shall provide a user’s manual that speci-
a non-essential ice detector system shall also be labeled with
fies:
the following information:
5.4.1 The functional operation of the system (including
5.1.1 Serial Number, and
items in Section 6, Functional Requirements).
5.1.2 Manufacturer’s Name.
5.5 ItispermissiblethattheInstallationandUserManualbe
5.2 Operating Conditions—The ice detection system manu-
one document, so long as it clearly delineates the two sections.
facturer shall specify the following limitations for proper
function:
6. Functional Requirements
5.2.1 Voltage operating range (min/max), if applicable,
5.2.2 Electrical load specifications, if applicable, 6.1 Intended Function:
5.2.3 Restrictions regarding the use and application of 6.1.1 The intended function(s) shall be specified, referenc-
deicing fluids with the system, if applicable. ing the FIDS FUNCTIONS defined within SAE AS 5498 or
5.2.4 Aircraft operating range and restrictions regarding: EUROCAE ED-103 Section 3, highlighting the possible de-
Speed, Temperature, altitude. viations and adaptations made for the user.
5.2.5 Environmental icing conditions and restrictions re- 6.1.2 The intended function shall be consistent with any
existing AFM Limitations and Procedures.
garding: Specification F3120/F3120MAtmospheric Icing Con-
ditions section.
6.2 Performance:
6.2.1 Compliance of the function(s) specified in 6.1.1 shall
5.3 Installation Manual—The manufacturer of the non-
essential ice detection system shall provide an installation be demonstrated (taking into account declared deviations and
adaptations) through test conditions of SAE AS 5498 or
manual that specifies the following information so that an
installer can determine appropriate use for an aircraft installa- EUROCAE ED-103, “Minimum Operational Performance
Specification for Inflight Icing Detection Systems.”
tion:
5.3.1 A full description of the intended function(s) of the 6.2.1.1 These characteristics shall be verified by test of a
functionally equivalent system.
system including the possible restrictions / limitations, refer-
encingtheFIDSFUNCTIONSdefinedwithinSAEAS5498or 6.2.1.2 This test need not be representative of any particular
aircraft installation and may be done in a wind tunnel, on an
EUROCAE ED-103A Section 3.
5.3.2 An explicit compliance statement to this specification, aircraft, or other testing method.
5.3.3 The operation limitations (including the items in 5.2,
6.3 Accessibility of Controls—Adjustments not normally
Operating Conditions),
made during flight (for example, setup, calibration, etc.) shall
5.3.4 The environmental conditions (including items in
notbeaccessiblefromthetop-leveluserinterface(thatis,there
Section 7, Environmental Requirements),
mustbeamenuorspecialentrythatrequiresadeliberateaction
5.3.5 Installation and calibration instructions required for
to enter setup mode).
proper operation of all intended functions of the system,
6.4 Software—If the system uses software, it shall function
as described in the system’s user manual. The software
configuration shall be controlled by the manufacturer.
TABLE 1 Aircraft Icing Certification Basis 6.4.1 If the device can have field loadable software, the
revision shall reside on, or in, the product such that a user
...