1、_ SAE Technical Standards Board Rules provide that: “This report is published by SAE to advance the state of technical and engineering sciences. The use of this report is entirely voluntary, and its applicability and suitability for any particular use, including any patent infringement arising there
2、from, is the sole responsibility of the user.” SAE reviews each technical report at least every five years at which time it may be revised, reaffirmed, stabilized, or cancelled. SAE invites your written comments and suggestions. Copyright 2013 SAE International All rights reserved. No part of this p
3、ublication may be reproduced, stored in a retrieval system or transmitted, in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without the prior written permission of SAE. TO PLACE A DOCUMENT ORDER: Tel: 877-606-7323 (inside USA and Canada) Tel: +1 724-776-497
4、0 (outside USA) Fax: 724-776-0790 Email: CustomerServicesae.org SAE WEB ADDRESS: http:/www.sae.org SAE values your input. To provide feedback on this Technical Report, please visit http:/www.sae.org/technical/standards/AIR6232 AEROSPACE INFORMATION REPORT AIR6232 Issued 2013-08 Aircraft Surface Coat
5、ing Interaction with Aircraft Deicing/Anti-Icing Fluids RATIONALE This SAE Aerospace Information Report (AIR) provides a description of screening methods for verifying whether aircraft surface coatings have adverse effects on aircraft deicing/anti-icing fluid performance as published in the holdover
6、 time guidelines. The surface coatings include thin film coatings, typically less than 1 mil (0.0254 mm) thick and sometimes called paint sealants or protectants, as well as bulk coatings that are typically greater than 2 mils (0.0508 mm) thick. Although recommended performance criteria have been ou
7、tlined, ultimately, the interpretation of the test results outlined in this document will be left to the discretion of the aircraft operator. FOREWORD Aircraft operators rely on the use of AMS1424 and/or AMS1428 deicing/anti-icing fluids during winter operations to provide a limited period of protec
8、tion against frozen or freezing precipitation while the aircraft is on the ground. Methods of protection of aircraft surfaces with these fluids are described in ARP4737. The protection time can be estimated using fluid-specific holdover time guidelines that are published by the Federal Aviation Admi
9、nistration (FAA) and Transport Canada (TC). Holdover time values for deicing/anti-icing fluids are derived from standard endurance time testing procedures that are described in ARP5945 and ARP5485. The aerodynamic performance of deicing/anti-icing fluids is evaluated according to the procedure descr
10、ibed in AS5900. Recently, aircraft operators have expressed interest in the use of aftermarket coatings on aircraft surfaces for various purposes, including appearance enhancement, fuel savings, and ice shedding. The coatings may be designed to have hydrophilic or hydrophobic properties, and therefo
11、re, the interaction of these coatings with AMS1424 and/or AMS1428 deicing/anti-icing fluids and their associated holdover times is unclear. Since aircraft coatings may affect fluid wetting capability and resulting fluid thickness, they could affect a fluids holdover time protection. Therefore, the i
12、nteraction of aircraft surface coatings and aircraft deicing/anti-icing fluids should be evaluated with respect to holdover time performance and aerodynamic performance. In addition, test methods are available to help characterize the various aircraft surface coating properties, including durability
13、, hardness, weathering, effect on aerodynamic drag, ice adhesion, ice accumulation, contact angle, and thermal conductivity. This AIR6232 provides test methods which can serve as screening indicators for compatibility and additional test methods which can be used to characterize the different coatin
14、gs. SAE INTERNATIONAL AIR6232 Page 2 of 18 1. SCOPE This SAE Aerospace Information Report (AIR) provides descriptions of test methods for determining if an aircraft surface coating of any thickness has adverse effects on aircraft deicing/anti-icing fluids with respect to fluid holdover time performa
15、nce and aerodynamic performance. Although not the primary mandate of the G-12 Aircraft Ground Deicing Committee, this document also provides descriptions of suggested test methods for evaluating aircraft surface coatings with respect to durability, hardness, weathering, aerodynamic drag, ice adhesio
16、n, ice accumulation, contact angle, and thermal conductivity. These additional tests can provide informational data for characterizing the coatings and may be useful to operators when evaluating the coatings. 1.1 Purpose To provide a reference method for evaluating the interaction of aircraft surfac
17、e coatings with respect to aircraft deicing/anti-icing fluid holdover time performance and aerodynamic performance. To provide additional informational test methods that can be used for characterizing the aircraft surface coatings. 2. REFERENCES 2.1 Applicable Documents The following publications fo
18、rm a part of this document to the extent specified herein. The latest issue of SAE publications shall apply. The applicable issue of other publications shall be the issue in effect on the date of the purchase order. In the event of conflict between the text of this document and references cited here
19、in, the text of this document takes precedence. Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained. 2.1.1 SAE Publications Available from SAE International, 400 Commonwealth Drive, Warrendale, PA 15096-0001, Tel: 877-606-7323 (
20、inside USA and Canada) or 724-776-4970 (outside USA), www.sae.org. AMS1424 Deicing/Anti-Icing Fluid, Aircraft, SAE Type I AMS1428 Fluid, Aircraft Deicing/Anti-Icing, Non-Newtonian (Pseudoplastic), SAE Types II, III, and IV AMS1650 Polish, Aircraft Metal AMS3095 Paint: High Gloss for Airline Exterior
21、 System AMS-C-83231A Coatings, Polyurethane, Rain Erosion Resistant for Exterior Aircraft and Missile Plastic Parts ARP4737 Aircraft Deicing/Anti-icing Methods ARP5485 Endurance Time Tests for Aircraft Deicing/Anti-icing Fluids, SAE Type II, III, and IV AS5900 Standard Test Method for Aerodynamic Ac
22、ceptance for SAE AMS 1424 and SAE AMS 1428 Aircraft Deicing/Anti-icing Fluids ARP5945 Endurance Time Tests for Aircraft Deicing/Anti-icing Fluids, SAE Type I AIR6130 Cadmium Plate Cyclic Corrosion Test SAE INTERNATIONAL AIR6232 Page 3 of 18 2.1.2 FAA Publications Available from Federal Aviation Admi
23、nistration, 800 Independence Avenue, SW, Washington, DC 20591, Tel: 866-835-5322, www.faa.gov. Official FAA Holdover Time Tables Winter 20XX-20XX. (New document published for each winter. Always use the latest issue; search for “FAA Holdover Time.”) FAA-Approved Deicing Program Updates, Winter 20XX-
24、20XX. (New document published for each winter. Always use the latest issue; search for “FAA-Approved Deicing Program.”) 2.1.3 Transport Canada Publications Available from Transport Canada, Civil Aviation Directorate, Standards Branch, 330 Sparks Street, Ottawa, Ontario, K1A 0N5, Canada, Tel: 613-990
25、-2309 or 1-866-995-9737, http:/www.tc.gc.ca/eng/civilaviation/standards/commerce-holdovertime-menu-1877.htm. Transport Canada Holdover Time Guidelines Winter 20XX-20XX. (New document published for each winter. Always use the latest issue). Guidelines for Aircraft Ground Icing Operations. TP14052E, A
26、pril 2005. Aircraft Ground De/Anti-Icing Fluid Holdover Time and Endurance Time Testing Program for the 2001-02 Winter. TP13991E, December 2002. 2.1.4 Other Publications Goldhammer, Mark I., and Plendl, Bruce R., “Surface Coatings and Drag Reduction,” AERO magazine, The Boeing Company, edition Q1, 2
27、013. AIMS 09-00-002 Evaluation of Maintenance Materials, Airbus AIP 94, 133109-1 Nonwetting of Impinging Droplets on Textured Surfaces AIP 97, 234102 Frost Formation and Ice Adhesion on Superhydrophobic Surfaces APS 106, 036102 Rapid Deceleration-Driven Wetting Transition during Pendant Drop Deposit
28、ion on Superhydrophobic Surfaces ASTM C518-10 Standard Test Method for Steady-State Thermal Transmission Properties by Means of the Heat Flow Meter Apparatus ASTM D5930-01 Standard Test Method for Thermal Conductivity of Plastics by Means of a Transient Line-Source Technique ASTM E1225-04 Standard T
29、est Method for Thermal Conductivity of Solids by Means of the Guarded-Comparative-Longitudinal Heat Flow Technique ASTM F483 Standard Practice for Total Immersion Corrosion Test for Aircraft Maintenance Chemicals ASTM F484 Standard Test Method for Stress Crazing of Acrylic Plastics in Contact with L
30、iquid or Semi-Liquid Compounds ASTM F502 Standard Test Method for Effects of Cleaning and Chemical Maintenance Materials on Painted Aircraft Surfaces ASTM F519-93 Standard Test Method for Mechanical Hydrogen Embrittlement Evaluation of Plating/Coating Processes and Service Environments SAE INTERNATI
31、ONAL AIR6232 Page 4 of 18 ASTM F1110 Standard Test Method for Sandwich Corrosion Test D6-17487 Evaluation of Airplane Maintenance Materials, Boeing ISO 8301 Thermal insulation - Determination of steady-state thermal resistance and related properties - Heat flow meter apparatus“ ISO 11507 Paints and
32、varnishes - Exposure of coatings to artificial weathering - Exposure to fluorescent UV lamps and water ISO 22007-2:2008 Plastics - Determination of thermal conductivity and thermal diffusivity - Part 2: Transient plane heat source (hot disc) method“ ISO 22007-3:2008 Plastics - Determination of therm
33、al conductivity and thermal diffusivity - Part 3: Temperature wave analysis method“ ISO 22007-4:2008 Plastics - Determination of thermal conductivity and thermal diffusivity - Part 4: Laser flash method 2.2 Definitions and Abbreviations ADVANCING CONTACT ANGLE: The advancing angle is the largest pos
34、sible contact angle attained by the drop during volume addition before the motion of the contact line. Similarly, it is the maximum angle attained by the advancing front on an inclined surface before the motion of the contact line. AERODYNAMIC ACCEPTANCE TEST: A performance test required under 3.2.5
35、 of AMS1428 and defined in AS5900. AIRCRAFT SURFACE COATING: A coating applied to an aircraft surface with properties that may be icephobic, hydrophobic, super-hydrophobic, or hydrophilic. This term as used in the document is not intended to refer to surface finishes that have been qualified by the
36、original equipment manufacturer BOUNDARY LAYER DISPLACEMENT THICKNESS (BLDT): The measured displacement of the air flow over a surface. The increase in BLDT over the flat plate surface caused by the fluid flow-off during the AS5900 aerodynamic acceptance is directly related to loss of lift during ta
37、keoff. BUFFER: The difference between OAT and the freezing point of the fluids used. CASSIE STATE: When the liquid of a drop does not fill the voids in the solid on which it sits and the voids remain filled with air, resulting in a hydrophobic condition, the opposite of Wenzel State. CONTACT ANGLE:
38、The angle, conventionally measured relative to the liquid-air and liquid-sold interfaces, quantifying the wettability of a solid surface by a liquid. CONTACT ANGLE HYSTERESIS: The difference between the advancing and receding contact angles. ENDURANCE TIME: Time that a fluid can endure defined and c
39、ontrolled temperature and precipitation conditions before visual failure. Endurance time tests are defined in ARP5485 and ARP5945. FAA: United States Department of Transportation, Federal Aviation Administration. HOLDOVER TIME (HOT): Starting from the time of initial application of an anti-icing flu
40、id, the time that the fluid is expected to provide protection of an aircraft against freezing or frozen precipitation. HOLDOVER TIME GUIDELINE: A table giving the holdover time for various precipitation conditions and temperatures, with cautions and notes, giving guidance to ground deicing/anti-icin
41、g crews and pilots. The “holdover time guideline” is also often referred to as the “holdover time table.” SAE INTERNATIONAL AIR6232 Page 5 of 18 HYDROPHILIC SURFACE: A surface producing a contact angle of 90 degrees. ICEPHOBIC SURFACE: A surface producing a reduction in ice adhesion. LOWEST ON-WING
42、VISCOSITY (LOWV): Lowest viscosity of a fluid for which the applicable holdover time table can be used. LOWEST OPERATIONAL USE TEMPERATURE (LOUT): The lowest temperature at which a Type I/II/III/IV fluid can be used on an aircraft, generally recognized as the higher of: a. the lowest temperature at
43、which it meets the aerodynamics acceptance test (AS5900) for a given type of aircraft; or b. the freezing point of the fluid plus the freezing point buffer of 7 C for Type II/III/IV fluids, or 10 C for Type I fluids. MAXIMUM ON-WING VISCOSITY (MOWV): Maximum viscosity of a fluid which is still aerod
44、ynamically acceptable. OAT: Outside Air Temperature. RECEDING CONTACT ANGLE: The receding angle is smallest possible angle which can be measured when liquid is removed from the drop. Similarly, it is the minimum angle attained by the receding front on an inclined surface before the motion of the con
45、tact line. ROLL-OFF ANGLE; The tilt angle of a surface relative to horizontal at which the water drop starts to slide on the surface and varies between 0 and 90 degrees. Also called sliding angle. SLIDING ANGLE: The tilt angle at which the water drop starts to slide on the surface and varies between
46、 0 and 90 degrees. Also called roll-off angle. STANDARD ALUMINUM TEST PLATE: Aluminum test plate surface used for endurance time testing of Type I and Type II/III/IV fluids in accordance with ARP5945 and ARP5485. SUPER-HYDROPHOBIC SURFACE: A surface producing a static contact angle of 150 degrees an
47、d a roll-off angle of less than 10 degrees. TREATED SURFACE: A surface that has been treated with an aircraft surface coating of any thickness. UNTREATED SURFACE: A surface in its original condition from the airplane manufacturer, or a surface that has been painted with a coating qualified by the ma
48、nufacturer for use on that surface, that has not been treated with an aircraft surface coating. WENZEL STATE: When the liquid of a drop fills the voids in the solid on which it sits, the opposite of Cassie State. 3. COMPARATIVE FLUID ENDURANCE TIME TESTS Tests should be conducted with AMS1424 Type I
49、 fluids and AMS1428 Type II/III/IV fluids to compare the endurance times of fluids applied to aluminum test plate surfaces treated with the aircraft surface coating to the endurance times of the same fluids applied to an untreated standard aluminum test plate (and as an optional test, a freshly painted aluminum test plate which serves as reference tool). If the coating being tested will typically be applied to painted surfaces, consi
