SAE ARP 4737H-2008 Aircraft Deicing Anti-icing Methods《航空器除冰 防结冰方法》.pdf

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 theref

2、rom, is the sole responsibility of the user.” SAE reviews each technical report at least every five years at which time it may be reaffirmed, revised, or cancelled. SAE invites your written comments and suggestions. Copyright 2008 SAE International All rights reserved. No part of this publication ma

3、y 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: 724-776-4970 (outside USA)

4、Fax: 724-776-0790 Email: CustomerServicesae.org SAE WEB ADDRESS: http:/www.sae.orgARP4737H AEROSPACERECOMMENDEDPRACTICEIssued 1992-10 Revised 2008-07 Superseding ARP4737G Aircraft Deicing/Anti-icing Methods RATIONALEThe purpose of this revision is to include additional recommendations and refine exi

5、sting recommendations from operational experiences gained and advanced deicing technologies implemented since the previous publication. FOREWORDThe purpose of this document is to provide guidelines for the methods and procedures used in performing the maintenance operations and services necessary fo

6、r proper deicing and anti-icing of aircraft on the ground. Exposure to weather conditions, on the ground, that are conducive to ice formation, can cause accumulation of frost, snow, slush, or ice on aircraft surfaces and components that can adversely affect aircraft performance, stability, and contr

7、ol and operation of mechanical devices such as control surfaces, sensors, flaps, and landing gear. If frozen deposits are present, other than those considered in the certification process, the airworthiness of the aircraft may be invalid and no attempt should be made to fly the aircraft until it has

8、 been restored to the clean configuration. Regulations governing aircraft operations in icing conditions shall be followed. Specific rules for aircraft are set forth in United States Federal Aviation Regulations (FAR), Joint Aviation Regulations (JAR), Canadian Air Regulations, and others. Paraphras

9、ed, these rules relate that NO ONE SHOULD DISPATCH OR TAKE OFF AN AIRCRAFT WITH FROZEN DEPOSITS ON COMPONENTS OF THE AIRCRAFT THAT ARE CRITICAL TO SAFE FLIGHT. A critical component is one which could adversely affect the mechanical or aerodynamic function of an aircraft. The intent of these rules is

10、 to ensure that no one attempts to dispatch or operate an aircraft with frozen deposits adhering to any aircraft component critical to safe flight. The ultimate responsibility for the determination that the aircraft is clean and meets airworthiness requirements rests with the pilot in command of the

11、 aircraft. Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-SAE ARP4737H - 2 -TABLE OF CONTENTS 1. SCOPE 41.1 Field of Application 42. APPLICABLE DOCUMENTS 42.1 SAE Publications. 42.2 U.S. Government

12、Publications 53. DEFINITIONS . 53.1 Abbreviations 53.2 Buffer/Freezing Points 53.3 Fluids. 53.4 Methods/Procedures. 63.5 Conditions Conducive to Aircraft Icing on Ground 73.6 Check 83.7 Contamination Check 93.8 Representative Surfaces. 93.9 Cold Soaked Wing 94. TRAINING AND QUALIFICATION 95. FLUID S

13、TORAGE AND HANDLING. 105.1 Storage 105.2 Fluid Transfer Systems . 105.3 Application Equipment 115.4 Special Considerations for SAE Type II, III, and IV Deicing/Anti-icing Fluids 116. METHODS/PROCEDURES 126.1 Deicing 126.2 Anti-icing . 156.3 Limits/Precautions. 166.4 Local Frost Prevention in Cold So

14、aked Wing Areas. 197. GENERAL AIRPLANE REQUIREMENTS AFTER DEICING/ANTI-ICING 207.1 Wings, Tail, and Control Surfaces 207.2 Pitot Heads, Static Ports, Airstream Direction Detector Probes, and Angle of Attack Sensors . 207.3 Engine Inlets . 207.4 Airconditioning Inlets/Exits 207.5 Landing Gear and Lan

15、ding Gear Doors 207.6 Fuel Tank Vents 207.7 Fuselage . 217.8 Flight Control Check . 218. CHECKS . 218.1 Type of Checks Required . 219. PRETAKEOFF CHECK 22Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,

16、-,-SAE ARP4737H - 3 -10. COMMUNICATIONS/PROCEDURES 2210.1 General . 2210.2 Anti-icing Codes 2210.3 Emergency Procedures 2310.4 Aircraft Movement. 2311. HOLDOVER TIME 2312. NOTES 24APPENDIX A 25Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networki

17、ng permitted without license from IHS-,-,-SAE ARP4737H - 4 -1. SCOPE 1.1 Field of Application 1.1.1 This document establishes the minimum requirements for ground based aircraft deicing/anti-icing Methods and procedures to ensure the safe operation of aircraft during icing conditions. This document d

18、oes not specify requirements for particular airplane models. NOTE: Particular airline or aircraft manufacturers published manuals, procedures, or methods supplement the information contained in this document. 1.1.2 Agreements and Contracts This information is recommended as a basis for maintenance o

19、perations and service support agreements. 1.1.3 Safety - Hazardous Materials While the materials, methods, applications, and processes described or referenced in this specification may involve the use of hazardous materials, this specification does not address the hazards which may be involved in su

20、ch use. It is the sole responsibility of the user to ensure familiarity with the safe and proper use of any hazardous materials and processes and to take necessary precautionary measures to ensure the health and safety of all personnel involved. 1.1.4 All guidelines referred to herein are applicable

21、 only in conjunction with the referenced SAE specifications. Specific requirements for airplane model type are not included. Due to aerodynamic and other concerns application of deicing/anti-icing fluids shall be carried out in compliance with engine and aircraft manufacturers requirements. 2. APPLI

22、CABLE DOCUMENTS The following publications form 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 te

23、xt of this document and references cited herein, 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 SAE Publications Available from SAE International, 400 Commonwealth Drive, War

24、rendale, PA 15096-0001, Tel: 877-606-7323 (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 ARP1971 Aircraft Deicing Vehicle -

25、Self-Propelled, Large and Small Capacity ARP5149 Training Program Guidelines for Deicing/Anti-Icing of Aircraft on Ground AS5635 Message Boards (Deicing Facilities) AIR9968 Viscosity Test of Thickened Aircraft Deicing/Anti-Icing Fluids Copyright SAE International Provided by IHS under license with S

26、AENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-SAE ARP4737H - 5 -2.2 U.S. Government Publications Available from DODSSP, Subscription Services Desk, Building 4D, 700 Robbins Avenue, Philadelphia, PA 19111-5094 or from the FAA web site at http:/www.faa.gov.AC 20-

27、117 Hazards Following Ground Deicing and Ground Operations in Conditions Conducive to Aircraft Icing AC 120-60 Ground Deicing and Anti-icing Program AC 150/5300-14 Design of Aircraft Deicing facilities FSAT 00-05 and FSAW 00-02 Approving Infrared Technology for Aircraft Ground De-Icing/Anti-Icing Fa

28、cilities. 3. DEFINITIONS 3.1 Abbreviations C = Celsius F = Fahrenheit OAT = Outside Air Temperature FP = Freezing point h = Hours min = Minutes LOUT = Lowest Operational Use Temperature 3.2 Buffer/Freezing Points The difference between OAT and the freezing point of the fluids used. 3.3 Fluids CAUTIO

29、N: SAE Type I fluids supplied as concentrates for dilution with water prior to use shall not be used undiluted, unless they meet aerodynamic performance and freezing point buffer requirement (reference AMS1424). 3.3.1 Deicing fluids are: a. Heated water b. SAE Type I fluid (see caution) c. Heated co

30、ncentrates or mixtures of water and SAE Type I fluid d. Heated concentrates or mixtures of water and SAE Type II fluid e. Heated concentrates or mixtures of water and SAE Type III fluid f. Heated concentrates or mixtures of water and SAE Type IV fluid Deicing fluid is normally applied heated to assu

31、re maximum deicing efficiency. Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-SAE ARP4737H - 6 -3.3.2 Anti-icing fluids are: a. Heated SAE Type I fluid (see previous caution) b. Heated mixtures of w

32、ater and SAE Type I fluid c. Concentrates or mixtures of SAE Type II fluid and water d. Concentrates or mixtures of SAE Type III fluid and water e. Concentrates or mixtures of SAE Type IV fluid and water NOTE: Temperature of both a. and b. shall be at least 60 C (140 F) at the nozzle. Upper temperat

33、ure limit shall not exceed fluid and aircraft manufacturers recommendations.SAE Type II and IV fluids for anti-icing are normally applied unheated on clean aircraft surfaces but may be applied heated. SAE Type III fluids for anti-icing may be applied heated or unheated on clean aircraft surfaces. 3.

34、3.3 Fluid terms are: a. Newtonian fluids are defined as fluids whose viscosities are shear independent and time independent. The shear rate of a Newtonian fluid is directly proportional to the shear stress. The fluid will begin to move immediately upon application of a stress; it has no yield stress

35、 to overcome before flow begins. NOTE: SAE Type I fluids are considered Newtonian. b. Non-Newtonian fluids are defined as fluids whose viscosities are shear and time dependent and whose shear rate is not directly proportional to its shear stress. The fluid will not begin to move immediately upon app

36、lication of a stress, it has a yield stress to overcome before flow begins. NOTE: SAE Type II, III, or IV fluids containing thickeners demonstrate a pseudoplastic behavior which is defined as a decrease in viscosity with an increase in shear rate. 3.3.3.1 The lowest operational use temperature (LOUT

37、) is the higher (warmer) of1. The lowest temperature at which the fluid meets the aerodynamic acceptance test (according to AS5900) for a given type (high speed or low speed) of aircraftand 2. The freezing point of the fluid plus the freezing point buffer of 10 C for Type I fluid and 7 C for Type II

38、, III or IV fluids.For applicable values refer to the fluid manufacturers documentation.3.4 Methods/Procedures 3.4.1 Deicing is a procedure by which frost, ice, slush, or snow is removed from the aircraft in order to provide clean surfaces.3.4.2 Anti-icing is a procedure, which provides protection a

39、gainst the formation of frost or ice and accumulation of snow or slush on clean surfaces of the aircraft for a limited period of time (holdover time). Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-

40、SAE ARP4737H - 7 -3.4.3 Deicing/anti-icing is a combination of the two procedures described previously. It can be performed in one or two steps.3.4.3.1 One step deicing/anti-icing is carried out with an anti-icing fluid. The fluid used to deice the aircraft remains on aircraft surfaces to provide li

41、mited anti-icing capability. 3.4.3.2 Two step deicing/anti-icing consists of two distinct steps. The first step, deicing, is followed by the second step, anti-icing, as a separate process. Anti-icing fluid is applied to protect the relevant surfaces thus providing maximum possible anti-icing capabil

42、ity. 3.4.4 Holdover time is the estimated time anti-icing fluid will prevent the formation of frozen contamination on the protected surfaces of an aircraft. 3.5 Conditions Conducive to Aircraft Icing on Ground 3.5.1 Frost Ice crystals that form from ice saturated air at temperatures below 0 C (32 F)

43、 by direct sublimation on the ground or other exposed objects. 3.5.2 Freezing Fog A suspension of numerous minute water droplets which freezes upon impact with ground or other exposed objects, generally reducing the horizontal visibility at the earths surface to less than 1 km (5/8 mile). 3.5.3 Snow

44、 Precipitation of ice crystals, most of which are branched, star-shaped, or mixed with unbranched crystals. At temperatures higher than -5 C (23 F), the crystals are generally agglomerated into snowflakes. 3.5.3.1 Snow is defined to include snow grains. Snow grains are precipitation of very small wh

45、ite and opaque particles of ice that are fairly flat or elongated with a diameter of less than 1 mm (0.04 in). When snow grains hit hard ground, they do not bounce or shatter. 3.5.4 Freezing Drizzle Fairly uniform precipitation composed exclusively of fine drops diameter less than 0.5 mm (0.02 in) v

46、ery close together which freezes upon impact with the ground or other exposed objects. 3.5.5 Light Freezing Rain Precipitation of liquid water particles which freeze upon impact with exposed objects, either in the form of drops of more than 0.5 mm (0.02 in) or smaller drops which, in contrast to dri

47、zzle, are widely separated. Measured intensity of liquid water particles are up to 2.5 mm or 25 g/dm2/h (0.10 in/h) with a maximum of 0.25 mm (0.01 in) in 6 min. 3.5.6 Rain or High Humidity (On Cold Soaked Wing) Water forming ice or frost on the wing surface, when the temperature of the aircraft win

48、g surface is at or below 0 C (32 F). 3.5.7 Rain and Snow Precipitation in the form of a mixture of rain and snow. For operation in light “rain and snow” treat as light freezing rain. Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-SAE ARP4737H - 8 -3.5.8 Slush Snow or ice that has been reduced to a soft watery mixture by rain, warm temperature, and/ or chemical treatment. 3.5.9 Ice Crystals/Diamond Dust A fall of unbranched