DLA MIL- DTL-27723 F-2013 PROBE TOTAL TEMPERATURE DEICEABLE.pdf

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1、Comments, suggestions, or questions on this document should be addressed to Defense Supply Center Richmond, ATTN: DLA-Aviation, 8000 Jefferson Davis Highway, Richmond, VA 23297-5616 or e-mailed to STDZNMGTdla.mil. Since contact information can change, you may want to verify the currency of this addr

2、ess information using the ASSIST database at https:/assist.dla.mil. . AMSC N/A FSC 6685 MIL- DTL-27723F 16 Jul 2013 SUPERSEDING MIL- P-27723E 15 March 1985 MILITARY SPECIFICATION PROBE, TOTAL TEMPERATURE, DEICEABLE This specification is approved for use by all Departments and Agencies of the Departm

3、ent of Defense. 1. SCOPE 1.1 Scope. This document covers the requirements for total temperature probes capable of operating during atmospheric icing conditions. 1.2 Classification. The total temperature probes will be of the following types (see 6.2). Type I - Single element Type II - Dual element I

4、nactive for new design after 24 March 1999. INCH-POUND Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-27723F 2 1.3 Part or identifying number (PIN). The PIN for total temperature probes is formed as shown. The former MS27188 number is retain

5、ed for continuity. 2. APPLICABLE DOCUMENTS 2.1 General. The documents listed in this section are specified in sections 3 and 4 of this specification. This section does not include documents cited in other sections of this specification or recommended for additional information or as examples. While

6、every effort has been made to ensure the completeness of this list, document users are cautioned that they must meet all specified requirements of the documents cited in sections 3 and 4 of this specification, whether or not they are listed. 2.2 Government documents. 2.2.1 Standards and handbooks. T

7、he following standards and handbooks form a part of this document to the extent specified herein. Unless otherwise specified, the issues of these documents are those cited in the solicitation or contract. DEPARTMENT OF DEFENSE SPECIFICATIONS MS33678 - Connector, Receptacle, Electric, Integral Mounti

8、ng DEPARTMENT OF DEFENSE STANDARDS MIL-STD-130 - Identification Marking of U.S. Military Property MIL-STD-464 - Electromagnetic Environmental Effects Requirements for Systems MIL-STD-810 - Environmental Engineering Considerations and Laboratory Tests MIL-STD-889 - Dissimilar Metals MIL-STD-31000 - T

9、echnical Data Packages DEPARTMENT OF DEFENSE HANDBOOKS MIL-HDBK-831 - Preparation of Test Reports (Copies of these documents are available online at https:/assist.dla.mil or from the Standardization Document Order Desk, 700 Robbins Avenue, Building 4D, Philadelphia, PA 19111-5094.) MS 27188 - X Form

10、er MS sheet number Prefix for military specification 1 = Type I - Single element 2 = Type II - Dual element Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-27723F 3 2.3 Non-government publications. The following documents form a part of this

11、document to the extent specified herein. Unless otherwise specified, the issues of these documents are those cited in the solicitation or contract. SAE INTERNATIONAL SAE-AS31061 - Connector, Plug, Electric, Straight, Solder Contacts, AN Type SAE-AS31071 - Connector Plug, Electric, Quick Disconnect S

12、AE-AS-31081 - Connectors, Plug, Electric, Solder Contact, 90 Degree, AN Type (Copies of these documents are available online at http:/www.sae.org/servlets/index or from SAE, Inc., 400 Commonwealth Drive, Warrendale PA 15096.) AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA NASM24694 - Screw, Machine, Fl

13、at Countersunk Head, 100 Deg., Structural, Cross Recessed, UNC-3A and UNF-3A (Copies of this document are available online at www.aia-aerospace.org/or from Aerospace Industries Association of America, 1250 I St. NW, Suite 1100, Washington, DC 20005) 2.4 Order of precedence. Unless otherwise noted he

14、rein or in the contract, in the event of a conflict between the text of this document and the reference cited herein (expect for related specification sheets), the text of this document takes precedence. Nothing in this document, however, supersedes applicable laws and regulations unless a specific

15、exemption has been obtained. 3. REQUIREMENTS 3.1 First article. When specified, a sample shall be subjected to a first article inspection (see 4.3 and 6.2). 3.2 Specification sheets. The individual item requirements shall be as specified herein and in accordance with the applicable specification she

16、et. In the event of any conflict between the requirements of this specification and the specification sheet, the latter shall govern. 3.3 Recycled, recovered, or environmentally preferable materials. Recycled, recovered, or environmentally preferable materials should be used to the maximum extent po

17、ssible, provided that the material meets or exceeds the operational and maintenance requirements, and promotes economically advantageous life cycle costs. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-27723F 4 3.4 Materials. 3.4.1 Nonmagnet

18、ic materials. Nonmagnetic materials shall be used for all parts except where magnetic materials are essential. 3.4.2 Fungus resistant material. Materials that are nutrients for fungi shall not be used where it is practical to avoid them. Where used and not hermetically sealed, they shall be treated

19、with a fungicidal agent acceptable to the procuring activity. 3.4.3 Corrosive Fumes. The materials, as installed in the probe and under the service conditions specified herein, shall not liberate toxic, harmful or corrosive fumes. 3.4.4 Metals. Metals shall be of a corrosion-resistant type or suitab

20、ly treated to resist corrosion due to fuels, salt fog, or atmospheric conditions likely to be found in storage or normal service. 3.4.4.1 Dissimilar metals. Unless suitably protected against electrolytic corrosion, dissimilar metals shall not be used in intimate contact with each other. Dissimilar m

21、etals are defined in MIL-STD-889. 3.4.5 Protective treatment. When materials are used in the construction of the probe that are subject to deterioration when exposed to climatic and environmental conditions likely to occur during service usage, they shall be protected against such deterioration in a

22、 manner that shall in no way prevent compliance with the performance requirements of this specification. The use of any protective coating that may crack, chip, or scale with age or with extreme climatic or environmental conditions shall be avoided. 3.5 Design and construction. 3.5.1 Design. The des

23、ign of the probe shall conform to figures 1 and 2 and shall include a resistance element, air scoop, strut, mounting flange, electrical connector, and heaters necessary to prevent the formation of ice. The design details shall in no way constitute a waiver from the performance requirements specified

24、 herein. 3.5.1.1 Temperature compensation. The deicing heater element shall be automatically regulated in such a manner that the power dissipated through the heater will be an inverse function of the heater element temperature. Provided by IHSNot for ResaleNo reproduction or networking permitted wit

25、hout license from IHS-,-,-MIL-DTL-27723F 5 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-27723F 6 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-27723F 7 3.5.2 Construction. 3.5.2.1

26、 Temperature resistance relationship. The temperature sensing element shall be constructed of pure platinum wire and the temperature versus resistance relationship shall be accordance with the Callendar-Van Dusen equation: Where: RT= resistance at temperature T in C R0= resistance at 0C = 0.003925 =

27、 1.45 = 0.0 (for temperatures above 0C) = 0.10 (for temperatures below 0C) T = temperature in C The resistance of the temperature-sensing element shall be adjusted to 50.00 ohms at 0C. Deviations from the Callendar-Van Duse equation over the temperature range of the probe shall be no greater than al

28、lowed by the following equation: T = (0.25 + 0.005T) Where: T = temperature in C T = allowable deviation in C When T is below 0C, the absolute value in C shall be used in this equation. 3.5.2.2 Hermetic Sealing. The temperature-sensing and deicing elements shall be hermetically sealed. 3.6 Performan

29、ce. The probe shall be capable of meeting the requirements specified herein under the following conditions a. Temperature temperatures ranging from -70C to +350C. b. Humidity relative humidity up to 100 percent. c. Vibration vibration in accordance with MIL-STD-810, method 514, operational condition

30、s for fixed wing jet aircraft. d. Thermal shock cycling at temperatures ranging from 0C 5C to 2005C alternately for 30 minute periods. e. Temperature resistance measurable resistance over the range of 0C to the boiling point of water. f. Insulation satisfactory electrical resistance measurements of

31、the temperature-sensing element after being submerged in water for a period of 8 hours. g. Salt fog simulated sea salt atmosphere. h. Fungus fungus as encountered in tropical climates. i. Sand and dust sand and dust particles as encountered in desert areas. Provided by IHSNot for ResaleNo reproducti

32、on or networking permitted without license from IHS-,-,-MIL-DTL-27723F 8 3.6.1 Insulation resistance of temperature-sensing element. The temperature-sensing element shall have an insulation resistance greater than 10 megohm (M). 3.6.2 Thermal response. When subjected to an internal airflow of mach 0

33、.3 at sea level, the time constant shall not exceed 1.5 seconds. 3.6.3 Reactance. The impedance of the temperature-sensing element shall not vary more than 0.04 ohm at any frequency from 0 to 2,000 cycles per second (cps) when tested for inductive or capacitive reactance effect. 3.6.4 Self-heating.

34、A current of 50 milliamperes (ma) in the sensing element shall not change the resistance more than 3C at sea level with an internal airflow of mach 0.3. 3.6.5 Static loading. The probe shall withstand static impact pressure up to mach 2.0. 3.6.6 Deicing and anti-icing. With the heater operating at r

35、ated voltage, accumulated ice shall be removed from the inlet in less than 2 minutes and ice which would affect the temperature indicator shall not re-form for a continuous period of 15 minutes when the probe is subjected to a wind tunnel speed of 32525 knots at a temperature of -305C with a liquid

36、water content of 1.250.25 grams per cubic meter. 3.6.7 Recovery error. The recovery error shall be no greater than 0.5 percent of the absolute total temperature. 3.6.8 Conduction and radiation errors. Conduction and radiation errors shall not exceed the tolerance specified in Table 1. Table I. Aerod

37、ynamic conditions. 3.6.9 Deicing heater error. The deicing heater element shall not change the indicated temperature of the temperature-sensing element more than 1C when the deicing heater element is operated at rated voltage and the probe is in an internal airflow of mach 0.3 at sea level condition

38、s. Stagnation Pressure mmHg Stagnation Temperature C Allowable error in measured stagnation temp percent 1,000 250 0.5 1,000 350 0.5 100 250 0.5 100 350 0.7 30 250 0.7 30 350 1.0 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-27723F 9 3.6.10

39、 Deicing heater element life. The heater power consumption (see 4.6.10) shall change no more than 10 percent after a deicing heater element life test. No damage shall result that would otherwise affect proper operation of the probe. 3.6.11 Insulation resistance of deicing heater element. The deicing

40、 heater element shall have an insulation resistance greater than 1 megohm when measured with 500V root mean square (rms) 60 hertz current applied. 3.6.12 Still air operation. The probe, while in room temperature air, shall be capable of withstanding the heat caused by the operation of the deicing he

41、ater. 3.6.13 Low temperature exposure and power consumption. After exposure to a temperature of -70C and when power is applied to the heater element, the initial power surge shall not exceed 1,200W. After 5 seconds, the power consumption shall not exceed 700W and after 20 seconds it shall not exceed

42、 500W. 3.6.14 High temperature exposure. After high temperature exposure, the resistance of the temperature-sensing element determined at 0C and at 100C shall not differ by more than the equivalent of 0.2C from the resistance values before high temperature exposure. 3.7 Part numbering and interchang

43、eable parts. All parts having the same manufacturers part number shall be functionally and dimensionally interchangeable. The item identification and part number requirements of MIL-DTL-31000 shall govern the manufacturers part numbers and changes thereto. 3.8 Operating power. The deicing heater ele

44、ment shall operate on 115V, 400 hertz alternating current (AC). 3.8.1 Heater power consumption. The nominal heater power consumption shall be 350W when the heater is operating under in-flight icing conditions with the static temperature ranging from -10 to -35C and an indicated air-speed of from 200

45、 to 350 knots. 3.9 Weight. The weight of the single-element probe shall not exceed 400 grams and the weight of the dual-element probe shall not exceed 500 grams. 3.10 Identification of product. Equipment, assemblies, and parts shall be marked for identification in accordance with MIL-STD-130. 3.11 W

46、orkmanship. The probe shall be constructed and finished paying particular attention to neatness and thoroughness of soldering, wiring, marking of parts and assemblies, plating, welding, brazing, and freedom of parts from burrs and sharp edges. 3.11.1 Cleaning. The probe shall be thoroughly cleaned a

47、nd loose, spattered, or excess solder, metal chips, and other foreign materials shall be removed during and after final assembly. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-DTL-27723F 10 4. VERIFICATION 4.1 Classifications of inspection. The

48、 inspection requirements specified herein shall be as follows: a. First article inspection (see 4.3) b. Acceptance tests (see 4.4) 4.2 Test conditions. Unless otherwise specified, the probe shall be tested in air at standard conditions at room temperature (approximately 25C) and at sea level pressure (approximately 760 mm Hg). 4.2.1 Calibration stability. During the course of the tests, a change in calibration which does not meet the requirements of 3.5.2.1 shall constitute failure. This does not imply compulsory calibration after each te