NAVY MIL-I-21735 A-1969 INDICATOR AIRSPEED AND MACH NUMBER PITOT STATIC 60 TO 650 KNOTS《60至650海里每小时 全压静压飞行速度和马赫数指示器》.pdf

1、MIL-T-Z173SA(AS) 31 JAWJARY 1969 SUPERSEDING 10 December 1958 MIL-1-21735 (AER) MILITARY SPECIFICATION INDICATOR; AIRSPEED AND MACH hWBER, PITOT STATIC, 60 to 650 KNOTS _. This specification has been approved by the Naval Air Systems Command, Department of the Navy. 1. SCOPE 1.1 Scope - The indicato

2、r covered by this specification shall indicate airspeed and Mach number with the indicated airspeed range from 60 to 650 knots, Mach range from O. 4 to 2. O Mach, at altitudes from - 1,000 to 50,000 feet, and as listed on MS28089. 2. APPLICABLE DOCUMENTS 2.1 General - The following documents of the

3、issue in effect on the date of invitation for bids, form a part of this specification to the extent specified herein. SPECIFICATIONS Military MIL-D-1000 /i Drawings, Engineering and Associated Lists MIL-E -5272 Environmental Testing, Aeronautical and Associated Equipment, General Specification for M

4、IL-1-5415 Indicators; Airspeed, Pitot-static Pressure, General Specification for MIL- C-14806 Coating, Reflection Reducing, For Instrument. Cover Glasses and Lighting Wedges Al IL-L-2 546 7 Lighting, Integral, Aircraft hist riitiiciit, Gene ral Specification for / !=- / 7 THIS DOCUMENT CONTAINS 80 P

5、AGES. 0 , , - -. /- IW titi 10 4 t _-_.-7azSE STRAIGHT OSLI“ .n y 11 no mrr BLOW i-c- 7- .- e- ,- -, Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- MIL-I-23735A bb 9797906 0330567 9 MIL- 1-2 17 3 5A (AS) 3.9 Nameplate - Nameplate, as specified in M

6、IL-1-5415, shall be marked: INDICATOR, AIRSPEED AND MACH NUMBER PITOT-STATIC, 60 TO 650 KNOTS MS28089- (add proper dashnumber) MANUFACTURERS KAME OR TRADEMARK AND 8- MANUFACTURERS PART NO. MANUFACTURERS SERLAL NO. CONTRACTORORDERNO. U. S. PROPERTY 4. QUALITY ASSURANCE PROVISIONS 4.1 Responsibility f

7、or inspection - Unless otherwise specified in the contract or purchase order, the supplier is responsible for the performance of all inspection requirements as specified herein. Except as otherwise specified in the contract or order, the supplier may use his own or any other facilities suitable for

8、the performance of the inspection requirements specified herein, unless disapproved by the Government. The Government reserves the right to perform any of the in- spections where such inspections are deemed necessary to assure supplies and services conform to prescribed requirements. 4.2 Classificat

9、ion of Inspection - Inspection of the indicator shall be classified as follows: (a) Qualification inspection: Qualification inspection consists of examinations and tests performed on sample indicators sub- mitted for approval as a qualified product. (b) Quality conformance inspection: Quality confor

10、mance inspec- tion consists of examinations and tests performed on indicators manufactured and submitted for acceptance under contract. 4.3 Qualification inspection - The qualification inspection of the indi- cators shall consist of all of the examinations and tests of this specification performed i

11、n the order specified under the paragraph headed Inspection Methods and shall in- clude the Reliability Qualification Phase Tests. 4.3.1 Qualification Inspection Sample - Qualification inspection samples shall consist of four indicators manufactured in accordance with this specification. The indicat

12、ors submitted or qualification inspection shall have beeii prcviously sub- jectd oiily to the iiidividunl and sampljng plmi A inspectioiis. Two s:iinplcs sli:ill )e otwii*(lc(l wiili siilqlj(!* yuaiiti,ntivo ksi, (hit: :it tlic! siipplicrs oxpcnw (J i li(* IN):I- tory dcuigii:itc?tl iti tlic letter

13、of authorix:,tioii. (Scc U. 4. ) iwo sainples sii:iIl lx+-., Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- MIL-I-23735A bb 9979906 0330570 5 W -. MIL-I-21i3 5A(AS) retained by the supplier for the Reliability Qualification Phase testing which will

14、 be run by the suppIier at his plant. 4.3.1.1 Sample Identification - Each inspection sample shall be plainly identified by an attached durable tag marked with the following information: INDICATOR, AIRSPEED AND MACH NUMBER, PITOT STATIC, 60 TO 650 KNOTS, MS28089 (add proper dash no. ) Submitted (dat

15、e) by (Manufacturers name and part Number) for Sampling Plan B Tests of MIL-I-21735A Authorized by Contract/order No. tests). or (reference letter authorizing - 4.4 Quality Conformance Inspection - The supplier shall furnish ail samples and shall be responsible for accomplishing all the inspections

16、designated by the procuring activity. Quality conformance inspection shall be under the super- vision of the government quality control representative. The supplier shall furnish test reports showing detailed quantitative results for all tests required by this speci- fication, signed by an authorize

17、d representative of the supplier or laboratory as ap- plicable. Acceptance or approval of material during the course of manufacture shall in no case be construed as a guarantee of the acceptance of the finished product. Quality Conformance Inspection shall consist of the following tests of MIL-1-541

18、5 and as specified herein: (a) Individual Tests (b) Sampling Plan A Tests (c) Sampling Plan i3 Tests (d) Reliability Assurance Tests (e) Longevity Tests (f ) Maintainability Demonstration 4.4.1 . Individual Tests - Each indicator submitted for acceptance shall be subjected to and meet the Individual

19、 Test. This test shall determine compliance with the requirements of material, workmanship and operational accuraq. Examination of Product Leakage Scale Error at Room Temperature Hysteresis -After Effect i Friction Error Position Error Pointer Zero Position Error Lighting - InQividual (Lighted Indic

20、ators Only) ./- Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-I-21735A bb 7779706 0130571 7 MIL-I-21735A(AS) ! 4.4.2 Sampling Plans - The Sampling Plans shall consist of Sampling Plan A and Sampling Plan B tests. The tests samples selected for

21、sampling tests shall first have passed the Individual test. The test samples which have been subjected to Sampling A or Reliability test shall not be delivered on contract until thes have been refurbished and resubmitted and passed all the Individual tests. Test samples which have been subjected to

22、the Sampling Plan B or Longevity test shall not be delivered on contract. CZuantity Offered for Acceptance First 15 Next 50 Next 75 Next SOO Quantity to be Selected for Sampling Plan A Tests 1 (Zero when Sampling Plan B is invoked) 1 1 1 Each additional 200 or 1 fraction thereof I When a defective i

23、ndicator is detected, no items from those still on hand or later produced shall be accepted until the extent and cause of failure have been determined and appropriately corrected. in addition, when a failure occurs, shift to one sample out of the next fifteen and proceed as indicated. (One from the

24、next 50, etc.) 4.4.2. i Scope of Sampling Plan A Test - Each sample selected for Sam- pling Plan A Test shall be subjected to the following tests in the order listed: Weight Magnetic Effect Damping High Temperature Operation Low Temperature Operation Vibration Error Lighting Sampling Plan A (lighted

25、 indicators onlx) Overpressure 4.4.2.2 Sampling Plan B Test - Two indicators shall be selected at random from the first 15 produced on contract and submitted within 10 days after manufacture. These samples shall be forwarded at the suppliers expense to a government laboratory designated by the procu

26、ring activity. Each sample shall be plainly identified by a ctiirablc tag (see 4.3.1.1). Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-1-21 73 5A(AS) tests. Any design, material or performance defect made evident during this test shall be corre

27、cted by the supplier to the satisfaction of the procuring activity. Fail- ure of the sample units to pass any of the tests shall be cause for deliveries of indi- cators under the contract to cease until proper corrective action is approved and accomplished. 4.4.2.2.2 Scope of Sampling Plan B Test -

28、Each sample selected for Sam- pling Plan B Test shall be subjected to the following tests in the order listed: Sampling Plan A Tests Vibration Failure High Temperature Exposure Low Temperature Exposure Acceleration Humidiw Seasoning Fungus Aging Salt Spray Lighting Test Sampling Plan B (lighted indi

29、cators only) Mounting Lug Internal Inspection Maintainability Demonstration 4.5 Standard Conditions for Test - Unless otherwise specified, all inspection required by this specification shall be made under the following conditions: Temperature Pressure Humidity input Power Altitude change rate Room a

30、mbient 25“ +5“ C Normal atmospheric (approximately 29.92 inches Hg) Room ambient 40 to 90 percent relative humidity 5 +O. 1V AC, 400 +5 cps (Lighted indicators only) corresponding to 6 , O00 feet per minute 4.5.1 Test Readings - Unless otherwise specified, before a test reading is taken the indicato

31、r shall be tapped at 60 cps, with a innximum double amplitude of O. 002 inch. 4.5.2 Lighting - The indicator lighting system slid1 hc ciiergizcd aiid shall operate satisfactorily during all tests except humidity, sc:isoning, fungus, :ging, inorinting lug, and saltaspray. The indicator lighting shall

32、 opcrritc s;itis:ictoi.ily after completion of each test unless otherwise specified herein. n# - - . O- i I /;i - _ - c- - -7 k- 11 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-4.6 Test Methods - The indicator shall satisfy the performance require

33、ments specified in Section 4 of MIL-1-5415, and as modified herein. TABLE I TEST ALUE ES Tests and Test Points kiction Error: Indicator Airspeed Pointer Mach Scale osition Error: Indicator Air speed Point er Mach Scale ?ohter Zero Position libration Error: Test Altitude - 35,000 feet Indicated Airsp

34、eed - 350 knots Maximum Vibration - Pointer Maximum Variation - Pointer herpressure: Static Connection - 6 inches Water Pitot Connection - 40 inches Hg. Vibration Failure: Test Altitude - 35,000 feet indicated Airspeed - 350 knots Damping: Time required for the airspeed pointer to travel from full s

35、cale deflection to the 90 knots graduation Seasoning Aging Tolerance 2 5. O knots 5. O knots 5. O knots 5.0 knots 1/16 inch 4. o knots 4. o lulots 2. O knots 2. o knots 1. O +* o seconds -0.2 3. O knots 3. O knots 4.6.1 Examination of Product - Examination of Product per MII,-1-5415. 4.6.2 Leakage -

36、 - ;Y ?- -7 12 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TABLE II AIRSPEED SCALE ERROR TEST POINTS AND TOLERANCES beed hots - 60 70* 80 90 loo* 110 120“ 130 140 150* 160 170 180* 190 200* 220 250* 280 300* 320 350“ 3 80 400* 450* 500* 550* 600*

37、 650 - Pressure Inches of Water 2.352 3.203 4.188 5.305 6.557 7.943 9.465 11.123 12.922 14.858 16.935 19.154 21.517 24.025 26.679 32.436 42.222 Pressure Inches of Mercury (Hg) I 3.924 4.534 5.195 6.286 7.502 8.385 10.868 13.776 17.159 21.075 25,589 Room Temperature Tolerance Knots 2. o 2. O 2. o 2.

38、O 2. o 2. o 2. o 2: o 2. o 2.5 2.5 2.5 2.5 2.5 3, O 3. O 3. O 3. O 4. O 4. O 4. O 4. O 5. O 5. O . 6.0 6. O 7. O 7. O High and Low Temp. Tolerance Knots - 4. O - - 4. O 4. O - - - 4.5 - - 4.5 5. O 5. O 6. O 6. O 7.0 7. O s. o 8:O 9. o - - - - - - Note: For sampling and qualification tests use all te

39、st points. For individual tests use test points marked with an asterisk. 4.6.2.1 Case Leak - This test shall be performed as specified in ML-I- 511 5. -*r? -1. ci. 2.2 Diaphrngni Capsulc Lcak -This tcst shull bc I)csrormerl as spcci- ficd iii MIL-I-415. .Q. . Provided by IHSNot for ResaleNo reproduc

40、tion or networking permitted without license from IHS-,-,- x- = MIL-I-ZL735A bb a 77777Ob 0330575 4 - MIL-1-2173 5A (AS) TABLE DI MACH NUMBER SCALE ERROR TEST POINTS AKD TOLERANCES Pressure Altitude Feet IC 1000 O O* O O O O O* 5 10* 15 20“ 25 30* 35 40 * 45 50 50 50 50* 50 50 50 50“ 50 50 Inches Hg

41、 29.921 29.921 29.921 29.921 29.921 29.921 29.921 24.896 20.577 16.886 13.750 11.103 8.885 7.041 5.538 4.355 3.425 3.425 3.425 3.425 3.425 3.425 3.425 3.425 3.425 3.425 Mach gumher .4 .5 .6 .7 .8 .9 1.0 1. o 1.0 1. o 1.0 1. o 1.0 1.0 1.0 1. o .7 .8 .9 1.0 1.1 1.2 1.4 1.G 1.8 2. O - Airspeed Knots 26

42、5 331 397 463 529 595 661 613 566 520 475 432 390 350 313 279 165 192 219 248 278 309 368 426 480 532 Differential Pressure Inches Hg 3.487 5.572 8.243 11.583 15.689 20.685 26.718 22.230 18.374 15.078 12.278 9.915 7.934 6.287 4.945 3.889 1.326 1.796 2.367 3.058 3.880 4.820 7.018 9.606 12.567 15.8!)2

43、 Room Temperature Tolerance Knots 6 6 8 9 10 12 12 12 11 10 10 9 8 7 6 6 4 4 4 5 6 6 7 9 1 o 11 High and Low Temp. Tolerance * Knots Note: For Sampling and Qualification tests use all test points. For Individual tests use test points marked with an asterisk. 4.6.3 Scale Error at Room Temperature - 4

44、.6.3.1 Airspeed Scale - This test shsll be performed as specified in JIlL-I-5-115. The errors at the test points shall not exceed those specified in Table II. 1.Li.s.2 Wich Suniber Scale Error - Test shall be conductcd by cutablisliiiig tlic spccified altitude- aiid setting the indicated airspeed po

45、iii / 1.1 .- _- - Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- MIL-I-Z1735A(AS) 3 graduation at each of the specified test points. The error shall then be determined by reading the airspeed value indicated by the airspeed poirder. The errors shal

46、l . not exceed the tolerances specified i normal, dial face up, dial face down, right side up, right side down, and bottom up. 4.6.7 Pointer Position Error - Pointer position error shall be as specified by MIL-1-5415 and Table I. 4.6.8 Lighting (Individual) - The indicator shall be subjected to and

47、meet the requirements of the individual tests in MIL-L-25467 and MIL-L-27160. 4.6.9 Weight of the indicator shall not exceed 1.5 pounds. 4.6.10 I I -1 Damping - Damping per MIL-1-5415 and Table I. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- MIL-

48、I-23735A 66 7799906 0330577 B . - I 4.6.11 Magnetio Effect - The lighted indicator shall be properly connected and power applied. The indicator shall be tested per MIL-1-5415 by revolving it 360 _ degrees at the positions O, 45, 90, 135, 180, 226, 270, and 315 degrees from the initial position. Defl

49、ection of the compass shall not exceed 1 degree. Tli st shall be repeated, without power, and the same tolerance shall apply. 4.6.12 Low Temperature Operation(This test may be combined with the Low temperature exposure test at the discretion of the testing agency) - The indicator shall be properly connected except that no p