NAVY MIL-STD-5522-2000 TEST REQUIREMENTS AND METHODS FOR AIRCRAFT HYDRAULIC AND EMERGENCY PNEUMATIC SYSTEMS《飞机液压和气压应急系统的试验要求和方法》.pdf

《NAVY MIL-STD-5522-2000 TEST REQUIREMENTS AND METHODS FOR AIRCRAFT HYDRAULIC AND EMERGENCY PNEUMATIC SYSTEMS《飞机液压和气压应急系统的试验要求和方法》.pdf》由会员分享，可在线阅读，更多相关《NAVY MIL-STD-5522-2000 TEST REQUIREMENTS AND METHODS FOR AIRCRAFT HYDRAULIC AND EMERGENCY PNEUMATIC SYSTEMS《飞机液压和气压应急系统的试验要求和方法》.pdf（46页珍藏版）》请在麦多课文档分享上搜索。

1、NOT MEASUREMENT I SENSITIVE MIL-STD-5522 17 March 2000 SUPERSEDING 30 September 1975 MIL-T-5522D DEPARTMENT OF DEFENSE TEST METHOD STANDARD TEST REQUIREMENTS AND METHODS FOR AIRCRAFT HYDRAULIC AND EMERGENCY PNEUMATIC SYSTEMS AMSC NIA FSC 1650 Provided by IHSNot for ResaleNo reproduction or networkin

2、g permitted without license from IHS-,-,-MIL-STD-5522 FOREWORD 1. This standard is approved for use by all Departments and Agencies of the Department of Defense (DoD). 2. This standard established in determining methods for testing aircraft hydraulic and emergency pneumatic systems. This standard co

3、vers test methods for aircraft subsystems, weapon system and support equipment. This standard provides contractor for preparation of a detail test procedure for hydraulic and emergency pneumatic systems of a specific aircraft. 3. Beneficial comments (recommendations, additions, deletions) and any pe

4、rtinent data which may be of use in improving this document should be addressed to: Commander, Naval Air Warfare Center Aircraft Division, Code 414100B120-3, Highway 547, Lakehurst, NJ 08733-5100, by using the Standardization Document Improvement Proposal (DD Form 1426) appearing at the end of this

5、document or by letter. 11 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-STD-5522 1. SCOPE l. 1 Scope. This standard establishes test and test method requirements for aircraft and weapons hydraulic and emergency pneumatic systems design and inst

6、allation with operating pressure ranges from 3,000 psi to 8,000 psi and temperature ranges from -65 “F to + 450 “F. 2. APPLICABLE DOCUMENTS 2.1 General. The documents listed in this section are specified in sections 3, 4, and 5 of this standard. This section does not include documents cited in other

7、 sections of this standard or recommended for additional information or as examples. While every effort has been made to ensure the completeness of this list, document users are cautioned that they must meet all specified requirements documents cited in sections 3,4, and 5 of this standard, whether

8、or not they are listed. 2.2 Government documents. 2.2.1 Specifications, standards, and handbooks. The following specifications and standard form a part of this document to the extent specified herein. Unless otherwise specified, the issues of these documents are those listed in the issue of the Depa

9、rtment of Defense Index of Specifications and Standards (DoDISS) and supplement thereto, cited in the solicitation (see 6.3). SPECIFICATIONS DEPARTMENT OF DEFENSE MIL-F-8785 - Flying Qualities of Piloted Airplanes. STANDARDS DEPARTMENT OF DEFENSE MIL-STD-8 10 - Environmental Engineering Consideratio

10、ns and Laboratory Tests. (Unless otherwise indicated, copies of the above specification and standard are available from the Standardization Document Order Desk, 700 Robbins Avenue, Building 4D, Philadelphia, PA 191 11-5094.) 2.2.2 Other Government documents, drawings and publications. The following

11、other Government publication forms a part of this document to the extent specified herein. Unless otherwise specified, the issues are those cited in the solicitation. 1 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-STD-5522 United States Govern

12、ment Printing Office GPO Style Manual (Copies of the GPO Style Manual are available from the Superintendent of Documents. U.S. Government Printing Office, North Capitol and H street, N. W., Washington, DC 20402-0001.) 2.3 Order of precedence. In the event of a conflict between the text of this stand

13、ard and the 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. 3. DEFINITION 3.1 Aircraft varidrive operation. A demonstration of normal operation of the air

14、craft hydraulic and pneumatic systems with the use of varidrive motor inplace of engine. 3.2 Cycle. A cycle is a full travel of service from down to up and return to original down. An illustration of a full cycle would be a landing gear down when valve closed and up when valve opened and return to o

15、riginal down when valve closed. 3.3 Emergency operation. A hydraulic and pneumatic power system reverts from normal system pressure to emergency system pressure when normal system pressure is reduced in detrimental manner. 3.4 Elapse time. Time duration taken to complete a prescribed operation from

16、start to finish. 3.5 Fatigue life. Anticipated life of component expected to last prior to fail due to repeated stress. 3.6 Functional test. A test performed on systems or system components to ensure components and systems are in proper working order and their performance conforms to the specificati

17、on. 3.7 Half cycle. A half cycle is a selector valve and control valve operates one complete cycle. It is illustrated as a landing gear from down to up. 3.8 Mission profile. Demonstration of all satisfactory functions of hydraulic and pneumatic systems and components during a mission. A mission incl

18、udes satisfactory completion of tasks mission from startup to shutdown. 3.9 Normal system. Hydraulic and pneumatic systems and components are functioning properly under the specified condition. 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-ST

19、D-5522 3.10 Post test inspection. Examination of components inspected after actual test. 3.1 1 Power braking system. A control unit generated pressure by manual actuation and a manually generated pressure is boosted by pressure from a power generating system. 3.12 Pump ripple. Pressure variance prod

20、uced by the pump. 3.13 Resonant condition. A condition when components are exposed to resonant frequencies. 3.14 Resonance ripple freauencies. Vibration frequencies at a resonant stage transmitted from hydraulic pump. 3.15 Simulator tests. Tests conducted in a simulator where installation of compone

21、nts and tubing are identical to actual aircraft. 3.16 Unsymmetrical loading. Uneven or unbalance loading subjected to the control surface of the aircraft. 4. GENERAL REQUIREMENTS 4.1 Recycled, recovered, or environmentally preferable materials. Recycled, recovered, or environmentally preferable mate

22、rials shall be used to the maximum extent possible provided that the material meets or exceeds the operational and maintenance requirements, and promotes economically advantageous life cycle costs. 4.2 Acronym use. The use of acronym shall be in accordance with GPO style manual. 4.3 Test requirement

23、s. new aircraft. One or more of a new series of aircraft shall complete the tests specified in this standard before first flight. If an aircraft simulator is not available, the simulator tests shall be performed on the aircraft. Test requirements versus test methods are tabulated in table I. 4.4 Sim

24、ulator. All simulator tubing and component installations shall be identical to those in the first flight aircraft. All tubing flatness greater than 5 percent for 3,000 PSI and above, and 10 percent for less than 3,000 PSI operating pressure shall be pre-stressed. 4.4.1 Proof pressure. Proof pressure

25、 testing of simulator hydraulic systems shall be performed with all components installed. System shall be tested to the requirements of table II as applicable. 3 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- . 9 d Provided by IHSNot for ResaleNo r

26、eproduction or networking permitted without license from IHS-,-,-MIL-STD-5522 4.4.2 System functional. System functional tests shall be performed on the simulator to ensure that the systems and subsystems meet the design objectives. All normal operating requirements and emergency operations shall be

27、 demonstrated in their most adverse condition. 4.4.3 Failure modes and effects. Failure modes and effects tests shall be conducted prior to first flight to evaluate the failure modes which are critical from a safety point of view or whose effects are unpredictable from the failure mode and effects a

28、nalyses. 4.4.4 Mission profile. Mission profile (see 3.8) test shall be performed to demonstrate that all normal missions can be satisfied. This test shall include start-up, taxi, take-off, climb-out, cruise, mission maneuvering, return flight, landing, taxi, park, and shut-down. 4.4.5 Vibration sur

29、vey. Vibration survey shall be performed on the simulator to ensure that no detrimental resonant conditions (see 3.13) exist induced by the hydraulic system. 4.4.6 Peak pressure. Pressure survey shall be performed on the simulator to verify that system pressure peaks do not exceed the design require

30、ments. 4.4.7 Pump ripple. Pump ripple (see 3.12) test shall be performed to ensure that no resonance ripple frequencies (see 3.14), created by any device, cause detrimental and destructive effects to the hydraulic system or aircraft. All normal speed ranges of the pump or other ripple- generating de

31、vices shall be investigated. 4.4.8 System temperatures. System temperatures shall be monitored on the simulator to validate the analytical data. Deviation to predicted temperatures shall be investigated and resolved. Extreme limits of the temperature envelope shall be tested by allowing the system t

32、emperature to rise to simulator limits and then extrapolating data to the extremes of the flight envelope. 4.4.9 Post test inspection. Post test inspection (see 3.10) shall be conducted to determine condition of the hydraulic and pneumatic systems at the conclusion of each test. Data such as tempera

33、ture, fluid level, accumulator pressure, quantity of dissolved air, air bottle pressure shall be noted. Any deviation to predicted values shall be investigated and resolved. 4.4.10 Engine compatibility. Engine mounted hydraulic components and systems shall demonstrate their compatibility with relate

34、d engine operation on simulators such as engine test stand, air inlet control test stand, and thrust reverser test stand. 4.5 Aircraft ground cart. All systems operable through ground cart test connections shall be demonstrated during the test. 5 Provided by IHSNot for ResaleNo reproduction or netwo

35、rking permitted without license from IHS-,-,-MIL-STD-5522 TABLE II. Hydraulic Pressures. Pressure ( Il ) Component or and below 31 and below 21 Characteristic Remarks Class 8000 Class 5000 Pumx, Pressures a. Systems relief valve maximum pressure at rated flow b. Thermal relief valve cracking pressur

36、e Proof Pressure (minimum) a. Lines, fittings, hoses and couplings (1) Pressure circuits (2) Return and case drain circuits b. Accumulators c. Low pressure side of reservoir and pump suction line for the following reservoir types (1) Bootstrap reservoir (2) Gas pressurized reservoirs d. Components u

37、nder system pressure I a. Pump pressure at System design 100% 100% zero flow pressure b. Pump minimum 100% -150psi 100% -150psi pressure at full flow Relief Valve Pressure Settings 100% +S50 psi 100% +lo00 psi 100% +S50 psi 100% +lo00 psi 200% 100% 200% “ “ 150% The pressure settings for a specific

38、valve shall be in accordance with the applicable valve specification Proof pressures values for hoses to be in accordance with the applicable hose specification 150% of reservoir operating pressure 200% of reservoir operating pressure 6 Provided by IHSNot for ResaleNo reproduction or networking perm

39、itted without license from IHS-,-,-MIL-STD-5522 TABLE 11. Hydraulic pressures - (continued) e. Components under return pressure only f. Heat exchangers g. Complete system (1) Pressure side (2) Return side Burst Pressures a. Lines, fittings, hoses and couplings (1) Pressure circuits (2) Return and ca

40、se drain circuits b. Accumulators c. Low pressure side of reservoir and pump suction line for the following reservoir (1) Bootstrap reservoir (2) Gas pressurized reservoirs d. Components under system pressure e. Components under return pressure only 100% 150% 100% 150% I 150% 75% 150% 75% 400% 400%

41、200% 400% 250% 150% 300% 150% 400% 200% 150% Except for hoses which shall be 125% of system pressure 150% of maximum operating pressure Aircraft installed systems only Burst pressure values for hoses to be in accordance with the applicable hose specification 300% of reservoir operating pressure 400%

42、 of reservoir operating pressure Except for hoses which shall be 125% of system pressure 7 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-STD-5522 TABLE 11. Hydraulic pressure - (continued) f. Heat exchangers 250% of maximum operating pressure g

43、. Collapse pressure of external external parts subject to suction 50 psid 50 psid - I/ Percentage of supply pressure in psi. - 2/ 5000 PSI supply pressure. - 3/ 8000 PSI supply pressure. 4.5.1 System proof pressure. Proof pressure of aircraft hydraulic and pneumatic systems shall be performed with c

44、omponents installed. System shall be tested to the requirements of table II as applicable. 4.5.2 System functional. System functional tests (see 3.6) shall demonstrate satisfactory operation of all systems and their compatibility with designated ground carts. 4.5.3 Peak pressure. Pressure survey sha

45、ll be performed to determine that system pressure peaks from ground cart operation shall not exceed the design requirements. 4.5.4 Pump ripple. Pump ripple tests shall be performed to ensure that no resonant ripple frequencies created by ground cart operation cause detrimental and destructive effect

46、s to the hydraulic system or aircraft. Particular attention shall be given to the aircraft hydraulic plumbing installation between the system pump(s) and the pressure line filter(s). All normal speed ranges of the generating device shall be investigated. 4.5.5 Post test inspection. A post test inspe

47、ction shall be performed to determine any leakage or damage to components, lines and structure. 4.6 Aircraft varidrive operation (see 3.1). Varidrive pumps shall be installed in approximately the normal pump position in the aircraft. This test shall demonstrate normal operation of the aircraft hydra

48、ulic and pneumatic systems with engine driven variable pumps. 4.6.1 System functional. Functional test shall perform the start, all engine RPM ranges, and shut down of the hydraulic and emergency pneumatic systems. The systems shall be operated through all normal and emergency modes. 4.6.2 Mission p

49、rofile and failure mode. Mission profile and failure mode tests specified in paragraph 5.3.2 of this standard shall be performed on the aircraft to demonstrate that safety of flight shall not be endangered. 8 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-STD-5522 4.6.3 Vibration survey. A vibration survey shall be conducted to det