NAVY MIL-T-18606-1955 TEST PROCEDURES FOR AIRCRAFT ENVIRONMENTAL SYSTEMS《飞机环境系统测试系统》.pdf
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1、k 1 MIL-T-LB606 16 m 3999906 0425769 2 m . r- - _ MILITARY SPECIFICATION TEST PROCEDURES FOR AIRCRAFT CABIN PRESSURIZING AND AIR CONDITIONING SYSTEMS This specification has been approved by the Bureau of Aeronautics, Department of the Navy 1. SCOPE 1.1 This specification covers the testing of cabin
2、pressurizing and air conditioning systems as installed in aircraft to demonstrate safety and satisfactory performance of the installation. The procedures outlined herein shall be followed, as applicable, for the testing of pressurized and non-pressurized aircraft. 2. APPLICABLE DOCUMENTS 2.1 The fol
3、lowing specifications and publications, of the Issue in effect on date of invitation for bids, form a part of this specification. SPECIFICATIONS MILITARY MIL-T-5842A Transparent Areas, Anti-Icing, Defrosting and Defogging Systems, General Specification for PUBLICATIONS AIR FORCX - NAVY AERONAUTICAL
4、BLIXTIN No. 421 Atmospheric Proprieties - Extreme Cold and Hot; Standard for Aeronautical Design (When requesting specifications, standards, drawings, and publications refer 60 both title and number. Copies of this specification and applicable specifications may be obtained upon application to the C
5、ommanding Officer, U. S. Naval Air Station, Johnsville, Pennsylvania, Attention Technical Records Division) 3. REQUIREMENTS 3.1 3.1.1 Suitable Instrumentation shall be installed to determine the weight flow of air, the temperature differential, and the pressure drop through each of the major compone
6、nts of the system. The accuracy of these measurements should be within plus OE minus 5 percent. 3.1.2 cent of passenger and crew accommodations occupied during cooling tests and a maximum of 10 percent of the passenger accommodations occupied during heating tests. tribction from forward to rear and
7、top to bottom of all occupied spaces within the air- plane. 3.1.4 Equipment shall be provided to determine the direction of flow and the General test equipment and requirements. System performance tests shall be conducted with a minimum of 75 per- 3*1.3 Instrumentation shall be provided to determine
8、 the temperature dis- Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-_-_. _- _.I- _I_p- MIL-T-1bOb 16 W 7799906 0425770 7 W - aircraft at regular intervals using a reliable type of psychrometer. Pressure taps shall be so located as to determine all
9、pressures 3.3.5 Air velocity measurements. 3.3.5.1 A suitable velometer shall be used to determine air velocities in 3.3.5.2 Air velocities across the cabin thermostat sensing element and passenger and crew compartments. temperature indicating instrument, if installed, shall be determined by use of
10、a suit- able velometer. 3.3.6 in order that rates of temperature and pressure changes and time intervals required to obtain stab?lized conditions within the cabin can be noted. Time measurements.-Time measurements shall be recorded continuously 4. QUALITY ASSURANCE PROVISIONS . 4.1 Ground tests. 4.1
11、.1 Safety tests.-The aircraft shall be inspected to determine that all cabin air entries are so located that no drain or exhaust of inflammable or noxious fluid and gases can enter the scoop during flight or on the ground during cross wind conditions. . 4.1.1.1 Combustion heater installations. 4.1.1
12、.1.1 With an adjustable external power source connected to the airplane, the voltage shall be adjusted to that normally supplied by the aircraft system. 4.1.1.1.2 If the installation does not include blowers required for ground operation, external equipment required to supply in-flight conditions sh
13、all be attached. 4,1.1.1.3 With blowers in operation, the aircraft heating system shall be turned on and checked for normal operation. 4.1.1.1.4 With system operating normally, the combustion air source shail be disconnected or deactivated, to determine that no unsafe condition will be created by lo
14、ss of combustion air through failure of combustion air blower or icing of combustion air scoop in flight, System shall be adjusted as required, 3 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-T-18606( Aer ) 4.1.1.1.5 with system operating norma
15、lly, the ventilating air source shall be disconnected or deactivated to determine that no unsafe condition will be created by loss of ventilating air through failure of equipment or icing of air inlet in flight 4.1.1.1.6 With system operating normally, deactivate or bypass the normal temperature con
16、trol system to allow heater outlet air temperature to increase to the overheat switch setting. (Reduce ventilating air flow if required.) determined that no unsafe Condition exists at the temperatures encountered and that the overheat circuit functions properly. supplied to the aircraft until all of
17、 the components of the system cease to operate. It shall be determined that no unsafe condition is created due to low voltage operation. With the system turned on and all electrical power disconnected from the aircraft (external blowers operating if used), reduce the voltage to 50 per- cent of the n
18、ormal aircraft system voltage and reGonnect to the aircraft. Gradually increase the voltage until all components are operating normally and it shall be determined that no unsafe condition is created by low voltage condition. It shall be 4.1.1.1.7 With the system operating normally, gradually decreas
19、e the voltage 4.1.1.1.8 4.1.1.1.9 Conditions required to cause the aircraft heater to backfire shall be created to determine that combustion air and exhaust systems are secure and adequate for the heater. These conditions may be created by reduction of combustion air flow o? disconnecting the igniti
20、on system for a brief period of time. At least three substantial backfires shall be created before considering the system adequate. Ducts and heater shall be inspected for damage after test. lations shall be tested to show that no unsafe condition would be created by failure of the exhaust gas passa
21、ge within the unit. that pressures within the ventilating air passage are sufficient to prevent flow of exhaust gases into this passage. 4.1.1.2 Exhaust gas heat exchangers.-Engine exhaust gas heat exchanger instal- One means of verification would be to ascertain 4.1.2 Performance tests. 4.1.2.1 Gro
22、und tests ahall be conducted on aircraft equipped with ground conditioning equipment to determine if satisfactory temperatures and air flow rates are obtained. The air distribution shall be observed and flow rates measured to determine proper balance of the s stem. All temperatures, pressures, air v
23、elocities, and humidity (in transports7 specified in section 3 shall be recorded. -4.1.2.2 On pressurized aircraft, ground operation shall be tested or other- wise analyzed in order to determine the optimum configuration for comfort in hot weather while the airplane is taxiing or waiting take-off cl
24、earance. determine the cabin leakage rate. Pressure controls, flow controls and all pressure relief valves shall be checked to ascertain that the units are operating properly and are within tolerance limits. 4.1.2.3 Pressurized aircraft shall be pressurized to design differential to 4.2.1- Safety te
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