V45 航空仪表 标准查询与下载
共找到 902 条与 航空仪表 相关的标准，共 61 页
This notice should be filed in front of MIL-I-27202A, dated 2 September 1980
INDICATOR, ELECTRICAL TACHOMETER, 0-110 PERCENT RPM, INTEGRALLY LIGHTED
- ICS
- 49.090
- CCS
- V45
- 发布
- 1996-01-15
- 实施
This notice should be filed in front of MIL-I-25908C, dated 11 May 1987.
INDICATOR, RATE OF FLOW, EFU-45A, FUEL TOTALIZING, 0-120,000 PPH
- ICS
- 49.090
- CCS
- V45
- 发布
- 1996-01-15
- 实施
This notice should be filed in front of MIL-I-25907C, dated 30 June 1994.
INDICATOR, RATE OF FLOW, EFU-4/A, FUEL TOTALIZING, 500-15,000 PPH
- ICS
- 49.090
- CCS
- V45
- 发布
- 1996-01-15
- 实施
This notice should be filed in front of MIL-I-25906D, dated 30 June 1993.
INDICATOR, RATE OF FLOW EFU-3A, FUEL, 0-15,000 PPH
- ICS
- 49.090
- CCS
- V45
- 发布
- 1996-01-15
- 实施
This notice should be filed in fiont of MS28013A dated 09 February 1971
INDICATOR-POSITION, HORIZONTAL STABILIZER
- ICS
- 49.090
- CCS
- V45
- 发布
- 1996-01-15
- 实施
This notice should be filed in front of MIL-I-25859C, dated 30 January 1995.
INDICATOR, THRUST AEU-2/A, SYNCHRO STYLE, PRESSURE RATIO, 1.2.3.4 UNITS, INTEGRALLY LIGHTED
- ICS
- 49.090
- CCS
- V45
- 发布
- 1996-01-15
- 实施
This notice should be filed in front of MIL-I-25482D, dated 30 September 1993
INDICATOR, ENGINE TESTING
- ICS
- 49.090
- CCS
- V45
- 发布
- 1996-01-15
- 实施
This notice should be filed in front of MIL-I-25438D, dated 11 January 1988.
INDICATOR, PRESSURE, TYPE MO-2
- ICS
- 49.090
- CCS
- V45
- 发布
- 1996-01-15
- 实施
This notice should be filed in front of MIL-I-25324C. dated 15 June 1992.
INDICATOR, RATE OF FLOW, FUEL 0-12,000 PPH
- ICS
- 49.090
- CCS
- V45
- 发布
- 1996-01-15
- 实施
This notice should be filed in front of MIL-I-7566C, dated 15 July 1993.
INDICATOR, SYSTEM, FUEL FLOWMETER, GENERAL SPECIFICATION FOR
- ICS
- 49.090
- CCS
- V45
- 发布
- 1996-01-15
- 实施
This notice should be filed in front of MIL-1-65 14B, dated 15 March 1988.
INDICATOR, OIL PRESSURE, 0-200 PSI 320 DEGREE, TYPE B-9C
- ICS
- 49.090
- CCS
- V45
- 发布
- 1996-01-15
- 实施
This notice should be filed in front of MS28036D dated 13 March 1987
INDICATOR-TRUE AIRSPEED, TYPE M-1A
- ICS
- 49.090
- CCS
- V45
- 发布
- 1996-01-15
- 实施
This notice should be filed in front of MIL-I-5IS4B(USAF) dated i6 January i968
INDICATOR, TRUE AIRSPEED, TYPE M-5
- ICS
- 49.090
- CCS
- V45
- 发布
- 1996-01-15
- 实施
This notice should be filed in front of MIL-I-27196C(USAF) dated 11 March 1988. MIL-I-Z7196C(USAF) is inactive for new design and is no longer used, except for replacement purposes.
INDICATOR, VERTICAL VELOSITY AAU-9/A, INTEGRALLY LIGHTED
- ICS
- 49.090
- CCS
- V45
- 发布
- 1996-01-15
- 实施
This notice should be filed in front of MIL-I-27304E, dated 4 April 1977.
INDICATOR, RATE OF FLOW
- ICS
- 49.090
- CCS
- V45
- 发布
- 1996-01-15
- 实施
Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS--
INDICATOR, PRESSURE, EGU-9/A
- ICS
- 49.090
- CCS
- V45
- 发布
- 1996-01-15
- 实施
This notice should be filed in front of MIL-A-83212A(USAF) dated 28 October 1976.
ALTIMETER, PRESSURE AAU-27/A
- ICS
- 49.090
- CCS
- V45
- 发布
- 1996-01-15
- 实施
This notice should be filed in front of MIL-1-83 ISiB(USAF) dated 16 October 1974.
INDICATOR, INDICATED-AIRSPEED AVU-22/A (INDICATOR-TRANSDUCER)
- ICS
- 49.090
- CCS
- V45
- 发布
- 1996-01-15
- 实施
This SAE Aerospace Standard (AS) provides guidelines for the functional, performance, qualification and acceptance testing, and documentation requirements for the components of an airborne engine vibration monitoring (EVM) system which is intended for use as a turbojet engine rotor unbalance indicating system, per FAR 25.1305 (D)(3) on transport category airplanes. For the purpose of this document, this means a system which can provide real-time flight deck displays of engine vibration caused by rotor unbalance, throughout the flight envelope, which are suitable for: a. relating to engine vibration limits (where such limits are specified), b. use in ice shedding procedures, and c. helping the flight crew to determine which engine has the higher level of vibration, following an engine damage event. As a minimum, the functional capability for such a system shall include the ability to compute and display vibration levels specifically related to the rotational speed(s) of the engine rotor(s). Systems which can produce only broadband vibration outputs have been used in the past but they are not considered suitable for the above purposes. Some EVM systems may also generate other outputs, suitable for such functions as engine vibration trend monitoring or trim balance calculation, but these are considered to be outside the scope of the requirements for a minimum system. This document also defines some recommended, optional, functions and features which, while they are outside the scope of minimum requirements, are nevertheless considered to be highly desirable for a practical system. It should be noted that systems incorporating capabilities such as described above are also sometimes referred to by the abbreviation AVM. However, there are, or can be, airborne measurements taken of vibrations from sources other than the engines. For the purpose of this document the more descriptive term, engine vibration monitor (EVM), will be used. The purpose of this document is to provide guidance on the requirements for airborne EVM systems for turbojet engines on transport category airplanes.
AIRBORNE ENGINE VIBRATION MONITORING (EVM) SYSTEM, GUIDELINES FOR PERFORMANCE STANDARD FOR
- ICS
- 49.050
- CCS
- V45
- 发布
- 1996-01-01
- 实施
This standard covers Airspeed Instruments which display airspeed of an aircraft, as follows: Type A - air driven, direct reading, self contained; Type B - electrically operated, self contained; and Type C - electrically operated, input from a remote sensor. This standard establishes minimum performance standards for total and static pressure actuated airspeed instruments.
Airspeed Instruments
- ICS
- 49.090
- CCS
- V45
- 发布
- 1996-01-01
- 实施
