| Name |
Description |
Abstract |
Status |
Publication date |
Edition |
Number of pages |
Technical committee |
ICS |
| ISO 461-1:1985 |
Aircraft — Connectors for ground electrical supplies — Part 1: Design, performance and test requirements |
Specifies the characteristics for connectors used to supply electrical power from a ground source to an aircraft. Describes the aircraft fixed connector (respectable) and the ground supply free connector (plug), their polarity or phase sequence, current ratings, control current female contact, sealing, voltage rating, replaceability of female contacts, inspection and testing and marking and ordering procedures.
|
Withdrawn |
1985-04 |
Edition : 1 |
Number of pages : 4 |
Technical Committee |
49.060
Aerospace electric equipment and systems
;
49.100
Ground service and maintenance equipment
|
| ISO 461-1:2003 |
Aircraft — Connectors for ground electrical supplies — Part 1: Design, performance and test requirements |
ISO 461-1:2003 specifies the design, performance and test requirements for electrical connectors used to supply electrical power from a ground source to an aircraft.
ISO 461-2 specifies the dimensions of the connectors.
|
Published |
2003-06 |
Edition : 2 |
Number of pages : 7 |
Technical Committee |
49.060
Aerospace electric equipment and systems
;
49.100
Ground service and maintenance equipment
|
| ISO 461-2:1985 |
Aircraft — Connectors for ground electrical supplies — Part 2: Dimensions |
Gives the values for the following connectors used to supply electrical power from a ground source to an aircraft: aircraft fixed connector style 1A; 28 V d. c. and style 2A; 112 V d. c., ground supply free connector style 1B; 28 V d. c. and style 2B; 112 V d. c., 400 Hz 3-phase aircraft fixed connector style 3A; 2OO V a. c. and 4OO Hz, 3-phase ground supply free connector style 3B; 200 V a. c.
|
Published |
1985-04 |
Edition : 1 |
Number of pages : 7 |
Technical Committee |
49.060
Aerospace electric equipment and systems
;
49.100
Ground service and maintenance equipment
|
| ISO/R 461:1965 |
Connections for aircraft ground electrical supplies |
|
Withdrawn |
1965-11 |
Edition : 1 |
Number of pages : 8 |
Technical Committee |
49.060
Aerospace electric equipment and systems
;
49.100
Ground service and maintenance equipment
|
| ISO/R 469:1966 |
Withdrawal of ISO/R 469-1966 |
|
Withdrawn |
1966-02 |
Edition : 1 |
Number of pages : 1 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 1965:1973 |
Aluminium terminal ends for crimping to aircraft aluminium electrical cables |
Specifies the characteristics of these components with aluminium conductors in locations in which the stabilized conductor temperature does not exceed 105 degrees centigrade. Includes information on terminology, materials, demensions, finish, inhibitors, inspection, markings, performance and installation.
|
Published |
1973-02 |
Edition : 1 |
Number of pages : 2 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 530:1975 |
Aircraft — General purpose push-pull single-pole circuit-breakers — Dimensions |
The dimensions of ratings up to and including 35 A circuit breakers shall not exceed those shown in figure 1. The dimensions of the part projecting through the mounting panel shall be as shown in figure 1. The holes in the mounting panel for fixing the circuit-breaker shall be as shown in figure 2. The small panel hole may be used to prevent rotation of the circuit-breaker.
|
Published |
1975-02 |
Edition : 1 |
Number of pages : 2 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 1033:1975 |
Aircraft — Dimensions for general purpose push-pull three-pole circuit-breakers |
Specifies the dimensions of breakers of ratings up to and including 35 A. The dimensions of the breakers and of the part projecting through the mounting panel, shall be as shown in figure 1. The holes in the panel for mounting the breaker shall be as shown in figure 2. The small panel hole may be used to prevent rotation of the breaker.
|
Published |
1975-12 |
Edition : 1 |
Number of pages : 1 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 1198:1972 |
Sealed-beam landing lamps for aircraft — Dimensions |
Gives the values shown in the figures 1 to 3. These values are listed in tables. All values are relacted to landing lamps 28 V, 600 W; 28 V, 600/400 W; 28 V, 250 W.
|
Published |
1972-05 |
Edition : 1 |
Number of pages : 4 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 1466:1973 |
Lever-operated manual switches for aircraft — Performance requirements |
Gives the requirements for two classes of single-hole fixing switches for use in nominal 28 V d. c. and 115/200 V three-phase, 400 Hz a.c. systems. Class 1 switches are sealed and are suitable for higher altitude and temperature conditions than are Class 2 switches, which are sealed only at the lever entry. Furthermore, gives requirements for dimensions, operation, construction, voltage and current ratings, environment, tests, type tests, production tests, quality tests, declarations and marking.
|
Published |
1973-09 |
Edition : 1 |
Number of pages : 8 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 1467:1973 |
General purpose push-pull single-pole circuit-breakers for aircraft — Performance requirements |
Specifies the requirements for circuit breakers having an inverse time/current characteristic, of normal ratings up to and including 35 A, for use in nominal 28 V d. c. and/or 115 V single-phase 4OO Hz a. c. line to neutral circuits. Includes definitions, design requirements, requirements for dimensions, construction, voltage and current ratings, environment, time/current characteristics, making and breaking capacity, endurance, tests, type tests, production tests, quality tests, declarations and marking.
|
Published |
1973-11 |
Edition : 1 |
Number of pages : 9 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO/CD 1467 |
General purpose push-pull single-pole circuit-breakers for aircraft — Performance requirements |
Specifies the requirements for circuit breakers having an inverse time/current characteristic, of normal ratings up to and including 35 A, for use in nominal 28 V d. c. and/or 115 V single-phase 4OO Hz a. c. line to neutral circuits. Includes definitions, design requirements, requirements for dimensions, construction, voltage and current ratings, environment, time/current characteristics, making and breaking capacity, endurance, tests, type tests, production tests, quality tests, declarations and marking.
|
Under development |
|
Edition : 2 |
|
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 1509:1973 |
General purpose push-pull three-pole circuit-breakers for aircraft — Performance requirements |
Gives the requirements for circuit breakers having an inverse time/current characteristic, of normal ratings up to and including 35 A, for use in nominal 115/200 V three-phase 4OO Hz a. c. circuits. Includes definitions, design requirements, requirements for dimensions, construction, voltage and current ratings, environment, time/current characteristics, making and breaking capacity, endurance, tests, type tests, production tests, quality tests, declarations and marking.
|
Published |
1973-11 |
Edition : 1 |
Number of pages : 9 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO/CD 1509 |
General purpose push-pull three-pole circuit-breakers for aircraft — Performance requirements |
Gives the requirements for circuit breakers having an inverse time/current characteristic, of normal ratings up to and including 35 A, for use in nominal 115/200 V three-phase 4OO Hz a. c. circuits. Includes definitions, design requirements, requirements for dimensions, construction, voltage and current ratings, environment, time/current characteristics, making and breaking capacity, endurance, tests, type tests, production tests, quality tests, declarations and marking.
|
Under development |
|
Edition : 2 |
|
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 1540:1977 |
Aerospace — Characteristics of aircraft electrical systems |
|
Withdrawn |
1977-12 |
Edition : 1 |
Number of pages : 19 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 485:1973 |
Aircraft water-methanol pressure connections |
Gives the dimensions of 19 mm and 38 mm bore pressure connections. A space envolope is also specified for each size of connection. Dimensions and tolerances for connections are given in figures 1 and 3, and those for space envelopes in figures 2 and 4. The values are listed in tables.
|
Published |
1973-02 |
Edition : 1 |
Number of pages : 9 |
Technical Committee |
49.080
Aerospace fluid systems and components
;
49.100
Ground service and maintenance equipment
|
| ISO 1540:1984 |
Aerospace — Characteristics of aircraft electrical systems |
Specifies the characteristics of electrical power supplied to the terminals of airborne equipment and defines limits for those aspects of utilization equipment which may adversely affect the characteristics of electrical power supplied to other equipment. Its purposes to achieve compatibility between airborne utilization equipment and aircraft electrical power supplies. Ground support electrical power supplies forms the subject of a separate International Standard.
|
Withdrawn |
1984-11 |
Edition : 2 |
Number of pages : 19 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 1540:2006 |
Aerospace — Characteristics of aircraft electrical systems |
ISO 1540:2006 specifies the characteristics of electrical power supplied to the terminals of electrical utilization equipment installed in an aircraft. It is intended to support the interface definition for user equipment designed to accept electrical power on a variety of new civil aircraft applications, such as those certified via the Technical Standard Order (TSO) certification process. It might not be desirable for equipment targeted to a single application or specific military application to follow ISO 1540:2006 because of the penalties associated with multi-application.
ISO 1540:2006 also attempts to provide background to the development of these requirements that may be useful to those designing and/or integrating modern aircraft electrical systems. The delivered quality of this electrical power is a result of the combined characteristics of the electrical power source, distribution and user equipment. While only user equipment restrictions are specifically defined, background to key source and distribution equipment interfaces are identified in order to support development of the overall system.
A wide variety of electrical supply types and distribution parameters have been considered, as may be found on both small and large transport aircraft. Sources considered include physically rotating and static types, provided either on-aircraft, or as part of the ground support equipment. Distribution voltages addressed are
nominal 14 V, 28 V and 42 V d.c.;nominal 26 V a.c., 400 Hz, one-phase;nominal 115/200 V rms and 230/400 V rms a.c., both one-phase and three-phase, at either a nominal 400 Hz constant frequency (CF), or over a variable frequency (VF) range which includes 400 Hz.
|
Published |
2006-02 |
Edition : 3 |
Number of pages : 56 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO/CD 1540 |
Aerospace — Characteristics of aircraft electrical systems |
ISO 1540:2006 specifies the characteristics of electrical power supplied to the terminals of electrical utilization equipment installed in an aircraft. It is intended to support the interface definition for user equipment designed to accept electrical power on a variety of new civil aircraft applications, such as those certified via the Technical Standard Order (TSO) certification process. It might not be desirable for equipment targeted to a single application or specific military application to follow ISO 1540:2006 because of the penalties associated with multi-application.
ISO 1540:2006 also attempts to provide background to the development of these requirements that may be useful to those designing and/or integrating modern aircraft electrical systems. The delivered quality of this electrical power is a result of the combined characteristics of the electrical power source, distribution and user equipment. While only user equipment restrictions are specifically defined, background to key source and distribution equipment interfaces are identified in order to support development of the overall system.
A wide variety of electrical supply types and distribution parameters have been considered, as may be found on both small and large transport aircraft. Sources considered include physically rotating and static types, provided either on-aircraft, or as part of the ground support equipment. Distribution voltages addressed are
nominal 14 V, 28 V and 42 V d.c.;nominal 26 V a.c., 400 Hz, one-phase;nominal 115/200 V rms and 230/400 V rms a.c., both one-phase and three-phase, at either a nominal 400 Hz constant frequency (CF), or over a variable frequency (VF) range which includes 400 Hz.
|
Under development |
|
Edition : 4 |
|
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 1547:1975 |
Aircraft — Precision fuse-links — General requirements |
Includes the requirements for these components for use in aircraft electrical systems having voltage and frequency characteristics conforming to ISO/R 222, at any ambient temperature from -65 to + 85 °C, and all altitudes from 0 to 24 000 m. Gives terminology, requirements for dimensions, temperature and altitude rating, current, voltage and breaking-capacity ratings, environment, temperature rise, time/current characteristics, endurance, identification and marking, tests, type tests, production routine test, production quality tests and a method of measurement of voltage drop.
|
Published |
1975-12 |
Edition : 1 |
Number of pages : 4 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 1548:1976 |
Aircraft — Precision fuse-links — Type A |
Includes the requirements for these components for use in aircraft electrical systems having voltage and frequency characteristics conforming to ISO/R 222, at any ambient temperature from -65 to +85 degrees centigrade, and all altitudes from 0 to 24 000 m. Gives terminology, requirements for dimensions, current, voltage and breaking-capacity ratings, time/current characteristics and tests.
|
Published |
1976-03 |
Edition : 1 |
Number of pages : 20 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 1549:1976 |
Aircraft — Precision fuse-links — Type B |
Includes the requirements for these components for use in aircraft electrical systems having voltage and frequency characteristics conforming to ISO/R 222, at any ambient temperature from -65 to + 85 °C, and all altitudes from 0 to 24 000 m. Gives terminology, requirements for dimensions, current, voltage and breaking-capacity ratings, time/current characteristics and tests.
|
Published |
1976-03 |
Edition : 1 |
Number of pages : 12 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 1949:1973 |
Design requirements for aircraft electrical plug and socket connectors |
|
Withdrawn |
1973-05 |
Edition : 1 |
Number of pages : 10 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 1949:1987 |
Aircraft — Electrical connectors — Design requirements |
Lays down the general performance requirements and standardization principles. Is intended to cover types designed to use crimped, soldered and welded contacts accommodating aircraft cables. Does not define a particular type dimensionally. Outlines the basic design, mechanical and electrical requirements and basic environmental conditions of operation.
|
Published |
1987-07 |
Edition : 2 |
Number of pages : 12 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 3914-1:1982 |
Textile machinery and accessories — Cylindrical tubes — Part 1: Recommended values of inner diameters and lengths |
|
Withdrawn |
1982-11 |
Edition : 1 |
Number of pages : 2 |
Technical Committee |
59.120.20
Winding machines and equipment
|
| ISO 1966:1973 |
Crimped joints for aircraft electrical cables |
Describes the design requirements and tests for the crimping of insulated and non-insulated terminations to general purpose cables, with conductors of copper, copper alloy, aluminium or aluminium alloy, in locations in which the stabilized conductor temperature does not exceed the values specified for the relevant type, i. e. 105 °C, 190 °C or 260 °C. The type of cable with which the terminations are intended to be made has to be declared.
|
Published |
1973-02 |
Edition : 1 |
Number of pages : 7 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 1967:1974 |
Aircraft — Fire-resisting electrical cables — Dimensions, conductor resistance and mass |
Includes the characteristics of cables with single copper conductors, for use at a nominal voltage of 6OO V, a maximum frequency of 2 OOO Hz and a continuous temperature not exceeding 28O °C (ambient temperature plus heating) but which may withstand 4OO °C for a limited period. The cables will retain a certain amount of dielectric strength when subjected to a flame of 1 1OO °C for 5 min.
|
Published |
1974-02 |
Edition : 1 |
Number of pages : 1 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 2032:1973 |
Heat-resisting equipment wires for aircraft |
Gives the requirements for a range of wires (hook-up wires) designed for the internal wiring of meters, panels and electrical and electronic equipment for use on aircraft. Three classes of wire are specified, type A for use at voltages up to 25O V r. m. s., type B for use up to 6OO V r. m. s. and type C for use up to 1 000 V r. m. s. Includes the requirements for wires with copper conductors, including those with an outer covering in the form of an metal braid.
|
Published |
1973-04 |
Edition : 1 |
Number of pages : 4 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 2042:1973 |
Aircraft electrical circuit diagrams |
Provides for unifomity in the preparation of diagrams to permit the greates ease of drawing consistent with the need for clear definition and legibility. It is intended that these drawing should be of a format suitable for use as production drawings or for reproduction in wiring diagram manuals. A diagram illustrating the application of the principles laid down herein is shown in the annex.
|
Published |
1973-10 |
Edition : 1 |
Number of pages : 4 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 2100:1972 |
Tests for aircraft electrical plug and socket connectors |
|
Withdrawn |
1972-12 |
Edition : 1 |
Number of pages : 11 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 2100:1987 |
Aircraft — Electrical connectors — Tests |
Lays down test procedures and performance requirements. Gives test details relating to the procedure and test results required. Includes contact and insulation resistances, shell continuity, sealing, contact holding force, contact retention, low temperature handling, immersion at low air pressure, resistance to fluids, voltage proof, vibration, thermal shock, endurance, magnetic effect, climatic, acceleration, salt spray, dust, flammability etc.
|
Published |
1987-07 |
Edition : 2 |
Number of pages : 12 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 2155:1974 |
Aircraft — Fire-resisting electrical cables — Performance requirements |
Gives the requirements for cables for the wiring of aircraft circuits, comprising single conductors with copper core covered with nickel or any other material of equivalent properties, suitable for use at a rated voltage up to 6OO V and at a frequency not exceeding 2 OOO Hz. The cables are intended for use at a temperature which may reach 28O °C in continuous service (ambient temperature plus heating) and 4OO °C for a limited period.
|
Published |
1974-02 |
Edition : 1 |
Number of pages : 3 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 2156:1974 |
Aircraft — Fire-resisting electrical cables — Methods of test |
Specifies the tests suitable for establishing the compliance of cables with the performance requirements stated in ISO 2155. Is intended to serve as a basis for test specifications to be included in the relevant national standards when the Official Board of Inspection considers that existing tests are inadequate. The tests are classified in type tests only, type tests and routine productions tests and typ tests and production quality tests.
|
Published |
1974-02 |
Edition : 1 |
Number of pages : 7 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 2277:1973 |
Static invertors for aircraft |
Specifies the general design and test requirements for 4OO Hz inverters. Furthermore gives preferred ratings, supply characteristics, output voltage and frequency, efficiency, regulation response and stability, voltage balance, waveform and modulation of output voltage, control of voltage and frequency, adjustment of voltage, phase sequence, protection, environment, terminal identification, components, radio interference, magnetic influence, starting, cooling, tests, declarations and marking.
|
Published |
1973-04 |
Edition : 1 |
Number of pages : 8 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 2315:1980 |
Aircraft — Two- and four-pole sealed electromagnetic relays, 2 A and 3 A — Clearance and fixing dimensions |
Includes the dimensions of relays with a rated breaking capacity equal to 2 A or 3 A. Applies to the relays currently used for aircraft electrical power systems. The characteristics of these relays will be defined in a future International Standard.
|
Published |
1980-10 |
Edition : 2 |
Number of pages : 8 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 2436:1973 |
Heat-resisting equipment wires for aircraft — Methods of test |
This International Standard specifies the rest procedures suitable for establishing the compliance of wires with the performance requirements stated in ISO 2032. They are intended for use as a basis for specifying tests in the relevant national specifications when the national type approving authorities consider that existing tests are inadequate. The test procedures are classified in type tests only, type and production routine tests and type and production quality tests.
|
Published |
1973-04 |
Edition : 1 |
Number of pages : 2 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 2574:1974 |
Aircraft — Electrical cables — Identification |
|
Withdrawn |
1974-11 |
Edition : 1 |
Number of pages : 1 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 2574:1994 |
Aircraft — Electrical cables — Identification marking |
Specifies the way in which single-core, multi-core and coaxial cables used in the wiring of aircraft are to be marked as to type, size, origin, date etc. in order to facilitate servicing, the investigation of faults and replacement. Also specifies the approved methods for the marking of cores. Supplements those standards relating to marking that already exist. Allows for the codification of manufacturer's identities by individual countries.
|
Published |
1994-06 |
Edition : 2 |
Number of pages : 7 |
Technical Committee |
01.070
Colour coding
;
49.060
Aerospace electric equipment and systems
|
| ISO 2635:1979 |
Aircraft — Conductors for general purpose aircraft electrical cables and aerospace applications — Dimensions and characteristics |
Gives the values of multi-wire conductors over the nominal cross-sectional area range O,15 to 107 mm . Does not apply to conductors for fire-resistant cables or for thermocouple extension cables. Conductors of nominal cross-sectional area 0,25 mm and 0,15 mm are produced in high-strength copper alloy, and conductors of nominal cross-sectional areas greater than 0,25 mm are produced in copper of electrotechnical quality.
|
Withdrawn |
1979-04 |
Edition : 1 |
Number of pages : 2 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 2635:2003 |
Aircraft — Conductors for general purpose aircraft electrical cables and aerospace applications — Dimensions and characteristics |
ISO 2635:2003 specifies the dimensions, electrical characteristics and mechanical characteristics of multi-strand conductors for general-purpose aircraft electrical cables and aerospace applications. It applies to stranded conductors over the nominal cross-sectional area range 0,12 mm2 to 107 mm2 inclusive.
It is not applicable to conductors for fire-resistant cables or for thermocouple extension cables. Conductors for fire-resistant cables are specified in ISO 1967 and for thermocouple extension cables are specified in ISO 8056-1.
|
Published |
2003-11 |
Edition : 2 |
Number of pages : 6 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 2635:2003/Amd 1:2017 |
Aircraft — Conductors for general purpose aircraft electrical cables and aerospace applications — Dimensions and characteristics — Amendment 1: Correction of table 1 |
|
Published |
2017-06 |
Edition : 2 |
Number of pages : 1 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 2678-1:1977 |
Environmental tests for aircraft equipment — Part 1: Insulation resistance and high voltage tests for electrical equipment |
|
Withdrawn |
1977-12 |
Edition : 1 |
Number of pages : 3 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 2678:1985 |
Environmental tests for aircraft equipment — Insulation resistance and high voltage tests for electrical equipment |
Is part of a series of standards specifying tests. The tests given herein have to be considered as two different tests. A high insulation resistance Alone does not prove that the insulation is free from defects. Gives requirements for tests. Relates the insulation requirements to four categories of equipment. Does not deal with the insulation testing of equipment installed in aircraft.
|
Published |
1985-05 |
Edition : 2 |
Number of pages : 3 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 3282:1976 |
Aircraft — Dimensions for single-hole and triple-hole mounting (Class 3) lever-operated manual switches |
Includes the overall dimensions, including terminal screws for switches, having the characteristics specified in ISO 3456. These dimensions shall be in accordance with figure 1 and the table. The holes in the mounting panel for fixing the switch to the panel in the case of single-hole mounting shall be as shown in figure 1a) and in the case of triple-hole mounting as shown in figure 2.
|
Published |
1976-02 |
Edition : 1 |
Number of pages : 2 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 3389:1975 |
Aircraft — Radio frequency flexible coaxial cables — Dimensions and electrical characteristics |
Specifies these quantities for a limited range of cables. Relates to cables in two categories of operational temperature ranges, namely from -40 °C to +85 °C and from -55 °C to +200 °C. An annex is included to list those cables which were in use prior to the publication of this standard. Furthermore describes the construction and manufacture and the designation.
|
Withdrawn |
1975-09 |
Edition : 1 |
Number of pages : 3 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 3456:1975 |
Aircraft — Lever-operated manual switches (Class 3) — Performance requirements |
Specifies the values for single- and triple-hole mounting of these switches for use in nominal 28 V d. c. and 115/200 V three-phase, 400 Hz a. c. systems. They are environmentally sealed and suitable for higher altitude and temperature conditions than are Class 2 switches which are sealed only at the lever entry. They do not have the positive action features of the Class 1 and Class 2 switches specified in ISO 1466.
|
Published |
1975-12 |
Edition : 1 |
Number of pages : 6 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 4084:1977 |
Aircraft — Repairable contactors (not hermetically sealed) — Performance requirements |
Applies to contactors for use in nominal 28 V d. c. or 115/200 V three-phase, 400 Hz a. c. systems having the characteristics specified in ISO 1540. Applies to contactors carrying loads greater than 1 kVA a. c. or 0,5 kW d. c. Three temperature classes and two types of sealing, environmentally sealed and enclosed, are specified. Is applicable to single-pole and multi-pole contactors, electromagnetically operated and magnetically held, or electromagnetically operated and mechanically or magnetically latched, controlled by a voltage of 28 V d. c. or 115 V, 400 Hz a. c.
|
Withdrawn |
1977-12 |
Edition : 1 |
Number of pages : 7 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 5066-1:1986 |
Aircraft — Hermetically sealed monostable electrical relays, 2A and 3A — Part 1: Operating characteristics and test conditions |
Specifies these quantities. Does not specify a particular model of relay as regards dimensions, but proposes limits for the number of variants which may be included in each individual range. Gives a general view of the basic specifications relating to mechanical and electrical construction of these relays and of the basic service environment conditions.
|
Published |
1986-11 |
Edition : 1 |
Number of pages : 6 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 5066-2:1986 |
Aircraft — Hermetically sealed monostable electrical relays, 2A and 3A — Part 2: Type approval tests |
Gives the methods for these relays, the operating characteristics of which are specified in ISO 5066-1. The relays shall be subjected to the tests in the order stipulated in table 8 in the annex of ISO 5066-1 and in accordance with clause 4 herein as regards the preliminary checks and with clause 5 as regards tests No. 1 to 20.
|
Published |
1986-11 |
Edition : 1 |
Number of pages : 8 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 5843-1:1985 |
Aerospace construction — List of equivalent terms — Part 1: Aerospace electrical equipment |
Establishes a list of terms in English, French, Russian and German. The list is given in English in alphabetical order. This list is the first part of equivalent terms used in the field of aerospace construction.
|
Published |
1985-02 |
Edition : 1 |
Number of pages : 26 |
Technical Committee |
49.060
Aerospace electric equipment and systems
;
01.040.49
Aircraft and space vehicle engineering (Vocabularies)
|
| ISO 5866:1983 |
Aircraft — 2 and 3A plug-in base change-over relays, Type II, with crimped connections — Clearance and fixing dimensions |
Lays down the dimensions and specifies the fixing and the designations of these relays. The characteristics and performance requirements will be specified in forthcoming International Standards. Includes definition, dimensions of two pole and four pole relays, arrangement of terminals of bases and dimensions after coupling the contacts, holes in the support, connections for crimping and designation.
|
Published |
1983-11 |
Edition : 1 |
Number of pages : 7 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 5867-1:1996 |
Aircraft — Electromagnetic relays and contactors — Part 1: General requirements |
Performance requirements for electromagnetic relays and contactors for use in nominal 28 V d.c. or 115 V/200 V 3-phase, 400 Hz, a.c. systems having the characteristics specified in ISO 1540. Contains the performance requirements for relays and contactors having nominal contact ratings of 5 A a.c., 5 A d.c. or greater.
|
Published |
1996-02 |
Edition : 1 |
Number of pages : 47 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 6858:1982 |
Aircraft — Ground support electrical supplies — General requirements |
Gives electrical output characteristics, and interface requirements, between an aircraft and ground support electrical supplies. Requirements for safety features are also included. The facilities covered by this International Standard are intended to supply power to an aircraft. In some cases the facility may also be capable of being used for aircraft engine starting.
|
Withdrawn |
1982-08 |
Edition : 1 |
Number of pages : 7 |
Technical Committee |
49.060
Aerospace electric equipment and systems
;
49.100
Ground service and maintenance equipment
|
| ISO 8668-3:1994 |
Aircraft — Terminal junction systems — Part 3: Detail specification for type 1 system |
Specifies the particular characteristics of a terminal junction system, designated as type 1 and intended for use at temperatures between -55 °C and +155 °C. The systems covered herein comprise: feedback modules and feedthrough modules in four sizes; frames adapted to these modules; module clamps and inserts; removable identification tags; removable male crimp contacts of sizes 22, 20, 16 and 12; sealing plugs.
|
Published |
1994-12 |
Edition : 1 |
Number of pages : 22 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 6858:2017 |
Aircraft — Ground support electrical supplies — General requirements |
ISO 6858:2017 specifies the electrical output characteristics and interface requirements between an aircraft and ground support electrical supplies. This includes all external electric power generation facilities, provided as part of a central source or in point-of-use application. Requirements for safety features are also included. Performance and safety issues under regional control are not addressed in this document. Requirements for ground traffic control purposes, such as towing points, identification and warning lights, etc. are also excluded.
The electrical characteristics relate to nominal 28 V DC and either 115/200 V or 230/400 V three-phase, 400 Hz AC outputs measured at the aircraft attaching connector as indicated in Figure 1.
|
Published |
2017-11 |
Edition : 2 |
Number of pages : 35 |
Technical Committee |
49.060
Aerospace electric equipment and systems
;
49.100
Ground service and maintenance equipment
|
| ISO 6859-1:1982 |
Aircraft — Proximity switches — Part 1: General requirements |
Specifies general requirements for aircraft, suitable for use in nominal 28 V d. c. systems, or 115/200 V, 400 Hz a c. systems, having the characteristics specified in ISO 1540. Two classes of switches are specified: class 1: switches for use in unprotected positions on aircraft; class 2: switches intended for less arduous environments.
|
Published |
1982-02 |
Edition : 1 |
Number of pages : 19 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 8056-1:1985 |
Aircraft — Nickel-chromium and nickel-aluminium thermocouple extension cables — Part 1: Conductors — General requirements and tests |
Specifies the design requirements and tests for the conductors of these cables for installation in temperature indicator and control systems. Methods for determining the thermo-e. m. f. of conductor wires against platinum are given in the annex.
|
Published |
1985-04 |
Edition : 1 |
Number of pages : 6 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 8056-2:1988 |
Aircraft — Nickel-chromium and nickel-aluminium thermocouple extension cables — Part 2: Terminations — General requirements and tests |
Includes the design requirements and tests for the crimping of non-insulated terminations to the standard flexible conductors of extension cables in such a manner that the thermoelectric integrity and constancy of resistance of a thermocouple circuit are contained within specified limits.
|
Published |
1988-10 |
Edition : 1 |
Number of pages : 4 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 8056-2:1988/Amd 1:2016 |
Aircraft — Nickel-chromium and nickel-aluminium thermocouple extension cables — Part 2: Terminations — General requirements and tests — Amendment 1 |
|
Published |
2016-07 |
Edition : 1 |
Number of pages : 1 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 8056-3:1987 |
Aircraft — Nickel-chromium and nickel-aluminium thermocouple extension cables — Part 3: Crimp-type ring terminal ends — Dimensions |
Lays down the dimensions for these parts for use in temperature indicator and control systems with flexible thermocouple extension cables at nominal voltage of 600 V and a maximum frequency of 2 000 Hz. Gives conductor size range and cable insulation range.
|
Published |
1987-07 |
Edition : 1 |
Number of pages : 2 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 8056-4:1987 |
Aircraft — Nickel-chromium and nickel-aluminium thermocouple extension cables — Part 4: Crimp-type butt connectors — Dimensions |
Lays down the dimensions for these parts for use in temperature indicator and control systems with flexible thermocouple extension cables at nominal voltage of 600 V and a maximum frequency of 2 000 Hz. Gives conductor size range and cable insulation range.
|
Published |
1987-07 |
Edition : 1 |
Number of pages : 2 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 8668-1:1986 |
Aircraft — Terminal junction systems — Part 1: Characteristics |
Specifies the general operating characteristics and standardization principles. Does not define a specific pattern for the connection system from the point of view of dimensions, but lays down limits for the design and performance for each system. This part lays down the basic requirements for the mechanical structure and electrical performances as well as the basic environmental conditions in service.
|
Published |
1986-10 |
Edition : 1 |
Number of pages : 6 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 8668-2:1986 |
Aircraft — Terminal junction systems — Part 2: Tests |
Describes the test procedures and performance requirements for the characteristics of systems specified in ISO 8668-1. Shall be read in conjunction with it. The tests and performance requirements shall comply with the details given in the table. Deals with contact resistance and measurement of voltage drop in the annex.
|
Published |
1986-10 |
Edition : 1 |
Number of pages : 11 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO/DIS 8668-2 |
Aircraft — Terminal junction systems — Part 2: Tests |
Describes the test procedures and performance requirements for the characteristics of systems specified in ISO 8668-1. Shall be read in conjunction with it. The tests and performance requirements shall comply with the details given in the table. Deals with contact resistance and measurement of voltage drop in the annex.
|
Under development |
|
Edition : 2 |
|
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 8668-4:1993 |
Aircraft — Terminal junction systems — Part 4: Detail specification for type 2 system |
Specifies the particular characteristics of a TJS designated as type 2 and intended for use at temperatures from - 55 °C to + 155 °C. The junction system comprises feedback modules in four sizes; feedthrough modules in four sizes; frames adapted to these modules: monolithic frame and double frame for feedback modules and double frame for feedthrough modules; spacers; removable male crimp contacts of sizes 22, 20, 16 and 12; sealing plugs.
|
Published |
1993-10 |
Edition : 1 |
Number of pages : 29 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 8668-5:1992 |
Aircraft — Terminal junction systems — Part 5: Detail specification for type 3 system |
Gives a description of the design of the type 3 terminal junction system and establishes the specific characteristics for: design requirements, type approval tests, production and quality tests. Shall be read in conjunction with ISO 8668-1 and ISO 8668-2.
|
Published |
1992-07 |
Edition : 1 |
Number of pages : 59 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 8668-6:1994 |
Aircraft — Terminal junction systems — Part 6: Detail specification for type 4 system |
Specifies the specific characteristics of a Terminal Junction System (TJS), designated as type 4 and particularly designed for aircraft applications. Shall be read in conjunction with ISO 8668-1 and ISO 8668-2.
|
Published |
1994-08 |
Edition : 1 |
Number of pages : 56 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 8815:1994 |
Aircraft — Electrical cables and cable harnesses — Vocabulary |
Defines the terms used in the aircraft industry related to aircraft electric cables and cable harnesses.
|
Published |
1994-11 |
Edition : 1 |
Number of pages : 15 |
Technical Committee |
49.060
Aerospace electric equipment and systems
;
01.040.49
Aircraft and space vehicle engineering (Vocabularies)
|
| ISO/DIS 8815 |
Aircraft — Electrical cables and cable harnesses — Vocabulary |
Defines the terms used in the aircraft industry related to aircraft electric cables and cable harnesses.
|
Under development |
|
Edition : 2 |
|
Technical Committee |
49.060
Aerospace electric equipment and systems
;
01.040.49
Aircraft and space vehicle engineering (Vocabularies)
|
| ISO 8816:1993 |
Aircraft — Solid-state remote power controllers — General requirements |
Specifies the general requirements (materials, construction, terminals, enclosures), design and performance requirements (design characteristics, operating characteristics, environmental conditions) and associated tests.
|
Published |
1993-04 |
Edition : 1 |
Number of pages : 18 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 8816:1993/Amd 1:2012 |
Aircraft — Solid-state remote power controllers — General requirements — Amendment 1 |
|
Published |
2012-09 |
Edition : 1 |
Number of pages : 1 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 8843:1991 |
Aircraft — Crimp-removable contacts for electrical connectors — Identification system |
The system specified consists of two colour bands around the external diameter of the crimp barrel and, for thermocouple contacts, of additional letters or of a colour point.
|
Withdrawn |
1991-12 |
Edition : 1 |
Number of pages : 2 |
Technical Committee |
01.070
Colour coding
;
49.060
Aerospace electric equipment and systems
|
| ISO 8843:2005 |
Aircraft — Crimp-removable contacts for electrical connectors — Identification system |
ISO 8843:2005 establishes a system for identifying crimp-removable contacts for electrical connectors. The system specified in this International Standard consists of two colour bands around the external diameter of the crimp barrel and, for thermocouple or high-temperature contacts, of additional letters or of a colour point; the system, however, does not preclude further means being used to identify additional parameters, such as cable size and material.
This contact identification system applies, when specified, to ISO standard contacts. The use of the system is recommended for contacts of both the preferred and non-preferred types. In contacts of the preferred type, the contact active portion and the wire gauge accepted by the contact barrel have the same size. In contacts of the non-preferred type, the size of the active portion of the contact differs from the wire gauge accepted by the crimp barrel.
|
Published |
2005-07 |
Edition : 2 |
Number of pages : 3 |
Technical Committee |
01.070
Colour coding
;
49.060
Aerospace electric equipment and systems
|
| ISO 8843:2005/Amd 1:2012 |
Aircraft — Crimp-removable contacts for electrical connectors — Identification system — Amendment 1 |
|
Published |
2012-09 |
Edition : 2 |
Number of pages : 1 |
Technical Committee |
01.070
Colour coding
;
49.060
Aerospace electric equipment and systems
|
| ISO 6773:1994 |
Aerospace — Fluid systems — Thermal shock testing of piping and fittings |
Cancels and replaces the first edition (1982). Provides an environmental test method for thermal shock testing of fluid system piping and fittings, excluding hose and hose assemblies.
|
Published |
1994-10 |
Edition : 2 |
Number of pages : 2 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO 10296:1992 |
Aircraft — Hybrid remote power controllers — General requirements |
Specifies the general design and performance requirements. The controllers consist of an electromagnetic device or a combined electromagnetic/solid-state device for load switching, and a solid-state control circuit for control of the load-switching devices. On aircraft, they are used to close and open the electrical circuit and to protect wiring and equipment in the event of overload or short-circuit conditions.
|
Published |
1992-08 |
Edition : 1 |
Number of pages : 11 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 12384:2010 |
Aerospace — Requirements for digital equipment for measurements of aircraft electrical power characteristics |
ISO 12384:2010 specifies the requirements for digital measuring methods and digital measuring equipment for aircraft electrical power characteristics, including accuracy, algorithms and digital measuring equipment. The measuring equipment should be applied mainly for the use of laboratory or rig tests.
ISO 12384:2010 can be applied to digital measuring equipment which is involved in the measurement of power electrical characteristics of the power supply system, power distributing systems and the utilization of equipment in aircrafts.
|
Published |
2010-11 |
Edition : 1 |
Number of pages : 13 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 13832:2013 |
Aerospace — Wire, aluminium alloy and copper-clad aluminium conductors — General performance requirements |
ISO 13832:2013 specifies the dimensions, electrical characteristics and mechanical characteristics of aluminium-based and copper-clad aluminium (CCA) conductors, for lightweight aircraft electrical cables and aerospace applications. It applies to stranded conductors over the nominal cross-sectional area range 0,22 mm2 to 107 mm2 inclusive.
It is not applicable to conductors for conventional copper-based cables, fire-resistant cables or for thermocouple extension cables. Conductors for copper-based cables are specified in ISO 2635, for fire-resistant cables are specified in ISO 1967 and for thermocouple extension cables are specified in ISO 8056 1.
|
Published |
2013-03 |
Edition : 1 |
Number of pages : 11 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 20894:2018 |
Aircraft — LED based taxiing lightsystem — General requirements |
This document specifies characteristics and interface requirements for the LED taxiing light system.
|
Published |
2018-09 |
Edition : 1 |
Number of pages : 10 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 20949:2018 |
Aircraft — Smart contactor — General requirements |
This document specifies the definitions, titles of design and general requirements and test methods to determine the performance of smart contactors for use in aircraft electrical power systems. The smart contactor consists of a switching driving circuit and a power switch for protection, action on control signals, and providing status information.
|
Published |
2018-11 |
Edition : 1 |
Number of pages : 24 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO/TR 21891:2017 |
Aerospace electrical requirements — Sleeves and moulded shapes — Specifications for aircraft use |
ISO/TR 21891:2017 brings together, in a single list, those standards for insulation and/or mechanical/environmental protection sleeves and heat shrink moulded shapes that have been determined as being suitable for use on aircraft. The range of sleeves includes heat shrink, extruded (non-heat shrink) and textile.
|
Published |
2017-07 |
Edition : 1 |
Number of pages : 8 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO/IEC TR 22560:2017 |
Information technology — Sensor networks — Use cases of aeronautics industry: Active Air-flow Control |
ISO/IEC TR 22560:2017(E) This Technical Report describes the concepts, issues, objectives, and requirements for the design of an active air-flow control (AFC) system for commercial aircraft based on a dense deployment of wired and wireless sensor and actuator networks. It focuses on the architecture design, module definition, statement of objectives, scalability analysis, system-level simulation, as well as networking and implementation issues using standardized interfaces and service-oriented middleware architectures.
|
Published |
2017-10 |
Edition : 1 |
Number of pages : 45 |
Technical Committee |
35.110
Networking
;
49.060
Aerospace electric equipment and systems
|
| ISO/DIS 24065 |
Aerospace — High power solid state power controller — General performance requirements |
|
Under development |
|
Edition : 1 |
Number of pages : 19 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 24071:2022 |
Aircraft — Auto-transformer rectifier units (ATRUs) — General requirements |
This document specifies the general requirements and test methods for auto-transformer rectifier units (ATRUs) for use in aircraft electrical systems.
This document is mainly applicable to ATRUs of 18-pulse and 24-pulse types.
|
Published |
2022-08 |
Edition : 1 |
Number of pages : 14 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 451:1976 |
Aircraft — Pressure re-oiling connection |
Includes the basic dimensions for use with all oils for aircraft engines, and the clearance envelope to be provided. The dimensions and tolerances of the connection and space envelope are given in the figure and the table.
|
Published |
1976-06 |
Edition : 1 |
Number of pages : 2 |
Technical Committee |
49.080
Aerospace fluid systems and components
;
49.100
Ground service and maintenance equipment
|
| ISO 27027:2008 |
Aerospace — Solid-state remote power controllers — General performance requirements |
ISO 27027:2008 specifies the definitions, general performance requirements and test methods to determine the performance of solid-state (remote) power controllers (SSPC) for use in aerospace electrical power systems.
The solid-state (remote) power controller consists of solid-state switching device(s) and associated solid-state circuitry for protection, action of control signals and providing status information.
|
Withdrawn |
2008-05 |
Edition : 1 |
Number of pages : 13 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO 27027:2014 |
Aerospace — Solid-state remote power controllers — General performance requirements |
ISO 27027:2014 specifies the definitions, titles of general performance requirements, and test methods to determine the performance of solid state (remote) power controller (SSPC) for use in aerospace electrical power systems.
The SSPC consists of solid state-switching device(s) and associated solid-state circuitry for protection, action of control signals, and providing status information.
|
Published |
2014-10 |
Edition : 2 |
Number of pages : 20 |
Technical Committee |
49.060
Aerospace electric equipment and systems
|
| ISO/R 10:1955 |
Withdrawal of ISO/R 10-1955 |
|
Withdrawn |
1955-12 |
Edition : 1 |
Number of pages : 1 |
Technical Committee |
49.080
Aerospace fluid systems and components
;
49.100
Ground service and maintenance equipment
|
| ISO 11:1980 |
Aircraft — Pressure cabin ground test connections |
|
Withdrawn |
1980-03 |
Edition : 1 |
Number of pages : 2 |
Technical Committee |
49.080
Aerospace fluid systems and components
;
49.100
Ground service and maintenance equipment
|
| ISO 11:1987 |
Aircraft — Ground pressure testing connections for pressure cabins |
Specifies the basic dimensional and access clearance requirements for pressure connections on pressurized aircraft for coupling with the hose unit or adaptor of ground pressurizing equipment. Three sizes of connection are specified 22,22 mm, 46,04 mm and 72,39 mm for the recommended cabin volumes: not exceeding 1O m^3, 1O to 45 m^3 and 45 to 170 m^3.
|
Published |
1987-02 |
Edition : 2 |
Number of pages : 2 |
Technical Committee |
49.080
Aerospace fluid systems and components
;
49.100
Ground service and maintenance equipment
|
| ISO 12:1976 |
Aerospace — Pipelines — Identification scheme |
|
Withdrawn |
1976-11 |
Edition : 1 |
Number of pages : 5 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO 12:1987 |
Aerospace — Pipelines — Identification |
Lays down die requirements for a scheme to indicate, by appropriate marking, the functions or contents of rigid pipe assemblies in aircraft and spacecraft systems, but excluding those in aero-engines with the exception of those which connect directly to the airframe systems at their break points. These requirements may also be applied to hose assemblies, if desired. The purpose of the scheme is to provide the minimum identification necessary for normal maintenance purposes.
|
Published |
1987-05 |
Edition : 2 |
Number of pages : 5 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO 45:1990 |
Aircraft — Pressure refuelling connections |
Specifies the basic dimensions and access clearance. The basic dimensions shall be as specified in figure 1. The clearance allowed around the connector shall be in accordance with figure 2.
|
Published |
1990-12 |
Edition : 2 |
Number of pages : 4 |
Technical Committee |
49.050
Aerospace engines and propulsion systems
;
49.080
Aerospace fluid systems and components
;
49.100
Ground service and maintenance equipment
|
| ISO 102:1976 |
Aircraft — Gravity filling orifices |
|
Withdrawn |
1976-04 |
Edition : 1 |
Number of pages : 1 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO 102:1990 |
Aircraft — Gravity filling orifices |
Specifies the minimum internal diameters of the orifice for fuel, lubricants and other fluids.
|
Published |
1990-07 |
Edition : 2 |
Number of pages : 1 |
Technical Committee |
49.080
Aerospace fluid systems and components
;
49.100
Ground service and maintenance equipment
|
| ISO/R 443:1965 |
Marking of aircraft gas cylinders |
|
Withdrawn |
1965-07 |
Edition : 1 |
Number of pages : 2 |
Technical Committee |
01.070
Colour coding
;
49.080
Aerospace fluid systems and components
|
| ISO 450:1976 |
Aircraft — Connection for water of drinkable quality |
|
Withdrawn |
1976-06 |
Edition : 1 |
Number of pages : 1 |
Technical Committee |
49.080
Aerospace fluid systems and components
;
49.100
Ground service and maintenance equipment
|
| ISO 7169:1984 |
Aerospace construction — Separable tube fittings for fluid systems — General specification |
|
Withdrawn |
1984-09 |
Edition : 1 |
Number of pages : 13 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO 1022:1988 |
Aerospace — Gaseous oxygen replenishment connection for use in fluid systems (old type) — Dimensions (Inch series) (Not valid for new designs) |
Specifies the mating dimensions and access clearance. Is not applicable to new designs; for the latter, reference should be made to ISO 8775. The requirements apply to coupling mating dimensions, thread, plugging of orifice and access clearance.
|
Withdrawn |
1988-01 |
Edition : 1 |
Number of pages : 3 |
Technical Committee |
49.080
Aerospace fluid systems and components
;
49.100
Ground service and maintenance equipment
|
| ISO/R 1022:1969 |
Gaseous oxygen replenishment couplings for aircraft |
|
Withdrawn |
1969-03 |
Edition : 1 |
Number of pages : 2 |
Technical Committee |
49.080
Aerospace fluid systems and components
;
49.100
Ground service and maintenance equipment
|