| Name |
Description |
Abstract |
Status |
Publication date |
Edition |
Number of pages |
Technical committee |
ICS |
| ISO 10502:2012 |
Aerospace — Hose assemblies in polytetrafluoroethylene (PTFE) for use up to 232 °C and 10 500 kPa — Technical specifications and requirements |
ISO 10502:2012 specifies requirements for polytetrafluoroethylene (PTFE) hose assemblies for use in aircraft hydraulic, fuel and lubricating oil systems at temperatures between -55 °C (-67 °F) and 232 °C (450 °F) for Class I assemblies and between -55 °C (-67 °F) and 135 °C (275 °F) for Class II assemblies, and at nominal pressures up to 10 500 kPa (1 523 psi) (105 bar). The hose assemblies are also suitable for use within the same temperature and pressure limitations in aerospace pneumatic systems where some gaseous diffusion through the wall of the PTFE liner is tolerated.
ISO 10502:2012 covers hose assemblies of the following classes:
· class I: hose assemblies with fitting of corrosion-resistant steel or titanium parts [232 °C (450 °F)];
· class II: hose assemblies with fitting of corrosion-resistant steel and aluminium parts [135 °C (275 °F)], DN12 and larger.
|
Published |
2012-02 |
Edition : 2 |
Number of pages : 19 |
Technical Committee |
49.080
Aerospace fluid systems and components
;
83.140.40
Hoses
|
| ISO 10583:1993 |
Aerospace fluid systems — Test methods for tube/fitting assemblies |
The test methods specified apply to fitting assemblies used in aircraft fluid systems in the pressure and temperature ranges covered by pressure classes B, D and E, and temperature types I, II and III of ISO 6771. Applies each time that it is referred to in a procurement specification or other definition document which contain the pass/fail criteria for these tests.
|
Published |
1993-05 |
Edition : 1 |
Number of pages : 4 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO/DIS 10583 |
Aerospace fluid systems — Test methods for tube/fitting assemblies |
|
Under development |
|
Edition : 2 |
|
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO 11217:1993 |
Aerospace — Hydraulic system fluid contamination — Location of sampling points and criteria for sampling |
Specifies location and criteria for hydraulic system fluid particulate contamination in aeroplanes, helicopters and space vehicles, and provides indirectly related references. Requirements are specified in SAE ARP 4268 which is adopted as a de facto ISO international Standard. For the purposes of international standardization, the outlined modification shall apply to clause 2 of AS4059A.
|
Withdrawn |
1993-05 |
Edition : 1 |
Number of pages : 1 |
Technical Committee |
49.080
Aerospace fluid systems and components
;
49.100
Ground service and maintenance equipment
|
| ISO 11218:1993 |
Aerospace — Cleanliness classification for hydraulic fluids |
Requirements are specified in SAE AS4059A which is adopted as a de facto ISO international Standard. For the purposes of international standardization, the outlined modification shall apply to the specific clause of AS4059A.
|
Withdrawn |
1993-05 |
Edition : 1 |
Number of pages : 1 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO 11218:2017 |
Aerospace — Cleanliness classification for hydraulic fluids |
ISO 11218:2017 specifies a cleanliness classification for hydraulic fluids in aeroplanes, helicopters and space vehicles.
|
Published |
2017-02 |
Edition : 2 |
Number of pages : 2 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO 11639:2010 |
Aerospace — Part numbering for hose assemblies |
ISO 11639:2010 specifies a hose-assembly designation system and presents a part numbering scheme for aerospace fluid-system hose assemblies.
|
Published |
2010-06 |
Edition : 1 |
Number of pages : 8 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO 12333:2000 |
Aerospace — Constant displacement hydraulic motors — General specifications for 35 000 kPa systems |
|
Withdrawn |
2000-02 |
Edition : 1 |
Number of pages : 24 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO 12334:2000 |
Aerospace — Hydraulic, pressure-compensated, variable delivery pumps — General requirement for 35 000 kPa systems |
|
Withdrawn |
2000-02 |
Edition : 1 |
Number of pages : 28 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO 12584:2013 |
Aerospace — Hydraulic fluid components — Expression of particulate contamination levels |
ISO 12584:2013 defines the method of reporting and communicating the contamination (or cleanliness) level of components used in aerospace fluid systems.
It also presents a coding system which allows cleanliness data to be reported, both in a shortened manner and in a complete manner, when communicating for reporting contamination level measurement results and for specifying cleanliness requirements.
|
Published |
2013-11 |
Edition : 1 |
Number of pages : 10 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO 14085-1:2015 |
Aerospace series — Hydraulic filter elements — Test methods — Part 1: Test sequence |
ISO 14085-1:2015 specifies a test sequence for evaluation of characteristics of the hydraulic fluid filter elements under standard conditions.
ISO 14085-1:2015 is not intended to qualify a filter element under replicate conditions of service; this can only be done by a specific test protocol developed for the purpose, including actual conditions of use, for example the operating fluid or contamination.
The tests data resulting from application of this part of ISO 14085 can be used to compare the performance of aerospace hydraulic filter elements.
|
Published |
2015-03 |
Edition : 1 |
Number of pages : 6 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO 14085-2:2015 |
Aerospace series — Hydraulic filter elements — Test methods — Part 2: Conditioning |
ISO 14085-2:2015 specifies
- a procedure to thermally condition a hydraulic filter element to presumed aerospace hydraulic system stresses,
- a test procedure to complete cold soaks, hot soaks, and temperature variation in a combined manner, and
- a test procedure to simulate cold starts.
ISO 14085-2:2015 is not intended to qualify a filter element under replicate conditions of service; this can only be done by a specific test protocol developed for the purpose, including actual conditions of use, for example the operating fluid or contamination.
ISO 14085-2:2015 is intended to provide a test procedure that yields reproducible thermal test conditioning of a hydraulic filter element, for simulation of the thermal stresses typically encountered in an aerospace hydraulic system.
The conditioning test procedures defined in this part of ISO 14085 are intended to be used prior to performance tests as specified in other parts of this International Standard.
The tests data resulting from application of this part of ISO 14085 can be used to compare the performance of aerospace hydraulic filter elements.
|
Published |
2015-03 |
Edition : 1 |
Number of pages : 13 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO 14085-3:2015 |
Aerospace series — Hydraulic filter elements — Test methods — Part 3: Filtration efficiency and retention capacity |
ISO 14085-3:2015 describes two methods to measure in repeatable conditions the filtration efficiency of filter elements used in aviation and aerospace hydraulic fluid systems. It can be applied when evaluating the overall characteristics of a filter element per ISO 14085‑1, or separately.
Since the filtration efficiency of a filter element can change during its service life as it is clogging, this test method specifies its continuous measurement by using on-line particle counters with continuous injection of test contaminant and recirculation of particles not retained by the test filter element until the differential pressure across the element reaches a given final or "terminal" value.
ISO 14085-3:2015 allows the efficiency to be measured under both steady or cyclic flow conditions. It also is applied to measure the stabilized contamination levels that are produced by the filter element while testing with cyclic flow.
ISO 14085-3:2015 is not intended to qualify a filter element under replicate conditions of service; this can only be done by a specific test protocol developed for the purpose, including actual conditions of use, for example the operating fluid or contamination.
The tests data resulting from application of this part of ISO 14085 can be used to compare the performance of aerospace hydraulic filter elements.
|
Published |
2015-03 |
Edition : 1 |
Number of pages : 37 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO/DIS 14085-3 |
Aerospace series — Test methods for hydraulic filter elements — Part 3: Filtration efficiency and retention capacity |
ISO 14085-3:2015 describes two methods to measure in repeatable conditions the filtration efficiency of filter elements used in aviation and aerospace hydraulic fluid systems. It can be applied when evaluating the overall characteristics of a filter element per ISO 14085‑1, or separately.
Since the filtration efficiency of a filter element can change during its service life as it is clogging, this test method specifies its continuous measurement by using on-line particle counters with continuous injection of test contaminant and recirculation of particles not retained by the test filter element until the differential pressure across the element reaches a given final or "terminal" value.
ISO 14085-3:2015 allows the efficiency to be measured under both steady or cyclic flow conditions. It also is applied to measure the stabilized contamination levels that are produced by the filter element while testing with cyclic flow.
ISO 14085-3:2015 is not intended to qualify a filter element under replicate conditions of service; this can only be done by a specific test protocol developed for the purpose, including actual conditions of use, for example the operating fluid or contamination.
The tests data resulting from application of this part of ISO 14085 can be used to compare the performance of aerospace hydraulic filter elements.
|
Under development |
|
Edition : 2 |
Number of pages : 37 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO 24568:2021 |
Aerospace — Metric series pipe coupling 8°30' up to 28 000 kPa dynamic beam seal — Technical specification |
This document specifies the required characteristics, inspection and test methods, quality assurance and procurement requirements for metric series 8°30’ dynamic beam seal pipe couplings, for temperature ranges type II and III according to ISO 6771 and nominal pressure up to 28 000 kPa.
|
Published |
2021-07 |
Edition : 1 |
Number of pages : 23 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO 14085-4:2015 |
Aerospace series — Hydraulic filter elements — Test methods — Part 4: Verification of collapse/burst pressure rating |
ISO 14085-4:2015 describes a method for verifying the collapse/burst pressure rating of an aerospace hydraulic fluid power filter element. This represents the capability of a filter element to withstand a designated differential pressure in the normal (intended) direction of flow, created by flowing contaminated fluid through the filter element until either collapse/burst occurs or the maximum expected differential pressure is reached without element failure.
The collapse/burst pressure test can be conducted in conjunction with an efficiency test performed according to the procedure defined in the ISO 14085-3 by continuing the contaminant injection until the designated filter element differential pressure is reached.
ISO 14085-4:2015 is not intended to qualify a filter element under replicate conditions of service; this can only be done by a specific test protocol developed for the purpose, including actual conditions of use, for example the operating fluid or contamination.
The tests data resulting from application of this part of ISO 14085 can be used to compare the performance of aerospace hydraulic filter elements.
|
Published |
2015-03 |
Edition : 1 |
Number of pages : 9 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO 14085-5:2015 |
Aerospace series — Hydraulic filter elements — Test methods — Part 5: Resistance to flow fatigue |
ISO 14085-5:2015 specifies a method for determining the resistance of a filter element to flow fatigue caused by varying flow through the filter in various stages of the filter contaminant loading process. The filter is subjected to a uniform varying flow rate for a specified number of cycles, at a number of predetermined differential pressures.
Although the number of cycles and differential pressure conditions used in this part of ISO 14085 is meant to simulate possible service conditions, this part of ISO 14085 is not intended to qualify a filter element under replicate conditions of service; this can only be done by a specific test protocol developed for the purpose, including actual conditions of use, for example the operating fluid, contamination, and exact cyclic flow conditions.
ISO 14085-5:2015 establishes a method for verifying the ability of a filter element to withstand the stress caused by cyclic differential pressures induced by a variable flow rate.
The test data resulting from application of this part of ISO 14085 can be used to compare the performance of aerospace hydraulic filter elements.
|
Published |
2015-03 |
Edition : 1 |
Number of pages : 7 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO 14085-6:2015 |
Aerospace series — Hydraulic filter elements — Test methods — Part 6: Initial cleanliness level |
ISO 14085-6:2015 defines a reference method for determining the level of cleanliness of new filter elements for use in aircraft hydraulic systems, after production prior to shipment, or prior to installation in the circuit.
It applies to filter elements used on systems requiring fluid cleanliness conditions defined in the particular specification.
The tests data resulting from application of this part of ISO 14085 can be used to compare the cleanliness of aerospace hydraulic filter elements.
|
Published |
2015-03 |
Edition : 1 |
Number of pages : 7 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO 14952-1:2003 |
Space systems — Surface cleanliness of fluid systems — Part 1: Vocabulary |
ISO 14952-1:2003 defines the basic terms for use in cleaning processes for equipment and components used in space fluid systems. It is applicable to terms used in the description of processes for the cleaning, analysis and verification of fluid systems used in ground support equipment, launch vehicles and spacecraft.
|
Published |
2003-11 |
Edition : 1 |
Number of pages : 7 |
Technical Committee |
49.080
Aerospace fluid systems and components
;
49.140
Space systems and operations
|
| ISO 14952-2:2003 |
Space systems — Surface cleanliness of fluid systems — Part 2: Cleanliness levels |
ISO 14952-2:2003 defines the cleanliness levels used in the cleaning, analysis, and verification procedures for space fluid systems. It establishes a common nomenclature for use in describing cleanliness levels for equipment used in ground support equipment, launch vehicles and spacecraft.
ISO 14952-2:2003 is used to specify the cleanliness level of fluid system components and equipment used in space systems. It is applicable equally to ground support equipment, launch vehicles and spacecraft.
|
Published |
2003-11 |
Edition : 1 |
Number of pages : 6 |
Technical Committee |
49.080
Aerospace fluid systems and components
;
49.140
Space systems and operations
|
| ISO 14952-3:2003 |
Space systems — Surface cleanliness of fluid systems — Part 3: Analytical procedures for the determination of nonvolatile residues and particulate contamination |
ISO 14952-3:2003 provides sampling and analytical test methods to validate the cleanliness levels of parts and components that have been precision cleaned, and identifies processes that may be used for the verification of cleanliness in ground support equipment, launch vehicles and spacecraft. ISO 14952-3:2003 is used to sample and verify the level of cleanliness of parts and components that have been precision cleaned and applies equally to parts, components and systems in ground support equipment, launch vehicles and spacecraft.
|
Published |
2003-11 |
Edition : 1 |
Number of pages : 15 |
Technical Committee |
49.080
Aerospace fluid systems and components
;
49.140
Space systems and operations
|
| ISO/TR 10201:1989 |
Aerospace — Standards for electronic instruments and systems |
|
Withdrawn |
1989-10 |
Edition : 1 |
Number of pages : 12 |
Technical Committee |
49.090
On-board equipment and instruments
|
| ISO/TR 10201:1991 |
Aerospace — Standards for electronic instruments and systems |
|
Withdrawn |
1991-11 |
Edition : 2 |
Number of pages : 5 |
Technical Committee |
49.090
On-board equipment and instruments
|
| ISO 14952-4:2003 |
Space systems — Surface cleanliness of fluid systems — Part 4: Rough-cleaning processes |
ISO 14952-4:2003 provides requirements related to rough-cleaning processes used to prepare parts and components for precision cleaning. It identifies precleaning processes that can be used for ground support equipment, launch vehicles and spacecraft.
Rough cleaning removes contaminants such as weld scale, heat-treat scale, corrosion, oxide films, oils, grease, shop soil, fuel and carbon deposits. Rough cleaning is considered a normal shop process and usually does not require special environmental controls, packaging, handling or storage beyond accepted good practice.
ISO 14952-4:2003 is applicable equally to ground support equipment, launch vehicles and spacecraft.
|
Published |
2003-11 |
Edition : 1 |
Number of pages : 4 |
Technical Committee |
49.080
Aerospace fluid systems and components
;
49.140
Space systems and operations
|
| ISO 14952-5:2003 |
Space systems — Surface cleanliness of fluid systems — Part 5: Drying processes |
ISO 14952-5:2003 provides guidance related to processes used to dry parts and components that have been subjected to solvent-based or water-based cleaning processes, and identifies drying processes that can be used for equipment that has been cleaned for use in ground support equipment, launch vehicles and spacecraft. Vacuum drying can be used to remove entrapped fluids from intricate parts when normal purging methods have been found to be ineffective.
|
Published |
2003-11 |
Edition : 1 |
Number of pages : 3 |
Technical Committee |
49.080
Aerospace fluid systems and components
;
49.140
Space systems and operations
|
| ISO 14952-6:2003 |
Space systems — Surface cleanliness of fluid systems — Part 6: Precision-cleaning processes |
ISO 14952-6:2003 specifies precision-cleaning processes for parts, components and systems used in flight-critical fluid applications. It can be used on equipment for ground support equipment, launch vehicles and spacecraft.
ISO 14952-6:2003 identifies precision-cleaning processes and procedures that can be used on parts and components used in fluid systems and is applicable equally to ground support equipment, launch vehicles and spacecraft.
|
Published |
2003-11 |
Edition : 1 |
Number of pages : 7 |
Technical Committee |
49.080
Aerospace fluid systems and components
;
49.140
Space systems and operations
|
| ISO 16031-1:2002 |
Aerospace fluid systems — O-rings, inch series: Inside diameters and cross sections, tolerances and size-identification codes — Part 1: Close tolerances for hydraulic systems |
ISO 16031-1 specifies the inside diameters, cross-sections, tolerances and size identification codes for inch O-rings used in aerospace fluid systems.
The dimensions and high precision tolerances specified in ISO 16031-1 are suitable for nitrile and ethylene propylene materials intended for use in high pressure hydraulic fluid systems provided that suitable tooling be available.
|
Published |
2002-06 |
Edition : 1 |
Number of pages : 15 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO 16031-2:2003 |
Aerospace fluid systems — O-rings, inch series: Inside diameters and cross-sections, tolerances and size-identification codes — Part 2: Standard tolerances for non-hydraulic systems |
ISO 16031-2:2003 specifies the inside diameters, cross-sections, tolerances and size identification codes for inch O-rings used in aerospace fluid systems intended for use in non-hydraulic systems.
ISO 16031-2:2003 is applicable, provided that suitable tooling is available, to O-rings made from all other elastomeric materials other than nitrile and ethylene propylene materials, for which ISO 16031-1 specifies the dimensions.
Specifications for O-rings with an inside diameter up to 12,7 mm have been taken from ISO 16031-1, because the same tolerances are applicable to the O-rings in ISO 16031-2:2003.
|
Published |
2003-09 |
Edition : 1 |
Number of pages : 13 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO 17775:2006 |
Aircraft — Ground-service connections — Potable water, toilet-flush water and toilet drain |
ISO 17775:2006 specifies the detail dimensions of the male connector interfaces, fitted to an aircraft, used for servicing of the potable water systems, the toilet-flush water systems, and the toilet drain systems currently in common use. ISO 17775:2006 is applicable to all commercial aircraft with water and toilet systems and is recommended for military and private aircraft that use water and toilet systems.
ISO 17775:2006 does not include requirements for the ground half (female) couplings or protective caps, but provides sufficient interface details for such items to be designed. It does not include any specified dimensions for the clearance required around the connector on the aircraft body itself for either any protective caps or ground half couplings, although general recommendations are made.
|
Published |
2006-12 |
Edition : 1 |
Number of pages : 3 |
Technical Committee |
49.080
Aerospace fluid systems and components
;
49.100
Ground service and maintenance equipment
|
| ISO 18170:2017 |
Aerospace series — AC induction electric motor driven, variable delivery, hydraulic pumps — General requirements |
ISO 18170:2017 establishes the general requirements for electric motor driven, variable delivery, hydraulic pumps suitable for use in aircraft hydraulic systems.
ISO 18170:2017 includes the general requirements for Alternating Current (AC) induction electric motor powered units. The AC power electrical power supply can be either controlled to provide a Constant Frequency (CF) or uncontrolled to provide a Variable Frequency (VF) AC supply to the electric motor.
ISO 18170:2017 is intended to be used in conjunction with the detail specification that is particular to each application.
|
Published |
2017-04 |
Edition : 1 |
Number of pages : 54 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO/DIS 18170 |
Aerospace series — AC induction electric motor driven, variable delivery, hydraulic pumps — General requirements |
ISO 18170:2017 establishes the general requirements for electric motor driven, variable delivery, hydraulic pumps suitable for use in aircraft hydraulic systems.
ISO 18170:2017 includes the general requirements for Alternating Current (AC) induction electric motor powered units. The AC power electrical power supply can be either controlled to provide a Constant Frequency (CF) or uncontrolled to provide a Variable Frequency (VF) AC supply to the electric motor.
ISO 18170:2017 is intended to be used in conjunction with the detail specification that is particular to each application.
|
Under development |
|
Edition : 2 |
Number of pages : 54 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO 18387:2019 |
Aerospace — Linear hydraulic utility actuator — General specifications |
This document establishes the general requirements for a linear hydraulic utility actuator, herein referred to as a "utility actuator", for use in flight vehicle hydraulic systems at pressures up to 35 000 kPa (5 000 psi).
These requirements include:
— design requirements;
— test requirements.
This document is intended to be used in conjunction with the detail specification that is particular to each application.
NOTE Although Brake pistons and Landing Gear Bogie (Truck) Pitch Trimmers are utility actuators, they are outside the scope of this document. This is because these devices are considered to be specialist actuator devices due to their specific duty cycles requiring a separate set of tailored requirements.
|
Published |
2019-09 |
Edition : 1 |
Number of pages : 47 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO 18487-1:2017 |
Aerospace series — Titanium tube for 35 MPa operating pressure — Part 1: Inch series |
ISO 18487-1:2017 is applicable to seamless tubing of circular cross-section made from titanium alloy and intended for use primarily in systems with system operating pressure of 35 MPa (5 080 psi) (Pressure Class J), but usage is not limited to such applications.
|
Published |
2017-04 |
Edition : 1 |
Number of pages : 13 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO 19631:2015 |
Aerospace series — Tube fittings for fluid systems, 5 080 psi (35 000 kPa) — Qualification specification |
ISO 19631:2015 specifies performance and quality requirements for the qualification and manufacture of standard tube fittings to ensure reliable performance in aircraft hydraulic 5 080 psi (35 000 kPa) systems.
ISO 19631:2015 specifies baseline criteria for the design and manufacture of system fittings that are qualification tested on engines.
ISO 19631:2015 covers fittings from size ?04 to ?20 used for the following:
? separable/permanent pipe end fittings;
? permanent connection fittings;
? separable connection fittings.
ISO 19631:2015 covers fittings of the temperature types and pressure classes specified in ISO 6771.
|
Published |
2015-09 |
Edition : 1 |
Number of pages : 20 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO 19632:2015 |
Aerospace series — Fitting end, 24° internal cone, external thread, flareless type extra fine thread pitch inch series — Design standard |
ISO 19632:2015 specifies the dimensions, tolerances and the required characteristics of a fitting end, 24° cone, external thread, flareless type, size ‑04 up to ‑20 for use in hydraulic and fluid systems at 35 000 kPa (5 080 psi), diameter 6,35 mm ≤ D ≤ 31,75 mm (1/4 inch ≤ D ≤ 1 1/4 inch) for aerospace applications.
This is a design standard.
|
Published |
2015-07 |
Edition : 1 |
Number of pages : 7 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO 22072:2005 |
Aerospace — Electrohydrostatic actuator (EHA) — Characteristics to be defined in procurement specifications |
ISO 22072:2005 defines the general characteristics, requirements and design data to be included in the procurement technical specification of an electrohydrostatic actuator (EHA) to be used to power aircraft control surfaces or other moving parts of an aerospace vehicle.
|
Withdrawn |
2005-06 |
Edition : 1 |
Number of pages : 11 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO 22072:2011 |
Aerospace — Electrohydrostatic actuator (EHA) — Characteristics to be defined in procurement specifications |
ISO 22072:2011 defines the general characteristics, requirements and design data to be included in the procurement technical specification of an electrohydrostatic actuator (EHA) to be used to power aircraft control surfaces or other moving parts of an aerospace vehicle.
This type of actuator is an alternative to the hydraulically powered servo-control actuators that are currently used. It is intended that ISO 22072:2011 cover the unique requirements of EHAs.
|
Published |
2011-08 |
Edition : 2 |
Number of pages : 12 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO 22089:2009 |
Aerospace — Hydraulic power transfer units — General specifications |
ISO 22089:2009 establishes the general requirements for hydraulic Power Transfer Units (PTUs)
ISO 22089:2009 covers uni-directional and bi-directional PTUs.
ISO 22089:2009 is used in conjunction with the detail specification particular to each application.
|
Published |
2009-02 |
Edition : 1 |
Number of pages : 48 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO/TR 10201:1996 |
Aerospace — Standards for electronic instruments and systems |
|
Withdrawn |
1996-06 |
Edition : 3 |
Number of pages : 16 |
Technical Committee |
49.090
On-board equipment and instruments
|
| ISO/TR 10201:2001 |
Aerospace — Standards for electronic instruments and systems |
|
Withdrawn |
2001-03 |
Edition : 4 |
Number of pages : 16 |
Technical Committee |
49.090
On-board equipment and instruments
|
| ISO 22181:2021 |
Aerospace fluid systems and components — Variable displacement hydraulic motors — General specifications |
This document establishes the general requirements for variable displacement uni-directional and bi-directional hydraulic motors, suitable for use in aircraft hydraulic systems at pressures up to 35 000 kPa (5 000 psi).
These requirements include:
— design requirements;
— test requirements.
Primary and secondary function motors (see Clause 4) are covered in this document; however, actuators with internal rotation angle limits and low-speed motors are not covered.
This document is intended to be used in conjunction with the detail specification that is particular to each application.
|
Published |
2021-02 |
Edition : 1 |
Number of pages : 38 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO 22431:2018 |
Aerospace series — Pipe coupling 8°30' — Dynamic beam seal end for ferrule, welded — Geometric configuration |
ISO 22431:2018 specifies the dimensions of the dynamic beam seal end for welded ferrules for pipe couplings 8°30′, nominal pressure up to 28 000 kPa, for aerospace applications.
|
Published |
2018-03 |
Edition : 1 |
Number of pages : 4 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO 22433:2018 |
Aerospace series — Pipe coupling 8°30' — Dynamic beam seal end for elbows, tees and crosses — Geometric configuration |
ISO 22433:2018 specifies the dimensions of the dynamic beam seal end for elbows, tees and crosses for pipe couplings 8°30′, nominal pressure up to 28 000 kPa, for aerospace applications.
|
Published |
2018-03 |
Edition : 1 |
Number of pages : 3 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO 22436:2018 |
Aerospace series — Pipe coupling 8°30' — Thread end — Geometric configuration |
ISO 22436:2018 specifies the characteristics of the thread end for 8°30′ pipe couplings, nominal pressure up to 28 000 kPa, for aerospace applications.
|
Published |
2018-03 |
Edition : 1 |
Number of pages : 8 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO 22437:2018 |
Aerospace series — Pipe coupling 8°30' in titanium alloy — Nut for welded ferrule |
ISO 22437:2018 specifies the characteristics of nuts for welded ferrules, for pipe couplings 8°30′, in titanium alloy, for aerospace applications.
Nominal pressure: up to 28 000 kPa
Temperature range: −55 °C to 135 °C
|
Withdrawn |
2018-03 |
Edition : 1 |
Number of pages : 4 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO 22438:2018 |
Aerospace series — Pipe coupling 8°30' in titanium alloy — Thrust wires |
ISO 22438:2018 specifies the characteristics of thrust wires for attaching thrust wire nuts onto tees and elbows for pipe couplings 8°30′, for aerospace applications.
|
Withdrawn |
2018-03 |
Edition : 1 |
Number of pages : 3 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO 23748:2016 |
Aerospace series — O-ring grooves — Dimensions |
ISO 23748:2016 specifies the dimensions of grooves for use with O-rings for aerospace in static sealing applications:
- radial sealing: rod or bore mounted O-rings;
- axial sealing: internal or external pressure source.
|
Published |
2016-10 |
Edition : 1 |
Number of pages : 30 |
Technical Committee |
49.080
Aerospace fluid systems and components
;
49.100
Ground service and maintenance equipment
|
| ISO 23748:2016/Amd 1:2021 |
Aerospace series — O-ring grooves — Dimensions — Amendment 1 |
|
Published |
2021-02 |
Edition : 1 |
Number of pages : 1 |
Technical Committee |
49.080
Aerospace fluid systems and components
;
49.100
Ground service and maintenance equipment
|
| ISO 23933:2006 |
Aerospace — Aramid reinforced lightweight polytetrafluoroethylene (PTFE) hose assemblies, classification 135 degrees C/20 684 kPa (275 degrees F /3 000 psi) and 135 degrees C/21 000 kPa (275 degrees F/3 046 psi) — Procurement specification |
ISO 23933:2006 specifies requirements for aramid reinforced lightweight polytetrafluoroethylene (PTFE) hose assemblies for use in aircraft hydraulic, oil and fuel systems at temperatures between -55 °C and 135 °C (-65 °F and 275 °F) and at a nominal pressure of 21 000 kPa (210 bar) (3 046 psi) or 20 684 kPa (3 000 psi). The hose assemblies are also suitable for use within the same temperature and pressure limitations in aircraft pneumatic systems where some gaseous diffusion through the wall of the PTFE liner may be tolerated.
|
Published |
2006-01 |
Edition : 1 |
Number of pages : 23 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO 23935:2006 |
Aircraft — Environmental test procedures for airborne fluid system components — Resistance to fire in designated fire zones |
ISO 23935:2006 specifies the requirements for tests which may be applied to all fluid system components located in zones designated as "fire zones" and built to satisfy the minimum level specified for withstanding fire.
It does not relate to withstanding fire outside designated fire zones, nor to flammability requirements, or to those conditions induced by the flame coming from the combustion chamber.
|
Published |
2006-06 |
Edition : 1 |
Number of pages : 5 |
Technical Committee |
49.080
Aerospace fluid systems and components
|
| ISO 3004-4:1986 |
Light gauge metal containers — Capacities and related cross-sections — Part 4: Open-top cans for edible oil |
|
Withdrawn |
1986-10 |
Edition : 2 |
Number of pages : 2 |
Technical Committee |
55.120
Cans. Tins. Tubes
|
| ISO 27996:2009 |
Aerospace fluid systems — Elastomer seals — Storage and shelf life |
ISO 27996:2009 is applicable to the general requirements for data recording procedures, packaging, and storing of elastomeric seals and seal assemblies which include an elastomeric element prior to the seal being assembled into hardware components.
The requirements for packaging are an integral part of the controlled storage procedure and provide a means of positive product identity from the time of manufacture to the time of assembly into a component.
ISO 27996:2009 does not establish limitations or storage times for assembled components nor the operating life of these components.
The information contained in ISO 27996:2009 is intended for use by those organizations that do not have specific requirements or recommendations already in place for the control of elastomeric seals and seal assemblies.
ISO 27996:2009 can be specified in control, storage and procurement documents. However, when the requirements of ISO 27996:2009 are in conflict with the customer's requirements or specifications, the requirements of the customer's detailed specifications take precedence.
|
Published |
2009-02 |
Edition : 1 |
Number of pages : 8 |
Technical Committee |
49.080
Aerospace fluid systems and components
;
83.140.50
Seals
|
| ISO/DIS 27996 |
Aerospace fluid systems — Elastomer seals — Storage and shelf life |
ISO 27996:2009 is applicable to the general requirements for data recording procedures, packaging, and storing of elastomeric seals and seal assemblies which include an elastomeric element prior to the seal being assembled into hardware components.
The requirements for packaging are an integral part of the controlled storage procedure and provide a means of positive product identity from the time of manufacture to the time of assembly into a component.
ISO 27996:2009 does not establish limitations or storage times for assembled components nor the operating life of these components.
The information contained in ISO 27996:2009 is intended for use by those organizations that do not have specific requirements or recommendations already in place for the control of elastomeric seals and seal assemblies.
ISO 27996:2009 can be specified in control, storage and procurement documents. However, when the requirements of ISO 27996:2009 are in conflict with the customer's requirements or specifications, the requirements of the customer's detailed specifications take precedence.
|
Under development |
|
Edition : 2 |
Number of pages : 8 |
Technical Committee |
49.080
Aerospace fluid systems and components
;
83.140.50
Seals
|
| ISO 268:1980 |
Aircraft — Mechanical and electromechanical indicators — General requirements |
States the requirements which are generally applicable. Is to be read in conjunction with specifications for individual indicators. An indicator is regarded as a unit primarily concerned with the visual display of information. The size and type of the finished indicator case shall be declared by the manufacturer in sufficient detail to facilitate subsequent installation.
|
Published |
1980-07 |
Edition : 1 |
Number of pages : 5 |
Technical Committee |
49.090
On-board equipment and instruments
|
| ISO 5065-1:1986 |
Aircraft — Magnetic indicators — Part 1: Characteristics |
Specifies the general operating characteristics and standardization principles. Lays down the basic requirements relating to the mechanical and electrical characteristics as well as the basic environmental conditions in service. ISO 5065-2 gives details of the tests referred to in this part of ISO 5065. Includes design requirements, type approval testing and production and quality testing.
|
Published |
1986-10 |
Edition : 1 |
Number of pages : 6 |
Technical Committee |
49.090
On-board equipment and instruments
|
| ISO 5065-2:1986 |
Aircraft — Magnetic indicators — Part 2: Tests |
Gives the test procedures and performance requirements for the characteristics of these devices specified in ISO 5065-1 and shall be read in conjunction with it. The requirements shall comply with the details given in the table. It includes contact forces, supply voltage and current consumption, lamps, insulation resistance, thermal shock, low and high temperature operation, damp heat, life, acceleration, vibration, mechanical shock, temperature and altitude, resistance to fluids, drip test, sand and dust.
|
Published |
1986-10 |
Edition : 1 |
Number of pages : 7 |
Technical Committee |
49.090
On-board equipment and instruments
|
| ISO 6702-1:1991 |
Aircraft — Requirements for on-board weight and balance systems — Part 1: General |
Specifies requirements for the function, characteristics, and installation of an on-board weight and balance system for use on civil transport aircraft. This first edition cancels and replaces the first edition ISO 6702:1984.
|
Published |
1991-11 |
Edition : 1 |
Number of pages : 14 |
Technical Committee |
49.090
On-board equipment and instruments
;
49.120
Cargo equipment
|
| ISO 6702-2:1991 |
Aircraft — Requirements for on-board weight and balance systems — Part 2: Design, performance and interface characteristics |
Requirements are specified in ARINC 737:1985 together with its Supplement 1 (1988), which are adopted as a de facto ISO International Standard.
|
Published |
1991-11 |
Edition : 1 |
Number of pages : 1 |
Technical Committee |
49.090
On-board equipment and instruments
;
49.120
Cargo equipment
|
| ISO 6702:1984 |
Aircraft — Requirements for on board weight and balance control systems |
|
Withdrawn |
1984-12 |
Edition : 1 |
Number of pages : 4 |
Technical Committee |
49.090
On-board equipment and instruments
;
49.120
Cargo equipment
|
| ISO/R 837:1968 |
Aircraft seat rails and pins |
|
Withdrawn |
1968-10 |
Edition : 1 |
Number of pages : 3 |
Technical Committee |
49.095
Passenger and cabin equipment
|
| 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 43:1976 |
Aircraft — Jacking pads |
Specifies the profiles and dimensions of main and axle jacking pads and the clear space to be provided around these pads. They are to be limited to the six designs shown in the figures 1 to 6, which specify the shape, size and clearances to be provided around the pads.
|
Withdrawn |
1976-07 |
Edition : 1 |
Number of pages : 4 |
Technical Committee |
49.100
Ground service and maintenance equipment
|
| ISO 43:2016 |
Aircraft — Jacking pads |
ISO 43:2016 specifies the profiles and dimensions of aircraft jacking pads and the minimum clearance to be provided around them. Aircraft jacking pads, also called adapters, can be attached to primary flight structure (PFS) or to axles.
|
Published |
2016-11 |
Edition : 2 |
Number of pages : 2 |
Technical Committee |
49.100
Ground service and maintenance equipment
|
| ISO 45:1980 |
Aircraft — Pressure refuelling connections |
|
Withdrawn |
1980-05 |
Edition : 1 |
Number of pages : 4 |
Technical Committee |
49.050
Aerospace engines and propulsion systems
;
49.100
Ground service and maintenance equipment
|
| 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 46:1973 |
Aircraft — Fuel nozzle grounding plugs and sockets |
Includes the dimensions of grounding plugs to be attached by cable to the nozzles of aircraft refuelling tankers. Details are also given of the sockets to be provided in the aircraft for the accomodation of the plugs and the minimum length, minimum diameter and material of the grounding cable.
|
Published |
1973-06 |
Edition : 1 |
Number of pages : 1 |
Technical Committee |
49.100
Ground service and maintenance equipment
|
| 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 405:1964 |
Aircraft tow bar connections to tractors |
|
Withdrawn |
1964-12 |
Edition : 1 |
Number of pages : 1 |
Technical Committee |
49.100
Ground service and maintenance equipment
|
| ISO 413:1974 |
Aircraft — Heads of lubricating nipples |
Specifies the envelope dimensions of axial type nipples and determines the clearance space which shall be provided in the region of the nipple to allow the lubricating gun to be connected, and the operating angle dimensions for the lubricating process. The tip design of the nipples is optional provided the profile remains within the envelope shown in figure 1.
|
Published |
1974-11 |
Edition : 1 |
Number of pages : 1 |
Technical Committee |
49.035
Components for aerospace construction
;
49.100
Ground service and maintenance equipment
|
| 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 3691:1980 |
Powered industrial trucks — Safety code |
Specifies the safety requirements for the manufacture, application, operation and maintenance of powered industrial trucks.
|
Withdrawn |
1980-11 |
Edition : 2 |
Number of pages : 35 |
Technical Committee |
53.060
Industrial trucks
|
| 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 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 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 1021:1980 |
Aircraft — Engine nacelle fire extinguisher apertures and doors |
Relates to openings for the insertion of the nozzles of ground fire extinguishing equipment. If one or more openings are provided, they shall be either round or square in shape and of the following dimensions: Round; the diameter shall be from 1OO mm minimum to 13O mm maximum; Square; the sides of the squares shall be from 1OO mm minimum to 13O mm maximum.
|
Published |
1980-10 |
Edition : 1 |
Number of pages : 1 |
Technical Committee |
49.100
Ground service and maintenance equipment
|
| 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
|
| ISO 1023:1974 |
Aircraft — High pressure air charging valves |
Includes the coupling dimensions and access clearance. The basic dimensions of the valve and the access clearance to be provided shall conform to the requirements of figure 1. The valves shall be provided at the coupling end with a srew thread conforming to the requirements of figure 2. The valves are given in tables.
|
Withdrawn |
1974-07 |
Edition : 1 |
Number of pages : 2 |
Technical Committee |
49.080
Aerospace fluid systems and components
;
49.100
Ground service and maintenance equipment
|
| ISO 1034:1973 |
Aircraft — Ground air-conditioning connections |
Gives the requirements for 127 mm and 203 mm connections for the purpose of air-conditioning from ground sources. The conncetions shall comply with the basic dimensional requirements shown in either figure 1 or figure 2 as appropriate. The ground unit must not project more than 14,O mm beyond the sealing plane except through defined openings.
|
Published |
1973-06 |
Edition : 1 |
Number of pages : 2 |
Technical Committee |
49.080
Aerospace fluid systems and components
;
49.100
Ground service and maintenance equipment
|
| ISO 1464:1979 |
Aircraft — Clearance dimensions for tripod jacks |
|
Withdrawn |
1979-09 |
Edition : 1 |
Number of pages : 2 |
Technical Committee |
49.100
Ground service and maintenance equipment
|
| ISO 1464:1985 |
Aerospace — Tripod jacks — Clearance dimensions |
Specifies the minimum clear space to be provided beneath the aircraft main jacking points. Is not intended to define fully all jack clearance deminsions. In situations where clearances are critical, it should be used as a design aid only. Final critical clearances should be established by using actual jack dimensions.
|
Withdrawn |
1985-05 |
Edition : 2 |
Number of pages : 4 |
Technical Committee |
49.100
Ground service and maintenance equipment
|
| ISO 1464:2018 |
Aerospace — Tripod jacks — Clearance dimensions |
ISO 1464:2018 specifies the minimum clear space to be provided beneath the aircraft main jacking points, in order to accommodate tripod jacks and thus ensure adequate clearance between the jacks and the adjacent aircraft structure.
ISO 1464:2018 is not intended to define fully all jack clearance dimensions. In situations where clearances are critical, it is used as a design aid only. Final critical clearances are established by using actual jack dimensions.
|
Published |
2018-01 |
Edition : 3 |
Number of pages : 4 |
Technical Committee |
49.100
Ground service and maintenance equipment
|
| ISO 1465:1976 |
Aircraft — Liquid oxygen replenishment couplings — Mating dimensions |
|
Withdrawn |
1976-06 |
Edition : 1 |
Number of pages : 3 |
Technical Committee |
49.080
Aerospace fluid systems and components
;
49.100
Ground service and maintenance equipment
|
| ISO 1465:1989 |
Aircraft — Liquid oxygen replenishment couplings — Mating dimensions |
Specifies the mating and clearance dimensions. The mating dimensions and characteristics of the ground half shall conform to those in figure 1 and table 1. The aircraft half shall mate with the ground half. The clearance envelope in the aircraft to accommodate the ground half for the purposes of coupling and uncoupling the hose unit shall be in accordance with figure 2 and table 2.
|
Published |
1989-09 |
Edition : 2 |
Number of pages : 3 |
Technical Committee |
49.080
Aerospace fluid systems and components
;
49.100
Ground service and maintenance equipment
|
| ISO 1825:1975 |
Rubber hoses for aircraft ground fuelling without static conducting wire |
|
Withdrawn |
1975-03 |
Edition : 1 |
Number of pages : 2 |
Technical Committee |
49.100
Ground service and maintenance equipment
;
83.140.40
Hoses
|
| ISO 1825:1996 |
Rubber hoses and hose assemblies for aircraft ground fuelling and defuelling — Specification |
Gives requirements for six types of hose and hose assembly for use in all operations associated with the ground fuelling and defuelling of aircraft. Replaces the first edition.
|
Withdrawn |
1996-12 |
Edition : 2 |
Number of pages : 24 |
Technical Committee |
49.100
Ground service and maintenance equipment
;
83.140.40
Hoses
|
| ISO 1825:2010 |
Rubber hoses and hose assemblies for aircraft ground fuelling and defuelling — Specification |
ISO 1825:2010 specifies the dimensions and construction of, and requirements for, four types of hose and hose assembly for use in all operations associated with the ground fuelling and defuelling of aircraft.
All four types are designed for
use with petroleum fuels having an aromatic-hydrocarbon content not exceeding 30 % by volume;
operation within the temperature range of -30 °C to +65 °C and such that they will be undamaged by climatic conditions of -40 °C to +70 °C when stored in static conditions;
operation at up to 2,0 MPa (20 bar) maximum working pressure, including surges of pressure which the hose can be subjected to in service.
|
Withdrawn |
2010-03 |
Edition : 3 |
Number of pages : 27 |
Technical Committee |
49.100
Ground service and maintenance equipment
;
83.140.40
Hoses
|
| ISO 3174:1994 |
Aircraft — Connections for checking hydraulic systems by ground appliances — Threaded type |
Cancels and replaces the first edition (1981). Specifies the requirements for connections installed in aircraft hydraulic system pressure and suction lines, intended for checking the systems by means of ground appliances.
|
Published |
1994-12 |
Edition : 2 |
Number of pages : 9 |
Technical Committee |
49.080
Aerospace fluid systems and components
;
49.100
Ground service and maintenance equipment
|
| ISO 4116:1980 |
Ground equipment requirements for compatibility with aircraft unit load devices |
|
Withdrawn |
1980-10 |
Edition : 1 |
Number of pages : 4 |
Technical Committee |
49.100
Ground service and maintenance equipment
;
49.120
Cargo equipment
|
| ISO 1825:2017 |
Rubber hoses and hose assemblies for aircraft ground fuelling and defuelling — Specification |
ISO 1825:2017 specifies the dimensions and construction of, and requirements for, four types of hose and hose assembly for use in all operations associated with the ground fuelling and defuelling of aircraft.
All four types are designed for:
a) use with petroleum fuels having an aromatic-hydrocarbon content not exceeding 30 % by volume;
b) operation within the temperature range of −30 °C to +65 °C and such that they will be undamaged by climatic conditions of −40 °C to +70 °C when stored in static conditions;
c) operation at up to 2,0 MPa (20 bar) maximum working pressure, including surges of pressure which the hose can be subjected to in service.
NOTE 1 Type C hoses are intended for general pressure applications on all vehicles used for plane fuelling. They can also be used for vehicle/rail car loading and discharge where excessive vacuum does not occur.
NOTE 2 Type F hoses can be used for plane delivery applications on vehicles that are also used for defuelling at high flow rates where type C hoses are not suitable.
NOTE 3 Type E and F hoses can also be used for vehicle/rail car loading and discharge, for trailer to fueller transfer and for elevation platform supply (riser) to provide greater kink resistance.
|
Published |
2017-11 |
Edition : 4 |
Number of pages : 27 |
Technical Committee |
49.100
Ground service and maintenance equipment
;
83.140.40
Hoses
|
| ISO 1950:1974 |
Aircraft — Identification of servicing, maintenance, ground handling and safety/hazard points |
Includes the symbols, and their positions and sizes, to be used for the marking of these points, to enable them to be quickly identified during intermediate stops an scheduled flights and during scheduled maintenance checks. Requirements for warning markings, to prevent damage to equipment or injury to personnel, and for the marking of batches are also included.
|
Withdrawn |
1974-05 |
Edition : 1 |
Number of pages : 7 |
Technical Committee |
49.100
Ground service and maintenance equipment
|
| ISO 2026:1974 |
Aircraft — Connections for starting engines by air |
Specifies the dimensions which are necessary to ensure international interchangeability of connectors with adaptors. Also gives the minimum clearances required on the aircraft to provide adequate access for the ground adaptor. The basic dimensions and tolerances for connections on aircraft and the minimum clearances around the connector, on the aircraft, are given in figure 1 and table 1 and figure 2 and table 2, respectively.
|
Withdrawn |
1974-11 |
Edition : 1 |
Number of pages : 4 |
Technical Committee |
49.080
Aerospace fluid systems and components
;
49.100
Ground service and maintenance equipment
|
| ISO 2026:2020 |
Aircraft — Connections for starting engines by air |
This document specifies the dimensions of connections for starting aircraft engines by air, which are necessary to ensure international interchangeability of connectors with adaptors. lt also gives the minimum clearances required on the aircraft to provide adequate access for the ground adaptor.
|
Published |
2020-06 |
Edition : 2 |
Number of pages : 5 |
Technical Committee |
49.080
Aerospace fluid systems and components
;
49.100
Ground service and maintenance equipment
|
| ISO 2046:1973 |
Gaseous breathing oxygen supplies for aircraft |
Specified the pressure and characteristics and is applicable primarily to gas as supplied by manufacterer. Is also an acceptable standard which may be invokes in subsequent stages of distribution. The characteristics include purity, water, odour, flammability and toxity and solids.
|
Published |
1973-12 |
Edition : 1 |
Number of pages : 1 |
Technical Committee |
49.100
Ground service and maintenance equipment
|
| ISO 2434:1973 |
Compressed non-breathing air for use in aircraft |
Specifies the pressure and characteristics of air, compressed in oil-lubricated equipment. Is not intended to cover air for breathing purposes or air for use in oxygen systems. The compressed air supply pressure shall ensure charging of aircraft systems up to 343 bar at 20 °C. The air shall contain not more than a total of O,OO5 mg of oil vapour and particulate matter per cubic decimetre of air at 15 °C and 1 O13 mbar.
|
Published |
1973-12 |
Edition : 1 |
Number of pages : 1 |
Technical Committee |
49.100
Ground service and maintenance equipment
|