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MHT1063-2016: Installation requirements for spraying equipment of aircraft
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Installation requirements for spraying equipment of aircraft
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MH/T 1063-2016
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Basic data | Standard ID | MH/T 1063-2016 (MH/T1063-2016) | | Description (Translated English) | Installation requirements for spraying equipment of aircraft | | Sector / Industry | Civil Aviation Industry Standard (Recommended) | | Classification of Chinese Standard | V53 | | Classification of International Standard | 65.060 | | Word Count Estimation | 10,149 | | Date of Issue | 2016-01-27 | | Date of Implementation | 2016-05-01 | | Regulation (derived from) | ?Civil Aviation Industry Standard Announcement 2016 No.2 | | Issuing agency(ies) | Civil Aviation Administration of China | | Summary | This standard specifies the requirements for the installation and testing of aircraft spraying equipment. This standard applies to the installation, modification and acceptance of aircraft spraying equipment (hereinafter referred to as spraying equipment). Other aircraft spraying equipment can refer to the implementation. | MHT1063-2016: Installation requirements for spraying equipment of aircraft---This is a DRAFT version for illustration, not a final translation. Full copy of true-PDF in English version (including equations, symbols, images, flow-chart, tables, and figures etc.) will be manually/carefully translated upon your order.
Installation requirements for spraying equipment of aircraft
ICS 65.060
V 53
MH
Civil Aviation Industry Standard of the People's Republic of China
Aircraft spraying equipment installation requirements
2016-01-27 released
2016-05-01 Implementation
Issued by Civil Aviation Administration of China
Foreword
This standard was drafted in accordance with the rules given in GB/T 1.1-2009.
This standard was proposed by the Transportation Department of the Civil Aviation Administration of China.
This standard was approved by the Aircraft Airworthiness Certification Department of the Civil Aviation Administration of China.
This standard is under the jurisdiction of the China Academy of Civil Aviation Science and Technology.
Drafting organization of this standard. The Second Research Institute of Civil Aviation Administration of China.
The main drafters of this standard. Zhu Chuanyin, Jin Junhao, Wang Bingxi, Ge Qimo, Tang He, Wang Peng, Yan Fengshuo.
Aircraft spraying equipment installation requirements
1 Scope
This standard specifies requirements for the installation and test verification of aircraft spraying equipment.
This standard applies to the installation, modification and acceptance of aircraft spraying equipment (hereinafter referred to as spraying equipment). Other aircraft spraying equipment can refer to
carried out.
2 Terms and definitions
The following terms and definitions apply to this document.
2.1
Medicine box tank
Container for storing spray liquid.
2.2
Door box door-box
Located at the junction of the medicine box and the pump, there are devices with openings such as a discharge port and an emergency release door.
Note. Rewrite MH/T 0017-1998, definition 7.25.
2.3
Wind driven pump
A device that uses wind as kinetic energy to provide power for the spray system.
2.4
Spray control valve
A device installed on the main pipe of the spray system to adjust the spray pressure and flow rate.
[MH/T 1049-2012, definition 2.1]
2.5
Nozzle
Parts of spray equipment that generate and release mist.
[MH/T 0017-1998, definition 7.1]
2.6
Spray boom
Fix the nozzle and the pipeline device to transport the spray liquid.
[MH/T 0017-1998, definition 7.4]
2.7
Swath width
In the spraying operation, the distance between the center lines of two adjacent spray patterns.
[MH/T 0017-1998, definition 6.2.5.3]
3 Basic requirements
3.1 The spraying equipment shall be approved by the airworthiness department before installation.
3.2 The spraying equipment should have a product qualification certificate and related technical documents.
3.3 Components and sub-components should comply with relevant standards or pass necessary tests.
3.4 The corrosion resistance of the spraying equipment should meet the equipment environment and use requirements.
3.5 The materials of spraying equipment shall meet relevant requirements.
3.6 The equipment should be installed in accordance with the requirements and methods of the technical documents.
3.7 The combination of the self-weight and loading capacity of the spraying equipment should ensure that the weight of the aircraft's center of gravity is within the allowable weight center of gravity envelope.
3.8 After the spraying equipment is installed, the aerodynamic characteristics of the aircraft should not be seriously affected.
3.9 After the spraying equipment is installed, it should not affect the control performance of the aircraft.
4 Inspection before installation
4.1 Packaging
4.1.1 The packaging of the new components of the spraying equipment should be intact.
4.1.2 Inventory pipes should be oil-sealed according to relevant technical requirements, and both ends of the pipes should be wrapped after oil sealing.
4.1.3 The inlet and outlet of the spraying equipment pipes that have been disassembled or decomposed when the aircraft is transferred should be blocked or other protective measures.
4.1.4 When the equipment packaging does not meet the above requirements, the reasons should be ascertained and the normal use should not be affected before installation.
4.2 Model, mark and label
4.2.1 Model
The model of spraying equipment shall be certified for airworthiness and the naming shall comply with relevant regulations.
4.2.2 Marking
The markings on the inlet and outlet of the medicine pump and flow meter, the joints of the air-conditioning and hydraulic system, and the operating mechanism should be intact and clear.
4.2.3 Signs
The sprinkler system accessories should generally have signs, and the signs and their fixing methods should comply with relevant regulations.
4.3 Appearance quality
4.3.1 There should be no dirt such as oil and chemicals on the surface of the spraying equipment.
4.3.2 The surface of the spraying equipment should not have sharp edges, burrs, cracks and defects that affect its strength and function.
4.4 Physical inspection of defects
It is advisable to use methods such as magnetic flaw detection, X-ray flaw detection, fluorescence or ultrasonic (or according to the method indicated on the drawing) to detect the lack of materials of equipment parts.
For sinks and processing defects, parts that have been inspected for cracks or other defects should not be used.
5 Installed
5.1 Medicine box
5.1.1 Installation position
The medicine box should be installed according to the design position, generally located near the center of gravity of the aircraft.
5.1.2 Shape
The shape and dimensions of the medicine box should meet the requirements of relevant technical documents. If it contains the aerodynamic surface of the aircraft, its surface should meet the requirements of the aircraft shape and be smooth.
smooth.
5.1.3 Surface
5.1.3.1 The inner and outer surfaces of the medicine box should be clean and smooth, and there should be no creases, pits (except for the composite medicine box) and scratches.
5.1.3.2 The depth of the depression on the surface of the composite box should not be greater than 1.5 mm; when the depth of the depression is greater than 1.5 mm,
Within an area of 300 mm, there should be no more than one recess; the edge of each recess should be no less than 150 mm from the edge of the opening or the board.
Damage to the box material. The outer surface of the box can be properly polished.
5.1.4 Assembly
5.1.4.1 When the assembly of composite materials and metal parts requires file repair, the metal parts should be filed and the repaired area should be coated with primer, and only when necessary
The edge of composite board can be filed. A hard pad made of the same material can be added to the assembly gap. When light pressure can eliminate the gap or the gap (δ) does not
It is not necessary to add pads when it is larger than 0.3 mm. When δ is larger than 0.3 mm but not larger than 0.7 mm, a hard pad should be added.
5.1.4.2 The gap between the mouth cover and the upper wall should not be greater than 1.0 mm, and the butt gap should not be greater than 1.0 mm. The deviation of the mechanical connection spacing should not
More than 2.0 mm.
5.1.4.3 The parts and standard parts specified in the technical documents shall be used to fix and insure the medicine box. Along its length
The gap should be eliminated, but the rod should not be pre-tightened. The tension force of the steel cable shall meet the requirements of relevant technical documents.
5.1.5 Medicine tank filling port
The filling port of the medicine box should have a self-sealing device. The filling port should have a built-in filter, equipped with a reliable leak-proof cover and locking mechanism.
5.2 Door box
5.2.1 The door box should use lightweight, corrosion-resistant materials, reliable performance, easy to operate, easy to clean and maintain.
5.2.2 The installation position of the door box should ensure that the liquid in the medicine tank can be emptied when the aircraft is in flight or on the ground, and that during emergency release,
Does not damage the aircraft or affect flight safety.
5.3 Air driven pump (including fan)
5.3.1 The air-driven pump is usually installed under the fuselage structure.
5.3.2 The angle of the fan should be adjusted according to the requirements of the relevant technical documents; the fan blades should be free of cracks and defects, flexible in rotation, braking and manipulating
The structure is reliable; bearings and other rotating parts should be filled with lubricant according to relevant regulations.
5.3.3 The rotation plane of the fan should not intersect the cockpit, and as far as possible not to the fuel tank, lubricating oil tank, fuel and lubricating oil pipeline and hydraulic pressure
The pipelines intersect to avoid damage to the pilot and the aircraft due to damage to the wind-driven device.
5.3.4 Protective measures should be taken to protect the cockpit and critical parts of the aircraft from breakdown or damage when the wind driven device is damaged.
5.4 Spray control valve
5.4.1 The switch device of the spray control valve should be sensitive and reliable.
5.4.2 The spray control valve should have a bypass pipeline or install a pressure relief valve to prevent excessive pipeline pressure after the valve is closed.
5.4.3 The installation position of the spray control valve with the bypass pipe outlet should be lower than the bottom of the chemical tank (or the lowest liquid level in the chemical tank).
5.5 Filter
5.5.1 The filter should be clean, free of liquid chemical residue and no blockage.
5.5.2 The filter should be free of defects such as corrosion, broken wires, bulging, etc.
5.5.3 The specifications and levels of the filter screen should be suitable and meet the requirements of the system, and be easy to replace.
5.6 Boom
5.6.1 The spray boom should be installed symmetrically, usually along the span. The installation location should be behind and below the trailing edge of the wing.
5.6.2 The surface of the spray rod should be smooth, the welding seam should be airtight welding seam, the welding scar should be uniform and continuous, with small protrusions.
5.6.3 The bend of the spray boom should be smooth. The docking between the spray rod and the fixed point of the fuselage, the spray rod and the spray rod should not be rigid, so as not to increase the fixed point,
The extra load of tie rods and other components causes damage to parts and even the body.
5.7 Nozzle
5.7.1 It shall meet the system design requirements and the function of the drip-proof device shall be intact.
5.7.2 The nozzle should meet the requirements for use, and should be adjusted in time according to the operating requirements and operating quality.
5.7.3 The spray head should match the layout of the spray boom.
5.7.4 The clogged nozzle should be cleaned up in time, and the failed diaphragm should be replaced.
5.8 Dosing system
5.8.1 It shall meet the requirements for filling fluid on the ground without stopping the engine.
5.8.2 Should bring self-sealing device.
5.8.3 The pipeline should be far away from power lines and electrical switches.
5.9 Hard and soft control system
5.9.1 The relevant lap technology should comply with the general rules for aircraft laps.
5.9.2 Unless otherwise specified in the technical documents, all movable joints (including bearings) should be coated with lubricant.
5.9.3 The installation support position should have sufficient strength and rigidity, and the handle position should conform to the pilot's control habits.
5.9.4 The installation position and marking of the controls in the cabin shall ensure convenient operation and prevent confusion and misoperation. Make sure that the driver is sitting
In the posture, each control device can be operated unobstructed throughout the entire process without interference from the cockpit structure.
5.9.5 It should be ensured that the control force, action, effect, and handle shape of the control system meet the requirements of the aircraft control design.
5.9.6 The tie rod assembly should meet the following requirements.
a) After riveting, there is no movable gap between the earring joint (or sleeve) and the pipe;
b) The gap between the rivet head and the pipe is not more than 0.3 mm;
c) The size of the rivet hole is increased by 0.1 mm according to the nominal diameter of the rivet;
d) Ovality of pipe riveting. the difference between long diameter and short diameter is not more than 0.5 mm;
e) The deviation between the axis of the tie rod rivet hole and the axis of the pipe is not more than 0.8 mm, and the gap between the end surface of the pipe and the mating surface of the sleeve is not fit.
Not more than 0.5 mm;
f) The end of the earring bolt or fork of the tie rod is not screwed through the inspection hole when adjusting outward;
g) After the joint bearing is installed in the earring bolt and sealed, it should be checked in accordance with the general specifications in the oiled state. The inner and outer rings of the bearing should rotate flexibly.
5.9.7 The assembly of steel cables shall meet the following requirements.
a) When the steel cable with joint is installed in the fork joint, the threaded part passes through the fork joint observation hole;
b) The steel cable is coated with grease;
c) Screw into the joint of the adjusting sleeve, and the screwed part exceeds the observation hole of the sleeve. The exposed thread part is greater than 10 mm for adjustment
The length of the steel cable section (see Figure 1).
Figure 1 Adjusting the cable
5.9.8 The operation of the spray control valve shall meet the following requirements.
a) During normal operation, the joystick has no idle stroke, and the force of the rocker arm is 8 N±2 N when there is no load;
b) During normal operation, the rocker arm can stop at any position.
5.9.9 Pipelines operated by hydraulic pressure and compressed gas shall meet the following requirements.
a) The rubber pipeline is within the validity period and the pipeline is unobstructed;
b) The joints at both ends of the pipeline are intact, the pipeline connection is reliable and anti-loosening measures are taken.
The pipeline should be fixed nearby with nylon cable ties and metal clamps. When using metal clamps to fix the pipes, rubber and other soft materials should be used.
Line protection. The distance between the fixed points should not be greater than 300 mm.
5.9.10 The clearance of the brake shoe of the pneumatic pump (steel cable) should be adjusted reasonably to ensure that the brake rocker arm (connected with the steel cable) maintains a proper air gap.
stroke.
5.9.11 The minimum gap between the movable parts of the control system and other parts (including structures) should not be less than 5 mm at any position, and the steel cables should be secure.
Rely on fixed on the body.
5.10 Pressure gauge
5.10.1 The appearance should not have defects such as rust, peeling off the coating, cracks, scratches, pores and indentations.
5.10.2 The marking of the sensor (model, trademark, serial number) should be correct and clear.
5.10.3 The markings of the indicator (model, trademark, serial number and dial scale) should be correct and clear.
5.10.4 Calibration should be calibrated before installation. The air tightness, error, hysteresis, insulation resistance and other indicators of the sensor should meet the system design requirements.
5.11 Flowmeter
The range, working pressure, and accuracy of the flowmeter should meet the requirements of the system; the flow code should be corrected before installation, and the flowmeter should be kept clean.
5.12 Connecting pipelines and supporting structures
5.12.1 The outer surface of the connecting pipe should not be crushed or scratched. The allowable scar depth should not exceed 0.15 mm, the length should not exceed 10 mm, and
No more than 5 locations within 1 m. The scar should be polished with No. 0 sandpaper and painted.
5.12.2 The ellipticity when the connecting pipe is bent should not exceed 15% of the nominal diameter (that is, the difference between the major axis and the minor axis and the percentage of the nominal diameter
Greater than 15%). Micro-waviness is allowed when the pipeline is bent, but the corrugation height should not be greater than 1 mm, and the wave crest spacing should not be greater than 10τ (τ
Is the wall thickness of the pipe).
5.12.3 The connecting pipe shall be airtight tested and qualified according to the relevant technical documents.
5.12.4 Before installation, the plugs, caps or other protective parts at both ends of the connecting pipe should be intact. Only before the connecting pipe and the piece are connected, can the
Remove the protective parts at both ends of the connecting pipe.
5.12.5 The laying method of the connecting pipe should ensure smooth liquid flow.
5.12.6 The connecting pipe shall be fixed firmly and ensure that there is no moving gap.
5.12.7 The clearance between the filling pipe and the aircraft structure should not be less than 5 mm.
5.12.8 When using quick-release joints to connect pipelines, prevent loosening measures should be taken.
5.12.9 The installation position of the pipeline should avoid the fire source. When it cannot be avoided, the pipe made of refractory material should be used.
5.12.10 The threaded part of the threaded connection should be greased.
5.13 Motor drive mechanism, hydraulic drive mechanism
5.13.1 Electrical plugs and hydraulic connectors should be connected reliably and securely.
5.13.2 Cables and hydraulic conduits should be fixed nearby with flexible binding such as nylon ties.
6 Test verification
6.1 Leakage test
Add water according to the aircraft's allowable loading capacity and keep it for 1 hour, and there should be no leakage in all parts. If there is leakage, find the cause and eliminate it;
After the cause is eliminated, the test should be repeated until there is no leakage.
6.2 Emergency release test
After the 7.1 test, perform the functional test of the commercial emergency release device according to the relevant technical requirements, and the emergency release flow should not be less than
100 kg/s, the emergency launch start time should not exceed 2 s.
6.3 Ground operation test of the system
The ground operation test of the system shall at least meet the following requirements.
a) Fill the medicine tank with water to not less than 70% of the volume of the medicine tank, drive the aircraft engine on the ground, release the brake of the air pump, and open the spray control valve.
Make the gauge pressure greater than or equal to 0.2 MPa, perform a spray test for 1 min; then close the spray control valve, and the pump continues to work for 0.5 min.
When opening and closing the spray control valve, there is no leakage at the pipes, joints, nozzles, and chemical pumps;
b) After the air pump brakes, the fan stops rotating.
6.4 Pressure adding liquid test
Use a ground pump to add water to the medicine tank. When the pressure is 0.28 MPa, check the working condition of the filling indicator system.
6.5 Matching and debugging of operation and spraying
6.5.1 Determine the corresponding relationship between the rotation angle (or displacement) of the control handle of the spray control valve and the rotation angle of the spray control valve, and proceed according to the relevant matching relationship.
Commissioning to meet the requirements of relevant technical documents.
6.5.2 Determine the corresponding relationship between the displacement of the fan control handle and the fan rotation angle, and debug according to the relevant matching relationship to meet the requirements of the relevant technology
Document requirements.
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