OpenLegislation

Chapter GROUP 3E

Changes not yet applied. Later legislation changes this provision in ways not yet written into the text below:

Aircraft, Spacecraft, Marine Equipment and Ships (Other than Warships and Naval Equipment)

NOTES:

1. The period of civil use referred to in heads (c) and (d) above begins with the date that the particular engine or helicopter power transfer system (model and specifications) or its most recent modification was certified as airworthy for commercial service or commercial navigability under the standards and requirements of the government of the country in which it was manufactured: modification does not include minor safety or operational changes which do not significantly enhance the performance of a particular gas turbine aero-engine or improve its reliability. For the purposes of this entry:

  1. (a)

    A gas turbine aero-engine which is recertified as the result of incorporating any technology listed in Table 1 below is to be treated as a newly certified engine. Recertification which does not result from incorporation of such technology, or modifications which do not require recertification by national authorities, will not affect the period of civil use of the engine;

  2. (b)

    Modification of a gas turbine APU by incorporation of any technology listed in Table 1 will cause it to be treated as a new APU. Other modifications will not affect the period of civil use of the APU.

  3. (c)

    Modification of a helicopter power transfer system by incorporation of any technology listed in Table 2 will restart the period of civil use for the helicopter power transfer system as though it were newly certified in a helicopter. Other modifications will not affect the period of civil use of the helicopter power transfer system.

2. This entry does not include gas turbine engines, APUs and helicopter power transfer systems for civil use and modifications (and technology therefor) certified or recertified for civil use, as described in Note 1 prior to the1st January 1979, other than: Helicopters over 4,530 kg empty weight, and power transmissions systems therefor.

Note: Empty weight is understood to include normal installation and normal minimum crew, but does not include fuel or payload.

Aero-engines, the following–

  • (i) Piston engines;

  • (ii) Jet engines of less than 2,625 kg thrust;

  • (iii) Turboprop or turboshaft engines of less than 2,500 horsepower or with a residual thrust of less than 453 kg.

3. Head (d) above does not include those engines which contain none of the technologies listed in Table 1 below for use in civil aircraft or civil helicopters.

IL1401

Reciprocating diesel engine development and production technologies, including specially designed software, the following–

  • (a) Development and production technology, including specially designed software, for reciprocating diesel engine ground vehicle propulsion systems having all of the following characteristics–

D

  • (1) a box volume of 1.2m3 or less;

  • (2) an overall power output of more than 750 kW based on 80/1269/EEC, ISO 2534 or national equivalents;

  • (3) a power density of more than 700 kW/m3 of box volume.

  • (b) Development and production technology for solid or dry film cylinder wall lubrication permitting operation at temperatures in excess of 723 K (450°C) measured on the cylinder wall at the top limit of travel of the top ring of the piston

D

  • (c) Production technology for specially designed components for high output diesel engines, the following:

  • (1) Production technology for any specially designed components when used in low heat rejection engines and employing ceramic material specified in entry IL1733

D

  • (2) Production technology for turbocharger systems with single-stage compressors and having all of the following characteristics

D

  • (A) operating at pressure ratios of 4:1 or higher;

  • (B) A mass flow in the range from 30 to 130 kg per minute; and

  • (C) Variable flow area capability within the compressor or turbine sections;

  • (3) Production technology for diesel fuel injection systems having all of the following characteristics

D

  • (A) Maximum fuel injection pressure of 1 × 108 pascal (1,000 bar) or more;

  • (B) Injection amount in excess of 230 mm3 injection per cylinder;

  • (C) Injection nozzle hole of 0.254 mm or less;

  • (D) Capability to complete fuel injection in 30 crank angle degrees or less;

  • (E) Electronic features for control of the fuel injection quantity, timing and duration throughout the engine speed and load range, through the use of appropriate sensors; and

  • (F) Designed for engines of more than eight cylinders.

In this entry–

  • “box volume” means the product of three dimensions at right angles to each other measured in the following way–

  • Length: the length of the crankshaft from front flange to flywheel face;

  • Width: the greatest of the following:

    • (a) the outside dimension from valve cover to valve cover;

    • (b) the dimension of the outside edges of the cylinder heads; or

    • (c) the diameter of the flywheel housing;

  • Height: the greater of the following:

    • (a) the dimension of the crankshaft centreline to the top plane of the valve cover (or cylinder head) plus 2 times the stroke; or

    • (b) the diameter of the flywheel housing;

  • “high output diesel engines” means diesel engines with a specified brake mean effective pressure of 180 kPa or more at a speed of 2,300 rpm, provided the rated speed is 2,300 rpm or more.

IL1416

Vessels (including ships and surface-effect vehicles), water-screw propellers and hub assemblies, water-screw propeller systems, moisture and particulate separator systems and specially designed components, the following–

  • (a) Hydrofoil vessels with automatically controlled foil systems which are capable of speeds of above 40 knots in rough water (Sea State Five)

S,I(b) Surface-effect vehicles

C

except hovercraft having all the following characteristics:

  • (1) designed to carry fewer than 5 passengers including the driver;

  • (2) dry mass less than 500 kg;

  • (3) maximum speed less than 50 knots (90 km/h) at Sea State 0;

  • (4) not designed for operation above Sea State 3;

  • (c) SWATH vessels having underwater hulls whose cross-sectional area varies along the longitudinal axis between points two major diameters from the bow and two major diameters from the stern

C

  • (d) Ships and vessels fitted with any of the following–

  • (1) equipment specified in Group 1, in entry IL1485 in this Group or in entry IL1501, IL1502 or IL1510 in Group 3F

S,I

  • (2) degaussing facilities

S,I

  • or

  • (3) closed ventilation systems designed into the vessel which are designed to maintain air purity and positive pressure regardless of the conditions external to the vessel except where those closed ventilation systems are specially designed for and incorporated in the vessel’s medical facilities only

C

  • (e) Water-screw propellers and hub assemblies, the following–

  • (1) supercavitating propellers rated at greater than 7.46 MW (10,000 hp)

C

  • (2) controllable-pitch propellers and hub assemblies rated at above 29.83 MW (40,000 hp) capacity

C

  • (f) Water-screw propeller systems, the following–

  • (1) contrarotating propeller systems rated at greater than 14.92 MW (20,000 hp)

C

  • (2) ventilated, base-ventilated and super-ventilated propeller systems and semi-submerged propeller systems (or surface propellers) rated at more than 2.24 MW (3,000 hp)

C

  • (3) systems employing pre-swirl and post-swirl techniques for smoothing the flow into a propeller so as to improve propulsive efficiency of–

  • (i) SWATH vessels, hydrofoil vessels, and surface-effect vessels

C

  • or

  • (ii) other vessels whose propeller rotational speed is above 200 rpm, or having propellers with a rating exceeding 44.74 MW (60,000 hp) per shaft

C

  • (4) pumpjet systems

C

  • (g) Moisture and particulate separator systems which are capable of removing 99.9 per cent of particles larger than 2 micrometres in diameter with a maximum pressure loss of 1.6 kPa (16 millibar) for gas turbine engine air inlets

C

  • (gg) Technology for moisture and particulate separator systems specified inhead (g) above, the following–

  • (1) technology for preventing water leakage around the filter stages

D

  • (2) technology for integrating the components of such a system

D

  • (h) Specially designed components for vessels specified in head (a), (b) or (c) above, the following–

  • (1) advanced hull forms which incorporate any of the following–

  • (i) stepped hulls for hydrofoil vessels

C

  • (ii) hulls for air cushion vehicles with trapezoidal platforms

C

  • (iii) hulls for surface effect vehicles with catamaran-like sidewalls

C

  • (iv) hulls for wing-in ground effect vehicles

C

  • (v) underwater hulls and struts for SWATH vessels

C

  • (2) fully submerged subcavitating or supercavitating hydrofoils

C

  • (3) lightweight structural components for SWATH vessels, hydrofoil vessels and surface effect vehicles, constructed using anisotropic, orthotropic or sandwich construction methods

C

In this subhead–

  • “anisotropic construction methods” means the use of fibre reinforcing members aligned so that the load-carrying ability of the structure can be primarily orientated in the direction of expected stress.

  • “orthotropic construction methods” means the means of stiffening plates, in which the structural members are at right angles to each other.

  • “sandwich construction methods” means the use of structural members or plates which are fabricated and permanently affixed in layers to enhance their strength and reduce their weight.

  • (4) flexible skirts, seals and fingers for surface effect vehicles

C

  • (5) systems for automatically controlling the stability of SWATH vessels, hydrofoil vessels or surface-effect vehicles

C

  • (6) power transmission shaft systems which incorporate composite material components, for SWATH vessels, hydrofoil vessels or surface effect vehicles

C

  • (7) lightweight, high capacity (K factor greater than 150) gearing (planetary, cross-connect and multiple input/output gears and bearings) for SWATH vessels, hydrofoil vessels and surface effect vehicles

C

  • (8) water-cooled electrical propulsion machinery (motor and generator), including AC-AC synchronous and AC-DC systems, sectored-disc and concentric-drum rotors for DC homopolar machines, for SWATH vessels, hydrofoil vessels and surface effect vehicles

C

  • (9) superconducting electrical propulsion machinery for SWATH vessels, hydrofoil vessels and surface effect vehicles

C

  • (10) lift fans for surface-effect vehicles, rated at greater than 300 kW (400 hp)

C

  • (11) waterjet propulsor systems rated at an input of 2.24 MW (3,000 hp) or greater for hydrofoil vessels or surface-effect vehicles

C

In this entry “pumpjet systems” means propulsion systems which utilise divergent nozzle and flow conditioning vane techniques to improve propulsive efficiency or reduce propulsion generated underwater radiated noise.

PL7009

Other vessels (including ships), the following: and specially designed components therefor–

  • (a) Vessels having special structural features for landing personnel and/or vehicles on a beach

I

  • (b) Vessels capable of supporting helicopter operations and maintenance

I

  • (c) Vessels capable of submerging

I

  • (d) Vessels not elsewhere specified in this Part of this Schedule of below 100 tonnes GRT including inflatable craft in an inflated or uninflated state except light vessels, fire floats and dredgers

I

  • (e) Ships with decks and platforms specially strengthened to receive weapons

S,L

IL1417

Submersible systems, including those incorporated in a submersible vehicle, and specially designed components, the following: and specially designed ODMA software therefor–

  • (a) Automatically-controlled atmosphere-regeneration systems specially designed or modified for submersible vehicles which, in a single chemical-reaction cycle, ensure carbon dioxide removal and oxygen renewal

C

  • (b) Systems specially designed or modified for the automated control of the motion of a submersible vehicle using navigation data and having closed-loop servo-controls so as to–

  • (1) enable the vehicle to move within 10m of a predetermined point in the water column

C

  • (2) maintain the position of the vehicle within 10m of a predetermined point in the water column

C

  • (3) maintain the position of the vehicle within 10m while following a cable on or under the sea bed

C

except–

automated control systems incorporated in underwater bulldozers or trench-cutters not capable of operating at depths greater than 100 metres and possessing only negative buoyancy.

  • (c) Underwater vision systems, the following–

  • (1) television systems (comprising camera, lights, monitor and signal transmission equipment) specially designed or modified for remote operation with a submersible vehicle, having a limiting resolution, when measured in the air, of more than 500 lines or underwater television cameras having a limiting resolution, when measured in the air, of more than 600 lines, using IEEE Standard 208/1960 or any equivalent standard

C

  • (2) systems specially designed or modified for remote operation with a submersible vehicle employing techniques to minimize the effects of back-scatter including range-gated illuminators and laser systems

C

except–

television cameras used merely through a porthole.

  • (d) Remotely controlled articulated manipulators specially designed or modified for use with submersible vehicles and having any of the following characteristics–

  • (1) systems which control the manipulator using information from sensors which measure force or torque applied to an external object, distance from an external object, or tactile sense between the manipulator and an external object

C

except systems where force or torque are only measured and then displayed to the operator.

  • (2) controlled by proportional master-slave techniques or by using a dedicated stored-programme computer

C

  • (3) capable of exerting a force of 250N or more or a torque of 250Nm or more and using titanium based alloys of fibrous and filamentary composite materials in their structural members

C

  • (e) Photographic cameras and associated equipment specially designed or modified for underwater use, having a film format of 35mm or larger, and capable of any of the following–

  • (1) film advancement of more than 5 frames per second

C

  • (2) annotating the film with data provided by a source external to the camera

C

  • (3) taking more than 400 full frame exposures without changing the film

C

  • (4) autofocusing or remote focusing specially designed or modified for use under water

C

  • (5) automatic back focal distance correction

C

  • (6) passive or automatic compensation control specially designed to permit underwater camera housings to be useable at depths exceeding 1,000m

C

  • (7) titanium underwater camera housing specially designed for depths exceeding 1,000m

C

  • (8) automatic exposure control by using sensing devices in or external to the camera if the camera is capable of operating at depths of more than 300m

C

  • (f) Light systems specially designed or modified for underwater use, the following–

  • (1) stroboscopic lights capable of–

  • (A) light output energy of more than 250 Joules per flash

C

  • (B) flash rates of more than 5 flashes per second at a light output energy of more than 10 Joules per flash

C

  • (2) other lights and associated equipment, designed for operation with equipment specified in sub-head (e)(1) or (e)(8) above

C

  • (g) Specially designed components for the equipment specified in heads (a) to (f) above

C

  • (h) Air-independent power systems specially designed for underwater use and specially designed components therefor, the following–

  • (1) Brayton, Stirling or Rankine Cycle Engine air-independent power systems having any of the following characteristics–

  • (A) specially designed chemical scrubber or absorber sub-systems to remove carbon dioxide, carbon monoxide and particulates from recirculated engine exhaust

C

  • (B) specially designed sub-systems for utilising a monoatomic gas

C

  • (C) specially designed devices for underwater noise reduction in frequencies less than 10KHz, or special mounting devices for shock mitigation

C

  • (D) specially designed systems for pressurising products of reaction or for fuel reformation, specially designed systems for the storage of products of the reaction, and specially designed systems for discharging the products of the reaction against a pressure of 100kPa (1 bar) or more

C

  • (2) Diesel Cycle Engine air-independent systems having all of the following characteristics

C

  • (A) specially designed chemical scrubber or absorber sub-systems to remove carbon dioxide, carbon monoxide and particulates from recirculated engine exhaust;

  • (B) specially designed sub-systems for utilising a monoatomic gas;

  • (C) specially designed devices for underwater noise reduction in frequencies less than 10kHz, or special mounting devices for shock mitigation;

  • (D) specially designed exhaust systems that do not continuously exhaust products of combustions;

  • (3) Alkaline, phosphoric acid or ion exchange membrane fuel cell air-independent power systems with an output exceeding 2kW and operating at a temperature of less than 523K having any of the following characteristics–

  • (A) specially designed enclosures for underwater noise reduction in frequencies less than 10kHz, or special mounting devices for shock mitigation

C

  • (B) specially designed systems for pressurising products of reaction or for fuel reformation, specially designed systems for the storage of products of the reaction, and specially designed systems for discharging the products of the reaction against a pressure of 100kPa (1 bar) or more

C

  • (4) Specially designed components for sub-systems specified in sub-head (h)(1)(C), (h)(2)(C) or (h)(3)(A) above

C

  • (i) Technology, the following–

  • (A) technology for air-independent power systems specified in sub-head (h)(1), (h)(2) or (h)(3) above

D

  • (B) technology for sub-systems and specially designed components specified in sub-head (h)(1)(A), (h)(1)(B), (h)(1)(C), (h)(3)(A) or (h)(4) above

D

  • (C) technology for sub-systems specified in sub-head (h)(2)(A), (h)(2)(B) or (h)(2)(C) above

D

In this entry “limiting resolution” in television is a measure of resolution usually expressed in terms of the maximum number of lines per picture height discriminated on a test chart.

IL1418

Deep submergence vehicles and autonomous submersible vehicles, the following–

  • (a) Deep submergence vehicles, manned or unmanned, tethered or untethered, capable of operating at depths exceeding 1,000m, and specially designed or modified associated systems and equipment therefor, including the following–

C

  • (1) pressure housings or pressure hulls;

  • (2) propulsion motors and thrusters;

  • (3) hull penetrators or connectors.

  • (b) Other manned underwater vehicles which are able to operate autonomously for ten hours or more, provided their maximum range underwater exceeds 15 nautical miles

C

In this entry–

  • “operate autonomously” means operate fully submerged, without snorkel, all systems working and cruising at the minimum speed at which the submersible can safely control its depth dynamically by using its depth planes only, with no need for a support vessel or support base on the surface, sea-bed or shore, and containing a propulsion system for submerged or surface use;

  • “range” means half the maximum distance the vehicle can cover.

IL1431

Marine gas turbine engines (marine propulsion or shipboard power generation engines), whether originally designed as such or adapted for such use, and specially designed components therefor

C

Note: for the purpose of this entry “shipboard power generation” does not include offshore platform applications.

IL1460

Aircraft and helicopters, including tilt wing and tilt rotor aircraft, aero-engines and aircraft and helicopter equipment, and technology therefor, the following–

  • (a) Aircraft and helicopters, except those which do not contain equipment specified in Group 1 or in the entries IL1485 or IL1501 in Groups 3E and 3F and which are of types which are in bona fide normal civil use

C

  • (b) Technology for aircraft and helicopter airframes (including airframes for tilt wing and tilt rotor aircraft), for aircraft propellers, and for aircraft and helicopter airframe, aircraft-propeller and helicopter-rotor-systems components, and specially designed ODMA software therefor, the following–

  • (1) design technology using computer-aided aerodynamic analyses for integration of the fuselage, propulsion system and lifting and control surfaces to optimize aerodynamic performance throughout the flight regime of an aircraft

B

  • (2) technology for the design of active flight control, the following–

  • (i) technology for configuration design for inter-connecting multiple microelectronic processing elements (on-board computers) to achieve high-speed data transfer and high-speed data integration for control law implementation

D

  • (ii) technology for control law compensation for sensor location and dynamic airframe loads, namely compensation for sensor vibration environment and for variation of sensor location from centre of gravity

D

  • (iii) technology for electronic management of systems redundancy and data redundancy for fault detection, fault tolerance and fault isolation

D

  • except–

  • technology for the design of physical redundancy in hydraulic or mechanical systems or in electrical wiring;

  • (iv) technology for design of flight controls which permit in-flight reconfiguration of force and moment controls

D

  • (3) design technology for integration of flight control, navigation and propulsion control data into a flight management system for flight path optimization

B

  • (4) design technology for protection of avionic and electrical sub-systems against electromagnetic pulse (EMP) and electromagnetic interference (EMI) hazards from sources external to the aircraft, the following–

  • (i) technology for design of shielding systems

B

  • (ii) technology for the configuration design of hardened electrical circuits and sub-systems

B

  • (iii) technology for determination of hardening criteria for the above

B

  • (5) technology for the design, production and reconstruction of adhesively bonded airframe structural members designed to withstand operational temperatures in excess of 120°C

D

except–

airframe structural members for engine nacelles and thrust reversers.

  • (6) technology for the design and production of propeller blades constructed wholly or partly of composite materials, and specially designed hubs therefor

D

except–

technology for the production of propeller blades–

  • (a) constructed wholly of wood or glass-fibre-reinforced plastics ;

  • (b) constructed mainly of wood or glass-fibre-reinforced plastics and which use other materials only in the leading edge or tip; or

  • (c) constructed mainly of glass-fibre-reinforced or carbon-fibre reinforced plastics.

  • (7) technology for the design and production of digital electronic synchrophasers specially designed for propellers; technology for the design of digital electronic controls for propellers; and technology for the production of digital electronic controls for the propeller blades and hubs specified in sub-head (b)(6) above

D

  • (8) technology for the design and production of active laminar flow control lifting surfaces including design data used to substantiate the design approach

D

  • (9) technology for the development of helicopter multi-axis fly-by-light or fly-by-wire controllers which combine the functions of at least two of the following into one controlling element

D

  • (i) collective controls;

  • (ii) cyclic controls;

  • (iii) yaw controls.

  • (10) technology for the development of circulation controlled anti-torque or directional control systems for helicopters

D

  • Note: “Circulation-controlled anti-torque and directional control systems” utilise air blown over aerodynamic surfaces to increase or control the forces generated by the surfaces. Buried fan-in-fin anti-torque designs fitted or not fitted with guide vanes such as the fenestron are excluded from this subhead.

  • (11) technology for the development of helicopter rotor blades incorporating variable geometry airfoils utilizing trailing edge flaps or tabs or pivoted nose droop, which can be controlled in position in flight

D

  • (12) technology for the development of active control of helicopter blades and other surfaces used to generate aerodynamic forces and moments

D

  • Note: “Active control” (of helicopter blades and other surfaces used to generate aerodynamic forces and moments) functions to prevent undesirable helicopter vibrations, structural loads or helicopter rotor dynamic behaviour by autonomously processing outputs from multiple sensors and then providing necessary preventive commands to effect automatic control.

  • (13) technology for the development and production of integrated automatic propulsion and airfoil control systems for tilt wing and tilt rotor aircraft

D

  • (c) Helicopter power transfer systems and technology therefor

C

  • except–

  • (i) helicopter power transfer systems for use in civil helicopters only, the following–

    • (1) those which have been in civil use in civil helicopters for more than eight years;

    • (2) those which do not contain, and were not fabricated utilizing, any of the technologies shown in Table 2 below;

    • (3) those for replacement in or servicing of specific, previously exported helicopters;

  • (ii) technological documents resulting from helicopter powertransfer system performance and installation design studies; fabrication technology, or overhaul and refurbishing technology for specific helicopter power transfer systems in civil use in civil helicopters for more than eight years, unless listed in Table 2 below.

  • Note: Documents resulting from helicopter power transfer system performance and installation design studies do not include documents containing technology for: computer-aided design (CAD); computer aided design/manufacturing (CAD/CAM); or parametric performance analysis, engine analysis and selection, or component design utilizing unpublished technical data.

  • (d) Gas turbine engines and auxiliary power units (APUs) for use in aircraft or helicopters and technology therefor

A

  • except–

  • (i) those for use in civil aircraft or civil helicopters only, the following–

    • (1) jet, turboprop and turboshaft aircraft engines in civil use in civil aircraft or civil helicopters for more than eight years;

    • (2) gas turbine powered aircraft APUs in civil use in bona fide civil aircraft or civil helicopters for more than eight years;

  • (ii) technological documents resulting from aircraft performance and installation design studies; fabrication technology, or overhaul and refurbishing technology for specific gas turbine aero-engines or gas turbine powered aircraft APUs in civil use in civil aircraft or civil helicopters for more than twelve years, unless listed in Table 1 below.

  • Note: Aircraft performance and installation design studies does not include technology for: computer-aided design (CAD); computer-aided design/manufacturing (CAD/CAM); or parametric engine performance analysis, engine cycle analysis and selection, or component aerodynamic design utilizing unpublished technical data.

  • (e) Specially designed components for gas turbine engines APUs and helicopter power transfer systems specified in heads (c) and (d) above, the following–

  • (1) embodying technologies listed in Table 1 or 2 below

C

  • (2) hot-section components

C

  • (3) engine control system components

C

  • (4) gas turbine engine or APU rotor system components (including bearings)

C

Table 1

Technology relating to the following

I. Materials and manufacturing procedures

Ceramic, ceramic-composite or composite hot-section components (combustor, turbine blades and vanes, seals, discs, flow path)

Turbine blades on basis of directional solidification or monocrystal technology

  • directional solidification

  • monocrystal technology

Turbine blades consisting of several parts connected by diffusion bonding

Fibre technology in frames or in highly stressed discs, castings, blades and vanes

Protective coating technology for air-cooled turbine blades and vanes with internal and external cooling passages and their related flow paths capable of operating in high gas temperature environments (in excess of 1,499°C), irrespective of the actual gas temperature environment in whcih they will be used, involving applications of metallic or ceramic materials by vapour, pack, plasma, electron team, sputtering or sintering processes

Metallic coatings

  • plasma sprayed

  • other

Ceramic Coatings

Application of powder metallurgy for fan compressor and turbine blades or vanes; discs, wheels, ruduction gears, engine main shafts and framees

  • discs

  • fan, compressor and turbine blades or vanes, wheels, reduction gears, engine main shafts and frames

Cooled components on basis of electrostream or laser drilling methods;

  • electrostream drilling

  • laser drilling

Electron beam drlling for small holes in turbine blades and vanes

Titanium or superalloy-casting on basis of centrifugal techniques

Ceramic core casting technology for casting holes in turbine blades and vanes

II. Construction methods

Adjustable flow path geometry and associated control system for:

  • fans

  • gas generator turbine(s)

  • fan/power turbine(s)

  • propelling nozzles

(Adjustable flow path geometry and associated control systems do not include: inlet guide vanes, variable pitch fans, variable stators or bleed valves for compressors.)

Full authority or hybrid digital electronic control and respective sensor equipment

High temperature (capable of utilizing gases heated above 1,100°C) heat exchangers for preheating compressor exit air

Combustors with combustion in several stages

Maintenance of compressor or turbine tip clearance through methods employing active compensating casing technology:

  • compressor alone

  • turbine alone

  • compressor and turbine

Ceramic bearings

Nozzles with thrust vectoring (not includng reverse thrust)

Table 2

Technology relating to the following

I. Materials and manufacturing procedures

A. Rotor heads, containing:

  • Hot-isostatically pressed materials

B. Gear boxes, containing:

  • Navikoff-type gears

  • Gears or gear support structures based on materials applying directional solidification or monocrystal technology

  • High contact-ratio double-helical (arrow-shaped) gears

  • Fibre technology

  • Hot-isostatically pressed components

  • Gear tooth surfaces hardened by vacuum carburizing or ion nitriding

C. Drive shaft systems containing super-critical drive shafts

II. Construction methods

A. Components fabricated by diffusion bonding

B. High-survivability loss-of-lubrication technology for high-speed bearings (DN equal to or greater and 2.4 million where D is expressed in millimetres and N in rpm)

In this entry–

  • “civil aircraft” and “civil helicopters” means only those types of civil aircraftr and civil helicopters which are listed by designation in published airworthiness certification lists by the civil aviation authorities to fly commercial civil internal and external routes or for normal civil, private or business use.

  • “helicopter power transfer systems” means all those components which transfer power from the engine to the main and tail rotor blade(s).

  • Note: Aero-engines, APUs or helicopter power transfer systems which have any special feature designed for a military application are specified in the entry ML10 in Group 1.

PL7026

Propulsion equipment and components therefor, the following–

ramjet engines

A

scramjet engines

A

pulsejet engines

A

combined cycle engines

A

devices to regulate combustion in goods specified in head (a), (b), (c) or (d) above

A

specially designed components for goods specified in head (a), (b), (c), (d) or (e ) above

A

PL7010

L,Z

PL7016

W

PL7011

L,I,Y,Z

IL1465

Spacecraft and launch vehicles, the following–

  • (a) spacecraft, manned or unmanned (not including their payloads)

A

  • except scientific mission space probes which do not contain equipment specified in head (c) below or elsewhere in this Schedule.

  • (b) Launch vehicles

A

  • (c) Propulsion systems, guidance equipment, attitude control equipment and on-board communications equipment for remote control of equipment specified in heads (a) or (b) above

A

  • (d) Specially designed components for equipment specified in head (a), (b) or (c) above

A

In this entry “spacecraft” means active and passive satellites and space probes.

PL7017

Liquid and slurry propellant control systems, having both the following characteristics and specially designed components therefor, except pumps and servo valves

A

  • (a) designed for propellants and related substances specified in PL5009 or PL7028;

  • (b) designed or modified to operate in environments of more than 10 g RMS between 20 Hz and 2000 Hz

PL7018

Pumps and servo valves for liquid and slurry propellant systems, having all the following characteristics

A

  • (a) designed for propellants and related substances specified in PL5009 or PL7028; and

  • (b) designed or modified to operate in environments of more than 10 g RMS between 20 Hz and 2000 Hz; and

  • (c)

  • (i) in the case of servo valves, having both the following characteristics:

    • (1) having an actuator response time of less than 100 × 10−3 seconds; and

    • (2) designed for a flow rate of 24 litres per minute or greater at an absolute pressure of 7000 kPa (1000psi) or greater; or

  • (ii) in the case of pumps, having both the following characteristics:

    • (1) a shaft speed of 8000 r.p.m. or greater; and

    • (2) providing a discharge pressure of 7000 kPa (1000psi) or greater.

PL7037

Vehicles designed or modified for the ground support of goods specified in IL1465

A

In this entry “ground support” means support in the form of transport, handling, control, activation or launching equipment for land or sea based goods.

IL1485

Inertial navigation systems, inertial equipment, gyroscopes (gyros) and accelerometers, and specially designed ODMA software therefor, the following: and specially designed components therefor–

  • (a) Gyro compasses with provision for determining and transmitting ship’s level reference data (roll, pitch) in addition to own ship’s course data

C

  • (b) Integrated digital flight instrument systems which include gyrostabilisers or automatic digital flight control systems for aircraft and specially designed ODMA software for the integration thereof

A

  • except–

  • (1) flight instrument systems integrated solely for VOR/ILS or MLS navigation and approaches;

  • (2) integrated flight instrument systems which–

    • (i) have been in normal civil use for more than two years; and

    • (ii) are standard equipment of civil aircraft and civil helicopters;

    An “integrated flight instrument system” means a primary instrument and display system using digital data processing techinques to provide manoeuvre guidance information

  • (c) Gyro-astro compasses and other devices which derive position or orientation by means of automatically tracking celestial bodies

A

  • (d) Gyro-stabilisers used for other purposes than aircraft control

C

  • except

  • (1) those for stabilising an entire surface vessel;

  • (2) those which have been in normal civil use for more than two years;

  • (e) Automatic pilots used for purposes other than aircraft control and specially designed ODMA software for the integration thereof

C

  • except–

  • marine types for surface vessels;

  • (f) Accelerometers designed for use in inertial navigation systems or in guidance systems of all t;ypes, having either of the following charactgeristics–

  • (1) a threshold of 0.05 g or less

A

  • (2) a non-linearity of less than 0.25 per cent of the full scale output

A

  • (g) Gyros with a rated free directional drift rate (rated free precession) of less than 0.5° (1 sigma or root mean square value) per hour in a 1 g environment

A

  • (h) Continuous output accelerometers and gyros, specified to function at acceleration levels greater than 100 g

A

  • (i) Inertial or other equipment using accelerometers specified in head (f) or (h) above or gyros specified in head (g) or (h) above, and systems incorporating such equipment, and specially designed ODMA software for the integration thereof

A

  • (j) Specially designed test calibration and alignment equipment for goods specified in heads (a) to (i) above

A