LRU (In Rs Laks) 1 Aircraft Avionics AUDIO CONTROL … of Item 5th Apr 2016 V… · 2 Aircraft...

No DivisionCategory of item/

LRUName of system/LRU Description Photo

Total Business

Value

(In Rs Laks)

1 Aircraft Avionics AUDIO CONTROL PANEL

The Audio Control Panel (ACP) is the part

of Communication Control System (CCS).

The Audio Control Panels are the Man-

Machine interface to the CAMU, not only

allows pilots to select and control the

various functions, they provide visual

indications of the system status.

72.99

2 Aircraft AvionicsCommunication Audio

Management Unit (CAMU)

The CAMU receives functions switch

control and volume level data from the

ACP. This information is used to switch,

set and route appropriate audio signal

paths to the required destination.

166.1

3 Aircraft Avionics DIGITAL VIDEO RECORDER

The Digital Video Recorder is an airborne

digital multi-channel recorder that

operates with an easy to handle Digital

Data cartridge based on a solid state non-

volatile memory technology.

189.1

volatile memory technology.

4 Aircraft Avionics DATA TRANSFER UNIT

The Data Transfer Unit (DTU) is the

connection between the DTC and the

aircraft avionic system through the Mil-

Std 1553B databus. The DTU fitted in the

rear cockpit right console. DTU is having

the slot to insert DTC along with

protective cover.

168.4

5 Aircraft Avionics DATA TRANSFER CATRIDGE

The Data Transfer Cartridge (DTC) is a

portable solid state, 32Mb memory unit

used to store data.

43.3

6 Aircraft Avionics

Engine Monitoring Panel

Electronics Unit (EMP EU)

Refer HAL E-procurement

portal for EOI (Expression of

Interest) Vide:

A/BA3/EOI/EMP/2016

Dtd.15/06/2016

The EMP-EU is interfaced to the Mission

Computer. Raw data about engine and

fuel sensors are processed and

transmitted by the EMP-UE to the display

unit and to MC

33.7



Total Business

Value

(In Rs Laks)

7 Aircraft Avionics

Engine Monitoring Panel Digital

Unit (EMP DU)

Refer HAL E-procurement

portal for EOI (Expression of

Interest) Vide:

A/BA3/EOI/EMP/2016

Dtd.15/06/2016

The EMP-DU is interfaced to the Engine

Monitoring Panel Electronic unit (EMP-

EU) by means of a synchronous serial

linc.

78.4

8 Helicopter Armament TURRET GUN SYSTEM

Single barrel turret gun is used for anti-

vehicle, anti-personnel and anti-aircraft

missions on Dhruv Mk-IV helicopters.

Single barrel turret gun is used on Dhruv

Mk‐‐‐‐IV helicopters.

20M621gun mounted on a THL20 turret.

SYSTEM CONSISTS OF

20mm Machine Gun

Turret Assembly

Ammunition Feeding Mechanism

Gun Processor unit

60000.0

Gun Processor unit

Gun Power Unit

Maintenance Brake Release Unit

Ballistic Computer System

9 Helicopter Avionics ELECTRO-OPTICAL SYSTEM

EO-POD is day and night Camera

mounted system and used for

surveillance purpose.

Line Of Sight (LOS) Drive Range

In Elevation: ‐‐‐‐90 to +35

In Azimuth: N x 360 (No limitation)

• LOS Speed and Acceleration

39000.0

10 Helicopter Avionics HELMET POINTING SYSTEM

•The Helmet Pointing System (HPS) is a

day & night helmet mounted display &

sight system. The system produces flight

symbology of critical flight indicators,

weapon sensors & mission information,

superimposed

Sensors:

Advanced sensor unit

Advanced magnetic transmitter unit

Day and night mounted display

22800.0

Day and night mounted display



Total Business

Value

(In Rs Laks)

11 Helicopter Avionics EW SUITE

It is multi sensor warning system

providing situational awareness to flight

crew. It consists of

a) Radar warning sensor

b.)Missile warning sensor

c.)Lase r warning sensor

34800.0

12 Helicopter MechanicalENGINE FIRE EXTINGUISHER

SYSTEM

It consists of two extinguishant bottles

containing Bromo tri fluoro methane

(CBrF3 or HALON 1301) extinguishing

agent. It contains check T valves, hoses,

tubes and spray nozzles.

OPERATING PRESSURE:

Operating pressure: 4137 KPa at 210C

Burst pressure: 16547 KPa

QUANTITY OF EXTINGUISHER AGENT:

11400.0

QUANTITY OF EXTINGUISHER AGENT:

1.3 Kg

QUANTITY OF NITROGEN: 0.045 Kg at

625 psi

TIME FOR EXTINGUISHING AGENT

DISCHARGE: 1sec

13 Helicopter Electrical FORMATION FLYING LIGHT

COMMAND BOX

Used for power supply and control of

formation lights.

OPERATION: It should contain following

light control switches,

1. ON/OFF switch

2. Flasher selector switch

3. Dimmer potentiometer

4. Mode selector switch

TECHNICAL REQUIREMENTS:

Flasher selector switch: Frequency: 0.5

Hz, 1 Hz and 1.5 Hz

Dimmer switch: Intensity shall be varied

in both modes

Mode selector switch: For selecting the

brilliancy of the lights to full or infrared

mode.

1560.0



Total Business

Value

(In Rs Laks)

14 Helicopter Electrical CHIP BURNING MODULE

It is to detect the chip and burn it of MGB

.

ELECTRICAL INTERFACE:

Supply Voltage: 28 V DC

Voltage Range: 16 V to 32 V DC

Connectors: As per MIL‐‐‐‐C‐‐‐‐38999 series

3/4 OR MIL‐‐‐‐C‐‐‐‐83723

DIMENSIONS: 190 mm (L) x 110 mm

(W) x 30 mm (H)

OPERATING TEMPERATURE: ‐‐‐‐45 0C to 71

0C

WEIGHT: 0.5 kg (Max.)

SOFTWARE REQUIREMENTS: To be

qualified to level C of RTCA‐‐‐‐DO‐‐‐‐178B

3600.0

To stop the fuel flow to the engine In

normal/emergency operation.




‐‐‐‐ ‐‐‐‐

15 Helicopter

Electro

Mechanical

System

FUEL SHUT OFF VALVE


Current Rating: 1 A (Max.)

Connectors: As per MIL‐‐‐‐C‐‐‐‐38999 series ¾

Cockpit indication for valve OPEN/CLOSE

condition.

OPERATING PRESSURE:

Normal fuel tank pressure: 1.5 bar

Crash condition pressure: 3.5 bar

FUEL TYPE: Aviation type gasoline

FLOW RATE: 225 litre/min with fuel head

of 200mm.

WEIGHT: 1 kg (Max.)

LOAD FACTORS:

Normal operation: +3.5 g to ‐‐‐‐1 g

During crash: 10 g all directions

750.0

16 Helicopter Electrical WANDER LIGHT

Wander lights are used for map reading

and acts as a backup for instrument

lighting.



Power consumption: 5 W


0C

DIMENSIONS: 95 mm (L) x 40 mm (DIA)

x 100 mm (H)

WEIGHT: 0.30 kg


Built in intensity control

145.0

Built in intensity control

Flood/spot light selection

Override switch for full intensity

Suitable filter for NVG compatible

operation.



Total Business

Value

(In Rs Laks)

17 Helicopter Avionics HF SYSTEM

HF communication system provides air to

ground and air to air long range and

short range communication system.

Frequency: 2‐‐‐‐30MHz

Channel spacing: 100Hz

Pre‐‐‐‐set channels: Minimum 99 user

programmable channels

Operational modes: USB (voice & data,

reduced carrier), LSB (voice & data), AM,

CW

Range: At least 750 Km at rated power

output with typical tube type antenna

TRANSMITTER CHARACTERISTICS:

Transmitter power output: 150 watts PEP

Sidetone output: 100mW/600ohms

Mic. Input level/Impedance: 0 to 1 V

across 150 ohms

RECEIVER CHARACTERISTICS:

Audio output: 100mW across 600 ohms

Squelch: Variable squelch control to be

available for Pilot to set squelch setting

3750.0

available for Pilot to set squelch setting

18 Helicopter Electrical ICE DETECTION SYSTEM

The system is used to detect and

measure icing severity whilst in flight

and also to detect snow and mixed

conditions. The ice detection component

of the system works by measuring the

speed at which ice is built up (or

melted) on a metal bar in the measuring

head.

ELECTRCAL INTERFACE:

Measuring head is supplied with 115V ac

and 28V dc voltages

1015.0



Total Business

Value

(In Rs Laks)

19 Helicopter Mechanical MGB OIL COOLER FAN

It provides cooling air to MGB oil cooler.

POWER SUPPLY:

Fan is mechanically driven by Auxiliary

Gear Box at 15,119rpm

Max available power supply for the fan:

8KW

FUNCTIONAL REQUIREMENTS:

(i) Volume flow rate at sea level and air

entry temperature of 750C: 1,000

litres/sec

(ii) Required pressure rise (static) at sea

level 750C air temperature: 600 mm H2O

(iii) Nominal speed of the fan and

direction of rotation: 15,119rpm

CW(looking at the fan input shaft)

(iv) Speed range: 95‐‐‐‐104% of nominal

speed (during operation)

:(v) Acceptable noise level: 89 dB (Max)

in 1m distance

OPERATING TEMPERATURE: ‐‐‐‐45 0C to

100 0C

825.0

‐‐‐‐

100 0C

DIMENSIONS:

Fan cross section including casing should

not exceed 254mm DIA



Total Business

Value

(In Rs Laks)

20 Helicopter Mechanical MGB OIL COOLER

The air cooled oil cooler dissipates main

gear box heat by exchanging heat

between gear box oil and fan air.

OPERATION:

Oil flow configuration is two‐‐‐‐pass

cross‐‐‐‐contra and cooling air flow is single

pass. There is one common cooling air

stream and two identical separate oil

streams. Oil temperature

control/pressure relief valves are fitted

in housings cast integrally with the

inlet/outlet tanks. Outlet Temp/

Pressure Valve OPEN/CLOSE condition

≤50C Valve OPEN through action of

thermal element ≥60C and pressure

drop 241 to 310 KPa or below Valve

CLOSED through action of thermal

element ≥60C and pressure drop 241 to

1020.0

element ≥60C and pressure drop 241 to

310 KPa or Above Valve OPEN through

pressure relief valve.

The matrix is of aluminium alloy to BS2

L61 secondary surface construction. Oil

valve housing are of aluminium alloy to

BS L99 and the air inlet and out let ducts

are fabricated from aluminium alloy

21 Helicopter Electrical PITOT STATIC PROBE

To provide pitot and static pressure input

to ADU.


Power supply for the heater: 28V DC

conform to MIL‐‐‐‐STD‐‐‐‐704D

Power consumption: 400watts/probe

(Max)

Insulation resistance between the heater

and the case: >10 MΩ 500V DC

OPERATIONAL PARAMETERS:

Pressure altitude: ‐‐‐‐500m to 7000m

Maximum air speed: 400KMPH

Maximum vertical speed: ± 25 m/sec

Maximum anticipated angle in all

directions: 30 degree

WEIGHT: 600g (Max)

RELIABILTY REQUIREMENTS:

Static pressure repeatability: ± 0.002 qc

1200.0

Static pressure repeatability: ± 0.002 qc

Pitot pressure repeatability: ± 0.005 qc



Total Business

Value

(In Rs Laks)

22 Helicopter Electrical POSITION LIGHT

Three lights are used to determine the

extreme points of the helicopter and also

to indicate its navigation. Position lights

Red and green are installed on left and

right end plates of horizontal stabilizer

and white light is installed on the

vertical fin.

Forward position light: RED

Forward position light: GREEN

Tail position light: WHITE


Connection through M4 ring tongue

terminals OR

As per MIL‐‐‐‐C‐‐‐‐26482 series 2 class L OR

MIL‐‐‐‐C‐‐‐‐38999 series 3/4


Power Consumption: 14 W (Max.) for

each light OPERATI0NAL REQUIREMENTS:

Normal day flight

Normal night flight

Night flight with NVG

225.0

Night flight with NVG

WEIGHT:

Forward position light: 0.2 kg (Max.) for

each light including LED source.

Rear position light: 0.5 kg (Max.)

including LED source.

RELIABILITY REQUIREMENTS:

MTBF: 30,000 flying hours

23 Helicopter Electrical ELECTRIC RESCUE HOIST

Rescue hoist is an electrically operated

system capable of lowering and raising

personnel from helicopter during

hovering. Rescue hoist is operated by

control pendant or by cyclic grip prom of

pilot/ co‐‐‐‐pilot. Maximum load capacity of

rescue hoist is 250kg.

Weight of the unit : 37kg

Maximum operating load : 250kg

Usable cable length : 40m

3750.0



Total Business

Value

(In Rs Laks)

24 Helicopter Electrical SLIP RING

Slip ring is a electromechanical device

that allows the transmission of electrical

signals from rotating mast to indicating

system

SPECIFICATIONS:

Number of channe ls 32

No. of rings/channel 1

Total no. of rings 32

Using voltage 10V

Nominal current 1A

Over current 2A

Variation of Circuit resistance

15 µV/mA

1KHz

4000 mΩ

34 AWG<10mΩ

60.0

To switch between pressure inputs from

static pressure line from pitot tube and

cabin pressure for emergency operations

when pitot static probe is blocked.

25 Helicopter

Electro

Mechanical

System

STATIC SELECTOR VALVE

when pitot static probe is blocked.

Dimensions : 64 x 44 x 70 in mm

o Weight :160 g

o Fitting : On instrument panel by 4

screws (lock nuts inserted)

o Pipe connection :M10 x 100

o Power Source :Pressure or vacuum

applied to the center pipe

connection

o Output use :Right or left pipe

connection

225.0



Total Business

Value

(In Rs Laks)

26 Helicopter MechanicalMAIN ROTOR & TAIL ROTOR

SERVO ACTUATOR

Main rotor actuator function is to

controls collective, pitch and roll

Movement.

Tail rotor actuator function is to controls

yaw Movement.

HYDRAULIC FLUID: MIL‐‐‐‐H‐‐‐‐5606

NOMINAL PRESSURE: 210 bar (Max.)

RETURN PRESSURE: 6.5 bar (Max.)

FLUID TEMPERATURE: ‐‐‐‐54 to 135 C


Nominal Power Supply: 28 V DC

Current Rating: 1 A (Max.)

MAIN POWER ACTUATOR STROKE: 54 mm

CSAS ACTUATOR STROKE: 10.8 mm

15000.0

To provide cooling to Hydraulic system

27 Helicopter Electrical VENTILATOR FAN

To provide cooling to Hydraulic system


Supply Voltage: 115/200 V, 3‐‐‐‐PHASE,

400 Hz

Start current: 6A maximum‐‐‐‐ High speed

condition

2.8A maximum‐‐‐‐ Low speed condition

Run current: 1.5A maximum‐‐‐‐ High speed

condition

0.7A maximum‐‐‐‐ Low speed condition

NOMINAL SPEED: 21,000 rpm‐‐‐‐ High

speed condition

11,500 rpm‐‐‐‐ Low speed condition


0C


High speed condition: 0.078 m3/s

volume flow at 1400 Pa

Low speed condition: 0.039 m3/s

Volume flow at 350 Pa

135.0

28 Hyderabad Avionics VCO Module for HF Transceiver

The VCO module generates frequency in

the range 112.5 to 140.4999 MHz with

reference to the input voltage (3 to 7V).

450.0



Total Business

Value

(In Rs Laks)

29 Hyderabad Avionics Serial I/O Module

The Serial I/O module accepts upto 16

asynchronous input channels and

controls 8 independent output channels.

1110.0

30 Hyderabad AvionicsVHF Power Amplifier Module

for V/UHF Transceiver

This module provides power

amplification upto 40W for VHF signals in

the range 100.1 to 149.975MHz (in AM)

& 156 to 173.975MHz(in FM).

1640.0

31 Hyderabad AvionicsUHF Power Amplifier Module

for V/UHF Transceiver

This module provides power

amplification upto 40W for UHF signals

in the range 220 to 399.975MHz (in AM &

FM).

1640.0

32 Hyderabad Avionics Blanking Signal Processing Unit

This unit provides blanking and

suppression signals to various RF

equipment on Aircraft to ensure

Electromagnetic compatibility (EMC)

requirements.

9361.0

33 Hyderabad Avionics Video Switching Unit

This unit receives video inputs from 27

channels and converts them to STANAG

3350B and switches the video signals as

per Mission Computer commands.

34969.5



Total Business

Value

(In Rs Laks)

34 Lucknow AvionicsType 24 Temperature

Probe(OAT)

This Outside Air Temperature (OAT)

Probe carries a temperature-sensitive

element in its tip and measures the air

temperatures( range -55°C to +250°C)

around it. Probe resistance shall be the

indicator of total air temperature .

582.9

35 Lucknow Avionics Accelerometer

This instrument sense and provides

visual display of A/C linear acceleration

(along longitudinal, lateral and and

vertical axes) in terms of i).

instantaneous value and ii). the

minimum and maximum values

experienced during a chosen period.

Operational range : - 5 to + 10 « g »

unit. Powered by 5V DC.

2064.3

This AOA Indicator operates with 28V

DC, displays the true AOA (free stream

36 Lucknow Avionics AoA Indicator

DC, displays the true AOA (free stream

AOA) of the aircraft from the local AOA

provided by DC voltage signal from

potentiometric AOA probe. Dial reading

of indicator shall be from -10 deg to

+20deg of AOA .

2375.5

37 Lucknow

Electro

Mechanical

System

Pressure Transducer To convert pressure into analog electrical

signal used in mechanical systems.1171.5

38 Lucknow

Electro

Mechanical

System

Pressure Switch

Pressure switch is a gauge pressure

sensing switch intendet to operate on

high pressure hydraulic systems.

342.0

39 Lucknow

Electro

Mechanical

System

Wheel Speed Transducer

It is required to convert rotational wheel

speed information into periodic voltage

siganls for anti-skid control and spoiler

actuation.

630.5



Total Business

Value

(In Rs Laks)

40 Lucknow

Electro

Mechanical

System

Anti skid valve

It is a two position three way valve is

used in on aircraft brake system. When

the solenoid is energised, the pressure

from brake system is supplied to the

brake unit. When de-energised the

pressure supply to the brake is cut-off

and the pressure in the brake line is

released to the tank.

420.4

41 Lucknow

Electro

Mechanical

System

Emergency Selector valve

This is an electrically operated motorized

butterfly valve. It contains two limit

switches for open / close position

monitoring. It isolate the air supply to

the cabin if required

340.3

42 Lucknow Electrical Integrated DC Motor -Type 1

It is a PMDC MOTOR which rotates the

shaft of TRIM Actuator. The Actuator

performs the collective & roll trim action

on control surface of Helicopter. It works

on 28 V DC supply.

376.5

on 28 V DC supply.

43 Lucknow Electrical Integrated DC Motor - Type 2

It is a PMDC MOTOR which rotates the

shaft of TRIM Actuator. The Actuator

performs the yaw trim action on control

surface of Helicopter. It works on 28 V

DC supply.

407.4

44 Engine Casting TURBINE WHEEL STG-1

The casting is a hydrostatic investment

casting. The material is INCO100. The

casting is having the fully finished

(Casting by its process) aerofoil blades.

This casting is used to make a Turbine

wheel stage-1 of the aero engine. This

turbine rotates at 45000 rpm. The

finished turbines required to be qualified

for its metallurgical properties in all

respects as a casting and the finished

turbines are substantiated for its

structural integrity and functional tests

and life establishment tests.

41.26



Total Business

Value

(In Rs Laks)



casting. The material is INCO100. The


(Casting by its process) aerofoil blades.

This casting is used to make a Turbine

wheel stage-2 of the aero engine. This

turbine rotates at 45000 rpm. The

finished turbines required to be qualified

for its metallurgical properties in all

respects as a casting and the finished

turbines are substantiated for its

structural integrity and functional tests

and life establishment tests.

50.06



casting. The material is Titanium MARM-

M-247. The casting is having the fully

finished (Casting by its process) aerofoil

blades. This casting is used to make a

Turbine wheel stage-3 of the aero

engine. This turbine rotates at 45000

rpm. The finished turbines required to be

184.07

rpm. The finished turbines required to be

qualified for its metallurgical properties

in all respects as a casting and the

finished turbines are substantiated for

its structural integrity and functional

tests and life establishment tests.

47 Engine Casting RADIAL STRAIGHTNER

This casting is made up of Titanium

material by investment casting. The


(Casting by its process) twin row aerofoil

vanes. It is used as a stator stage for the

Aero engines. The finished turbines

required to be qualified for its

metallurgical properties in all respects as

a casting.

820.61

48 Engine Casting STEELFLOW STAGHTNER

This casting is made up of Steel material

by investment casting. The casting is

having the fully finished (Casting by its

process) twin row aerofoil vanes. It is

used as a stator stage for the Aero

engines. The finished turbines required

to be qualified for its metallurgical

properties in all respects as a casting.

250.00



Total Business

Value

(In Rs Laks)

49 Engine Casting TURBINE CASING

This casting is made up of INCONEL 718

material by investment casting. The

casting is having the fully finished It is

used as a casing for the complete

Turbine assembly stator stage for the

Aero engines. The finished turbines

required to be qualified for its

metallurgical properties in all respects as

a casting.

1012.28

50 Engine MechanicalSEALOL SEALS

(6 types of seals)

The construction of sealol seal is,

graphite bearing seal face is connected

to one end of the bellow and other end of

the bellow is connected to the bearing

end for the shaft assembly. The function

of the sealol seal is to connect the

housing bearing surface to prevent leak

between the two medias (preferably air

and oil). It also allows the angular

misalignment of the shaft while loading

and rotating at high rpm as high as33000

to 42000 rpm.

22.31

It increases the velocity of hot gases exit

51 Engine Casting 1ST STAGE FT NGV

It increases the velocity of hot gases exit

from the HP turbine exit & directs the

gas to free turbine. The 1st stage nozzle

guide vane is secured to the combustion

chamber external casing, the

intermediate diffuser and the 1st stage

power turbine casing by a ring of bolts.

Investment casting in NC22FeD/

NiCr21Fe18Mo9

116.68

52 Engine Casting PT2 NOZZLE GUIDE VANE

It increases the velocity of hot gas exit

from 1st Stage free turbine disc & directs

the gas to free turbine disc. The 2nd

stage nozzle guide vane is secured to the

1st stage power turbine ring by a ring of

bolts. It ensures the ring of the 2nd

stage power turbine wheel.

Raw Material-CASTING/ INVESTMENT

CASTING

Mat Spec.-NC22FeD/ NiCr21Fe18Mo9

245.06

53 Engine Casting INTERMEDIATE CASING

Intermediate casing houses the first

stage compressor and second stage

compressor. And further intermediate

casing is further secured to air intake

casing and combustion chamber.

Invest ment casting in TA6V/Ti V64

material.

195.88



Total Business

Value

(In Rs Laks)

54 Engine CastingFRONT CASING

(ALUMINIUM)

Front casing is a main component of

reduction gear box located at the front of

Engine. Act as a Casing for main power

drive. The Casing bottom part is the

engine oil reservoir.

Aluminium Casting

211.13

55 Engine CastingREAR CASING

(ALUMINIUM)

Rear casing is a main component of

reduction gear box located at the front of

Engine. It act as casing.

Aluminium Casing made from plate

86.61

Armament Main Unit (AMU) is part of

Weapon Control System (WCS) on fighter

56 Overhaul Armament ARMAMENT AMIN UNIT (AMU)

Weapon Control System (WCS) on fighter

aircraft. It has timing circuits for internal

power supply. The unit controls for the

release of stores from the aircraft.

600.0

57 Overhaul Instrument Flexible Fuel Tanks with cover

plate.

Flexible Fuel Tank is a rubberized tank

installed in the Fuselage. Tanks are held

in position with the assistance of a Stud

Ring on either sides and at the ends

fitted with Doors

870.0

58 Overhaul MechanicalScrew & Nut Assembly

/Leading Cylinder

Screw & Nut Assembly is a sub-

assembly of Leading Cylinder used to

operate Flaps and Slats . It consists of a

multi start threaded Control Rod and

nut. One side eye end is fastened to the

actuation control.

900.0

59 Overhaul Instrument Potentiometer

The Potentiometer consists of a Shaft

that controls dual contact wipers, that

slide on a resistive winding which is

mounted ion a housed bearing. The shaft 600.0

and contact assembly can rotate freely

through 360 degrees



Total Business

Value

(In Rs Laks)

60 Overhaul Instrument Motors for Actuator

a) This motor is used for Operating Fuel

Valve with 90 degree angular movement.

b) Motor ( P/N.: 2701018101) s used for

Operating Butterfly valve with 90

degree angular movement.

300.0

61 Overhaul Mechanical Arrestor Hook AssemblyArrestor Hooks for retardation of the

aircraft during landing on the decks. 580.0

62 Overhaul Instrument Fuel Flow Indicator

The unit indicates the instanteneous

quantity of fuel consumed by the (Two)

engines. Indicator contains 2 separate 245.0

engines. Indicator contains 2 separate

movements, one for each engine.

63 Overhaul Instrument Combined Speed Indicator

The unit indicates Air speed and Mach

number. It is housed in a single case, Air

speed section is conventional capsule

driven which inturn indicates over the dial

through a pointer.

Mach number is indicated with 3 digit

counter visible through 2 cutouts on upper

1077.0

64 Overhaul Instrument Oxygen content gauge Oxygen consumption is indicated through

the pointer.453.0

65 Overhaul Instrument Fuel remaining Indicator Unit indicates reminder fuel in the aircraft. 387.0

66 Overhaul Electrical Central and Protection Unit

This unit controls the automatic switching

of the generator excitation and the main

line contactor when the parameters of the

three phase are within limits. If a fault

condition arises the generator becomes de-

excited and the main busbar dis-connected.

443.0

excited and the main busbar dis-connected.



Total Business

Value

(In Rs Laks)

67 Overhaul Avionics Fuel Flow Amplifier

The amplifier is the central element of a

fuel consumption indicating system for a

two engined aircraft. This amplifier

provides data on the instateneous fuel flow

to two engines and total quantity of fuel

consumed by two engines.

451.0

68 Overhaul Electrical Susceptiformer

Unit is designed to provide matching for the

ADF receiver sense aerial so that the total

capacitance presented to the receiver input

3000pF the susceptiformer is set during

manufacturing to suit a particular total

value of aerial capacitance plus cable

capacitance. it is assembled to receiver

72.0

69 Overhaul Electrical Gun Purging Actuator

It operates the Gun door, the actuator is a

linear actuator powered by a DC motor and

controlled with in preset limit by internal

micro switches. Actuator is fully sealed and

incorporates mechanical stops restraining

the plunger in the event of limit switch

failure.

364.0

The AJAX electro mechanical assembly is

mounted in parellel on the tail plane control

70 Overhaul Mechanical Ajax Assembly

mounted in parellel on the tail plane control

to give the pilot an artificial feel proportion

to the airspeed and altitude . It behaves as

a spring, stiffness of which veries with

aircraft speed and height. operates

automatically without pilot input.

4634.0

71 Overhaul Electrical Weapon control panel

It is a part of weapon control system which

provides pilot operated controls . bus-bar

indicators and the pilot store information

display. It has nine switches and five stores.

2821.0

72 Overhaul Electrical Monitor control panel

The weapon monitor panel is used only on

two seat aircraft, it dulicates the stores

information display given by the control

unit and provides monitoring of certain

selection made by the pilot. Two test

switches are fitted one for checking the

serviceability of the indicators and the

247.0

73 Overhaul Electro Mechanical Electro Pump

Electro pump provides the aircraft hydraulic

services in the event of failure of the Main

hydraulic pump. It comprises a self

regulating plunger type hydraulic pump

with variable flow rate, a compound self

cooling electric motor.

360.0



Total Business

Value

(In Rs Laks)

74 Overhaul Instrument LOX Amplifier

This unit is used to measure the quantity of

liquid oxygen available in the aircraft. The

10 liter oxygen tank is fitted with a probe

supplying the main signal used by the

oxygen quantity indicating system.

195.0

75 Overhaul Electrical Lighting Control Unit

The control unit in conjunction with power

supply unit provides a variable AC supply

for the aircraft cockpit fluorescent lighting.

This containg three microswitches, two

connector block, two twin ganged and one

single rheostat and an external mounted

connector.

194.0

76 Koraput Instrument Jet Nozzle flap indicator

The function of the sensor is to monitor

the position of the jet nozzle tilting unit

of AL-31FP engine powering SU-30MKI

aircraft (Thrust vector control).

Dual channel sine-cosine transformer

Power supply: 6±0.6V

Frequency : 2000±100Hz

6150

Frequency : 2000±100Hz

Ambient temperature range :(-60 to

220°) C.

77 Koraput Instrument Pressure sensor

The sensor measures the engine inlet air

pressure (absolute pressure) at Low

pressure compressor of AL-31FP engine.

The principle of sensor operation is to

transform the movement of sensing

element into electrical signal, which is in

proportion to this movement. When gaps

between coils and armature change,

output voltage of sensor also changes

and voltage output is fed to engine

controller of AL-31FP engine

Measuring range(Absolute):

- 0.1 to 1.6 kgf/cm2

16280

78 Koraput Electrical Spark Plug -1

Spark plug for ignition of fuel air mixture

inside combustion chamber of AL-31FP

engine.

Igniter with semi-conductive spark plug.

Spark frequency- 2-13 sparks/sec.

Input current – (2.5±1)A

2075



Total Business

Value

(In Rs Laks)

79 Koraput Electrical Spark Plug -2

Spark plug for ignition of fuel air mixture

inside combustion chamber of RD33

engine.

Igniter with semi-conductive spark plug.

Insulation Resistance: 500K Ohm at 500V

Breakdown voltage: 2000V

240

80 Koraput Instrument Temperature Sensor

Oil and fuel temperature sensor for

health monitoring of AL-31FP engine .

Electrical transducer :

Oil Temperature range- -60 to 300°C

Fuel Temperature range- -60 to 300°C

2310

The detector is installed on the right

flange and it senses the presence of

flames in the afterburner area. While

ДПИ-1500-5МПЛ is installed on the left

flange and it detects the presence of

flame on the external stabilizer of the

81 Koraput Instrument Ionization Flame Detector

flame on the external stabilizer of the

afterburner.

Feed system : single wire

Mass (max) : 0.55 Kg

Input voltage : 120 Volt AC

Resistance : 20 Mohm ,min in normal

conditions

1 Mohm , min in operating conditions

4790

82 Koraput Mechanical Plunger Spring

This spring is R25 aero engine main fuel

plunger pump that develops pressure up

to 70kg/sec

143

83 ARDC

Avionics Guillotine Assy[Cutter Unit

Assy]

This displays flight and mission critical

information to the pilot through the head

unit (Helmet Visor). The helmet visor is

attached to the pilot's helmet and it follows

his head movements. A magnetic field is

induced inside the cockpit by means of a

Magnetic Transmitter Coils Unit (MTCU).

The helmet incorporates a Digital Magnetic

Receiver sensor. This sensor senses and

sends the helmet angular and spatial

position in the cockpit within the magnetic

field to the LOS Computer Unit (LCU).

646

84 ARDC

Avionics Line of Sight Computer

Unit(LCU)

Part of Magnetic Transmitter Coils Unit

(MTCU)

Part of Magnetic Transmitter

Coils Unit (MTCU)

3295484 ARDC 32954



Total Business

Value

(In Rs Laks)

85 ARDC

Avionics Magnetic Transmitter Coil Unit

(MTCU)


(MTCU)


Coils Unit (MTCU)

916

86 ARDC

Avionics Seat Position Sensor

Assy (SPS Assy)


(MTCU)


Coils Unit (MTCU)

1388

87 ARDC

Electrical 30/40kVA IDG GCU The Generator Control Unit (GCU) provide

the control, regulation and protection for

IDG . It also controls the connection or

disconnection of the alternators output

from the aircraft electrical circuits.

6246

88 ARDC

Electrical 30/40kVA Integrated Drive

Generating System (IDG)

30/40 kVA Integrated Drive Generator

(IDG) delivers 3 phase AC supply of

115/200V, at 400 Hz as Main AC Power

source.This is the main AC source driven by

Aircraft Mounted Accessory Gear Box.

During normal operation this supplies

power to all AC Bus bars and through

Transformer Rectifier Units (TRUs) to DC

21482

89 ARDC

Instrument Pilot's Control Grip The Pilot’s Control grip is fitted on control

stick assembly and installed in the cockpit

at the pilot right hand facility. The control

grip will have the switches like

Communication sensor control switch, AP

Disconnect switch, Firing trigger,

Armament switch lever etc located

ergonomically.

2482

90 ARDC

Instrument Throttle GripThis grip is mounted on top of power

control lever in cockpit. The throttle grip

provides suitable and comfortable hand -

hold for the throttle stick and smooth

housing for the switches and cables.

1290



Total Business

Value

(In Rs Laks)

91 ARDC

Instrument Throttle Quadrant Assembly

(TQA) [Type: ET 20-AF]

This provides an interface between the pilot

and the engine fuel control system by

controlling the Fuel controls unit . The

aircraft requires a single lever in the

cockpit to control the engine operations.

The movements of the lever are fully

duplicated in both the front and the rear

cockpits.

11804

92 ARDCMechanical Pin, expandable Quick release

Aft Engine mount AssemblyIt is used for holding & locking thrid mount

of Engine.156

93 ARDC Electro mechanical

Ejection Seat This will provide safe ejection capability

during emergencies in take off phase,

landing phase & in Airborne phase. 21836

94 ARDC

Avionics GPS Antenna

This is an antenna for Global positioning

system.

21360

95 ARDC

Avionics Gyro Reference Unit (GRU)

This provides the information of

Roll,Pitch,Magnetic Heading, Rate (Pitch,

Roll & Yaw), Acceleration (X, Y & Z).

1856

96 ARDC

Avionics Multi Function Display

Unit[MFD]

It is a 5" x 5" / (6" x 6") color video

display and control terminal in the

avionics system.Input Votlage 28V.

Resolution: 600 x 600 color quad pixels12522

97 ARDC

Avionics V/UHF Blade Antenna It is a passive blade antenna and

operates in V/UHF frequency band.

V/UHF radio is connected to this antenna

through RF cable.

2336

98 ARDC

Avionics V/UHF Radio(ACR 500LA) This equipment provides secure

communication in VHF/UHF band, with

users of similar or compatible equipment

which may be either on ground or

airborne.

26520

99 ARDC

Avionics Enhanced VDR Unit Unified Video cum Digital

Recorder(UVDR) is an airborne Digital

multi-channel Recorder, which

simultaneously acquires & records

Digital Data from different sources to

analyse the performance of A/C sub-

15680

100 ARDCAvionics Remote Cartridge Unit Holder

(RCUH)Part of Unified Video cum Digital

Recorder(UVDR)

Part of Unified Video cum

Digital Recorder(UVDR)2584100 ARDC (RCUH)

Recorder(UVDR) Digital Recorder(UVDR)2584



Total Business

Value

(In Rs Laks)

101 ARDC

Avionics Removable Mass Memory

Device

(RMMD)

Part of Unified Video cum Digital

Recorder(UVDR)

Part of Unified Video cum

Digital Recorder(UVDR)4322

102 ARDC

Avionics High speed Blade Antenna (IFF

Antenna) This is an antenna used in Identification

friend,foe system.1464

103

ARDC Avionics 24 Port Gigabit Ethernet Switch The Multi-Mode Radar (MMR) is a pulse

Doppler radar, operates at X-band

frequency and supports Air-to-Air (AA),

Air-to-Sea(AS) and Air-to-Ground (AG)

missions when selected.

The three main sub-systems are the

Transmission System, Receiving System

and Signal Processing System

4136

104 ARDCAvionics MMR Front End Receiver Part of Multi-Mode Radar (MMR) Part of Multi-Mode Radar

(MMR)122680

105 ARDCAvionics MMR RADAR Processor(RP

Assy)

Part of Multi-Mode Radar (MMR) Part of Multi-Mode Radar

(MMR)86120

106 ARDCAvionics MMRTransmitter(Tx) Assy Part of Multi-Mode Radar (MMR) Part of Multi-Mode Radar

(MMR) 84960106 ARDC (MMR) 84960

107 ARDC

Avionics RAM (Altimeter) AntennaThis antenna is used to measure the

altitude above the terrain. 800

108 ARDC

Avionics RWR Antenna Spiral cavity

Backed

This provides early warning about RF

threats illuminating the aircraft. . The

RWR system is designed for threat

acquisition, target tracking, interception

and identification of airborne and ground

based missile guidance radars.The three

main sub-systems are the antenna,

552

109 ARDC Avionics RWR Power Divider Part of RWR system Part of RWR system 178

110 ARDC Avionics RWR- Switch Filter Assembly Part of RWR system Part of RWR system 14960

111 ARDC

Avionics TACAN Antenna This is an antenna used in line of sight

system (TACAN) which provides slant range

of the aircraft from the ground station

using transmitter/transponder technique.156

112 ARDC

Avionics VOR – ILS Antenna:(A) Part of TACAN System

354

113 ARDC

Avionics VOR – ILS Antenna: (B) Part of TACAN System

354

Avionics VOR Diplexer This system provides guidance in poor

114 ARDC

This system provides guidance in poor

visibility conditions during approach to

runway

314



Total Business

Value

(In Rs Laks)

115 ARDC

Avionics VOR-ILS Marker Antenna

Part of VOR-ILS Systems 186

116 ARDC

Electro Mechanical Avionics Flow Control ValveThis unit is used to control the cooling air

flow to avionics. This is a motorized

butterfly valve with position indicator, limit

switches for identifying fully open and

closed positions and mechanical end stops

1936

117 ARDC

Electro Mechanical Control Unit PressureReducing

& Shut Of

This is a remotely mounted unit which

controls the

Shut-off and Pressure regulation functions

of Pressure Regulating And Shut-Off Valve

(PRSOV). The Shut-off head of PRSOV is

controlled by the solenoid. Pressure control

in PRSOV is obtained by controlling servo

pressure to the Pressure Control Head of

PRSOV in conjunction with a remotely

mounted Datum Control Unit.

4036

118 ARDC

Electro Mechanical ECS Shut-Off Valve This valve is used to shut-off the flow to

ECS in case of over temperature due to any

failure in the upstream components thereby 1956118 ARDC failure in the upstream components thereby

protecting the system from further damage.1956

119 ARDCMechanical Hot Air Leak Sensing Element his element consists of a eutectic salt

whose impedance increases rapidly above a

pre-determined temperature

1428

120 ARDC

Instrument Hot Air Leak Detection Control

Unit

This unit is used to cut-off the bleed air in

case of hot air leak in the system.

642

121 ARDC

Mechanical Valve Pressure Reducing

&Shut-Off

It is a double headed, inline valve. The Shut-

off head is controlled by a remotely

mounted solenoid (Part of Datum Control

Unit), which supplies upstream pressure to

the rear of the Shut-off head. Pressure

control is obtained by the rear mounted

Pressure Control Head in conjunction with a

remotely mounted Datum Control Unit.

7008

122 ARDC

Electro Mechanical Pressure Reducer-Cabin Seal

This unit is used to regulate the cabin seal

pressure to a pre-determined value. It also

has a Over pressure relief function in case

of failure of the pressure regulating

function.

1340

123 ARDC

Instrument Temperature Sensor - Cabin

and Avionics

This unit is used to sense the temperature

at the cabin

inlet, Cabin outlet and Avionics inlet. It

gives an appropriate voltage as output

signal which is read by ECS Controller in

504


order to control the ECS



Total Business

Value

(In Rs Laks)

124 ARDC

Instrument Temperature Sensor - PHE

Outlet

This unit is used to sense the temperature

at the Outlet of the Primary Heat Exchanger

and give an appropriate voltage as output


order to control the ECS.

364

125 ARDC

Instrument Pneumatic Temperature SensorThis is a duct mounted, thermally operated

sensor with a bi-metallic sensing element.

This sensor takes the servo air supply from

the duct, modulates it to the required value

using the sensing element.

1170

126 ARDC

Electro Mechanical Primary Heat exchanger By-

Pass Valve

This valve is used to regulate the flow by-

passing the Primary Heat Exchanger to

achieve a controlled mixed temperature at

the outlet of Primary Heat Exchanger

3964

127 ARDC

Electro Mechanical Ejector Shut-Off ValveThis is a nominal 50mm inlet and 40 mm

outlet diameter, Solenoid operated,

pneumatically actuated butterfly valve with

limit switches to monitor fully open and

closed positions of the valve. This opens

when the solenoid is energized. Also, it has

an Over pressure relay which shall fully

open when the upstream pressure reaches

8932

open when the upstream pressure reaches

9.5 bars absolute.

128 ARDC

Mechanical High Pressure Water SeparatorThis unit is used to extract water from

incoming charge air. It is a high pressure

water separator of fixed angle, swirl type

with a wet air inlet, dry air outlet and a

water drain connection.

880

129 ARDC

Electrical Ground Power Receptacle

(GPR)

The ground electrical power supply

receptacle (aircraft plug) provides a

115/200V, 3 Phase , 400Hz AC Supply and

28Vdc when servicing the aircraft or

starting the engine .

86

130 ARDC

Electrical Undercarriage Display Unit This indicates the status of Airbrake, NWS,

Brake Fail, Antiskid, Brake Parachute,

Undercarriage Doors, three Gear Position

for gear Downlocked or Uplocked condition,

Arrestor Hook down indication and a BIP

switch. All indicators shall be NVG Gen 3

compatible.

770

131 ARDC

Electro Mechanical Undercarriage Selector Lever

[Undercarriage Control Lever]

This is a selection switch in cockpit which

controls normal Landing Gear extension and

retraction operation. It is a lever operated

snap action six pole double through switch

with multi poles to enable necessary relay

logic for retraction and extension operation

of the under carriage.this will have

indicators and override features integrated

1788

indicators and override features integrated

in it.



Total Business

Value

(In Rs Laks)

132 ARDC Hydraulic System

Control cable - Under

carriageEmergency

Pull cable with handle, accessories & casing

for manual operation of emergency controls 490


Control cable -

Park Brake Control

Pull cable with handle, accessories & casing

for manual operation of park/emergency

brake selector lever.506

134 ARDC Hydraulic SystemEmergency Underc-arriage

Selector Valve

2 position, 6 way manually operated valve.

It will be operated in case of emergency,

for extension of landing gear

3622


Pressure GaugeBourdon tube based gauge to display

pressure1158


Pressure Switch(P1&P3) Ty1 Converts pressure input to electrical signal

at a set value of pressure & it is used for

health

monitoring of hydraulic system

378


Pressure Switch (P2) Ty2 Converts pressure input to electrical signal


health


126



Pressure Switch(FCS) Ty3 Converts pressure input to electrical signal


health


756


Progressive Pressure Control

Valve

Progressively vary the output pressure

based

on lever travel. Full stroke travel of lever

should provide full pressure for parking of

the aircraft.

516


Slide & Swivel JointJoint capable of both sliding & swiveling

in different length & shapes472












in different length & shapes472144 ARDC Hydraulic System




Total Business

Value

(In Rs Laks)





















Pressure Switch(EMDP) Ty4 Converts pressure input to electrical signal


health monitoring of hydraulic system

564

152 ARDC Hydraulic SystemPressure Switch (Park) -Ty5 Converts pressure input to electrical signal


health monitoring of hydraulic system

320

153 ARDC

Electro Mechanical Antiskid Manifold Brake manifold receives signal from

antiskid brake controller and controls

corresponding hydraulic fluid flow to the

corresponding brakes.

The anti-skid brake manifold contains 4

pressure control servo valves, 2 shuttle

valves and 2 solenoid selector valves. The

manifold should be symmetric about its

axis. Each half is supplied by different

hydraulic systems.

12664

154 ARDC

Electro Mechanical Brake Feel Input

Potentiometer

This Brake feel module input potentiometer

converts the Brake pedal tip deflection into

electrical signal. The potentiometer will be

excited by +5 V DC(max) regulated power

supply from an electronic unit and the

position output of 0-5 V DC will be fed to

the digital conditioning hardware of

Electronic unit.

552



Total Business

Value

(In Rs Laks)

155 ARDC

Electro Mechanical Free castor valve

(Solenoid Cock)

The Free caster valve makes the steering

system to revert to the free caster mode, so

the aircraft can be steered by differential

braking of main wheels.

It's a tow-port two-way single solenoid

operated valve, the valve normally opens in

either direction and both the ports will be

closed when the solenoid is energised.

1016

156 ARDC

Mechanical Main Wheel TyreLeft side and Right side main landing gear

was fitted with a High Pressure 26 x 8.00 -

14 Tube less Cross Ply tires. The operating

temperature of tyre is -55 to 200 °C.

188

157 ARDC

Mechanical Nose Wheel Tyre Nose Landing gear is fitted with two High

Pressure 360 x 135 -6 tubeless cross Ply

tires. The operating temperature of the

tyre is -55 to 200 °C

136

158 ARDC

Electro Mechanical Nose Wheel Steering

Feedback

Potentiometer

The NWS feedback potentiometer is Rotary

potentiometer, senses the position of the

nose wheel during steering and transmits

the data to the electronic controller for

closed loop control.

62

closed loop control.

159 ARDC

Electro Mechanical Nose Wheel Steering Input

Potentiometer

The Nose Wheel Steering Input

potentiometer converts the Rudder pedal

deflection into electrical signal. the pot will

be excited by +10 V DC(max) regulated

power supply from an electronic unit and

the position output of 0-10 V DC will be fed

to the digital conditioning hardware of

340

160 ARDC

Electro Mechanical Nose Wheel Steering Manifold Nose wheel steering manifold is an electro

hydraulic servo control (EHSV) manifold

which receives the electrical signals from

the digital controller and it supplies the

hydraulic fluid to the LH/RH side of the NLG

steering actuator as demanded by the pilot.

The NWS manifold contains Electro

hydraulic control valve (EHSV), By pass

valve, Electro selector valve, Anti cavitation

valve and pressure relief valve.

76378

161 ARDC

Mechanical Air No-Fuel Float Valve When installed within the aircraft fuselage

tank will allow outward/inward venting of

the tank during refue/deful operation and

inward venting at all steady- state flight

condition. The valve will also prevent

overfilling/spillage and fuel from entering

the pressurisation and vent system during

inverted flights.

504



Total Business

Value

(In Rs Laks)

162 ARDC

Mechanical Cap,3" dia ,fuel,

composite,lightning safe

• Installed in the top surface of Fuel tanks

• It is used to access for gravity refueling

of the fuel tanks.

• It is leak proof and fool proof locking

adapter.

• Standard dia of filler cap: 3 inch (75mm),

Temperature range -53 Deg C to + 93Deg

C:Made of light weight material with

lightning protection. Max operating

pressure inside the tank is 50 Psig

300

163 ARDC

Electro Mechanical DC Starting Pump Supplies fuel in adequate quantity and at

required pressure for Jet fuel starter

• Installation : Flange mounted, installed

inside the fuel tank, submerged in inverted

flight compartment

• Nominal operating voltage: 28V DC

• Installation : Flange mounted, installed

inside the fuel tank, submerged in inverted

flight compartment

• Nominal operating voltage: 28V DC

1158

164 ARDC

Electro Mechanical Differential Pressure Switch • Provides indication to the controller

when differential pressure exceeds a pre-1242164 ARDC

when differential pressure exceeds a pre-

set value

• Operates on 28V DC

1242

165 ARDC

Electro Mechanical Double Ended Fuel

Booster Pump

• Duel inlet, centrifugal pump, driven by a

single electric motor

• Supplies fuel at required inlet conditions

(flow rate & pressure) to meet the

maximum engine demand (7 kg/sec).

• Installation : Vertically mounted inside

the fuel tank, submerged in inverted flight

compartment. Nominal operating voltage:

115 V AC, 3 phase, 400 Hz.

3202

166 ARDC

Mechanical Float Valve • Used in the refueling / fuel transfer

system

• Fuel transfer is initiated when fuel level

drops below the float valve level and stops

when float valves are fully immersed.

1650

167 ARDC

Mechanical Fuel Drain Valve • Spring loaded valve, used to drain fuel

from fuel tanks

• Valve should flush with the tank contour

• Installation : bottom most point of CFC

fuel tanks

380



Total Business

Value

(In Rs Laks)

168 ARDC

Electro Mechanical Fuel Emergency Pump • Helical impeller / vane type pump driven

by gear type hydraulic motor operating at

280 bar pressure.

• Operates when main booster pump is

fails, based on the input from the selector

valve.

• Installation : Flange mounted inside the

fuel tank, submerged in inverted flight

compartment with hydraulic motor and its

connections.

• Nominal operating voltage: 115 V AC, 3

phase, 400 Hz

1708

169 ARDC

Mechanical Fuel Shut Off Cock This is a motorized, bi-directional ball valve

with straight through hole designed for

unobstructed flow to the engine. The rapid

shut off is accomplished by a light weight

27 VDC permanent magnet motor. The gear

box coupled to cam drives this cam over an

angular travel of 90± 5. This valve is having

a provision for thermal relief on the up

stream side only to relieve high pressure

fuel due to high temperature when the

1814

fuel due to high temperature when the

valve is shut off.

170 ARDC

Electro Mechanical Motorized Shut Off Valve(Low

pr shut off cock)

It is motorized valve to shut-off / ON fuel

supply to the engine by the pilot selection.

•Bi-directional ball valve for unobstructed

flow to the engine Light weight 16/28 V DC

permanent magnet motor with construction

of gear box cam drives. •Valve has thermal

relief on the upstream of the flow.

•Normal operating pr : 350 kPa, Operating

time = 3 sec, Max flow rate 7.5 to 8.5

Kg/sec.

1476

171 ARDC

Electro Mechanical Power Take-off shaftDuring Engine starting , PTO shaft trasmits

power from AMAGB (Aircraft Mounted

Accessory Gear Box) to Engine gear box and

during normal operation , it transmits

power from engine gear box to AMAGB.

3594

172 ARDC

Mechanical Pressure Reducing

Valve

• Spring loaded plunger valve

• Used in fuel tank pressurization / vent

system for reducing the pressure of high

pressure air tapped from ECS to suit fuel

tank pressurization requirements

468

173 ARDC

Mechanical Pressure Reducing Valve• Spring loaded plunger valve

• Used in fuel tank pressurization / vent

system for reducing the pressure of high

pressure air tapped from ECS to suit fuel

tank pressurization requirements

468



Total Business

Value

(In Rs Laks)

174 ARDC

Electro Mechanical RefuelIing Valve • Used for pressure refueling of fuel tanks

• Operation (Open / close) based on the

signals from controller

• Operation (Open / close) based on the

signals from controller

• Differential pressure operated valve,

controlled by solenoid valve

2752

175 ARDC

Mechanical Stop Air Valve These valve is used to prevent:

1. Ingress of air into the fuel transfer line

from fuel tanks, once the transfer is

completed by actuation of float operated

valve.

2. Transfer of both fuel and air during

inverted / negative “g” flight conditions.

3. Fuel flow from transfer pipe to the tank

in case the line pressure in pipe line is

higher than tank pressure.

3606

Mechanical Straitener, Flow • Installed in the Engine fuel feed system

• It is used to measure the mass of the fuel

flow to the engine.

176 ARDC

flow to the engine.

• It is turbine (impeller) fuel flow meter ,

impeller speed is converted into electrical

frequency which is function of volumetric

flow rate.

• Temperature range -53 Deg C to + 93Deg

C: Max fuel temp : 120 Deg C ( short

duration)

164

177 ARDC

Mechanical Surge Relief Valve - F1A Tank • Spring loaded valve, installed on the fuel

tanks • Relieves excess fuel pressure when

tank pressure exceeds the pre-set value

• Valve closes automatically when tank

pressure falls below the pre-set value

1012

178 ARDC

Mechanical Relief Valve(Surge relief valve

F1/2 tank)

• Spring loaded valve, installed on the fuel





120

179 ARDC

Mechanical Surge Relief Valve - LH &RH

Wing Tanks

• Spring loaded valve, installed on the fuel





2024



Total Business

Value

(In Rs Laks)

180 ARDC

Electro Mechanical Transfer cum Refuelling Valve • Used in the refueling / fuel transfer

system

• Installed in collector tank and controlled

by the float valves connected via the servo

tube.

• Shall act as a NRV to prevent back flow of

fuel from collector tank to transferring

tanks.

1380

181 ARDC

Electro Mechanical Transmitter • Installed in the Engine fuel feed system

• It is used to measure the mass of the fuel

flow to the engine.

• It is turbine (impeller) fuel flow meter ,

impeller speed is converted into electrical

frequency which is function of volumetric

flow rate.

• Temperature range -53 Deg C to + 93Deg

C: Max fuel temp : 120 Deg C ( short

duration)

1548

182 ARDC

Mechanical Seal Rubber Special shaped

section-Engine Inlet It is used for sealing between Engine inlet

face and Aircraft air intake duct.110

183 ARDC

Instrument Charge Amplifier (Pre-

Amplifier)

The engine mount in the A/c is

incorporated with a piezo-electric type

transducer for measuring vibration levels.

Charge Amplifier amplifies this vibration

signal which is monitored by engine

monitoring electronic unit. This must be

cabable of an Input upto 100g's of high

frequency signal without saturating and

impacting the ability to handle low

frequency signal.Output voltage (max) 0 to

5Vp-p.Size: 170Cu.cm

volume.Weight<175gms.

598

184 Kanpur

Mechanical

Temperature Control VALVE

This valve controls the cabin

temperature by regulating the flow of

hot bleed air into the mixing

chamber.The temperature control valve

is a 38 mm (1.5 inch) diameter butterfly

valvepowered by a 28 V DC actuator. The

valve plate is attached to a spindle

supported in carbon bushes.The valve

aperture can be varied by application of

28 V DC to one of the two control inputs.

335.0



Total Business

Value

(In Rs Laks)

185 Kanpur

Instrument

Duct Temperature Sensor

The sensors are twin thermistor bead

types with the two beads mounted at the

end of a metal probe and encapsulated in

epoxy resin.Two temperature sensors

are fitted for regulating the cabin

temperature.

12.8

186 Kanpur Instrument Temperature Controller 272.9

187 Kanpur

Mechanical

CHECK VALVE

The check−valves are fitted in the LH/RH

bleed air line just before the point where

the air flows combine.The check−valves

are insert type, double flap stainless

steel check valves. The valves are biased

to the closed position by a torsion spring

and are also provided with over−center

stops. The valves are fitted in the bleed

air lines to prevent reverse flow if one

engine is shut down.

274.6

188 Kanpur

Mechanical

COOLING UNIT

The cold air unit is of the conventional

‘turbo-fan‘ type comprising an inward

flow radial turbine driving an axial flow

fan.

706.3

fan.

189 Kanpur

Mechanical

Shut Off VALVE

The shut−off valves are fitted directly

downstream of the bleed air elbows on

each engine. The valves are

pneumatically actuated in-line shut-off

valves controlled by a solenoid valve.

1248.0

190 Kanpur

Mechanical

WATER SEPARATOR

The water separator removes the

moisture from the conditioned air and is

acoalescer/swirl type with a relief

valve.An insulating jacket of

polyurethane foam is moulded to the

outside of the casing.

236.5

191 Kanpur

Mechanical

OVER TEMPERATURE SWITCH

The switch is fitted in the duct header

and provides warning if an over

temperature condition occur in the

distribution subsystem.The switch is

flange mounted and is equipped with an

wiring connector. It is of the high

expansion coefficient, spring bow type.

34.2

192 Kanpur

Mechanical

RAM AIR SHUTOFF

VALVE

The ram air shut-off valve is fitted

between the ram air inlet and the duct

header. The valve has a nominal

diameter of 80 mm and is powered by a

28 V DC actuator. The body and butterfly

are aluminium alloy, the latter being

attached to a spindle which is supported

in carbon bushes.

130.0

193 Kanpur Electrical FAN

It is an fan to cool the avianocis bay by

sucking the air from outside.it opeerates 615.8193 Kanpur Electrical FAN sucking the air from outside.it opeerates

at 28V and power consumption is 5W.

615.8



Total Business

Value

(In Rs Laks)

194 Kanpur

Mechanical

PRV & SOV

The valve provides shut off and pressure

regulating facilities for the bleed supply

to the heating and ventilation and air

conditioing system.

199.2

195 Kanpur

Mechanical

PRESSURE SWITCH

The switch monitors the supply pressure

to the air conditioning system so that in

the event of an over−pressure condition

the switch operates and the BLEED

PRESS warning light illuminates.

38.4

196 Kanpur Electrical SERVO MOTOR

The Servo actuator convert electrical

command signal from the flight computer

into mechanical commands which are

then transmitted to the elevator.

Electrical command signal are convert to

torque by a DC motor that drives a gear

train and techo.

The tacho provides an electrical output

signal proportional to elevator(for pitch)

/Aileron(for Roll)/Rudder(for Yaw)

moving speed. This signal feed back to

1577.6

moving speed. This signal feed back to

the flight computer, provides airplane

stability

1. Pitch Servo- Install in the rear fuslage

2. Roll-Servo- Install in the right wing

section near the fuslage.

3. Yaw Servo- install in the rear fuslage.

197 Kanpur

Mechanical

MOUNTING

This is a servo mount with slipping clutch

used in servocontrols of auto flight

system. Fitted on the cable drum by the

mean of six screw on its periphary. Its

used in Roll servo.

19.5

198 Kanpur

Mechanical

MOUNTING

This is servo mount with slipping clutch

used in servocontrols of auto flight

system. Fitted on the cable drum by the

mean of six screw on its periphary. Its

used in Pitch and Yaw Servo.

78.1



Total Business

Value

(In Rs Laks)

199 Kanpur

Instrument

FLAP TRANSMITTER

Flap transmitter is part of The stall

warning system which is fitted in the left

wing between the first flap bearing arm

and the fuselage.

The flap transmitter is connected to the

flaps and supplies a signal to the lift

computer dependent on flap position.

The lift computer evaluates this signal

together with the signal from the lift

transducer and processes the

information into a signal suitable for use

by the RSD (Reference Speed Deviation)

indicator.

380.1

An asymmetry control unit is fitted on

the outboard ends of the left and right

flap outer drive shafts. These two

asymmetry units compare the positions

of the left and right flaps and provide a

fail-safe circuit to stop the flaps when an

asymmetrical movement is detected. The

left and right asymmetry control unit

200 Kanpur Electrical SHAFT BRAKE

left and right asymmetry control unit

each consist of six cam−operated

contacts and an electromagnetic brake.

The brakes are controlled by relays

during flap extension and retraction.

Each contact in the left asymmetry unit

is paired with a contact in the right unit

to form an AND logic circuit which

decides whether the 28 V control line to

terminal R of the flap selector switch is

switched on or off.

Weight of wing tip brake with

asymmetric unit is 4 kg.

1030.1

201 Kanpur Electrical VOLTAGE REGULATOR

Voltage regulators are part of DC

generation system in the aircraft and

controls two 28V DC, 300A

Starter/generators working

simultaneously. Incorporates control and

protection circuits to ensure that the

required output voltage is maintained

within +/- 0.5 V throughout the normal

speed/load range of the generators.

Protoction is provided against

overvoltage, over-excitation and reverse

or differential current

657.9

202 Kanpur

Instrument

DC VOLTMETER,32V

One inch dial voltmeter used to display

28 V DC system voltage in the aircraft. 133.1202 Kanpur DC VOLTMETER,32V 28 V DC system voltage in the aircraft.

Range 0-32V. Mounted on overhead panel

133.1



Total Business

Value

(In Rs Laks)

203 KanpurInstrument

AC VOLTMETER,115VOne inch dial voltmeter used to display

115 VAC system voltage in the aircraft.

Mounted on overhead panel.

549.4


AMMETER,500AOne inch dial ammeter used to display

28V DC system load in the aircraft.

Mounted on overhead panel.

553.6

205 Kanpur Electrical POWER SUPPLY UNIT

The unit supplies pulsed out put to anti

collision lights and navigation lights. 28

V DC is applied to the power supply unit,

chopped amplified and rectified to 400

VDC. The 400 V DC is fed to the strobe

generator which provides the pulse

output for the lights.

65.9

206 Kanpur Electrical DIMMER

Controls light intensity of cockpit and

instruments light during day and night.

The annunciators and warning lamps can

be dimmed by the DIM switch

(DAY/NIGHT).

286.5

207 Kanpur ElectricalSTARTER GENERATOR

(300AMP)

Engines are started by

Starter/Generator. Once the engines are

started the unit works as DC generator

1542.6

208 Kanpur Instrument TECHO GENERATOR It generate the signal for engine RPM 350.6

209 Kanpur

Mechanical

FUEL PRESSURE SWITCH

Fuel pressure switch is part of low fuel

pressure warning system. Warning signal

is sent to warning panel when fuel feed

pressure drops below 600 mbars

58.2

210 KanpurMechanical

FIRE EXTINGUISHER Used to extinguish fire in Engine Nacelles 468.7


FUEL FLOWMETERIt provide signal to fuel low meter to

indicate fuel flow rate191.7


TRANSM. OIL

PRESSURE

Oil Pressure transmitter sense oil

pressure of engine oil provide input to oil

pressure indicator in Cokpit

278.2

213 Kanpur

Mechanical

UNFEATHRING PUMP

Pump supply engine oil under pressure

to propeller piston assembly via the

propeller pitch control and oil transfer

tube to change propeller angle from

feather to unfeather.

232.8

214 Kanpur

Mechanical

OIL COOLER

Oil cooler maintain the engine oil

temperature and it consist of a housing

with finned oil lines running

horizontaly.A by pass valve controlled by

oil temperature.

1174.0


FLOAT SWITCHFloat switch is installed in the fuel tanks

and gives low fuel level warning169.3

216 Kanpur

Mechanical

FUEL BOOSTER PUMP

Booster pump provide motive flow for

the jet pump to tranfer the fuel from one

tank to another and also provide the fuel

for engine.

1635.9

for engine.



Total Business

Value

(In Rs Laks)

217 Kanpur

Mechanical

PILOT VALVE

The left and right fuel control pilot valves

are installed in the top of the appropriate

inner wing tank. They control their

associated refueling valves.

Each fuel control pilot valve consists of a

float operated valve which opens or

closes

the fuel control line. The movements of

the float are damped by a spring. A drain

port

in the bottom of the valve container is

opened and closed by a solenoid valve

579.5

218 Kanpur Mechanical PILOT OPERATED CHECK VALVE

DO-228 Pilot Operated Check Valve

provides a bypass of the landing gear

Selector Valve in case of its jamming in

landing gear up position.

Provides additional return line in case of

emergency operation of Landing Gear

Extension. Operated by Pneumatic Pilot

Pressure.

360.0

Pressure.

219 Kanpur

Mechanical

VALVE

They open or close the refueling line to

that tank. Each refueling valve consists

of a diaphragm which acts on the valve

seat and opens or closes the refueling

line to

the tank. A small orifice in the diaphragm

allows the control line to the fuel control

pilot valve to be kept filled with fuel

during refueling.

The refueling valve support is fitted with

a spring loaded flapper valve which is

covered by an inlet screen and opens

during suction defueling.

372.0

220 Kanpur

Mechanical

JET PUMP

The motive fuel flow for all four jet

pumps is taken from a common pipe

which is

fed by the booster pumps. The venturi

effect created in the jet pumps by this

flow causes fuel to be pumped

continuously from each tank via the

transfer pipes into the

feeder tank

851.5



Total Business

Value

(In Rs Laks)

221 Kanpur

Mechanical

JET PUMP

The motive fuel flow for all four jet

pumps is taken from a common pipe

which is

fed by the booster pumps. The venturi

effect created in the jet pumps by this

flow causes fuel to be pumped

continuously from each tank via the

transfer pipes into the

feeder tank

1651.3


SHUT OFF VALVEIt open and closes to supply and to stop

the fuel flow in engine 441.2


CROSS FEED VALVECrossfeed valave used for inter- connect

of fuel line of both wings156.9

224 Kanpur

Mechanical

FUEL QUANT.TRANS.

Fuel quantity Transmitter are of the dual

concentric tube capacitive and changes

in direct relationship with change in fuel

level

919.9

225 Kanpur

Mechanical

FUEL QUANT.TRANS.




level

904.0

Mechanical Fuel quantity Transmitter are of the dual

226 Kanpur

Mechanical

FUEL QUANTITY TRANS.TANK




level

253.2

227 Kanpur

Instrument

LEVEL TRASMITTER




level

253.2

228 Kanpur

Mechanical

VALVE

The LH and RH fuel systems are two

independent systems, supplying fuel to

their respective engine. Both systems

are interconnected by a cross-feed line

which is provided with an electrically

controlled shut-off valve

825.3

229 Kanpur

Mechanical

DRAIN VALVE

One drain valve is fitted in each feeder

tank, one in each inner, two in each

outer tank

and one in each optional auxiliary wing

tank. The valves are spring loaded with a

bayonet type catch and are opened or

closed by pressing and turning with a

screwdriver.

384.9

230 Kanpur

Mechanical

VALVE

One drain valve is fitted in each feeder

tank.The valves are spring loaded with a

bayonet type catch and are opened or

closed by pressing and turning with a

screwdriver.

33.8



Total Business

Value

(In Rs Laks)

231 Kanpur

Mechanical

VALVE

A manual shut-off valve is mounted near

the refueling connector and provides the

connection to the crossfeed line via

which the feeder tanks can be defueled

43.3

232 Kanpur

Instrument

DISPLAY TERMINAL

Gun sight is an optical unit mounted in

the cockpit and used for aiming at the

target for firing of guns mounted on the

wing pylons. It works on opical

principles.

588.3

233 Kanpur Electrical WIPER MOTOR

The wiper motor is the part of wiper

system and provides the drive for the

wipers. The motor is series wound and

consists of a suppressor, thermal

overload protection and a parking switch.

163.5

234 Kanpur Hydraulic System WIPER ARM

The wiper arms are made of stainless

steel and are secured to the converter

/gearboxes of wiper system. A spring

located in the wiper arm presses the

wiper blade against the windshield. The

contact pressure of the wiper blade can

130.4

contact pressure of the wiper blade can

be adjusted by a screw on the arm pivot.

The arm position is adjustable on the

converter / gearbox shaft.

235 Kanpur Hydraulic System CONVERTER

Coverter is a worm drive gearbox with a

reduction ratio of 155:1. It is used in

wiper system. It converts rotational

motion from the wiper motor into an

oscillating angular motion.

261.3

236 Kanpur

Mechanical

VALVE

This is Restrictor / check valve fitted in

the extension line to the nose gear

actuator. The restrictor/ check valves

control the extension and retraction time

of the Main and Nose Landing Gears.

25.2

237 Kanpur Hydraulic SystemGEAR BLOW DOWN

UNIT

Emergency Gear Blow Down system

system is used to lower the landing

gears by nitrogen pressure in case of

hydraulic system failure. The main

component of this system is the gear

blow down unit. This consists of a

nitrogen bottle, blow down valve,

charging valve, pressure relief valve and

pressure gage. The blow down valve is

cable operated from an EMERG LDG

handle in the cockpit. A safety clip over

the handle guards against inadvertent

operation.

263.7



Total Business

Value

(In Rs Laks)

238 Kanpur Hydraulic SystemVALVE SELECTOR LANDING

GEAR

Landing Gear Selector Valve is a four

way, three position hyadraulic valve.

This selector valve directs the Hydraulic

pressure from Pressure line to extension

and retraction lines of Main and Nose

Gear actuators and return line for

extension and retraction of main and

nose landing gears. This unit consists of

two solenoids and pilot valve assembly.

527.0

239 Kanpur Hydraulic System BRAKE ACCUMULATOR

The brake accumulator supplies

hydraulic pressure to parking brake

system. It gets charged up again when

the power pack is operating. This

accumulator consists mainly of a cylinder

and a piston. The piston separates

precharged gas on one side from

hydraulic oil on the other side. The

hydraulic side is connected to a pressure

line of the hydraulic system.

243.1

240 Kanpur Hydraulic System PRESSURE GUAGEThis pressure gauge is used to indicate

the pressure of emergency brake / 59.0240 Kanpur Hydraulic System PRESSURE GUAGE the pressure of emergency brake /

parking brake accumulator.

59.0

241 Kanpur Hydraulic System FIRE EXTINGUISHER

Portable Fire Extinguishers are installed

one each in cockpit and cabin. These are

used to extinguish fire in the flight or

passenger compartment. It uses HALON

1211 (Bromochlorodifluoromethane

(BCF) as an extinguishant and are thus

suitable for use on minor electrical,

liquid or textile fires.

37.6

242 Kanpur Hydraulic SystemLOCKING,LANDING

GEAR (UPLOCK)

The Landing Gear - Up Lock is used to

lock and unlock the Main and Nose

landing Gears in retracted position. It is

a Hydro-mechanical unit. Locking is

provided mechanically through insertion

of hook whereas unlocking is provided by

hydraulic pressure in normal condition or

by gas pressure in emergency condition.

The mechanism also provides the

electrical indication of unlock position

through micro switch.

2023.1



Total Business

Value

(In Rs Laks)

243 Kanpur Hydraulic System NLG ACTUATOR

The Nose Landing Gear (NLG) Actuator is

double-acting hydraulic cylinder. This

actuator retracts to lower the NLG and

extends to raise the NLG. This actuator

locks internally in the retracted position

to keep the NLG in extended position

without pressure. The fully retracted

position of actuator is signaled

electrically. Actuator is normally

operated by hydraulic pressure and on

‘EMERGENCY’ arising out of hydraulic

failure; it is retracted by pneumatic

(nitrogen) pressure.

655.9

244 Kanpur Hydraulic System PRESSURE GAUGE

This pressure gauge is used to indicates

the pressure of Hydaulic system.

Pressure Range 0 to 350 bar, Hydraulic

Type.

246.0

These Main Landing Gear Actuators are

double-acting hydraulic cylinders. These

actuators extend to lower the MLG and

retract to raise the MLG. These actuator

lock internally in the extended position

245 Kanpur Hydraulic System MLG ACTUATOR

lock internally in the extended position

to keep the MLG in extended position

without pressure. The fully extended

position of actuators is signaled

electrically. Actuators are normally

operated by hydraulic pressure and on

‘EMERGENCY’ arising out of hydraulic

failure, actuators are extended by

pneumatic (nitrogen) pressure. The

actuators are fitted with shuttle valve to

facilitate the emergency operation. The

LH and RH actuators differ only in the

orientation of the shuttle valve.

677.5

246 Kanpur

Instrument

SWITCH

It is a rotatry switch mounted in control

panel of environmental system.This

switch is used to set the cabin

temperature from cold to hot.

56.2

247 Kanpur

Instrument

IMPACT SWITCH

The impact switch interrupts power to

the flight data recorder (depending on

forward "g" forces to prevent tape/data

erasing.

25.4

248 Kanpur

Instrument

FLUX VALVE

The flux valve senses the direction of the

earth's magnetic field and supplies the

information in a 3-wire synchro format

to the slaved directional gyro. They

consist of magnetic laminations which

are wire wound in a toroidal fashion. The

toroid is excited with 26 V,400Hz

20.2

toroid is excited with 26 V,400Hz

supplied from the slaved directional gyro.



Total Business

Value

(In Rs Laks)

249 Kanpur

Instrument

SIGNAL CONDITIONING UNIT

Signal conditioning unit processes

signals to suite various indicating

instruments of fuel and engine systems.

Torque indicator, fuel flow indicator and

Totalizer are fed with signal conditioning

unit

79.9


MOUNTING TRAYThis mounting tray is used to install

flight data recorder.64.3

251 Kanpur

Instrument

TAT SENSOR

TAT Sensor is obtained by a probe on the

airplane that measures the temperature

of the free air stream air at the airspeed

of the airplane.

478.6

252 Kanpur

Instrument

TEMP TRANSMITTER

This temp transmitter consist of a

resistance bulb which is connected in

one of the bridge circuit indicator. A

change in outside temperature varies the

resistance of the bulb and thus the

potential of the bridge. The resulting

change is indicated in °C.

10.8

253 KanpurInstrument LIGHT TRAY

ASSEMBLY

Mounting tray for Electric Attitude

Indicator1.3

Instrument The attitude indicator shows the familiar

254 Kanpur

Instrument

ATTITUDE INDICATOR

The attitude indicator shows the familiar

true sphere —type display. It

also contains an eyelid display and

inclinometer with white polar

lighting. The system is powered by 26 V

AC (400 Hz).

164.7


STALL WARNING HORNProvides audio warning for stall in the

aircraft43.8

256 Kanpur Instrument SPEAKER Horn for TCAS system 1.2

257 Kanpur

Instrument

TEMPERATURE SENSOR

The sensors are twin thermistor bead

types with the two beads mounted at the

end of a metal probe and encapsulated in

epoxy resin.Two temperature sensors

are fitted for regulating the cabin

temperature.

23.2

258 Kanpur Instrument INSTT DATA MODULE Stores calibration data of MSU in AHRS 7.8


MOUNTING TRAYAHRU(Attitude and heading reference

unit) mounting tray37.9

260 Kanpur

Instrument

CONTROL UNIT

Part of fuel indication system.Outputs

from fuel quantity transmitters are

supplied to the control unit where the

signals are processed into a form

suitable for the fuel quantity indicators

499.7

261 Kanpur

Instrument NOSE WHEEL

STREERING CONTROL

UNIT

Part of nose wheel steering system. It

consists of a servo channel,

monitor channel and control logic

circuitry to control steering.

117.9

Instrument Part of pitot/static system. The pitot

tube consists of a tube flange mounted

to the airplane and a wiring connector 262 Kanpur PITOT TUBE to the airplane and a wiring connector

for the heating element. Provides pitot

pressure to Air speed indicator,

maximum allowable speed indiator etc.

353.0



Total Business

Value

(In Rs Laks)

263 Kanpur AvionicsREMOTE ELECTRONIC UNIT

REU6100-3-(110)

Part of DVCS 6100 Interphone system.

All the signal proceesing of various

com/nav etc takes place within this unit.

530.2

264 Kanpur

Instrument

U/C SELECTOR LEVER

Installed on front panel used to select

landing gear position UP & DOWN.

Provides visual warning during transition

of landing gear from one position to

another

535.6

265 Kanpur Avionics ANTENNAAntenna for Collins Radar Altimeter ALT

55B/ALT1000689.4

266 Kanpur Avionics ANTENNA

Automatic Direction Finder (ADF 60)

conbined LOOP-Sense Antenna to receice

the signals from Non Direction Beacons.

229.9

267 Kanpur Avionics ANTENNAAntenna for Identification Friend & Foe

IFF 1410 system64.0

268 Kanpur Avionics ELT 503 (INCL BATTERY)Emergency Locator Transmitter is

automatic and manual activated to

transmit the distress signals

268.0

269 Kanpur Avionics ELT INTERFACE UNITPart of ELT 503 system. Used for

interfacing the other systems.80.5

interfacing the other systems.

270 Kanpur Avionics G-SWITCHG-Switch sense the impact of the aircraft

in terms of G-Values for automatic

activation of ELT.

36.6


MOUNTING TRAYFor mouting the ELT transmitter

alongwith G-Switch32.9

272 Kanpur Avionics REMOT CONTR.Part of ELT 503 system. Used to remotely

control the ELT system.22.6

273 Kanpur Avionics TRANSMITTER ELT 503 transmitter 95.4

274 Kanpur Avionics ANTENNA Antenna for VHF Navigation system VIR-

32/NAV 4000 system9.3

275 Kanpur Avionics ANTENNA

GPS antenna interfaced with Automatic

Identification System(AIS) used for

receiving GPS signals for computing own

LAT/LONG

13.2

276 Kanpur Avionics Combined CVR/FDR Deployable

This is a combined CVR/FDR/ELT system

which is deployable in emergency. The

system records cockpit voice in CVR and

flight data in FDR and can transmit on

distress frequency as part of ELT

3000.0

277 Kanpur AvionicsANTENNA RECEIVER

UNIT

Direction Finder system for search and

rescue operation682.7

278 Kanpur Avionics S.L.B.

Sonar Locator Beakon: SLB is a battery

operated underwater acoustic pulse

generator that is activated when the

water switch is immersed in either fresh

or salt water. The beacon is designed to

operate for a minimum of 30 days after

14.6

operate for a minimum of 30 days after

being immersed in the water. SLB is a

mandatory attachment with all the FDR

or CVRs across the world.



Total Business

Value

(In Rs Laks)

279 Kanpur

Instrument

ACCELEROMETER

Tri-axial Accelerometer: It is used for

sensing aircraft acceleration in three axis

(Normal, Longitudinal & Lateral), and

provide it to be recorded on Flight Data

Recorder (FDR)

198.5

280 Kanpur Avionics ANTENNA COUPLER

The amplified signal is routed to the KAC

1052 Antenna Coupler, which matches

the various impedances of the antenna

to the 50 Ω output of the transmitter.

Under microprocessor control, the KAC

1052 antenna coupler selects tuning

network configurations, impedance

transformations and binary capacitance

and inductance to produce a VSWR of

2.5:1 or less upon initial tune

494.5

281 Kanpur Avionics CONTROLLER UNIT

The PS 440 stand alone Control panel

provides control of the KHF 1050

communication radio system via a

dedicated low speed, Digital ARINC 429

bus. PS 440 allows the pilot to select the

frequency and mode of operation of the

system and displays that information to

550.6

system and displays that information to

the pilot

282 Kanpur Avionics POWER AMPLIFIER

The KPA 1052 is an High Frequency

Power Amplifier which amplifies the

excitation signal from the KRX 1053

Receiver/Exciter to 200 W PEP, or 50 W

of carrier power in AM. From 2.0 to

29.9999 MHz, the power amplifier is

capable of linear amplification of a 0

dBm (1 mW) signal to a 53 dBm (200 W)

output level at 50 input and output

impedance

219.6

283 Kanpur Avionics RECIEVER/EXCITES

The KRX 1053 is an HF Receiver/Exciter

that is designed to operate from 2.0 to

29.9999 MHz synthesized in 100Hz

steps. The unit will operate Amplitude

Modulation Equivalent and Upper and

Lower sideband modes

248.2

284 Kanpur Avionics OMNI DIRECT.ANTENNAIt is L band omnidirectional antenna

used for 1030/1090 Mhz transmission

and reception

50.1

285 Kanpur AvionicsALTITUDE ENCODER

(Blind Coder)

This altitide encoder provides Baro

altitude information in electrical signal

(gillham code)

7.1

286 Kanpur Avionics COAX RELAYthis relay is uesd for connecting/

switching the Mode S antenna to the

active transponder.

97.2

It is the conrol for TCAS and Mode

transpoder, generally used for setting 287 Kanpur Avionics CONTROLLER

transpoder, generally used for setting

range, Flight ID slection of active

transponder etc.

139.2



Total Business

Value

(In Rs Laks)

288 Kanpur Avionics MODE-S INSTT KIT

It consist of installation tary, connector

and PCB for installation of and coding of

Mode S address for the Mode S

transponder

146.5

289 Kanpur AvionicsMODE-S TRANSPO-

NDER

Mode transponder provide Mode A , C

and S information on interrogation fro

ATC of TCAS system of other aircraft. It

also support data link for exchange of

messages from the intruder aircraft.

2015.5

290 Kanpur Avionics TCAS PROCESSOR

The TCAS system is an airborne

surveillance system that maintains a

surveillance area around the aircraft

through use of replies received from

other aircraft transponders. It alerts the

crew to presence of nearby transponder

equipped aircraft provides the flight

crew with information about detected

and tracked aircraft near the own

aircraft. Provides traffic advisories of

potential conflicts. Provides resolution

advisories to avoid conflicts

1431.4

advisories to avoid conflicts

291 Kanpur AvionicsTCAS PROCESSOR

MTG TRAY

Mechanical tary in which TCAS processor

sits in.8.6

292 Kanpur Avionics TCAS TOP DIRECTI ANTENNADirectional antena opretaes in L band,

Transmit at 1030MHz and Recive 1090

MHz

135.0

293 Kanpur Avionics ANTENNA V/UHF Antenna. Part of V/UHF systems 48.7

294 Kanpur AvionicsRECEIVER/TRANSMI-

TTER(RT)

Receiver Transmitter of V/UHF system

ARC 210 for voice communication8359.7

295 Kanpur Avionics REMOTE CONTROL UNIT(RCU)Remote Control Unit for V/UHF system

ARC 210 for voice communication4746.5

296 Kanpur Avionics RT MOUNTMouting for RT unit and Part of ARC 210

system209.6

297 Kanpur Avionics VOR/GS ANTENNAAntenna for VIR-32 VHF navigation

system24.3

298 Kanpur Avionics COUPLER Part of VIR-32 VHF navigation system 2.8

299 Kanpur Avionics MOUNTING TRAYmechinal tray to which SELCAL decoder

sits in 109.7

300 Kanpur Avionics SELCAL CSD-714

The SELCAL system is selective calling

decoder that permits ground stations,

equipped with tone encoding equipment,

to call individual aircraft by transmitting

two pairs of selected audio tones. These

encoded audio tones will only activate a

“SELCAL" decoder unit set to respond to

that particular combination of tones.

When proper tones are received, decoder

operates a light, signaling that there is a

message intended for that particular

254.6

message intended for that particular

aircraft.



Total Business

Value

(In Rs Laks)

301 F&F Casting MGB HOUSING Mg alloy CASTING 393.60

302 F&F Casting INPUT HOUSING LH/RH Mg alloy CASTING 81.22

303 AERDC CASTINGS TURBINE NOZZLE

Scope of Work: To be indigenised / Develop

the unit and should be Form, Fit & Function

(FFF).

Material: Ni Alloy

Diameter:190-200 mm

No. of blades:20 to 35

233.3



304 AERDC CASTINGS TURBINE NOZZLES


(FFF).

Material: Ni Alloy

Diameter:160 mm


455.1

305 AERDC CASTINGS TURBINES



(FFF).

Material: Ni Alloy

Diameter:140-160 mm


114.5

306 AERDC CASTINGS COMPRESSOR



(FFF).

Type:Centrifugal compressor

No of Blades: 14 No

Diameter:200 mm

Matl: Al Alloy

144.6



Total Business

Value

(In Rs Laks)

307 AERDC ELECTRICAL STARTER MOTOR



(FFF).

Type:DC Series motor

Nominal Operating voltage :28 Volts

Max. current drawn (A): 300

Rated power @ 6000rpm (kW): 1.5

L:150 MM,D:90 MM

105.3

308 AERDC MECHANICAL BASE PUMP



(FFF).

Type:Electrical Dual Gear pump

Voltage:18-28 V

Oil flow rate:1 lpm

Fuel flow rate:2.5 lpm

84.3



(FFF).

309 AERDC MECHANICAL BACK PLATE

(FFF).

Backplate (fuel manifold) is secured to the

rear face of the combustor casing

Diameter:400 mm

Material:Aluminium alloy

22.4

310 AERDC MECHANICAL OIL TANK

Sheet metal componet

Tank capacity:1.5 lt

L=200 mm,H:200 mm,W:150 mm

Material: St. Steel

52.5

LRU (In Rs Laks) 1 Aircraft Avionics AUDIO CONTROL … of Item 5th Apr 2016 V… · 2 Aircraft...

Documents

Transcript of LRU (In Rs Laks) 1 Aircraft Avionics AUDIO CONTROL … of Item 5th Apr 2016 V… · 2 Aircraft...