FORM 2
THE PATENTS ACT, 1970
(39 of 1970) & The Patents Rules, 2003
COMPLETE SPECIFICATION
(See section 10 and rule 13)
1. TITLE OF THE INVENTION
Device for Testing, Adjustment and Simulation of Regulator Switch used in
Aircraft
2. APPLICANT(S) "
(a) NAME: HINDUSTAN AERONAUTICS LIMITED
(b) NATIONALITY: INDIAN
(c) ADDRESS: SM(PP-SUROH), Aircraft Overhaul Division, Nasik
3. PREAMBLE TO THE DESCRIPTION
COMPLETE The following specification
particularly describes the invention and
the manner in which is to be performed.

4. DESCRIPTION (Description shall start from next stage.) Refer An nexure I
5. CLAIMS (Not applicable for provisional specification. Claims should start with the preamble - "I/We claim" on separate page)
Refer Annexure II
6. DATE AND SIGNATURE (to be given at the end oflastpage of specification)
7. ABSTRACT OF THE INVENTION (to be given along with complete specification on separate page)
Refer Annexure III
Note:-
*Repeat boxes in case of more than one entry.
*To be signed by the applicant(s) or by authorized registered patent agent.
*Name of the applicant should be given in full, family name in the
beginning.
"Complete address of the applicant should be given stating the postal index
no./code, state and country.
*Strike out the column(s) which is/are not applicable.

ANNEXURE-I
1 Title of the Invention
Device for Testing, Adjustment and Simulation of Regulator Switch used in Aircraft
2 Field of the Invention
The invention relates to electrical, mechanical and aerospace engineering in general and the specifically to aircraft repair
3 Background of the Invention
The aircraft lighting system is designed to provide illumination for front as well as rear cabin internal surfaces and instruments boards in day and night condition. In both cabins for better illumination of instruments, test panels and instruments boards, a provision is made for white flood lights. The flood light lamps are powered from aircraft power source and the level of illumination of flood lights is controlled by regulator switch. The regulator switch installed on instruments board in both cabins for easy switching operation and control of illumination level of flood lights as per the requirement in both cabins. The regulator switch control the voltages of the flood light lamps through converters and converters are connecter and receive the power from aircraft power source. Sometime switching and control of illumination of flood light lamps operation are not smooth from regulator switches of cabin. The trial and error process is adopted for simulate and test the regulator switches of aircraft and it is a tedious, time consuming and resource intensive process.
Consequently, to reduce the cycle time of aircraft repair and overhaul, a device and methodology is developed to carry out repair, adjustment, test and load simulation (as per the aircraft condition) for regulator switches.

ANNEXURE-I
Prior Art
European patent EP3193228:
Method of autonomously operating an aircraft lighting system and autonomous exterior aircraft light, describes autonomous exterior aircraft light. Though it is related to an aircraft lighting system, it does not deal with device for test, adjustment and simulation of regulator switch used in illumination control for internal lighting system on aircraft either on the scope or on the functionality.
US patent US 5416672:
Aircraft illumination device, describes a systems for illuminating parts of an aircraft, including three low intensity position light mounted on the aircraft. Though it is related to an aircraft lighting system, it does not deal with device for test, adjustment and simulation of regulator switch used in illumination control for internal lighting system on aircraft.
European patent EP0736453:
Aircraft lighting system, is about external aircraft lighting systems, and in particular to such system for use with night vision goggle on fighter aircraft. Though it is related to an aircraft lighting system, it does not deal with the device for test, adjustment and simulation of regulator switch used in illumination control for internal lighting system on aircraft.
4 Brief Summary of the Invention
The present invention is a portable device for testing, adjustment and simulation of regulator switch of aircraft. Regulator switch is complex potentiometer arrangement with switching element and it work with voltage converter in aircraft for cabin lighting system of aircraft. This system is intended to work along with lighting management system of aircraft and as per the requirement of pilots. Regulator switch generate the signal for

switching ON/OFF of cabin flood lights and also control the illumination of cabin flood light.
The present invention deals with the innovative design of portable
r
device for testing the electrical parameter of regulator switch, adjustment of complex potentiometer arrangement with switching element and simulation of electrical load used in aircraft in a simple, less time consuming and with highly safer mode.
5 Detail description of the drawings
The invention can be better understood by reading the detail description of
the disclosed embodiment followed by the accompanied drawings:
Figure 1: Block diagram of Device for testing, adjustment and
simulation of regulator switch used in aircraft.
Figure 2: Schematic diagram of Device for testing, adjustment and
simulation of regulator switch used in aircraft.
Details of figure 1 & 2
1. Device
2. Connecting Element-1
3. Connecting Element-2
4. Holding fixture
5. Power Supply control
6. Indicating Element-1
7. Measuring Element-1
8. Converter
9. Selecting Element-3
10. Measuring Element-3
11. Electrical Load-2
12. Selecting Element-1
13. Measuring Element-2
14. Selecting Element-2

ANNEXURE-I
15. Measuring Element-3
16. Electrical Load-1
17. Regulator switch
18. Angle Measuring Element
19. Pointer
20.Tuning Device
21. Connecting loom
6 Detail Description of the Invention
The aircraft lighting system is designed to provide illumination for front as well as rear cabin internal surfaces and instruments boards in day and night condition. In both cabins for better illumination of instruments, test panels and instruments boards, a provision is made for white flood lights and the level of illumination of flood lights is controlled by regulator switch. The regulator switch installed on instruments board in both cabins for easy switching operation and control of illumination level of flood lights as per the requirement in both cabins. Number white flood lights is based on the design and pilot requirement on the aircraft.
Present invention deals with the innovative design of portable device for testing the electrical parameter of regulator switch, adjustment of complex potentiometer arrangement with switching element and simulation of electrical load used in aircraft specifically. A full understanding of the invention can be gained, when wherein parts are referred by the numerals read in conjunction with;
Figure 1: Block diagram of Device for testing, adjustment and simulation of regulator switch used in aircraft.
Figure 2: Schematic diagram of Device for testing, adjustment and simulation of regulator switch used in aircraft.

Device (1) for test, adjustment and simulation of regulator switch (17) is connected with Connecting Element-1 (3) used in aircraft and mounted on Holding fixture (4), Connecting Element-2 (2) is consist of a connecting element with flexible loom. Connecting Element-2 (2) receive 27 volt DC power from external power supply and it is electrically connected with Power Supply control (5). Power Supply control (5) is connected with a Selecting Element-1 (12), Selecting Element-2 (14), Selecting Element-3 (9), Converter (8) and Connecting Element-1 (3) through Connecting loom (21). Power Supply control (5) control and regulate the input power supply and the presence of input power is continuously displayed on Indicating Element-1 (6) and monitored through Measuring Element-1 (7). a) Testing of resistance:
Selecting Element-1 (12) is connected with Measuring Element-2 (13) and connected with regulator switch (17) through Connecting loom (21), when Selecting Element-1 (12) is selected for resistance check Measuring Element-2 (13) shows the value of resistance of regulator switch (17) under test.
i. Resistance value should be smoothly increases when regulator switch (17) shaft rotates in clockwise direction and maximum value of resistance is achieved at extreme clockwise direction. ii. Resistance value should be smoothly decreases when regulator switch (-17)- shaft rotatesJn anti-clockwise direction and minimum value of resistance is achieved at extreme anti-clockwise direction. After completion of resistance check Selecting Element-1 (12) is selected back to its initial position. b) Testing of Micro switches:
Selecting Element-2 (14), Measuring Element-3 (15) and Electrical Load-1 (16) is connected with regulator switch (17) through Connecting loom (21), When Selecting Element-2 (14) is selected at Position-1 and Position-2, the electrical load is connected across the micro-switches of regulator switch

(17) under test respectively and value of voltage drop is shown at Measuring
Element-3(15).
Higher voltage drop across the micro switches concluded that internal
condition of Micro switches is unacceptable and require replacement. After
completion of resistance check Selecting Element-2 (14) is selected back to
its initial position.
c) Adjustment of angle of rotation :
Regulator switch (17) is connected with Connecting Element-1 (3) mounted on Holding fixture (4). Holding fixture (4) consist of Angle Measuring Element (18), Pointer (19) and Tuning Device (20) use to tune the Regulator switch (17) as per the required angles.
i. When Pointer (19) is at extreme clockwise direction minimum angle
is observed at Angle Measuring Element (18).
ii. When Pointer (19) is at extreme anti-clockwise direction maximum
angle is observed in Angle Measuring Element (18)
iii. For adjustment of angle of rotation a Tuning Device (20) use to adjust
the angle of Regulator switch (17) at minimum and maximum position.
d) Simulation of aircraft electrical load:
Selecting Element-3 (9), Measuring Element-4 (10) and Electrical Load-2 (11) is connected with regulator switch (17) through Connecting loom (21), When Selecting Element-3 (9) is selected at load position (i.e Over-load and under-load)-Electrical Load-2 (11) is connected for Simulation of aircraft equivalent electrical load through converter (8).
After Simulation of aircraft electrical load Selecting Element-3 (9) is selected back to its initial position.

We Claim,
1. A device (1) for testing, adjustment and simulation of regulator switch
(17) used in aircraft comprising: A Connecting element-1(3) connected with regulator switch (17) and
mounted on Holding fixture (4), Power Supply control (5) is connected
with a Selecting Element-1 (12), Selecting Element-2 (14), Selecting
Element-3 (9), Converter (8) and Connecting Element-1 (3) through
Connecting loom (21); A Selecting Element-1 (12) is connected with Measuring Element-2 (13)
and use to measure the resistance of regulator switch (17) under test;
and A Selecting Element-2 (14) is connected with Measuring Element-3 (15)
and Electrical Load-1 (16), use to measure the voltage drop of regulator
switch (17) under test. 2. The device (1) claimed in Claim-1, comprising of Angle Measuring
Element (18), Pointer (19) and Tuning Device (20) use to tune the
Regulator switch (17) as per the required angles in a simple way.