Light source assembly and methods for aircraft external lighting

• US 7,055,994 B2
• Filed: 02/13/2003
• Issued: 06/06/2006
• Est. Priority Date: 09/19/2000
• Status: Expired due to Fees

• Current Assignee: L-3 Communications Corporation (L3Harris Technologies, Inc.)
• Original Assignee: L-3 Communications Corporation (L3Harris Technologies, Inc.)
• Inventors: Martin, John J.
• Primary Examiner(s): Tran, Thuy Vinh
• Application Number:
  US10/503,777
• Publication Number:
  US 20050093718A1
• Time in Patent Office: 1,209 Days
• Field of Search: 315 76- 77, 315/291, 315/307, 315/308, 315/246, 340981-982, 362/459, 362/470, 362543-547
• US Class Current: 362/470
• CPC Class Codes: B64D 2203/00 Aircraft or airfield lights using LEDs
• CPC Class Codes: B64D 47/06 for indicating aircraft presence
• CPC Class Codes: F21W 2107/30 for aircraft
• CPC Class Codes: H05B 45/10 Controlling the intensity of the light
• CPC Class Codes: H05B 45/3577 Emulating the dimming characteristics, brightness or colour temperature of incandescent lamps
• CPC Class Codes: H05B 45/3725 Switched mode power supply [SMPS]

Abstract

An aircraft light assembly comprises a light apparatus configured to be supported in a space on the body of an aircraft. The apparatus has one or more light emitting diodes (13) generating visible light and an outer structure overlying the LEDs. The outer structure includes a light transmission portion through which visible light from the LEDs can pass, and a metallic portion with an outer surface exposed to the external airflow. A heat-transmitting connection thermally links the LEDs to the metallic portion so that heat from the LEDs flows to the outer surface and is dissipated to the external airflow. The light assembly is configured to be secured in a conventional socket for an incandescent navigation light bulb and to receive the electrical current supplied thereto by the aircraft electrical system. Civilian applications of the unit have only visible LEDs. When the unit is for a military aircraft, it has electric circuitry connected with a visible light source and an IR light source, and the electric circuitry is configured to process the input current from the socket and based thereon operate in either a visible mode or covert IR mode. Where the current is in one electrical state, such as for example a certain voltage, the electric circuit sends power only to the visible light source. When the current is in a different electrical state, e.g., a different voltage level, the circuitry sends power only to the IR source, and no visible light is emitted. Different input current voltages or characteristics are also used to cause the IR emitter to flash in various patterns that can be programmed into the unit. All control may be accomplished over a single pair of wires, as in existing systems that do not have IR mode capability. To upgrade existing aircraft, light source units a shaped to fit in the apertures for existing lenses over incandescent navigational fixtures.

Claims

1. A dual mode light unit for an aircraft, said unit comprising:

light control circuitry configured to be operatively connected with wiring connecting with pilot interface circuitry so as to receive an electrical current therefrom,

a visible navigational light source connected with the light control circuitry, and

an infrared light source connected with the light control circuitry,

said light control circuitry, when the electrical current is in a first electrical state, supplying power to the visible navigational light source and, when the electrical current is in a second state, causing the visible light source to produce substantially no visible light and supplying power to the infrared light source so that the infrared light source pulses in a first time dependent pattern, and said pattern having pulses or intervals between pulses of two or more different durations.

2. The dual mode light unit of claim 1 wherein the aircraft wiring includes a socket and the unit includes a connector base structure configured to be received in the socket on the aircraft and to receive the electric current through the socket.

3. A method of providing an infrared light source to an aircraft having a navigational light connected with an electrical system supplying electric current thereto, the current being in one of a plurality of electrical states, and the aircraft having a pilot-accessible control therein responsive to which the pilot can selectively cause the current to change to a different electrical state for adjusting brightness of the navigation light, said method comprising:

removing the navigational light from the aircraft; and

inserting in said socket a dual mode light unit according to claim 2.

4. The dual mode light unit of claim 1 wherein the light control circuitry is configured to receive current having a varying voltage, said first and second electrical states of the current being first and second voltages thereof.

5. A method of providing an infrared light source to an aircraft having a navigational light connected with an electrical system supplying electric current thereto, the current being in one of a plurality of electrical states, and the aircraft having a pilot-accessible control therein responsive to which the pilot can selectively cause the current to change to a different electrical state for adjusting brightness of the navigation light, said method comprising:

removing the navigational light from the aircraft; and

inserting in said socket a dual mode light unit according to claim 4.

6. The dual mode light unit of claim 4 wherein the light control circuitry is configured to receive AC current having a varying voltage.

7. A method of providing an infrared light source to an aircraft having a navigational light connected with an electrical system supplying electric current thereto, the current being in one of a plurality of electrical states, and the aircraft having a pilot-accessible control therein responsive to which the pilot can selectively cause the current to change to a different electrical state for adjusting brightness of the navigation light, said method comprising:

removing the navigational light from the aircraft; and

inserting in said socket a dual mode light unit according to claim 6.

8. The dual mode light unit of claim 1 wherein said flash pattern is cyclically repeated.

9. A method of providing an infrared light source to an aircraft having a navigational light connected with an electrical system supplying electric current thereto, the current being in one of a plurality of electrical states, and the aircraft having a pilot-accessible control therein responsive to which the pilot can selectively cause the current to change to a different electrical state for adjusting brightness of the navigation light, said method comprising:

removing the navigational light from the aircraft; and

inserting in said socket a dual mode light unit according to claim 8.

10. The dual mode light unit of claim 1 wherein the light control circuitry, responsive to the current being in a third electrical state, causes the infrared light source to pulse in a second time dependent pattern different from the first pattern.

11. A method of providing an infrared light source to an aircraft having a navigational light connected with an electrical system supplying electric current thereto, the current being in one of a plurality of electrical states, and the aircraft having a pilot-accessible control therein responsive to which the pilot can selectively cause the current to change to a different electrical state for adjusting brightness of the navigation light, said method comprising:

removing the navigational light from the aircraft; and

inserting in said socket a dual mode light unit according to claim 10.

12. The dual mode light unit of claim 10 wherein the light control circuitry is configured to receive current having a varying voltage, said first, second, and third electrical states of the current being respective voltages thereof.

13. A method of providing an infrared light source to an aircraft having a navigational light connected with an electrical system supplying electric current thereto, the current being in one of a plurality of electrical states, and the aircraft having a pilot-accessible control therein responsive to which the pilot can selectively cause the current to change to a different electrical state for adjusting brightness of the navigation light, said method comprising:

removing the navigational light from the aircraft; and

inserting in said socket a dual mode light unit according to claim 12.

14. The dual mode light unit of claim 10 wherein the light control circuitry has an input through which a user can program the circuitry to select or define the flash patterns or to select the electrical states to which the circuitry responds.

15. A method of providing an infrared light source to an aircraft having a navigational light connected with an electrical system supplying electric current thereto, the current being in one of a plurality of electrical states, and the aircraft having a pilot-accessible control therein responsive to which the pilot can selectively cause the current to change to a different electrical state for adjusting brightness of the navigation light, said method comprising:

removing the navigational light from the aircraft; and

inserting in said socket a dual mode light unit according to claim 14.

16. The dual mode light unit of claim 1 wherein said visible light source comprises a set of LEDs supported in the unit and connected with the light control circuitry.

17. A method of providing an infrared light source to an aircraft having a navigational light connected with an electrical system supplying electric current thereto, the current being in one of a plurality of electrical states, and the aircraft having a pilot-accessible control therein responsive to which the pilot can selectively cause the current to change to a different electrical state for adjusting brightness of the navigation light, said method comprising:

removing the navigational light from the aircraft; and

inserting in said socket a dual mode light unit according to claim 15.

18. The dual mode light unit of claim 16 wherein the light unit is configured to be secured in a space in a body of the aircraft,

said light unit including a metallic portion exposed to external airflow when in said space, and

the LEDs being thermally linked to the metallic portion such that heat generated by the LEDs flows to the metal portion and is dissipated to the airflow such that the LEDs remain at temperatures within an operational temperature range thereof.

19. A method of providing an infrared light source to an aircraft having a navigational light connected with an electrical system supplying electric current thereto, the current being in one of a plurality of electrical states, and the aircraft having a pilot-accessible control therein responsive to which the pilot can selectively cause the current to change to a different electrical state for adjusting brightness of the navigation light, said method comprising:

removing the navigational light from the aircraft; and

inserting in said socket a dual mode light unit according to claim 18.

20. The dual mode light unit of claim 18 wherein the metallic portion supports a window member through which light from the LEDs can pass, said window and metallic portion closing said space against said external airflow over the aircraft body.

21. The dual mode light unit of claim 20, wherein the light control circuitry illuminates the LEDs by supplying to said LEDs an electrical power current derived from the electrical current received from the aircraft electrical system.

22. A method of providing an infrared light source to an aircraft having a navigational light connected with an electrical system supplying electric current thereto, the current being in one of a plurality of electrical states, and the aircraft having a pilot-accessible control therein responsive to which the pilot can selectively cause the current to change to a different electrical state for adjusting brightness of the navigation light, said method comprising:

removing the navigational light from the aircraft; and

inserting in said socket a dual mode light unit according to claim 21.

23. The dual mode light unit of claim 20 wherein said window and metallic portion define an outer surface that is conformal to an outer contour of the aircraft body.

24. A method of providing an infrared light source to an aircraft having a navigational light connected with an electrical system supplying electric current thereto, the current being in one of a plurality of electrical states, and the aircraft having a pilot-accessible control therein responsive to which the pilot can selectively cause the current to change to a different electrical state for adjusting brightness of the navigation light, said method comprising:

removing the navigational light from the aircraft; and

inserting in said socket a dual mode light unit according to claim 23.

25. The dual mode light unit of claim 20 wherein said metallic portion and the window form a structure that has an engagement structure engaging the aircraft body for securing the unit in said space and that emulates an engagement portion and outer contour of a lens used to cover the space when an incandescent light source is used for in the space as the navigational light source.

26. A method of providing an infrared light source to an aircraft having a navigational light connected with an electrical system supplying electric current thereto, the current being in one of a plurality of electrical states, and the aircraft having a pilot-accessible control therein responsive to which the pilot can selectively cause the current to change to a different electrical state for adjusting brightness of the navigation light, said method comprising:

removing the navigational light from the aircraft; and

inserting in said socket a dual mode light unit according to claim 25.

27. The dual mode light unit of claim 20 wherein said metallic portion and the window form a structure that has an engagement structure engaging the aircraft body for securing the unit in said space and that emulates an engagement portion and outer contour of a lens used to cover the space when an incandescent light source is used for in the space as the navigational light source together with a securement member that secures the lens in position over said space.

28. A method of providing an infrared light source to an aircraft having a navigational light connected with an electrical system supplying electric current thereto, the current being in one of a plurality of electrical states, and the aircraft having a pilot-accessible control therein responsive to which the pilot can selectively cause the current to change to a different electrical state for adjusting brightness of the navigation light, said method comprising:

removing the navigational light from the aircraft; and

inserting in said socket a dual mode light unit according to claim 27.

29. The dual mode light unit of claim 20 wherein said metallic portion includes a frame structure in which the window is securingly retained.

30. The dual mode light unit of claim 29 wherein said window is symmetrical and the frame structure receives the window in a symmetrical aperture therein.

31. A method of providing an infrared light source to an aircraft having a navigational light connected with an electrical system supplying electric current thereto, the current being in one of a plurality of electrical states, and the aircraft having a pilot-accessible control therein responsive to which the pilot can selectively cause the current to change to a different electrical state for adjusting brightness of the navigation light, said method comprising:

removing the navigational light from the aircraft; and

inserting in said socket a dual mode light unit according to claim 30.

32. A method of providing an infrared light source to an aircraft having a navigational light connected with an electrical system supplying electric current thereto, the current being in one of a plurality of electrical states, and the aircraft having a pilot-accessible control therein responsive to which the pilot can selectively cause the current to change to a different electrical state for adjusting brightness of the navigation light, said method comprising:

removing the navigational light from the aircraft; and

inserting in said socket a dual mode light unit according to claim 29.

33. A method of providing an infrared light source to an aircraft having a navigational light connected with an electrical system supplying electric current thereto, the current being in one of a plurality of electrical states, and the aircraft having a pilot-accessible control therein responsive to which the pilot can selectively cause the current to change to a different electrical state for adjusting brightness of the navigation light, said method comprising:

removing the navigational light from the aircraft; and

inserting in said socket a dual mode light unit according to claim 20.

34. The dual mode light unit of claim 1, and the light control circuitry including circuitry detecting whether the current has a voltage that is above a preselected threshold voltage level, and responsive to such a detection causes the light unit to operate in a visible mode wherein power is supplied to the visible light source.

35. A method of providing an infrared light source to an aircraft having a navigational light connected with an electrical system supplying electric current thereto, the current being in one of a plurality of electrical states, and the aircraft having a pilot-accessible control therein responsive to which the pilot can selectively cause the current to change to a different electrical state for adjusting brightness of the navigation light, said method comprising:

removing the navigational light from the aircraft; and

inserting in said socket a dual mode light unit according to claim 34.

36. The dual mode light unit of claim 1, and the light control circuitry, where the current has a voltage that is lower than a preselected threshold voltage level, operating the dual mode light unit in a covert mode wherein the light unit generates no visible light and power is supplied only to the infrared light source.

37. The dual mode light unit of claim 36 wherein the light control circuitry has an input through which a user can program the circuitry to define the threshold voltage level.

38. A method of providing an infrared light source to an aircraft having a navigational light connected with an electrical system supplying electric current thereto, the current being in one of a plurality of electrical states, and the aircraft having a pilot-accessible control therein responsive to which the pilot can selectively cause the current to change to a different electrical state for adjusting brightness of the navigation light, said method comprising:

removing the navigational light from the aircraft; and

inserting in said socket a dual mode light unit according to claim 37.

39. A method of providing an infrared light source to an aircraft having a navigational light connected with an electrical system supplying electric current thereto, the current being in one of a plurality of electrical states, and the aircraft having a pilot-accessible control therein responsive to which the pilot can selectively cause the current to change to a different electrical state for adjusting brightness of the navigation light, said method comprising:

removing the navigational light from the aircraft; and

inserting in said socket a dual mode light unit according to claim 36.

40. A method of providing an infrared light source to an aircraft having a navigational light connected with an electrical system supplying electric current thereto, the current being in one of a plurality of electrical states, and the aircraft having a pilot-accessible control therein responsive to which the pilot can selectively cause the current to change to a different electrical state for adjusting brightness of the navigation light, said method comprising:

removing the navigational light from the aircraft; and

inserting in said socket a dual mode light unit according to claim 1.

41. The method of claim 40 wherein the navigational light initially is in a socket covered by a lens held in place by a securement plate fastened to the body of the aircraft and overlying the lens, said dual mode light unit having a configuration that emulates the shape of the lens, the method further comprising

unfastening the securement plate from a mounting location thereof on the aircraft body;

removing the lens from a mounting location thereof on the aircraft body;

setting the dual mode light unit in the mounting location; and

fastening the securement plate over the dual mode light unit.

42. The method of claim 40 wherein the navigational light initially is in a socket covered by a lens held in place by a securement plate fastened to the body of the aircraft and overlying the lens, said dual mode light unit having a configuration that emulates the shape of the lens combined with the securement plate, the method further comprising unfastening the securement plate from a mounting location thereof on the aircraft body;

removing the lens from a mounting location thereof on the aircraft body;

setting the dual mode light unit in the mounting locations of the securement plate and the lens; and

fastening the dual mode light unit in said mounting location.

43. The method of claim 42 wherein the securement plate is fastened to the aircraft body by a bolt extending through a conforming passage therein, the dual mode light unit having a securement passage that matches the conforming passage of the securement plate, and

the step of fastening the dual mode light unit includes extending the bolt or a matching replacement bolt through the securement passage in said dual mode light unit and fastening the bolt to said aircraft body.

44. An aircraft light unit for placement in a space for a navigation light in a body of an aircraft through an opening, said aircraft having an electrical system supplying an electrical current to a socket in the space, said light unit comprising:

an electrical connector configured to be received in the socket and to electrically connect therewith so as to receive said electrical current;

circuitry connected with said electrical connector and receiving the electrical current therefrom;

a light unit housing configured to be supported on the aircraft body in the space and closing said opening; and

at least one visible light LED supported in the housing and being connected with the circuitry and receiving electrical power therefrom so that the LED emits visible light;

the housing including an outer portion over said opening and over the LED, said outer portion having a light transmissive member through which the visible light from the LED can pass, and a thermally conductive metal outer member supporting the light transmissive member over the LED;

said metal outer member and said light transmissive member defining an outer surface of the housing that is conformal to a contour of the body of the aircraft;

the LED having a thermal link to the metal outer member that carries heat from the LED to the metal outer member, the metal outer member having a metallic outer surface with a surface area large enough and the thermal link having sufficient thermal conductivity such that heat from the LED is dissipated into air flowing over the outer portion so as to keep the LED in an operational temperature range thereof.

45. The aircraft light unit of claim 44 wherein the electrical connector is a bayonet fixture.

46. The aircraft light unit of claim 45 wherein the circuitry is supported in the housing and the bayonet fixture is connected to the circuitry by a flexible electrical cable.

47. A method of installing a navigational light to an aircraft having wiring supplying electric current in one of a plurality of electrical states to a navigational light on the aircraft, said method comprising:

removing the navigational light from the aircraft; and

connecting a light unit according to claim 46 to the wiring of said aircraft.

48. A method of installing a navigational light to an aircraft having wiring supplying electric current in one of a plurality of electrical states to a navigational light on the aircraft, said method comprising:

removing the navigational light from the aircraft; and

connecting a light unit according to claim 45 to the wiring of said aircraft.

49. The aircraft light unit of claim 44 wherein the electrical current is alternating current and the circuitry converts the alternating current to DC current at an appropriate voltage for the LED and transmits the DC current to the LED.

50. A method of installing a navigational light to an aircraft having wiring supplying electric current in one of a plurality of electrical states to a navigational light on the aircraft, said method comprising:

removing the navigational light from the aircraft; and

connecting a light unit according to claim 49 to the wiring of said aircraft.

51. The aircraft light unit of claim 44 wherein the metal outer member has a frame structure that holds the transmissive member.

52. The aircraft light unit of claim 51 wherein the transmissive member is symmetrical across a center plane thereof.

53. A method of installing a navigational light to an aircraft having wiring supplying electric current in one of a plurality of electrical states to a navigational light on the aircraft, said method comprising:

removing the navigational light from the aircraft; and

connecting a light unit according to claim 52 to the wiring of said aircraft.

54. A method of installing a navigational light to an aircraft having wiring supplying electric current in one of a plurality of electrical states to a navigational light on the aircraft, said method comprising:

removing the navigational light from the aircraft; and

connecting a light unit according to claim 51 to the wiring of said aircraft.

55. The aircraft light unit of claim 44 wherein the outer surface of the light unit emulates an outer surface of a lens or an outer surface a lens in combination with a securement member used for covering the opening in the aircraft body when an incandescent bulb is used as a navigation light in the space.

56. A method of installing a navigational light to an aircraft having wiring supplying electric current in one of a plurality of electrical states to a navigational light on the aircraft, said method comprising:

removing the navigational light from the aircraft; and

connecting a light unit according to claim 55 to the wiring of said aircraft.

57. The aircraft light unit of claim 44 wherein the thermal link includes a metallic mounting structure on which the LED is mounted so as to transmit heat thereto, the mounting structure engaging the metal outer member.

58. A method of installing a navigational light to an aircraft having wiring supplying electric current in one of a plurality of electrical states to a navigational light on the aircraft, said method comprising:

removing the navigational light from the aircraft; and

connecting a light unit according to claim 57 to the wiring of said aircraft.

59. The aircraft light unit of claim 57 wherein the mounting structure and the metal outer member are of aluminum.

60. A method of installing a navigational light to an aircraft having wiring supplying electric current in one of a plurality of electrical states to a navigational light on the aircraft, said method comprising:

removing the navigational light from the aircraft; and

connecting a light unit according to claim 59 to the wiring of said aircraft.

61. A method of installing a navigational light to an aircraft having wiring supplying electric current in one of a plurality of electrical states to a navigational light on the aircraft, said method comprising:

removing the navigational light from the aircraft; and

connecting a light unit according to claim 44 to the wiring of said aircraft.

62. The method of claim 61 wherein the navigational light initially is in a socket covered by a lens held in place by a securement plate fastened to the body of the aircraft and overlying the lens, said light assembly having a configuration that emulates the shape of the lens, the method further comprising

unfastening the securement plate from a mounting location thereof on the aircraft body;

removing the lens from a mounting location thereof on the aircraft body;

setting the assembly in the mounting location; and

fastening the securement plate over the assembly.

63. The method of claim 61 wherein the aircraft initially has a navigational light in the socket covered by a lens held in place by a securement plate fastened to the body of the aircraft and overlying the lens, said light assembly having a configuration that emulates the shape of the lens combined with the securement plate, the method further comprising

unfastening the securement plate from a mounting location thereof on the aircraft body;

removing the lens from a mounting location thereof on the aircraft body;

setting the assembly in the mounting locations of the securement plate and the lens; and

fastening the assembly in said mounting location.

64. The method of claim 63 wherein the securement plate is fastened to the aircraft body by a bolt extending through a conforming passage therein, the assembly having a securement passage that matches the conforming passage of the securement plate, and

the step of fastening the assembly includes extending the bolt or a matching replacement bolt through the securement passage in said light assembly and fastening the bolt to said aircraft body.

65. The aircraft light unit of claim 44 wherein an infra red emitter is connected with the circuitry, and said circuitry includes discriminator circuitry that determines from a characteristic of the electrical current whether the unit is selected for a visible light mode or a covert IR mode, and illuminates the LED for visible mode, and illuminates the infra red emitter for covert IR mode.

66. The aircraft light unit of claim 65 wherein the circuitry has an input through which a user can program the circuitry to set the characteristic that is used by the discriminator circuitry.

67. A method of installing a navigational light to an aircraft having wiring supplying electric current in one of a plurality of electrical states to a navigational light on the aircraft, said method comprising:

removing the navigational light from the aircraft; and

connecting a light unit according to claim 66 to the wiring of said aircraft.

68. A method of installing a navigational light to an aircraft having wiring supplying electric current in one of a plurality of electrical states to a navigational light on the aircraft, said method comprising:

removing the navigational light from the aircraft; and

connecting a light unit according to claim 65 to the wiring of said aircraft.

69. An aircraft light assembly for an aircraft, said aircraft having a body with an outer surface exposed to an external airflow over the aircraft, said aircraft light assembly comprising:

a visible light apparatus configured to be supported on the body of the aircraft, said apparatus including one or more light emitting diode devices generating visible light; and

an outer structure overlying the light emitting diode devices, said outer structure having a light transmissive portion through which visible light from the light emitting diode devices can pass, and a metallic portion connected with the light transmissive portion and securing said light transmissive portion on the aircraft,

said metallic portion having an outer surface exposed to the external airflow; and

the light emitting diode devices being thermally linked to said metallic portion so that heat created in the light emitting diode devices flows to the outer surface of the metallic portion and is dissipated into the external airflow.

70. The aircraft light assembly of claim 69 wherein the aircraft body has edges defining an aperture in the outer surface of the aircraft body providing access to a space in the body of the aircraft,

said visible light apparatus being configured to be received in said space, and said outer structure being configured to engage the edges of the aperture on the aircraft body and to cover the aperture and enclose the space.

71. A method of installing navigational lighting on an aircraft having an electrical system supplying electric current to a navigational light on the aircraft, said method comprising:

removing the navigational light from the aircraft; and

connecting a light assembly according to claim 70 in place thereof.

72. The aircraft light assembly of claim 70 wherein said outer structure has an outer surface conformal with the outer surface of the aircraft body.

73. A method of installing navigational lighting on an aircraft having an electrical system supplying electric current to a navigational light on the aircraft, said method comprising:

removing the navigational light from the aircraft; and

connecting a light assembly according to claim 72 in place thereof.

74. The aircraft light assembly of claim 70 wherein said outer structure has an outer surface that duplicates an outer surface of a lens or lens assembly used to cover said aperture when an incandescent bulb is used as a navigational light in the space.

75. A method of installing navigational lighting on an aircraft having an electrical system supplying electric current to a navigational light on the aircraft, said method comprising:

removing the navigational light from the aircraft; and

connecting a light assembly according to claim 74 in place thereof.

76. The aircraft light assembly of claim 70 wherein the assembly includes circuitry adapted to receive electrical current from an electrical system of the aircraft, said circuitry conditioning said electrical current and transmitting electrical power therefrom to the light emitting diode devices so as to cause illumination thereof.

77. The aircraft light assembly of claim 76 wherein the assembly includes an electrical connector connected with the circuitry and adapted to be secured in a socket in the aircraft electrical system in said space.

78. A method of installing navigational lighting on an aircraft having an electrical system supplying electric current to a navigational light on the aircraft, said method comprising:

removing the navigational light from the aircraft; and

connecting a light assembly according to claim 77 in place thereof.

79. A method of installing navigational lighting on an aircraft having an electrical system supplying electric current to a navigational light on the aircraft, said method comprising:

removing the navigational light from the aircraft; and

connecting a light assembly according to claim 76 in place thereof.

80. The aircraft light assembly of claim 70 wherein the outer structure of the assembly is configured to emulate an outer surface and engagement structure of a lens assembly used to cover the aperture, the engagement structure of the lens assembly including a securement plate secured overlying a lens that covers the aperture when an incandescent bulb is used as a light source therein, and a fastener or bolt engaging and securing the securement plate to the aircraft body, said fastener engaging and securing the outer portion of the aircraft light assembly to the aircraft body when installed thereon.

81. A method of installing navigational lighting on an aircraft having an electrical system supplying electric current to a navigational light on the aircraft, said method comprising:

removing the navigational light from the aircraft; and

connecting a light assembly according to claim 80 in place thereof.

82. A method of installing navigational lighting on an aircraft having an electrical system supplying electric current to a navigational light on the aircraft, said method comprising:

removing the navigational light from the aircraft; and

connecting a light assembly according to claim 69 in place thereof.

83. The method of claim 80 wherein the navigational light initially is in a socket covered by a lens held in place by a securement plate fastened to the body of the aircraft and overlying the lens, said light assembly having a configuration that emulates the shape of the lens, the method further comprising

unfastening the securement plate from a mounting location thereof on the aircraft body;

removing the lens from a mounting location thereof on the aircraft body;

setting the assembly in the mounting location; and

fastening the securement plate over the assembly.

84. The method of claim 82 wherein the aircraft initially has a navigational light in the socket covered by a lens held in place by a securement plate fastened to the body of the aircraft and overlying the lens, said light assembly having a configuration that emulates the shape of the lens combined with the securement plate, the method further comprising

unfastening the securement plate from a mounting location thereof on the aircraft body;

removing the lens from a mounting location thereof on the aircraft body;

setting the assembly in the mounting locations of the securement plate and the lens; and

fastening the assembly in said mounting location.

85. The method of claim 84 wherein the securement plate is fastened to the aircraft body by a bolt extending through a conforming passage therein, the assembly having a securement passage that matches the conforming passage of the securement plate, and

the step of fastening the assembly includes extending the bolt or a matching replacement bolt through the securement passage in said light assembly and fastening the bolt to said aircraft body.