Aircraft instrumentation module

An instrumentation module for an aircraft, the instrumentation module comprising:

• first and second electronic display screens displaying first and second electronic indicator of at least one condition of the aircraft, wherein the at least one aircraft condition is selected from the group consisting of:
• attitude, altitude, airspeed, and slip,
• the first and second electronic display screens having an actual mounting orientation selected from among a plurality of selectable mounting orientations within the aircraft, wherein in one of the plurality of selectable mounting orientations the first electronic display screen is positioned horizontally adjacent to the second electronic display screen, and in the other of the plurality of selectable mounting orientations the first electronic display screen is positioned vertically adjacent to the second electronic display screen, and
• the first and second electronic indicators having an actual display orientation selected from among a plurality of selectable display orientations on the first and second electronic displays, wherein one of the first and second electronic indicators is displayed on one of the first and second display screens and the other of the first and second electronic indicators is displayed on the other of the first and second display screens;
• and
• a manual control device allowing selection of—
• which of the first and second electronic indicators is displayed on which of the first and second display screens, and
• the actual display orientation of the first and second electronic indicators on the first and second display screens.

A method of installing an instrumentation module in an aircraft, wherein the instrumentation module has an electronic display screen displaying an electronic indicator of at least one aircraft condition, the method comprising the steps of:

• mounting the instrumentation module such that the electronic display screen is in an actual mounting orientation selected from among a plurality of selectable mounting orientations, wherein the instrumentation module includes:
• first and second electronic display screens, wherein in one of the plurality of selectable mounting orientations the first electronic display screen is positioned horizontally adjacent to the second electronic display screen, and in another of the plurality of selectable mounting orientations the first electronic display screen is positioned vertically adjacent to the second electronic display screen;
• and
• first and second electronic indicators having an actual display orientation selected from among a plurality of selectable display orientations on the first and second electronic displays, wherein one of the first and second electronic indicators is displayed on one of the first and second display screens and the other of the first and second electronic indicators is displayed on the other of the first and second display screens;
• manually changing a display orientation of the electronic indicator to reflect the actual mounting orientation of the electronic display screen;
• manually changing which of the first and second electronic indicators is displayed on which of the first and second electronic display screens;
• and
• manually changing the actual display orientation of the first and second electronic indicators on the first and second electronic display screens.

An instrumentation module for an aircraft, the instrumentation module comprising:

• an electronic display screen displaying an electronic indicator of at least one aircraft condition;
• the electronic display screen having an actual mounting orientation selected from among a plurality of selectable mounting orientations within the aircraft;
• the electronic indicator having an actual display orientation selected from among a plurality of selectable display orientations on the electronic display;
• a manual control device allowing manual selection of the actual display orientation of the electronic indicator from among the plurality of selectable display orientations so that the actual display orientation of the electronic indicator corresponds to the actual mounting orientation of the electronic display screen;
• a first internal memory storing a first copy of the data;
• a second internal memory storing a second copy of the data;
• an interface facilitating a change to the first copy of the data;
• and
• a decision-making component deciding whether the change to the first copy of the data was completed;
• wherein if the change to the first copy of the data was completed, writing the first copy of the data over the second copy of the data;
• and
• wherein if the change to the first copy of the data was not completed, writing the second copy of data over the first copy of the data.

An instrumentation module for an aircraft, the instrumentation module comprising:

• an electronic display screen displaying an electronic indicator of at least one aircraft condition:
• the electronic display screen having an actual mounting orientation selected from among a plurality of selectable mounting orientations within the aircraft;
• the electronic indicator having an actual display orientation selected from among a plurality of selectable display orientations on the electronic display;
• a manual control device allowing manual selection of the actual display orientation of the electronic indicator from among the plurality of selectable display orientations so that the actual display orientation of the electronic indicator corresponds to the actual mounting orientation of the electronic display screen;
• a first internal memory storing certified software, wherein the certified software in operable for use in a certified system for the aircraft;
• a second internal memory storing non-certified software, wherein the non-certified software is not operable for use in the certified system for use in the aircraft;
• and
• wherein the certified software is partitioned from the non-certified software.

An instrumentation module for an aircraft, the instrumentation module comprising:

• an electronic display screen displaying an electronic indicator of at least one aircraft condition;
• the electronic display screen having an actual mounting orientation selected from among a plurality of selectable mounting orientations within the aircraft;
• the electronic indicator having an actual display orientation selected from among a plurality of selectable display orientations on the electronic display;
• a manual control device allowing manual selection of the actual display orientation of the electronic indicator from among the plurality of selectable display orientations so that the actual display orientation of the electronic indicator corresponds to the actual mounting orientation of the electronic display screen;
• an interface connecting the instrumentation module to a primary instrumentation system of the aircraft;
• wherein the primary instrumentation system determines a first altitude and a barometric pressure and, based thereon, calculates a first barometrically-corrected altitude;
• an altitude-determining component determining a second altitude, wherein the second altitude is approximately the same as the first altitude;
• a first calculating component receiving the first altitude and the first barometrically-corrected altitude from the primary instrumentation system via the interface, and, based thereon, calculating the barometric pressure;
• and
• a second calculating component receiving the second altitude and the calculated barometric pressure and calculating a second barometrically-corrected altitude, wherein the second barometrically-corrected altitude is approximately the same as the first barometrically-corrected altitude.

An instrumentation module for an aircraft, the instrumentation module comprising:

• an electronic display screen displaying an electronic indicator of a condition of the aircraft;
• the electronic indicator including:
• a current value for the condition of the aircraft and a range of possible values for the condition of the aircraft;
• a bar extending alongside the range of possible values for the condition of the aircraft, wherein the bar includes a plurality of colors, each color being associated with and communicating information about a sub-range of the range of possible values for the condition of the aircraft;
• and
• a manual control device allowing a user to manually choose the plurality of colors and to determine a position of each color within the bar to correspond to a particular sub-range of the range of possible values for the condition of the aircraft;
• the electronic display screen having an actual mounting orientation selected from among a plurality of selectable mounting orientations within the aircraft;
• the electronic indicator having an actual display orientation selected from among a plurality of selectable display orientations on the electronic display;
• and
• the manual control device allowing manual selection of the actual display orientation of the electronic indicator from among the plurality of selectable display orientations so that the actual display orientation of the electronic indicator corresponds to the actual mounting orientation of the electronic display screen.