Midcontinent 4300 Series Handbuch

MANUAL NUMBER 9015834-1

REV. D September 30, 2009

PILOTS GUIDE

for the

4300-xxx Series Electric Attitude Indicator

Mid-Continent Instruments and Avionics

9400 E. 34th Street N., Wichita, KS 67226 USA

Phone 316-630-0101 Fax 316-630-0723

[email protected]

Rev. D September 30, 2009 Page 2 of 9 Manual # 9015834-1

Pilots Guide

Forward

This manual provides operational instructions for use by persons who operate aircraft in

accordance with applicable Federal Aviation Regulations (Title 14 CFR).

We welcome your comments concerning this manual. Although every effort has been made

to keep this manual free of errors, some may occur. When reporting a specific problem,

please describe it briefly and include the manual part number, the paragraph/figure/table

number, and the page number. Please email or send your comments to:

Mid-Continent Instruments and Avionics

Attn: Technical Publications

9400 E. 34th ST North

Wichita, KS 67226 USA

Phone 316-630-0101 Fax 316-630-0723

[email protected]

Congratulations on selecting one of the most advanced new aviation products. The

design team at Mid-Continent has incorporated four decades of experience with aircraft

instrumentation to bring you the best possible reliability and value in aviation. We are

proud to offer the finest Attitude Indicator in its class. New technology allows our unit to

run twice as many hours as older designs. All this is backed by Mid-Continent’s world

class reputation for high quality and responsive service.

J. Todd Winter

President

Operating Instructions

4300-xxx Series Electric Attitude Indicator

Rev. D September 30, 2009 Page 3 of 9 Manual # 9015834-1

Pilots Guide

Table of Contents Page

Section 1 General Description

Purpose of Equipment 4

Physical Description 4

Functional Description 4

Gyro Warning Flag 4

Options and Configurations 4

Specifications 5

Section 2 Operation

General 7

Starting Procedures 7

In-Flight Procedures 7

Dynamic Errors 7

Figures List of Illustrations

Display Configurations 7

Typical Indicator Display Detail 6

Tables List of Tables

Options Table 4

Physical Characteristics 5

Performance 5

Light Tray Assembly Options 5

Operating Instructions

4300-xxx Series Electric Attitude Indicator

Rev. D September 30, 2009 Page 4 of 9 Manual # 9015834-1

Pilots Guide

Section 1: General Description

Purpose of Equipment

The 4300 Electric Attitude Indicator incorporates a moving display that simulates the earth’s

horizon and provides the pilot with a real time visual indication of the aircraft pitch and roll

attitude relative to the indicator symbolic airplane.

The instrument can function as a primary or standby indicator with special configurations

available to match existing systems or electronic flight displays. Panel tilt, input voltage,

lighting color/voltage, non-trimmable knob cover, front mount adapter plates and a slip

indicator are available as options.

Physical Description

The 4300 Electric Attitude Indicator incorporates pitch and roll displays that are

mechanically linked to a spinning mass gyroscope. The horizon bar moves behind the

symbolic airplane. Precession error is corrected by the 4300’s erection system or by pulling

the “PULL TO CAGE” knob. A warning flag drops into view if the gyro motor is not receiving

sufficient power to operate.

Functional Description

Model 4300-xxx Electric Attitude Indicators employ an efficient electrically driven internal

vertical gyroscope assembly incorporating a special air erection mechanism. This

mechanism simultaneously erects the pitch and roll axes of the gyroscope. Movement of the

aircraft generates a reaction of the display that simulates the visual reference seen by the

pilot when looking outside at the earth’s true horizon line.

The Indicator operates on any input voltage between 10 and 32 VDC. An integral lighting

system featuring a user replaceable light tray assembly that operates from the aircraft

lighting bus is available in 5V, 14V, or 28V versions (dependent on configuration).

Gyro Warning Flag

A power warning circuit monitors the electrical current used to power the gyro motor. When

a loss of input voltage occurs, the gyro warning flag comes into view.

Operating Instructions

4300-xxx Series Electric Attitude Indicator

Rev. D September 30, 2009 Page 5 of 9 Manual # 9015834-1

Pilots Guide

Options and Configurations

Options Table

Panel Tilt

Calibration 0to 20

Lighting Voltage 5V, 14V, or 28V (See Table 1.4)

Lighting Color Blue/White, White, or Red (See Table 1.4)

Miscellaneous

Parts: Non-trimmable Symbolic Airplane Knob Cover (P/N

36022)

Slip Indicator Kit (P/N 36023)

Front Mount Kit: 3/32” thk (P/N 36028-1) or 1/2” thk (P/N

36027-1)

Panel Wedges: 3(P/N PW3R-3) or 4(P/N PW3R-4)

Mating Connector Kit (P/N 9015514)

Table 1.1

Specifications

Physical Characteristics:

Qualification: FAA-TSO-C4c

Environmental

Qualification: RTCA DO-160D Environmental Category

C1BAB[(SBM)(RBB1)(P)]XXXXXXZZAZZ[WF]M[A3H33]XXA

Weight: 2.7 pounds maximum

Dimensions: Length behind panel (not including mating connector)

6.6 inches long maximum.

3.28 inches high maximum.

3.28 inches wide maximum.

Mating

Connector: MS3116F8-4S or equivalent (MCI P/N 9015514)

Cover Glass HEA (anti-reflective) coated.

Instrument

Panel

Mounting:

Rear mount. Front mount with adapter plate.

Table 1.2

Performance:

Reliability 7500 Hour Mean Time Between Failure (MTBF)

Initial Erection:

The "PULL TO CAGE" knob will erect the gyroscope to

within 2.0° of case vertical in roll and pitch from any

position at any time.

Final Erection:

The vertical gyroscope should be allowed to spin up for 3

minutes after rated power is applied and after initial

erection. After 5 minutes the final erection accuracy of

pitch and roll will be within 1of vertical.

Operating Instructions

4300-xxx Series Electric Attitude Indicator

Rev. D September 30, 2009 Page 6 of 9 Manual # 9015834-1

Pilots Guide

Erection Rate: Gyroscope will erect to local vertical in pitch and roll at

2.5° per minute minimum.

Warning Flag: A gyro warning circuit provides for continuous monitoring

of input voltage. If loss of input voltage occurs, the red

warning flag will appear.

Symbolic

Airplane:

The adjustment range will be 4minimum from the zero

pitch position.

Power

Consumption:

Starting:

Will not exceed 1.5A at 14 VDC.

Will not exceed 0.7A at 28 VDC.

Running:

Nominal 0.55A ±15% at 14 VDC.

Nominal 0.27A ±15% at 28 VDC.

Lighting: Will not exceed 2.5 watts for models using 5V, 14V, or

28V. Table 1.3

Light Tray Assembly Options

P/N 9015640-( )

5V 14V 28V

Blue/White -1 -2 -3

White -4 -5 -6

Red -7 -8 -9

Table 1.4

Operating Instructions

4300-xxx Series Electric Attitude Indicator

Rev. D September 30, 2009 Page 7 of 9 Manual # 9015834-1

Pilots Guide

Roll Pointer: A) Fixed roll pointer: Indicates aircraft roll displacement relative to

a rotating roll dial.

B) Rotating roll pointer: Indicates aircraft roll displacement

relative to a fixed roll dial.

Gyro Warning Flag: If loss of input voltage should occur, gyro warning flag will come

into view.

Display: Lower area of display, when referenced to the symbolic airplane,

indicates aircraft nose is below horizon or in a dive attitude. Upper

area of display indicates aircraft nose is above horizon or in a climb

attitude.

Symbolic Airplane: Indicates roll and pitch attitude relative to the horizon. The

symbolic airplane can be moved (pitch only) using the symbolic

airplane adjustment knob.

Horizon Line: Indicates earth horizon relative to aircraft pitch and roll attitude.

Caging knob:

(Manual Erection) When pulled, manually erects the gyro vertical to the case

orientation.

Symbolic Airplane

Adjustment Knob: Used to adjust the symbolic airplane.

Typical Electric Attitude Indicator Display

(Rotating Roll Dial, Fixed Roll Pointer, Traditional Wing Symbolic Airplane Shown)

Figure 1.2

Operating Instructions

4300-xxx Series Electric Attitude Indicator

Rev. D September 30, 2009 Page 8 of 9 Manual # 9015834-1

Pilots Guide

Section 2: Operation

General

This section describes the Model 4300-xxx Electric Attitude Indicator operating procedures.

The indicator is required to be installed in an aircraft with the specified inputs applied. Figure

1.2 provides an illustration of a typical Model 4300 display and a table describing indicator

functions.

Starting Procedures

The following operational procedures are recommended when preparing the indicator for

use:

CAUTION: THE INDICATOR MAY BE DAMAGED IF THE “PULL TO CAGE” KNOB IS

RELEASED WITH A “SNAP.” RELEASE “PULL TO CAGE” KNOB AVOIDING

A “SNAP” RELEASE.

NOTE: Indicator may be momentarily caged by pulling “PULL TO CAGE” knob to the fully

extended position, holding knob until the display stabilizes, and then allowing the

knob to return to the normal position.

A. Apply power to the indicator. Note that the Gyro Warning flag (red) will pull out-of-

view. Also allow three minutes for presentation stabilization.

B. On models with trim adjustment, rotate the symbolic airplane adjustment knob for

the desired pitch attitude presentation, i.e. aligning the symbolic airplane with the

horizon.

C. If caging is required, caging should be accomplished when the aircraft is in a

wings level, normal cruise attitude, as indicated by other instruments or the

horizon. If the gyro is caged when the aircraft is not in this attitude, the resulting

attitude presentation immediately after caging will be in error by the difference

between true vertical and actual aircraft attitude. Small errors in caging erection

will be corrected by the indicator to true vertical in pitch and roll at 2.5per minute

minimum (5/min. nominal).

In-Flight Procedures

A. Adjust the symbolic airplane to obtain desired pitch attitude presentation after

take-off.

B. In the event of errors in excess of 10caused by extended bank or fore-aft

acceleration, the indicator should be momentarily caged after the aircraft is

returned to level flight.

Operating Instructions

4300-xxx Series Electric Attitude Indicator

Rev. D September 30, 2009 Page 9 of 9 Manual # 9015834-1

Pilots Guide

Dynamic Errors

A. Turn Induced Errors

Pitch indication errors resulting from a standard coordinated turn (180 degrees in

one minute at a true airspeed of 156 knots) will not exceed 3. Dynamic errors

developed under non-standard conditions may be greater. Errors that develop will

be self corrected by the internal erection system or manually corrected by the

actuation of the caging system.

B. Acceleration & Deceleration Errors

Pitch indicating errors may occur due to accelerations experienced during takeoff,

climb-out, descent, and landing. Errors that develop will be self-corrected by the

internal erection system or manually corrected (in straight and level flight) by the

actuation of the caging system.

C. Taxiing Errors

A pitch and roll indicator display error of approximately 1will occur during a

sudden 90ground turn. A pitch indicator display error of approximately 2will

occur during a sudden 180ground turn. Errors that develop will be self corrected

by the internal erection system or manually corrected by the actuation of the

caging system.

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