Mid-Continent Instruments 4300-4 Series Technical Document

INSTALLATION MANUAL AND
OPERATING INSTRUCTIONS
4300-4XX Series Electric Attitude Indicator
MID-CONTINENT INST. CO., INC MANUAL NUMBER 9015762
9400 E 34th Street N, Wichita, KS 67226 USA REV B May 25, 2004
Phone [phone] •Fax [phone]

Mid-Continent Instruments, Wichita, KS
Rev B May 25, 2004 Manual Number 9015762 Page 2 of 21
FOREWORD
This manual provides information intended for use by persons who, in accordance with current
regulatory requirements, are qualified to install this equipment. If further information is required,
please contact:
Mid-Continent Instruments
Attn: Customer Service Dept.
9400 E. 34th ST North
Wichita, KS 67226 USA
Phone [phone] Fax [phone]
We welcome your comments concerning this manual. Although every effort has been made to
keep it 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. Send your comments to:
Mid-Continent Instruments
Attn: Technical Publications
9400 E. 34th ST North
Wichita, KS 67226 USA
Phone [phone] Fax [phone]
[email protected]
www.mcico.com
Copyright 2003
Mid-Continent Instrument Co., Inc.

Mid-Continent Instruments, Wichita, KS
Rev B May 25, 2004 Manual Number 9015762 Page 3 of 21
Table of Contents
Page
Section 1 General Description 5
1.1 Purpose of Equipment 5
1.2 Physical Description 5
1.3 Functional Description 5
1.4 Gyro Warning Flag 6
1.5 Options and Configurations 6
1.6 Specifications 6
Section 2 Installation 11
2.1 General 11
2.2 Pre-Installation Inspection 11
2.3 Parts 12
2.3.1 Included Parts 12
2.3.2 Installer Supplied Parts 12
2.3.3 Additional Optional Parts 12
2.4 Equipment Location 12
2.5 Installation 13
2.6 Continued Airworthiness 14
Section 3 Operation 18
3.1 General 18
3.2 Starting Procedures 18
3.3 In-Flight Procedures 18
3.4 Dynamic Errors 18
3.5 Standby Battery Operation 19
3.6 Equipment Limitations 21
Figure No. List of Illustrations
1.1 Display Configurations 8
1.2 Typical Indicator Display Detail 10
2.1 Outline Drawings 15
2.2 Rear-Mount Cutout Dimensions 16
2.3 Front-Mount Cutout Dimensions 16
2.4 Remote Mount Standby Battery Option
with 9015671 Kit 17
2.5 Nominal Battery Discharge Rate at 20°C 20
2.6 Effect of Low Temperature on Battery Capacity 21
2.7 Life Characteristics in Standby Use 21
Table No. List of Tables
1.1 Options Table 6
1.2 Physical Characteristics 6
1.3 Performance 7
1.4 Light Tray Assembly Options 7

Mid-Continent Instruments, Wichita, KS
Rev B May 25, 2004 Manual Number 9015762 Page 4 of 21
Revision Detail
Rev. Date Detail
N/R 10/1/03 Complete issue
A 11/4/03 Revise text for improved short battery test. Add text to Sec. 2.6.2.B for P/N
36029 battery charger.
B 5/25/04 Update display configurations Fig. 1.1, update connector pinout: Lighting
(No polarity), revise currents in table 1.3, add bezel dims to panel cutouts,
add DO-160D environmental test qualification in Table 1.2.

Mid-Continent Instruments, Wichita, KS
Rev B May 25, 2004 Manual Number 9015762 Page 5 of 21
Section 1: General Description
1.1 Purpose of Equipment
The Model 4300-4XX 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. In the event aircraft electrical
power is lost, the indicator will switch to an internal backup power source (rechargeable sealed
lead acid battery) to permit continued operation of the indicator. Panel tilt, input voltage, lighting
color/voltage, non-trimmable knob cover, front mount adapter plates and a slip indicator are
available as options.
1.2 Physical Description
The 4300-4XX 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 to indicate that the gyro motor is not receiving sufficient
power to operate. This will normally occur only if the unit is turned off, or after the internal
standby battery is exhausted.
1.3 Functional Description
Model 4300-4XX 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 4300-4XX Electric Attitude Indicator offers the unique feature of a self-contained standby
power source. Advances in the design of this gyro system allow it to operate for about one hour
after main input power is lost, depending on the battery condition at the time of power failure.
Anytime aircraft power is absent, with the unit in either power loss warning mode or turned off,
pushing the STBY PWR button will put the unit into the standby power mode. The instrument
will run from standby power until the internal battery is exhausted. If the unit is already running
on standby power (internal battery), pushing the STBY PWR button will turn the unit off
completely. Pushing the STBY PWR button again will restore unit operation to standby power.
Restoring aircraft power will clear any standby power mode and automatically resume standby
battery charging.
The indicator requires 10 to 32 VDC or +27.5 VDC (22.0 to 32.0 VDC) input voltage (dependent
on configuration). An integral lighting system featuring a user replaceable light tray assembly
operates from the aircraft lighting bus and is available in 5V, 14V, or 28V versions (dependent on
configuration). In standby power operation, low intensity LED powered dial lighting is
automatically turned on to provide nighttime visibility.
The internal battery is designed for emergency use only. Frequent use, extended discharging,
extended lack of charging, misuse and age will require battery replacement. Replacement can be
done in the field with or without removal of the attitude indicator. Do not operate this model

Mid-Continent Instruments, Wichita, KS
Rev B May 25, 2004 Manual Number 9015762 Page 6 of 21
without the specified battery intact. Battery substitution, modification, misuse and lack of
specified maintenance will void all warranties and hold the manufacturer harmless from any and
all claims or legal actions.
Refer to an FAA authorized maintenance facility for testing and maintenance of this instrument
excluding battery or light tray replacement.
1.4 Gyro Warning Flag
A warning circuit monitors the electrical voltage used to power the gyro motor. When the
Indicator is turned off, or after the internal battery is discharged, the gyro warning flag comes
into view. Anytime aircraft power is lost, including normal end-of-flight power down, the unit will
switch to the Power Loss Warning mode. If the STBY PWR button on the face of the instrument
is not pushed before the end of the (nominal) one-minute timing period, the instrument will turn
itself off and the gyro warning flag will appear. If the STBY PWR button is pushed, the gyro will
run from standby power until the internal battery is exhausted before the gyro warning flag
appears.
1.5 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)
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)
Remote Battery Mounting Kit (P/N 9015671)
Replacement Standby Battery (P/N 9015607)
Miscellaneous Parts:
Battery Charger (P/N 36029)
Table 1.1
1.6. Specifications
Physical Characteristics:
Qualification: FAA-TSO-C4c
Environmental Qualification: RTCA DO-160D Environmental Category
A2BAB[(SBM)(RBB1)]XXXXXXZZAZZ[RR]M[A3C3]XXA
Weight: 3.7 pounds (2.7 pounds without battery)
Dimensions: Length behind panel (not including mating connector)
6.6 inches long max. (battery not installed)
8.6 inches long max. (battery installed)
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

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Rev B May 25, 2004 Manual Number 9015762 Page 7 of 21
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.
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 gyro
voltage. If loss of gyro motor voltage occurs, the red warning flag
will appear. See section 3.5 for battery operation.
Symbolic Airplane:
The adjustment range will be ±4°minimum from the zero pitch
position.
Power Consumption:
Starting:
1.8A maximum (at 14 VDC input)
0.9A maximum (at 28 VDC input)
Running: Nominal 0.55A ±15% (at 14 VDC input)
Nominal 0.27A ±15% (at 28 VDC input)
Lighting: 2.5 watts maximum (for all models using 5V, 14V, or 28V lighting)
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

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Rev B May 25, 2004 Manual Number 9015762 Page 8 of 21
Rotating Roll Dial
Fixed Pointer
Traditional Symbolic Airplane
Fixed Roll Dial
Rotating Pointer
Traditional Symbolic Airplane
Rotating Roll Dial
Fixed Pointer
Delta Symbolic Airplane
Fixed Roll Dial
Rotating Pointer
Delta Symbolic Airplane
Face Layout A Face Layout B
Face Layout DFace Layout C
High Resolution Horizon DialHigh Resolution Horizon Dial
Rotating Roll Dial
Fixed Pointer Rotating Pointer
Fixed Roll Dial
Face Layout E Face Layout F
Standard Horizon DialStandard Horizon Dial
Standard Horizon Dial Standard Horizon Dial
Traditional Symbolic AirplaneTraditional Symbolic Airplane
Figure 1.1
Display Configurations

Mid-Continent Instruments, Wichita, KS
Rev B May 25, 2004 Manual Number 9015762 Page 9 of 21
Delta Symbolic Airplane
Rotating Roll Dial
Fixed Pointer
Fixed Roll Dial
Rotating Pointer
Delta Symbolic Airplane
Face Layout G Face Layout H
High Resolution Horizon Dial High Resolution Horizon Dial
Model
Number
Input
Voltage
Roll Dial Horizon Dial Symbolic
Airplane
Face
Layout
4300-401 27.5 VDC Rotating Standard Traditional A
4300-402 27.5 VDC Fixed Standard Traditional B
4300-403 27.5 VDC Rotating Standard Delta C
4300-404 27.5 VDC Fixed Standard Delta D
4300-411 10 to 32 VDC Rotating Standard Traditional A
4300-412 10 to 32 VDC Fixed Standard Traditional B
4300-413 10 to 32 VDC Rotating Standard Delta C
4300-414 10 to 32 VDC Fixed Standard Delta D
4300-431 10 to 32 VDC Rotating High Resolution Traditional E
4300-432 10 to 32 VDC Fixed High Resolution Traditional F
4300-433 10 to 32 VDC Rotating High Resolution Delta G
4300-434 10 to 32 VDC Fixed High Resolution Delta H
Figure 1.1, Cont.
Display Configurations

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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 operating 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

Mid-Continent Instruments, Wichita, KS
Rev B May 25, 2004 Manual Number 9015762 Page 11 of 21
Section 2: Installation
2.1 General
This section contains mounting, electrical connections and other information required for
installation. After installation of cabling and before installation of the equipment, ensure that
power is applied only to the pins specified in the interconnection diagram.
CAUTION: GYROS ARE DELICATE INSTRUMENTS! THE FOLLOWING PRECAUTIONS
MUST BE OBSERVED!!
A. A high gyroscope failure rate can be directly related to rough or improper handling.
Gyros are delicate and cannot withstand the shock of being dropped, jarred, or
struck by pieces of equipment. Do not place gyros on any hard surface. Pad with
generous foam. Handle like eggs!
B. To prevent damage to a gyro, the instrument should be transported to and from the
aircraft in it’s original shipping container. If this is impractical, the gyro should be
hand-carried carefully in an upright position.
C. A gyro should never be removed while it is spinning or running down. The instrument
normally operates at high RPM and may take 10 minutes or longer to run down. If it
is removed while running and tilted more than 20 degrees, the gyro can develop a
gimbal lock. The gimbal will tumble and start to spin. If gimbal lock occurs while the
rotor is turning, the gimbal may spin fast enough to damage the gimbal bearings,
requiring an overhaul.
D. A malfunctioning gyro should be handled with the same care given a new
instrument. Most malfunctioning instruments can be repaired and returned to
service. Using proper handling procedures during removal prevents additional
damage and helps ensure possible reuse.
2.2 Pre-installation Inspection
A. Unpacking: Carefully remove the attitude indicator from shipping container. The
shipping container and packing materials should be retained for use should the
attitude indicator require future shipment.
B. Inspect for Damage: Inspect the shipping container and indicator for any signs of
damage sustained in transit. If necessary, return attitude indicator to the factory
using the original shipping container and packing materials. File any claim for
damages with the carrier.
C. CAUTION: The unit is shipped with the battery cable disconnected to
prevent inadvertent operation of the indicator during shipping. If the cable
was found connected when received, check the battery condition per section 2.6.3
and then reconnect the battery during instrument installation if it checks out ok. The
battery pack may be permanently damaged by remaining discharged for extended
periods.

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Rev B May 25, 2004 Manual Number 9015762 Page 12 of 21
2.3 Parts
2.3.1 Included Parts
A. Model 4300-( ) Electric Attitude Indicator including Battery Pack (P/N 9015607).
B. Mating Connector, MS3116F8-4S or equivalent (P/N 9015514).
C. Installation Manual (P/N 9015762)
2.3.2 Installer Supplied Parts
A. Mounting Screw, 6-32UNC-2A. Three (3) required. (1” long screws are suggested for
panel thickness between 0.05 and 0.19, but may not be optimum in some installations.
The installer will need to determine what is correct for a particular installation.)
CAUTION: Do not exceed 1.06” screw depth into bezel!
2.3.3 Additional Parts that may be required
A. Symbolic Airplane Adjustment Knob Cover Kit: (P/N 36022)
B. Slip Indicator Kit (P/N 36023)
C. Front Mount Kit: 3/32” thk (P/N 36028-1) or 1/2” thk (P/N 36027-1)
D. Panel Wedges: 3” (P/N PW3R-3) or 4” (P/N PW3R-4)
E. Remote Battery Mounting Kit (P/N 9015671)
2.4 Equipment Location
The attitude indicator should be located within the aircraft in accordance with the following
considerations:
A. The indicator is ideally located in the instrument panel directly in line with the pilot's
normal line of sight. The "PULL TO CAGE" knob should be within easy reach.
Installations that result in viewing angles in excess of 30 degrees may reduce display
readability.
B. Compare the space requirements of the indicator with the installation area being
considered.
C. The power cable should not run adjacent to heaters, engine exhausts, or other heat
sources. Also, take care to route and tie the cable away from aircraft controls and
cables.
D. If remote mounting the standby battery, the cable length from the battery to the unit
should be kept as short as practical using wire of 22 AWG minimum. 18 AWG wire is
recommended for cable runs over 50 feet. Remote mounting the battery in a
location subject to extreme temperature variations may dramatically shorten the
emergency operation time available for the attitude indicator as well as the expected
battery lifetime (Fig 2.7 and 2.8). For optimum battery performance it is
recommended to mount the battery in a temperature controlled section of the
aircraft.

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Rev B May 25, 2004 Manual Number 9015762 Page 13 of 21
2.5 Installation
NOTE: Before installing unit, verify the option label on the unit matches the aircraft
requirements for instrument voltage, lighting voltage/color, and panel tilt.
Install the Electric Attitude Indicator within the aircraft in accordance with the aircraft
manufacturer’s instructions and the following steps:
A. Refer to Figure 2.1 for installation dimensions and electrical information.
B. Ensure the available instrument panel cutout meets the requirements of the
indicator. See Fig. 2.2 for details.
C. If a remote mounted standby battery is preferred:
1. Remove 4 screws mounting the standby battery to the rear of the indicator and
remove the standby battery.
2. Re-install the 4 screws into the rear of the indicator.
3. Mount the standby battery in a protected location inside the aircraft using
9015671 kit, oriented at any angle from horizontal to vertical. If mounted
vertically, cable side must be down as shown in Fig. 2.4.
4. Make an extension cable, 22 AWG minimum, using the connectors provided in
9015671 kit.
D. Plug the standby battery cable into the rear of the Indicator. The cable is
disconnected for shipping to prevent accidental activation and battery
discharge in transit.
E. The unit may start when the battery is connected. Momentarily push the STBY PWR
button, twice if necessary, until the Red Gyro Warning flag shows. Continue the
installation after the Gyro has spun down.
F. Attach aircraft electrical system cable to the round 4-pin indicator connector and
insert the indicator into the instrument panel cutout.
G. Secure the indicator to the instrument panel using the screw sizes called out in the
mounting instructions. Length of screws will be determined by aircraft instrument
panel thickness. The aircraft manufacturer or the installation facility is responsible
for supplying appropriate installation hardware.
H. Apply the correct input power to the indicator.
I. The Gyro Warning flag (red) will be out-of-view.
J. Check to determine that indicator internal lighting is working correctly.
K. After the unit has been powered for at least a 3-minute spin-up period, press and
hold the STBY PWR button. A green light will illuminate under the word TEST,
indicating the standby battery is functioning properly. If a red light illuminates, the
standby battery will need to be charged for 1 hour before retesting. If the standby
battery fails to pass the short battery capacity test after 1 hour charging, a full
battery capacity test must be performed. See Sect. 2.6.3.

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2.6 Continued Airworthiness
1. Recommended replacement interval for the standby battery (P/N 9015607) is 3 years
because of diminished capacity (See Fig. 2.7 for more information). This can be a user
replaceable item if desired. The standby battery contains lead. Recycle the battery in
accordance with state and local regulations.
2. If the 4300-4XX Electric Attitude Indicator has not been operated for an extended period
(more than 3 months) to keep the battery charged, the standby battery should be
charged by one of the following methods.
A. Keep the battery plugged into the 4300 Electric Attitude Indicator. Run the unit
overnight (approx. 15 hours) at the rated voltage.
B. Float Charging: Disconnect the battery from the indicator. Connect the battery
to a constant voltage source (battery plug (pin 1) red wire = positive) of 20.4 to
20.6 VDC continuously. Float charging may take 24 hours or longer to charge a
battery pack. MCI Battery Charger/Tester P/N 36029 may be used to apply an
initial charge. The charger automatically switches to maintain a float charge
indefinitely after initial charging is complete.
C. Routine Charging: Disconnect the battery from the indicator. Connect the
battery to a constant voltage source (battery plug pin 1 red wire = positive) of
21.6 to 22.1 VDC with a current limit of 0.1 ampere maximum. When the
charging current drops to approximately 5mA, the battery is fully charged and
should be disconnected. Leaving 21.6 to 22.1 VDC charge voltage on the battery
for an extended time will degrade its life. If continuous maintenance of the
charge is desired, refer to Paragraph B: Float Charging.
3. A full battery capacity test must be performed at least on an annual basis, as well as any
time there may be a question about battery performance (life).
Full Battery Capacity Test:
A. Disconnect battery pack from the 4300 Attitude Indicator.
B. Ensure the battery is completely charged and at or near normal room
temperatures (20-25°C). (Ref. Sect. 2.6.2)
C. Connect the battery to a load of 90 ohms (rated for 10 watts) for 60 minutes
while monitoring the battery voltage level.
i. If the battery voltage is above 15.0 volts at the end of the 60-minute
battery capacity test, the battery should be capable of continued use
after recharging is complete.
ii. If the battery voltage drops below 15.0 volts before the end of the 60-
minute test period while under load, the battery pack is nearing the end
of its service life and should be replaced.
D. Recharge the battery pack immediately. WARNING: The battery may be
permanently damaged if it is left in a discharged state. Recharge a discharged
battery as soon as possible and maintain with a float charge for maximum
battery life.
4. In normal use, the 4300-4XX supplies the proper float charge voltage to maintain its
battery at peak capacity, however, the battery will slowly self discharge if the attitude
indicator is left unused for long periods (over 4 months) the same as an automobile
battery. To restore a full charge, the battery should be periodically charged per Sect.
2.6.2, or removed from the installation and maintained on a charger such as is available
from Mid-Continent Instruments. (P/N 36029)
5. No other periodic scheduled maintenance or calibration is necessary for continued
airworthiness of the 4300 series Electric Attitude Indicator. If the unit fails to perform to
specifications, it must be removed and serviced by a qualified service facility.

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Figure 2.1 Outline Drawing

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Rev B May 25, 2004 Manual Number 9015762 Page 16 of 21
Figure 2.2: Panel Cutout Dimensions
Figure 2.3: Front Mount Panel Cutout Dimensions

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Rev B May 25, 2004 Manual Number 9015762 Page 17 of 21
(When mounted
vertically)
UP
End View Side View
Figure 2.4: Remote Mount Standby Battery Option, using
9015671 Kit

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Rev B May 25, 2004 Manual Number 9015762 Page 18 of 21
Section 3: Operation
3.1 General
This section describes the Model 4300-4XX 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.
3.2 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.” SLOWLY 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. 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 earth’s 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).
3.3 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.
3.4 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.

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B. Acceleration & Deceleration Errors
Pitch/roll 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.
3.5 Standby Battery Operation
Supply aircraft power to the instrument. The internal standby battery charges automatically
while the gyro is running. Lighting is on a separate circuit connected to the aircraft lighting bus.
A. Normal Flight
At loss of external power, an amber LED will flash indicating a Power Loss Warning.
With no further action from the pilot, the unit will turn off automatically (gyro flag in
view) after approximately one minute. This is to prevent battery discharge at the
end of a flight when the master power switch is placed in the off position.
B. Loss of Aircraft Power
When the instrument switches to Power Loss Warning, the amber LED flashes for
approximately one minute. This is intended to attract the pilot’s attention and
indicate that there has been a loss of primary power to the 4300 Attitude Indicator.
Pushing the STBY PWR button on the face of the instrument will allow the unit to
continue operating on the standby battery for nominally one (1) hour or until the
battery is exhausted. See Fig 2.5 for more information on battery discharge rate.
An independent standby dial lighting system also operates in this mode. The gyro
warning flag remains out of view, which indicates the gyroscope is valid and running
on standby battery power.
Any time aircraft power is absent, with the unit in either Power Loss Warning or shut
off, pushing the STBY PWR button will put the unit in the standby power mode. The
instrument will run from standby power until the standby battery is exhausted. If
the unit is running on the standby battery, pushing the STBY PWR button will turn
the unit off. Pushing the STBY PWR button again will restore standby power and
lighting.
Restoring aircraft power will clear any standby operation and resume automatic
battery charging.

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Rev B May 25, 2004 Manual Number 9015762 Page 20 of 21
C. Standby Battery Test
The control panel on the front of the instrument incorporates a manual test feature.
This test feature places the standby battery pack under load for approximately one
minute (the gyro is used as a load) while displaying either a red or green light under
the word TEST on the front panel.
To initiate this test, first turn on the indicator with aircraft power and allow the unit
to spin up for 3 minutes or more, then press and hold the STBY PWR button. After
several seconds the amber LED will start flashing, indicating unit has latched into
Battery Test Mode. The test runs for approximately one minute, during which time
the amber LED flashes continuously and either a red or green light is displayed under
the word TEST. Visually monitor the test lights until the amber LED stops flashing,
signaling the end of the test. A green light throughout the test indicates the standby
battery pack is healthy and should be able to function under normal operation. A red
light at any time during the test means that the standby battery is at least in need of
charging, or possibly replacement. Note, however, that a green light throughout this
short test does not guarantee that a full hour of operation time is available. Actual
operation time on the battery may vary considerably depending on temperature,
charge status, and battery condition. (See Sect. 3.6 for more details). Complete
charging may be required to bring the battery up to full charge if it has been stored
for more than four months or if it has been partially discharged. If a steady red light
is observed at any time during the test, charge the standby battery completely, using
one of the methods described in section 2.6.2 and retest the battery. If after
charging, the test still fails, service may be required. (See Sect. 2.6.3 for further
testing).
It is not recommended to test the battery when aircraft power is not available, but it
is possible to put the indicator into test mode while operating on the backup battery.
The test will run, but the indicator will turn off at the end of the test period. To turn
the indicator back on, simply push the STBY PWR button again.
Fig. 2.5: Nominal Battery Discharge Rate at 20°C