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INSTALLATION MANUAL

KFC 275/325FLIGHT CONTROL SYSTEM

MANUAL NUMBER 006-00659-0012REVISION 12 AUG, 2006

WARNINGThe enclosed technical data is eligible for export under License Designation NLR and is to be used solely by the individual/organization to whom it is addressed. Diversion contrary to U.S. law is prohibited.

COPYRIGHT NOTICE

©1997, 2004, 2006 Honeywell International Inc.

REPRODUCTION OF THIS PUBLICATION OR ANY PORTION THEREOF BY ANY MEANS WITHOUT THE EXPRESS WRITTEN PERMISSION OF HONEYWELL IS PROHIBITED, EXCEPT TO THE EXTENT REQUIRED FOR INSTALLATION OR MAINTENANCE OF THE RECIPIENT’S EQUIPMENT. FOR FURTHER INFORMATION CONTACT THE MANAGER, TECHNICAL PUBLICATIONS, HONEYWELL, ONE TECHNOLOGY CENTER, 23500 WEST 105th STREET OLATHE KS 66061 TELEPHONE: (913) 712-0400.

B KFC 275/325

Rev. 12, Aug/2006

Update Drawing revisions.

ITEM ACTION

Full Reprint Replaces all previous revisions.

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B KFC 275/325

TABLE OF CONTENTS

PARA PAGE

SECTION IGENERAL INFORMATION

1.1 INTRODUCTION............................................................................................................ 1-1

1.2 EQUIPMENT DESCRIPTION ........................................................................................ 1-1

1.2.1 MODES OF OPERATION.............................................................................................. 1-2

1.3 TECHNICAL CHARACTERISTICS ............................................................................... 1-3

1.3.1 SYSTEM TECHNICAL CHARACTERISTICS ................................................................ 1-3

1.3.2 SYSTEM COMPONENTS TECHNICAL CHARACTERISTICS ..................................... 1-5

1.4 UNITS AND ACCESSORIES SUPPLIED ................................................................... 1-18

1.4.1 KA 185A....................................................................................................................... 1-18

1.4.2 KCP 220....................................................................................................................... 1-18

1.4.3 KCP 220 ADAPTERS .................................................................................................. 1-19

1.4.3 KMC 221 ...................................................................................................................... 1-24

1.4.4 KDC 222....................................................................................................................... 1-24

1.4.5 KS 270A....................................................................................................................... 1-25

1.4.6 KS 271A....................................................................................................................... 1-25

1.4.7 KS 272A....................................................................................................................... 1-26

1.4.8 KAP 315A..................................................................................................................... 1-26

1.4.9 KAS 297C .................................................................................................................... 1-27

1.4.10 KMC 321 ...................................................................................................................... 1-28

1.4.11 KTA 336 ....................................................................................................................... 1-28

1.4.12 KSA 372....................................................................................................................... 1-29

1.4.13 KSA 372X..................................................................................................................... 1-30

1.4.14 KSA 372T..................................................................................................................... 1-30

1.5 INSTALLATION KITS.................................................................................................. 1-31

1.5.1 KA 185A Installation Kit................................................................................................ 1-31

1.5.2 KCP 220 Installation Kits.............................................................................................. 1-31

1.5.3 KMC 221 Installation Kits ............................................................................................. 1-32

1.5.4 KDC 222 Installation Kits ............................................................................................. 1-32

1.5.5 KS 270A/271A/272A Installation Kits ........................................................................... 1-33

1.5.6 KMC 321 Installation Kits ............................................................................................. 1-33

1.5.7 KAS 297C Installation Kits ........................................................................................... 1-34

1.5.8 KAP 315A Installation Kits ........................................................................................... 1-34

1.5.9 KTA 336 Installation Kit................................................................................................ 1-35

1.5.10 KSA 372/372T/372X Installation Kit ............................................................................. 1-35

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TABLE OF CONTENTS

1.6 ACCESSORIES REQUIRED, BUT NOT SUPPLIED .................................................. 1-36

1.7 RELATED PUBLICATIONS ........................................................................................ 1-37

1.8 LICENSE REQUIREMENTS........................................................................................ 1-37

1.9 CONTINUED AIRWORTHINESS INSTRUCTIONS .................................................... 1-38

1.9.1 EQUIPMENT................................................................................................................ 1-38

1.9.2 WIRES/COAX CABLES............................................................................................... 1-40

SECTION IIINSTALLATION

2.1 GENERAL INFORMATION ........................................................................................... 2-1

2.2 UNPACKING AND INSPECTING EQUIPMENT ........................................................... 2-1

2.3 EQUIPMENT INSTALLATION ...................................................................................... 2-1

2.3.1 AVIONICS COOLING REQUIREMENTS ...................................................................... 2-1

2.3.2 KFC 275/325 Installation................................................................................................ 2-2

2.3.3 Installation Procedures................................................................................................... 2-2

2.4 REMOVAL AND REINSTALLATION.......................................................................... 2-28

2.4.1 KCP 220 ADAPTER MODULE INSTALLATION.......................................................... 2-30

2.5 KFC 275/325 ALIGNMENT ......................................................................................... 2-31

2.4.1 KFC 275 FLIGHTLINE GYRO ALIGNMENT PROCEDURE........................................ 2-31

2.4.2 IN-FLIGHT ADJUSTMENTS........................................................................................ 2-33

2.4.3 SLIP-CLUTCH ADJUSTMENT .................................................................................... 2-34

SECTION IIIOPERATION

3.1 GENERAL...................................................................................................................... 3-1

TSO APPENDIX


B KFC 275/325

LIST OF FIGURES

FIG PAGE

FIGURE 2-1 KA 185A CONNECTOR P185A1 PIN FUNCTIONS .................................... 2-3FIGURE 2-2 KCP 220 CONNECTOR J2201 PIN FUNCTIONS ....................................... 2-4FIGURE 2-3 KCP 220 CONNECTOR J2202 PIN FUNCTIONS ....................................... 2-6FIGURE 2-4 KCP 220 CONNECTOR J2203 PIN FUNCTIONS ....................................... 2-8FIGURE 2-5 KMC 221 CONNECTOR P2211 PIN FUNCTIONS.................................... 2-10FIGURE 2-6 KDC 222 CONNECTOR P2221 PIN FUNCTIONS .................................... 2-12FIGURE 2-7 KS 270A CONNECTOR J2701A PIN FUNCTIONS................................... 2-13FIGURE 2-8 KS 271A CONNECTOR J2711A PIN FUNCTIONS................................... 2-14FIGURE 2-9 KS 272A CONNECTOR J2721A PIN FUNCTIONS................................... 2-15FIGURE 2-10 KS 272A CONNECTOR J2721A PIN FUNCTIONS................................... 2-16FIGURE 2-11 KAS 297C CONNECTOR P297C1 PIN FUNCTIONS................................ 2-17FIGURE 2-12 KAP 315A CONNECTOR P315A1 PIN FUNCTIONS................................ 2-19FIGURE 2-13 KMC 321 CONNECTOR P3211 PIN FUNCTIONS.................................... 2-21FIGURE 2-14 KTA 336 CONNECTOR J336-1 PIN FUNCTIONS .................................... 2-23FIGURE 2-15 KSA 372/X CONNECTOR J3721 PIN FUNCTIONS.................................. 2-25FIGURE 2-16 KSA 372T CONNECTOR J3721 PIN FUNCTIONS ................................... 2-26FIGURE 2-17 KSA 372 -80 AND -81 CONNECTOR J3721 PIN FUNCTIONS ................ 2-27FIGURE 2-18 KCP 220 ADAPTER MODULE REPLACEMENT....................................... 2-30FIGURE 2-19 KSM 375 & 376 CLUTCH ADJUSTMENT DRAWING ............................... 2-37FIGURE 2-20 KM 275 & 277 CLUTCH ADJUSTMENT DRAWING.................................. 2-39FIGURE 2-21 KA 185A INSTALLATION DRAWING ........................................................ 2-49FIGURE 2-22 KCP 220 OUTLINE AND INSTALLATION DRAWING............................... 2-51FIGURE 2-23 KMC 221 INSTALLATION DRAWING ....................................................... 2-53FIGURE 2-24 KDC 222 INSTALLATION DRAWING........................................................ 2-55FIGURE 2-25 KS 270A/KS 271A AND KM 275 INSTALLATION DRAWING ................... 2-57FIGURE 2-26 KS 272A AND KM 276 INSTALLATION DRAWING .................................. 2-59FIGURE 2-27 KAS 297C INSTALLATION DRAWING...................................................... 2-61FIGURE 2-28 KAP 315A INSTALLATION DRAWING...................................................... 2-63FIGURE 2-29 KMC 321 INSTALLATION DRAWING ....................................................... 2-65FIGURE 2-30 KTA 336 INSTALLATION DRAWING ........................................................ 2-67FIGURE 2-31 KSA 372 & KSM 375 INSTALLATION DRAWING ..................................... 2-69FIGURE 2-32 KSA 372 (-0059 & -0081) & KSM 375 INSTALLATION DRAWING........... 2-71FIGURE 2-33 KSA 37X AND KSM 375-50 INSTALLATION DRAWING .......................... 2-73FIGURE 2-34 KSA 372T AND KSM 375-60 INSTALLATION DRAWING......................... 2-75FIGURE 2-35 KSA 372X AND KSM 375X INSTALLATION DRAWING ........................... 2-77FIGURE 2-36 KFC 275 INTERCONNECT........................................................................ 2-79FIGURE 2-37 KFC 325 INTERCONNECT...................................................................... 2-103FIGURE 2-38 KFC 325 AFCS EFIS INTERCONNECT .................................................. 2-127FIGURE 2-39 KCP 220 ADAPTER ................................................................................. 2-151FIGURE 2-40 KCP 220 ADAPTER ................................................................................. 2-153


B KFC 275/325

LIST OF FIGURES


B KFC 275/325

SECTION IGENERAL INFORMATION

1.1 INTRODUCTIONThis manual contains information relative to the physical, mechanical, and electrical characteris-tics of the Honeywell KFC 275/325 Flight Control Systems. General installation procedures are also included. Specific installation requirements are contained in the STC Installation Manual that pertains to your type of aircraft or from the company which holds the Type Certificate the System was certified under.

1.2 EQUIPMENT DESCRIPTIONThe KFC 275 Flight Control System is a two axis Flight Director and Autopilot which will operate with 3" Flight Command and HSI instruments. The system consists of a KCP 220 Flight Computer, KDC 222 Air Data Computer, KMC 221 Mode Controller and KA 185A Annunciator Panel. The system uses digital signal processing for Mode Selection, Annunciation, and Command Compu-tation. The standard system includes RNAV/NAV/LOC coupling plus manual/auto trim. Half bank and Turbulence modes are also included. Options to this system are YAW axis control, airspeed gain scheduling, Go around mode, Airspeed hold mode, dual manual electric trim system with pilot priority and long range NAV system compatibility.The following assemblies are used:

The KFC 325 Flight Control System is a three axis Flight Director and Autopilot which will operate with 4" Flight Command and HSI instruments. The system consists of a KCP 220 Flight Computer, KDC 222 Air Data computer, KMC 321 Mode Controller and KAP 315A Annunciator Panel. The system also uses digital signal processing for Mode Selection, Annunciation, and Command Com-putation. The system comes standard with all the optional modes listed with the KFC 275. The system also has the option to be connected to standard 4" mechanical instruments or to an Elec-tronic Flight Instrument System (EFIS).The system includes the following assemblies:

Description Part Number

KCP 220 Flight Computer 065-00064-0005/XX

KDC 222 Air Data Computer 065-00085-XXXX

KMC 221 Mode Controller 065-00062-XXXX

KA 185A 3" Annunciator Panel 065-00087-XXXX

KAS 297C Altitude/Vertical Speed Selector

065-00089-0004/XXXX


KCP 220 Flight Computer 065-00064-0005/XXXX

KDC 222 Air Data Computer 065-00085-XXXX

KMC 321 Mode Controller 065-00086-XXXX

KAP 315A 4" Annunciator Panel 065-00063-XXXX

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Both systems can be used with the following servo actuators and servo capstans:

1.2.1 MODES OF OPERATION

KAS 297C Altitude/Vertical Speed Selector

065-00089-0004/XXXX


KS 270A Servo Actuator 065-00059-XXXX

KS 271A Servo Actuator 065-00060-XXXX

KS 272A Servo Actuator 065-00061-005X

KTA 336 Trim Adapter 065-00164-0X00

KSA 372 Servo Actuator 065-00056-005X, 008X

KSA 372T Servo Actuator 065-00155-005X

KSA 372X Servo Actuator 065-00056-007X

KM 275 Servo Capstan 065-00030-XXXX

KM 276 Servo Capstan 065-00031-XXXX

KSM 375 Servo Capstan 065-00015-XXXX

KSM 376 Servo Capstan 065-00023-XXXX

MODE GUIDANCE DISPLAY PROVIDED

Attitude Reference Power on, Gyros erected, warning flags out of view, and no modes selected. Existing Roll, Pitch, and Heading information is displayed but no flight commands are computed

Flight Director Pitch Attitude Hold and Wings Level commands. Commands to maintain Pitch Attitude that exists at the time of Flight Director Mode selection and a return to Wings Level condition.Pitch Attitude Trim is a sub-mode of Flight Director

Heading Select/Preselect Roll command to the heading selected on the PNI heading bug.

NAV Roll command to capture and track a navigation course provided by a NAV, RNAV, or Long Range Navigation Receiver/converter.

Approach Roll and Pitch commands to capture and track LOC and GS Beams, MLS Tracks, VOR, RNAV, and Long Range Navigation Approach course.

Back Course Roll command to capture and track a reverse LOC course.

Go Around Pitch up and wings level command to Missed Approach climb attitude.


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1.3 TECHNICAL CHARACTERISTICS

1.3.1 SYSTEM TECHNICAL CHARACTERISTICS

Vertical Speed Select/Prese-lect

Pitch command to capture and maintain a selected vertical speed.

Altitude Select/Preselect Pitch command to capture a selected altitude.

Altitude Hold Pitch command to hold a selected altitude.

IAS Hold Pitch command to hold an indicated Airspeed.

Half bank Roll commands to one half the certified maximum bank angle. half

Turbulence (Soft Ride) Decreases Pitch and Roll commands to provide smoother flight control.

Vertical Trim Pitch Command to modify engaged Altitude, Air-speed, or Pitch attitude.

Yaw Damper Provides stability in the Yaw axis and auto-matic turn coordination.

Autopilot Provides servo actuator commands to all the selected Flight Director modes. Also provides 3 axis stabilization and Automatic Pitch Trim.

KFC 275/325

Altitude Stability -1000 to 55,000ft

Directional Stability 360 deg +/- 2 deg

Altitude Hold Stability +/- 30ft

IAS Hold Stability +/- 3 Knots

IAS Range Up to 335 Knots with some flavors of system components.

Heading Stability +/- 3 deg

NAV and APPR Stability +/- 3 deg

Vertical Speed Hold Stability +/- 100 ft per minute

Maximum Bank Angles: Heading Modes NAV and APPR Modes Half Bank Mode

Up to 30 degUp to 30 degUp to 15 deg

Maximum Pitch Commands: Pitch Attitude Hold Glideslope

+20 deg and -10 deg from zero attitude+20 deg and -10 deg from zero attitude

Computed Roll Axis Command Rates

3.75 deg/sec Nominal7.5 deg/sec Nominal in APR capture

Altitude Overshoot Less than 100 ft for any ascent or descent up to 5000 ft per minute

Altitude Trim Rate 500 +/- 75 ft per minute

MODE GUIDANCE DISPLAY PROVIDED

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Vertical Trim Sensitivity .75 Kts per second for IAS Hold.6 deg to 1 dwg per second for Pitch Attitude Hold100ft per minute per second for Vertical Speed Hold

Glideslope Capture Computa-tion

Scheduled by Beam Closure Rate

VOR Crosswind Compensation Up to 30 deg right or left

NAV/APR/BC Logic Arm, Capture and TrackReversion to Capture from Track if Course Slew is greater then 10 deg per second

NAV/APR/BC Capture Capability All angles

NAV/APR/BC Capture Computa-tion

Scheduled by beam closure rate and airspeed

NAV Track Computation Scheduled by DME and Airspeed

APR/BC Track Computation Localizer and Glideslope gains scheduled by Radar Altimeter

Manual Trim Speed Computation Scheduled by Airspeed

Softride Criteria Pitch commands Limited to.1G(.15G in Pitch Attitude Trim)

Aural Alerting:

Autopilot Disconnect 2.4KHz tone for 2.0 sec

Manual/Autotrim Failure 2.4KHz modulated at 2.5Hz 50% DC

Altitude Band Crossing 4 tones, 2.5KHz for 1.0 sec

KFC 275/325

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1.3.2 SYSTEM COMPONENTS TECHNICAL CHARACTERISTICS

KA 185A

TSO Compliance: See Appendix A

Physical Dimensions: See FIGURE 2-21 KA 185A INSTALLATION DRAWING

Weight: See FIGURE 2-21 KA 185A INSTALLATION DRAWING

Mounting: Panel, with two #4 Flathead screws

Mating Connector: P/N 030-00107-0011 (2VK6D/1-2 VIKING)

Temperature Range: -20 deg C to 55 deg C

Altitude Range: Up to 55,000 FT

Power Inputs: 28VDC at 1.0A MAX

+5VDC at 0.1A MAX

Signal Inputs: A clock, strobe and serial data lines are used to determine which mode lights are activated.A one wire ground input to light the AP annun-ciator.

Signal Output: A one wire dimmed lamp bus for a Decision Height Annunciator

KCP 220


Physical Dimensions: See FIGURE 2-22 KCP 220 OUTLINE AND INSTALLATION DRAWING

Weight: See FIGURE 2-22 KCP 220 OUTLINE AND INSTALLATION DRAWING

Mounting: Remote with Honeywell supplied rack

Mating Connectors P/N 030-02350-0005 (HDC50F-200-14*23 POSITRONIC)P/N 030-02350-0035 (HDC50F-200-14*22 POSITRONIC)P/N 030-02350-0038 (HDC50F-200-14*32 POSITRONIC)

Temperature: -55 deg C to 70 deg C


Power Inputs: +28VDC at.8A+28VDC Trim Power at.1A

Power Outputs: +15VDC at.1A-15VDC at.1A+ 5VDC at.2A+21VDC at.2A-21VDC at.2A10 VAC 430Hz at 1.2 VA (KFC 275 VG Excitation)

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Signal Inputs:

Vertical Reference: 2 Wire, Pitch and Roll, 50mV AC per degree (KFC 275)3 Wire Pitch and Roll, 206mV AC per degree (KFC 325)

Directional Reference: 2 Wire Heading Datum, 550mV DC/Degree for KFC 275or 393mV AC/Degree for KFC 325.

Course Datum: 2 Wire Course Datum, 210mV DC/Degree for KFC 275or 393mV AC/Degree for KFC 325.

VOR/RNAV Receiver: 60mV DC/Degree/Localizer 15mV per Degree/VOR30mV/1NM RNAV Enroute. 120mV/1NM RNAV APPR.

LOC Energize Sense: Ground for LOC Enable

Glideslope Receiver: 214mV DC/Degree

Altitude Hold Error: .02Hz/FT (from KDC 222)

Glideslope Valid: 180mV for Valid

Middle Marker Sense: 1 Wire, 2VDC Minimum for MKR on

Outer Marker Sense: 1 Wire, 2VDC Minimum for MKR on

Radar Altitude: 2 wire DC differential voltage+/- 4mV/ft or +/- 10mV/ft

Mode Controller Interface: 3 Wire Serial

Altitude Selector Interface:

4 Wire Serial

Pitch Servo Tach Feedback: 2 Wire, DC Differential voltage

Roll Servo Tach Feedback: 2 Wire, DC Differential voltage

Yaw Servo Tach Feedback: 2 Wire, DC Differential voltage

Trim Servo Monitor: 2 Wire, DC Differential voltage

Yaw Rate Gyro: 200mV DC/Degree/Sec.

Roll Null Adjust: 1 Wire, 0 to +/- 15VDC.

Pitch Cmd Bar Adjust: 1 Wire, 0 to +/- 15VDC.

Roll Cmd Bar Adjust: 1 Wire, 0 to +/- 15VDC.

Airspeed: 1 Wire, 0 to 5VDC, low airspeed to high air-speed

Vertical Acceleration: -1.65V/G (UP)

Lateral Acceleration: -.18V/Degree (RIGHT)

NAV Steering Cmd: 393mV AC/Degree at 400Hz (ARINC 561-10)

Honeywell EFS-10, 40 System Interface:

4 Wire Serial ARINC 429

Honeywell DME Interface 2 Wire serial ARINC 429

Honeywell MLS Interface Analog

KCP 220

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Engine Out Sensing: 2 Wire, 26mVDC/PSI

Switched 28VDC (For Servo Engages):

1 Wire

Pitch Torque Sensing: 2 Wire, Open or GND, Gnd for autotrim drive.

Flaps Motor Sense: 2 Wire (Flap motor voltage)

Flaps Logic Sense: 2 Wire

Pilot/Copilot Manual Trim: 9 Wire

Yaw Rate Gyro Valid: Open = InvalidGround = Valid

VG Valid: Ground = Invalid28V = Valid

NAV Steering Valid: Ground = Invalid28V = Valid

Compass Valid: HI = InvalidGround = Valid

"G" Dump: HI = ValidGround = Dump

Radar Altimeter Valid Ground = Invalid28V = Valid

Signal Outputs:

Pitch Servo Drive: 2 Wire DC Differential, 0 to 28V max.

Pitch Trim Servo: 2 Wire DC Differential, 0 to 28V max.

Roll Servo Drive: 2 Wire DC Differential, 0 to 28V max.

Yaw Servo Drive: 2 Wire DC Differential, 0 to 28V max.

Servo Clutch Engages: 3 Wires, One to each servo, 28V to engage

Annunciator Interface: 3 Wire Serial (to Mode Control and Annunciator)

Roll Cmd Bar Drives: -.168V/Degree (RIGHT) = KFC 275+.75V/Degree (RIGHT) = KFC 325

Pitch Cmd Bar Drives: -.453V/Degree (UP) = KFC 275+1.0V/Degree (UP) = KFC 325

Pitch Rate: .1V/Degree/Sec (UP)

Command Bar Retract:

KFC 275 15V = In ViewOpen = Out of Vie

KFC 325 Open = In ViewGround = Out of View

Pilot/Copilot Manual Trim: 5 Wires

Yaw Rate Excitation: 26V AC 400Hz at 5VA

Aural Alert Drive: 2.4KHz sine wave sonalert drive

AP Valid: Open = Invalid, Ground = Validor Ground = Invalid, 28V = Valid

KCP 220

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VG Excitation: 10VAC at 400Hz (KFC 275)

Preflight Test Out: Open = No test28V = Test

KMC 221

TSO Compliance See Appendix A

Physical Dimensions: See FIGURE 2-23 KMC 221 INSTALLATION DRAWING

Weight: See FIGURE 2-23 KMC 221 INSTALLATION DRAWING

Mounting: Panel, with Honeywell supplied rack

Mating Connector: P/N 030-02349-0007 (HDC37F200-14*9 POSITRONIC)



Power Inputs: 28VDC at 1.5A+/- 15VDC at.070A

Signal Inputs: A clock, strobe and serial data lines are used to determine which mode lights are activated. A clock and a strobe are provided for button encoding. GA and CWS are on individual lines and are activated by grounding pins 4 and 3 respectively.

Signal Outputs: Serial data lines contain encoded button infor-mation. Individual lines are pulled to ground when any of the following are active: YD, BC, TRIM FAIL and AP HORN. Null outputs for Roll, Roll Command Bar, Pitch Command Bar, and Lat-eral Acceleration are provided.

KCP 220

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KDC 222


Physical Dimensions: See FIGURE 2-24 KDC 222 INSTALLATION DRAWING

Weight: See FIGURE 2-24 KDC 222 INSTALLATION DRAWING

Mounting: Remote, four #6 screws

Mating Connector: P/N 030-02348-0016 (HDC25F-200*16 POSITRONIC)



Power Inputs: +28VDC at 10mA+15VDC at 10mA-15VDC at 10mA+ 5VDC at 10mA

Signal Inputs:

Yaw Gyro Excitation: 26VAC at 400Hz

Preflight Test: Open = No Test28V = Test

Lateral Acceleration Null Adjust:

1 wire, 0 to +/- 15VDC

Pitch Rate: +.2VDC/Degree/Sec (UP)

Signal Outputs:

Lateral Acceleration: -.18VDC/Degree (RIGHT)

Vertical Acceleration: -1.65VDC/G (UP)

Altitude Oscillator: 4.75KHz

Airspeed: 0 to 5VDC, Low airspeed to high airspeed

"G" Dump: HI = ValidGround = Dump

IAS Range 275 Knots (-0000,-0001,-0002,-0010)335 Knots (-0020)

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KS 270A

TSO Compliance: TSO C9cDO 138 Env. Cat. BAJAAAXXXXXX

Lightning Susceptibility (-0018,-0019 & -0023 only)

Tested Per DO 160C Category K

Physical Dimensions: See FIGURE 2-25 KS 270A/KS 271A AND KM 275 INSTALLATION DRAWING

Weight: See FIGURE 2-25 KS 270A/KS 271A AND KM 275 INSTALLATION DRAWING

Mounting: Remote to KM 275/276/277 with 2 AN3 bolts

Mating Connector: P/N 030-02000-0000



Power Inputs: +14VDC at 5 amps max+28VDC at 5 amps max

Signal Inputs: Servo drive command signal (0 to +15VDC)Clutch Engage Signal (+14 or 28VDC)

Signal Outputs: Servo MonitorTach Feedback

KS 271A


Lightning Susceptibility (-06/-18 only)


Physical Dimensions: See FIGURE 2-25 KS 270A/KS 271A AND KM 275 INSTALLATION DRAWING

Weight: See FIGURE 2-25 KS 270A/KS 271A AND KM 275 INSTALLATION DRAWING








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KS 272A


Lightning Susceptibility (-56 only)


Special Operating Low Temperature:

Tested Per DO 138 to -55 deg C

Physical Dimensions: See FIGURE 2-26 KS 272A AND KM 276 INSTALLATION DRAWING

Weight: See FIGURE 2-26 KS 272A AND KM 276 INSTALLATION DRAWING








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KAS 297C

TSO Compliance: TSO C9c, C57aDO 160B Env. Cat. F1A/SP/XXXXXXZZABZ

Lightning Susceptibility (-12 thru 17)


Physical Dimensions: See FIGURE 2-27 KAS 297C INSTALLATION DRAWING

Weight: See FIGURE 2-27 KAS 297C INSTALLATION DRAWING

Mounting: Panel Mounted

Temperature: -20 deg C to +55 deg C


Power Inputs: 9 to 33VDC at.7 amps max

Lighting Requirements: 120mA max at 14VDC60mA max at 28VDC

Signal Inputs:

Encoding Altimeter Inputs: 11 Wire Grey CodeActive State = GroundInactive State = Open

Baro Correct Input: 4.2VDC to.40VDC

Altitude Oscillator Input: From KDC 222, 4.25KHz to 5.0KHz

4 Wire Data Bus From KCP 220

Signal Outputs:

Aural Alert Output 2 +/-.2Vp-p into a 500W load

Sonalert Output: Active State: Lo (NMT 1 +/-.5VDC at 10mA max)Active State: High (33VDC max)

Voice Enable Output: Active State: Lo (NMT 1 +/-.5VDC at 10mA max)

Active State: High (33VDC max)

Baro Pot Excitation Output: 5VDC

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KAP 315A


Physical Dimensions: See FIGURE 2-28 KAP 315A INSTALLATION DRAWING

Weight: See FIGURE 2-28 KAP 315A INSTALLATION DRAWING

Mounting: Panel, with four #6 screws

Mating Connector: P/N 030-02566-0005 (PT06E1626SW(SR) BENDIX)



Power Inputs: 28VDC at 1.1A MAX

Signal Inputs: A clock, strobe and serial data lines are used todetermine which mode lights are activated.1 wire ground input to light the AP annunciator

Signal Output: 1 wire dimmed light bus for Decision Height Lamps

KMC 321


Physical Dimensions: See FIGURE 2-29 KMC 321 INSTALLATION DRAWING

Weight: See FIGURE 2-29 KMC 321 INSTALLATION DRAWING

Mounting: DZUS Rails with Honeywell supplied screws

Mating Connector: P/N 030-02349-0007 (HDC37F-200-14*9 POSITRONIC)


Altitude Range Up to 55,000 FT

Power Inputs: 28VDC+/- 15VDC.070A

Signal Inputs: A clock, strobe and serial data lines are used to determine which mode lights are activated. A clock and a strobe are provided for button encoding. GA and CWS are on individual lines and are activated by grounding pins 4 and 3 respectively.

Signal Outputs: Serial data lines contain encoded button infor-mation. Individual lines are pulled to ground when any of the following are active: YD, BC, TRIM FAIL and AP HORN. Null outputs for Roll, Roll Command Bar, Pitch Command Bar and Lateral Acceleration are provided.

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KTA 336

TSO Compliance See Appendix A

Physical Dimensions: See FIGURE 2-30 KTA 336 INSTALLATION DRAWING

Weight: See FIGURE 2-30 KTA 336 INSTALLATION DRAWING

Mounting: Remote, four #6 screws




Power Inputs: +28VDC at 6 Amps max

Signal Inputs:

Autotrim Commands 2 wire; 0=off, +28=on

Autotrim Clutch Dr. 1 wire; 0=off, +28V=on

Autotrim Feedback 2 wire: 0=off, +28V=on

Manual Trim input (Pilot, Copilot)

3 wire; Varies with installation.

Preflight Test Engage, 1 wire; 0=off, +28V=on

Autopilot Engage, 1 wire; 0=off, +28V=on

Control Wheel Steering 1 wire; Open=off, 0=on

Aileron Trim Engage 2 wire; 0=off, +28V=on

Autopilot disconnect 1 wire; 0=off, +28V=on

Stick Shaker Engage 2 wire; 0=off, +28V=on

Emergency Trim Dr. 2 wire; 0=off, +28V=on

Signal Output:

Autotrim Drive 2 wire; 0=off, +28V=on

Trim Aural Alert 1 wire; 0=off, 2.2 VAC=on

Trim Visual Alert 1 wire; Open=off, 0=on

Autotrim Relay Dr.(Hi) 1 wire; 0=off, +28V=on

Autotrim Relay Dr. (Lo) 1 wire; Open=off, 0=on

Autotrim Clutch Engage 1 wire; 0=off, +28V=on

Trim Motor Brake 1 wire; +28V=off, 0=on

Manual Trim Voltage 1 wire; Varies with installation.

Autopilot Disconnect 1 wire; Varies with installation.

Trim in Motion Ann. 1 wire; Open=off, 0=on

Rev. 12, Aug/2006 00659I12.cks Page 1-14

B KFC 275/325

KSA 372

TSO Compliance: TSO C9c

DO 138 Env. Cat. AAJAAAXXXXXX

Lightning Susceptibility (-56,-57,-58,-59,-80,-81)


Physical Dimensions All versions except -59 and -81: Version -59 and -81

See FIGURE 2-31 KSA 372 & KSM 375 INSTALLATION DRAWINGSee FIGURE 2-32 KSA 372 (-0059 & -0081) & KSM 375 INSTAL-LATION DRAWING

Weight: All versions except -59 and -81: Version -59 and -81

See FIGURE 2-31 KSA 372 & KSM 375 INSTALLATION DRAWINGSee FIGURE 2-32 KSA 372 (-0059 & -0081) & KSM 375 INSTAL-LATION DRAWING

Mounting: Remote to KSM 375 with 4 AN3 bolts




Power Inputs: +28VDC at 5 amps max

Signal Inputs: Servo drive command signalClutch Engage Signal

Signal Outputs: Servo MonitorTach FeedbackClutch Monitor

Rev. 12, Aug/2006 00659I12.cks Page 1-15

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KSA 372X

TSO Compliance: TSO C9cDO 138 Env. Cat. AAJAAAXXXXXX



Physical Dimensions: See FIGURE 2-33 KSA 37X AND KSM 375-50 INSTALLATION DRAW-ING

Weight: See FIGURE 2-33 KSA 37X AND KSM 375-50 INSTALLATION DRAW-ING

Mounting: Remote to KSM 375X with 4 AN3 bolts





Signal Inputs: Servo drive command signal

Clutch Engage Signal

Signal Outputs: Servo Monitor

Tach Feedback

Clutch Monitor

Rev. 12, Aug/2006 00659I12.cks Page 1-16

B KFC 275/325

KSA 372T

TSO Compliance: TSO C9cDO 138 Env. Cat. AAJAAAXXXXXX



Physical Dimensions: See FIGURE 2-34 KSA 372T AND KSM 375-60 INSTALLATION DRAWING

Weight: See FIGURE 2-34 KSA 372T AND KSM 375-60 INSTALLATION DRAWING

Mounting: Remote to KSM 375 with 4 AN3 bolts





Signal Inputs: Servo drive command signal

Clutch Engage Signal

Signal Outputs: Servo Monitor

Tach Feedback

Clutch Monitor

Rev. 12, Aug/2006 00659I12.cks Page 1-17

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1.4 UNITS AND ACCESSORIES SUPPLIED

1.4.1 KA 185A

The KA 185A is available in two versions. KA 185A P/N 065-0087-00 has a black bezel. KA 185A P/N 065-0087-06 has a black bezel and is tested for Lightning Susceptibility per DO 160C Cate-gory K.

1.4.2 KCP 220

The KCP 220 is available in the following versions depending on aircraft.

PART NUMBER DESCRIPTION

065-00064-0000 Basic 2 Axis Computer

065-00064-0001 3 Axis Computer for use in Cessna 406 Cara-van II and Piper Cheyenne IIIA aircraft

065-00064-0005 3 Axis Computer with ARINC 429 Comm. for use in Beechcraft Baron and SIAI Marchet-ti/SF600 aircraft.

065-00064-0006 3 Axis Computer for use in the Grob Egrett air-craft.

065-00064-0007 3 Axis Computer for use with the EFS 40 in the Beech Baron and Pilatus Britten Norman BN2-T/LET-L410 aircraft.

065-00064-0008 3 Axis Computer for use in the Socata TBM 700 aircraft.

065-00064-0009 3 Axis Computer for use in Pilatus Brit-tain-Norman BN2T4S Defender.

065-00064-0012 3 Axis Computer for use in the Grob Egrett air-craft. This unit is also tested for Lightning Sus-ceptibility per DO 160C Category K.

065-00064-0015 3 Axis Computer for use in Pilatus PC12 air-craft. Lightning Tested.

065-00064-0017 3 Axis Computer for use in Pilatus PC 7 air-craft. Lightning Tested.

065-00064-0020 3 Axis Computer for use in Citation 500 air-craft. Lightning Tested. IAS capability to 335 knots.

Rev. 12, Aug/2006 00659I12.cks Page 1-18

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1.4.3 KCP 220 ADAPTERS

The KCP 220 requires adapters in the following versions:LOGIC ADAPTER

PN AIRCRAFT

065-05034-0000 TEST ADAPTERS -05 THRU -14

065-05034-0001 TEST ADAPTERS -15 AND ABOVE

065-05034-0002 NOT ASSIGNED


065-05034-0004 BARON E-55 BEECH

065-05034-0005 ANTONOV AN-28 B1, M KFC 325

065-05034-0007 SA1A MARCHETTI SF600

065-05034-0008 LET L-410 KFC 275

065-05034-0009 BRITTEN NORMAN ISL, KFC 325

065-05034-0010 SOCATA TBM 700 KFC 275

065-05034-0011 LET L-410 KFC 275


065-05034-0013 BRITTEN NORMAN DEF, KFC 275

065-05034-0014 CHILEAN TWIN OTTER DHC-6

065-05034-0015 GRUMMAN S2 TRACKER

065-05034-0016 SOCATA TBM 700B

065-05034-0017 GROB EGRETT, KFC 325

065-05034-0021 PILATUS PC12 1994

065-05034-0022 CITATION 500, KFC 325

065-05034-0023 BARON CERTICATION WITH EFIS

065-05034-0024 ANTONOV AN-28 B2 KFC 325

065-05034-0025 CITATION 500 LONG WING 1994

065-05034-0026 PILATUS PC12 1994 B

065-05034-0029 PILATUS PC-7 2005

TABLE 1-1 LOGIC ADAPTER PN CROSS REFERENCE

Rev. 12, Aug/2006 00659I12.cks Page 1-19

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OPTION ADAPTER

PN AIRCRAFT



065-05051-0002 TEST ADAPTER, -08

065-05051-0003 TEST ADAPTER -15 AND ABOVE

065-05051-0004 BARON E-55 BEECH



065-05051-0008 LET L-410 KFC 275


065-05051-0010 SOCATA TBM 700 KFC 275

065-05051-0011 LET L-410 KFC 275





065-05051-0016 SOCATA TBM 700B

065-05051-0017 GROB EGRETT, KFC 325

065-05051-0021 PILATUS PC12 1994

065-05051-0022 CITATION 500, KFC 325


065-05051-0024 ANTONOV AN-28 B2 KFC 325


065-05051-0026 PILATUS PC-12 YAW 2002 KFC 325

065-05051-0029 PILATUS PC-7 2005

TABLE 1-2 OPTION ADAPTER PN CROSS REFERENCE

Rev. 12, Aug/2006 00659I12.cks Page 1-20

B KFC 275/325

PITCH ADAPTER

PN AIRCRAFT





065-05052-0004 BARON E-55 BEECH



065-05052-0008 LET L-410 KFC 275


065-05052-0010 SOCATA TBM 700 KFC 275

065-05052-0011 LET L-410 KFC 275





065-05052-0016 SOCATA TBM 700B

065-05052-0017 GROB EGRETT, KFC 325

065-05052-0021 PILATUS PC12 1994

065-05052-0022 CITATION 500, KFC 325


065-05052-0024 ANTONOV AN-28 B2 KFC 325



065-05052-0029 PILATUS PC-7 2005

TABLE 1-3 PITCH ADAPTER PN CROSS REFERENCE

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ROLL ADAPTER

PN AIRCRAFT





065-05053-0004 BARON E-55 BEECH



065-05053-0008 LET L-410 KFC 275


065-05053-0010 SOCATA TBM 700 KFC 275

065-05053-0011 LET L-410 KFC 275





065-05053-0016 SOCATA TBM 700B

065-05053-0017 GROB EGRETT, KFC 325

065-05053-0021 PILATUS PC12 1994

065-05053-0022 CITATION 500, KFC 325


065-05053-0024 ANTONOV AN-28 B2 KFC 325


065-05053-0026 SOCATA TBM 700C UPDATE 1993

065-05053-0027 SOCATA TBM 700D

065-05053-0028 PLZ M-28 SKYTRUCK

065-05053-0029 PILATUS PC-7 2005

065-05053-0030 PILATUS PC-12/47 2005

065-05053-0031 PILATUS PC-12/45 2006

TABLE 1-4 ROLL ADAPTER PN CROSS REFERENCE

Rev. 12, Aug/2006 00659I12.cks Page 1-22

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065-05053-0032 PILATUS PC-12/47 2006

PN AIRCRAFT

TABLE 1-4 ROLL ADAPTER PN CROSS REFERENCE

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1.4.3 KMC 221

The KMC 221 is available in 12 versions. They are listed below:

* Units tested for Lightning Susceptibility per DO 160C Category K.

1.4.4 KDC 222

The KDC 222 is available in the following versions:

PART NUMBER BEZELCOLOR

WITHTRIMRING

BACKCOURSE

NAVINVALID

YAWDAMP

IAS LIGHT-NING TESTED *

065-00062-0000 BLACK YES YES NO YES NO NO

065-00062-0001 BLACK YES YES NO NO YES NO

065-00062-0002 BLACK NO YES NO YES NO NO

065-00062-0003 BLACK NO YES NO NO YES NO

065-00062-0004 GREY YES YES NO YES NO NO

065-00062-0005 GREY NO YES NO NO YES NO

065-00062-0006 GREY NO YES NO YES NO NO

065-00062-0007 BLACK YES YES NO NO YES NO

065-00062-0008 BLACK YES NO NO YES NO NO

065-00062-0009 BLACK YES NO NO YES NO NO

065-00062-0010 BLACK YES YES YES YES NO NO

065-00062-0018 BLACK YES YES NO YES NO YES


065-00085-0000 Air Data Computer

065-00085-0001 Air Data Computer with "G" Monitor

065-00085-0002 Air Data Computer with "G" Monitor and PFT Monitor

065-00085-0006 Air Data Computer with "G" Monitor, PFT Monitor and the unit is tested for Lightning Susceptibility per DO 160C Category K.

065-00085-0010 Air Data Computer with "G" Monitor, PFT Monitor, and IAS Sensor.

065-00085-0020 Air Data Computer with IAS Range to 335 Knots.

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1.4.5 KS 270A

The KS 270A for the KFC 275/325 is available in the following versions:

1.4.6 KS 271A



065-00059-0001 This is a pitch axis servo with a speed of 4.8 RPM.



065-00059-0018 This is a pitch axis servo with a speed of 2.4 RPM. The unit is also tested for Lightning Sus-ceptibility per DO 160C Category K.



065-00060-0000 This is a yaw or roll axis servo with a speed of 13.6 RPM.

065-00060-0001 This is a yaw or roll axis servo with a speed of 4.9 RPM.

065-00060-0018 This is a yaw axis servo with a speed of 13.6 RPM. The unit is also tested for Lightning Sus-ceptibility per DO 160C Category K.

065-00060-0019 This is a roll axis servo with a speed of 4.9 RPM. The unit is also tested for Lightning Sus-ceptibility per DO 160C Category K.

Rev. 12, Aug/2006 00659I12.cks Page 1-25

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1.4.7 KS 272A


1.4.8 KAP 315A

The KAP 315A is available in the following versions:


065-00061-0050 This is a pitch trim servo with a speed of 4.3 RPM.



065-00061-0056 This is a pitch trim servo with a speed of 3.8 RPM. The unit is also tested for Lightning Sus-ceptibility per DO 160C Category K.


065-00063-0000 Black Bezel

065-00063-0001 Gray Bezel

065-00063-0006 Black Bezel and Tested for Lightning Suscep-tibility Per DO 160C Category K.

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1.4.9 KAS 297C

The KAS 297C is available in the following versions:



LIGHTING KCP 220-01 COMPONLY

KCP 220-05 COMP& ABOVE

IMPROVED VS DAMPING

LIGHT-NING TESTED *

065-00089-0000 BLACK 28V YES NO NO NO

065-00089-0001 BLACK 5V YES NO NO NO

065-00089-0002 GREY 28V YES NO NO NO

065-00089-0003 GREY 5V YES NO NO NO

065-00089-0004 BLACK 28V NO YES NO NO

065-00089-0005 BLACK 5V NO YES NO NO

065-00089-0006 GREY 28V NO YES NO NO

065-00089-0007 GREY 5V NO YES NO NO

065-00089-0008 BLACK 28V NO YES YES NO

065-00089-0012 BLACK 5V NO YES NO YES

065-00089-0013 BLACK 28V NO YES YES YES

065-00089-0014 GREY 5V NO YES YES YES

065-00089-0015 GREY 28V NO YES YES YES



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1.4.10 KMC 321

The KMC 321 is available in the following versions:


1.4.11 KTA 336

The KTA 336 is for the KFC 275/325 is available in the following versions:


LIGHTING BACKCOURSE

NAVVALID

LIGHT-NING TESTED *

065-00086-0000 BLACK 28V YES NO NO

065-00086-0001 BLACK 5V YES NO NO

065-00086-0002 GREY 28V YES NO NO

065-00086-0003 GREY 5V YES NO NO

065-00086-0004 BLACK 28V NO NO NO

065-00086-0005 BLACK 5V NO NO NO

065-00086-0006 GREY 28V NO NO NO

065-00086-0007 GREY 5V NO NO NO

065-00086-0008 BLACK 28V YES YES NO

065-00086-0012 BLACK 28V YES NO YES

065-00086-0013 BLACK 5V YES NO YES

065-00086-0016 BLACK 28V NO NO YES

065-00086-0017 BLACK 5V NO NO YES

065-00086-0018 GREY 28V NO NO YES

065-00086-0019 GREY 5V NO NO YES


065-00164-0100 This is a Trim Adapter with Stick Shaker input features.

065-00164-0200 This is a Trim Adapter with Basic features.

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1.4.12 KSA 372

The KSA 372 for the KFC 275/325 is available in the following versions:


065-00056-0000 This is a pitch, yaw or roll servo with a speed of 16 RPM.

065-00056-0050 This is a pitch, yaw or roll servo with a speed of 16 RPM and a torque sensing voltage set at .5348 volts.


065-00056-0056 This is a pitch, yaw or roll servo with a speed of 16 RPM and a torque sensing voltage set at .5348 volts. The unit is also tested for Light-ning Susceptibility per DO 160C Category K.

065-00056-0057 This actuator incorporates a new face gear de-sign and improved motor specifications. The servo is designed for applications which re-quire high holding forces.

065-00056-0058 This actuator differs from a -56 only in the se-lection of speed limiting zeners.

065-00056-0059 This actuator differs from the -56 only as it contains a delay in the pitch trim sense output drive.

065-00056-0080 This actuator contains a delayed torque sens-ing output.

065-00056-0081 This actuator differ from the -80 in the thresh-old and delay time for torque sensing.

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1.4.13 KSA 372X

The KSA 372X for the KFC 275/325 is available in the following versions:

1.4.14 KSA 372T

The KSA 372T for the KFC 275/325 is available in the following versions:



065-00056-0071 This is a pitch, yaw or roll servo with a speed of 5 RPM and a torque sensing voltage set at .356 volts, but with high speed select zeners then the -70.

065-00056-0076 This is a pitch, yaw or roll servo with a speed of 5 RPM and a torque sensing voltage set at .356 volts. The unit is also tested for Lightning Susceptibility per DO 160C Category K.

065-00056-0077 This actuator differs from the -0070 with the torque sensing voltage set to.542 volts.


065-00155-0050 This is a trim servo with a speed of 16 RPM.

065-00155-0056 This is a trim servo with a speed of 16 RPM. The unit is also tested for Lightning Suscepti-bility per DO 160C Category K.

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1.5 INSTALLATION KITS

1.5.1 KA 185A Installation Kit

The KA 185A Installation Kit (P/N 050-02312-0000/0001) is available in both the solder and crimp style connector version. The kit consists of the following items:

PN DESCRIPTION REV-----------------------------------------------------------------------050-02312-0000 INSTALLATION KIT AA050-02312-0001 INSTALLATION KIT 2

--------------------------------------------------------------------------------------------------------SYMBOL PART NUMBER FIND NO DESCRIPTION UM -0000 -0001-------------------------------------------------------------------------------------------------------- 030-00107-0011 CONN DUEL RO EA 1.00 . 030-00107-0099 POLARIZING KEY, CARDEDGE CONN EA 1.00 . 030-01314-0000 CRIMP CONTACT EA . 12.00 030-02760-0000 CONN HSG 6P EA . 1.00 047-04886-0000 KA 285 NUT PLATE EA 1.00 1.00 088-00450-0000 HOOD CONN EA 1.00 . 088-03042-0000 HOOD MODIFICATION EA . 1.00 089-05111-0008 SCR, MACH, 4-40, FH 82, PH, SS, BLK OXD, 1/2 LG EA 2.00 2.00 089-06123-0007 SCR PHP 4-40X7/16 EA 2.00 2.00

1.5.2 KCP 220 Installation Kits

The KCP 220 Installation Kit (P/N 050-02291-0000/0002) is available in both solder and crimp style connector versions. The kit consists of the following items:

PN DESCRIPTION REV-----------------------------------------------------------------------050-02291-0000 INSTL KIT KCP220 2050-02291-0002 INSTL KIT KCP220 4

--------------------------------------------------------------------------------------------------------SYMBOL PART NUMBER FIND NO DESCRIPTION UM -0000 -0002--------------------------------------------------------------------------------------------------------REF1 155-05609-0000 INST DWG KCP 220 RF .00 .00 030-01157-0011 SOCKET CRMP 20G EA . 140.00 030-01176-0000 CONN SUB-D HSG 50S (FEMALE PINS) EA . 3.00 030-01186-0000 CONTACT SKT CRIMP EA . 10.00 030-01188-0000 PIN POLRZTN FEMALE EA . 3.00 030-02350-0005 CONN SUB-D CA 50S EA 1.00 . 030-02350-0035 CONN SUB-D CA 50S EA 1.00 . 030-02350-0038 CONN SUB-D CA 50S EA 1.00 . 030-02351-0004 HOOD/LVR ASSY ST E EA 3.00 3.00 057-03423-0000 LABELS, CONNECT EA 1.00 1.00 057-03423-0001 LABELS, CONNECT EA 1.00 1.00 057-03423-0002 LABELS, CONNECT EA 1.00 1.00 071-04038-0001 3 INCH MTG RACK W/AIR EA 1.00 1.00

VENDOR INFORMATION

030-02350-0005 Positronic HDC50S-200-14*9 030-02350-0035 Positronic HDC50S-200-14*22 030-02350-0038 Positronic HDC50S-200-14*32 030-02351-0004 Positronic MD-50-000-J-VL

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1.5.3 KMC 221 Installation Kits

The KMC 221 Installation Kit (P/N 050-02311-0000/0001) is available in both solder and crimp style connector versions. The kit consists of the following items:

PN DESCRIPTION REV-----------------------------------------------------------------------050-02311-0000 INSTALLATION KIT 0050-02311-0001 INSTALLATION KIT 0

--------------------------------------------------------------------------------------------------------SYMBOL PART NUMBER FIND NO DESCRIPTION UM -0000 -0001--------------------------------------------------------------------------------------------------------REF1 155-05612-0000 INSTALL DWG KMC221 RF .00 .00 030-01157-0011 SOCKET CRMP 20G EA . 36.00 030-01175-0000 CONN SUB-D HSG 37S (FEMALE PINS) EA . 1.00 030-01188-0000 PIN POLRZTN FEMALE EA . 1.00 030-02349-0007 CONN SUB-D CA 37S EA 1.00 . 030-02351-0003 HOOD/LVR ASSY ST E EA 1.00 1.00

VENDOR INFORMATION

030-01157-0011 Positronic FC6026D-14 030-01175-0000 Positronic RD37F00000 030-02349-0007 Positronic HDC37F-200-14*9 030-02351-0003 Positronic MD-37-000-J-VL

1.5.4 KDC 222 Installation Kits

The KDC 222 Installation Kit (P/N 050-02293-0000/0001) is available in both solder and crimp style connector versions. The kit consists of the following items:


--------------------------------------------------------------------------------------------------------SYMBOL PART NUMBER FIND NO DESCRIPTION UM -0000 -0001--------------------------------------------------------------------------------------------------------REF1 155-05606-0000 INSTALL DWG KDC222 RF .00 .00 030-01157-0011 SOCKET CRMP 20G EA . 24.00 030-01173-0000 CONN SUB-D HSG 25S (FEMALE PINS) EA . 1.00 030-01188-0000 PIN POLRZTN FEMALE EA . 1.00 030-02348-0001 CONN SUB-D CA 25S EA 1.00 . 030-02351-0002 HOOD/LVR ASSY ST E EA 1.00 1.00 057-02999-0000 HOSE DECAL EA 1.00 1.00 057-02999-0001 HOSE DECAL EA 1.00 1.00

VENDOR INFORMATION

030-01157-0011 Positronic FC6026D-14 030-01173-0000 Positronic RD25F00000 030-02348-0001 Positronic HDC25F-200*16 030-02351-0002 Positronic MD-25-000-J-VL

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1.5.5 KS 270A/271A/272A Installation Kits

The KS 270A/271A/272A Installation Kit (P/N 050-01450-0000/0001) is available in solder style connector only. The -0000 version kit is for the KS 270A/271A. The -0001 version kit is for the KS 272A. The kits consist of the following items:

PN DESCRIPTION REV-----------------------------------------------------------------------050-01450-0000 INSTALLATION KIT 3050-01450-0001 INSTALL KIT 2

--------------------------------------------------------------------------------------------------------SYMBOL PART NUMBER FIND NO DESCRIPTION UM -0000 -0001-------------------------------------------------------------------------------------------------------- 030-01008-0000 LVR/PVT ASSY EA 2.00 2.00 030-01009-0000 HOOD CONN EA 1.00 . 030-01010-0000 HOOD CONN EA . 1.00 030-02000-0000 CONN 14 PIN FEM EA 1.00 . 030-02002-0000 CONN 20 PIN FEM SOLDER EA . 1.00 057-01739-0000 INSTALLATION TAGS EA 1.00 . 089-05899-0003 SCR PHP 2-56X3/16 EA 4.00 4.00 090-00731-0000 NUT ANCHOR CORNER EA 2.00 2.00

1.5.6 KMC 321 Installation Kits

The KMC 321 Installation Kit (P/N 050-02292-0000/0001) is available in both solder and crimp style connector versions. The kit consists of the following items:


--------------------------------------------------------------------------------------------------------SYMBOL PART NUMBER FIND NO DESCRIPTION UM -0000 -0001--------------------------------------------------------------------------------------------------------REF1 155-05607-0000 INSTALLATION DWG RF .00 .00REF1 155-05612-0000 INSTALL DWG KMC221 RF . .00 030-01157-0011 SOCKET CRMP 20G EA . 36.00 030-01175-0000 CONN SUB-D HSG 37S (FEMALE PINS) EA . 1.00 030-01188-0000 PIN POLRZTN FEMALE EA . 1.00 030-02349-0007 CONN SUB-D CA 37S EA 1.00 . 030-02351-0003 HOOD/LVR ASSY ST E EA 1.00 1.00

VENDOR INFORMATION

030-01157-0011 Positronic FC6026D-14 030-01175-0000 Positronic RD37F00000 030-02349-0007 Positronic HDC37F-200-14*9 030-02351-0003 Positronic MD-37-000-J-VL

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1.5.7 KAS 297C Installation Kits

The KAS 297C Installation Kit (P/N 050-02563-0000/0001) is available in both solder and crimp style connector versions. The kit consists of the following items:

PN DESCRIPTION REV-----------------------------------------------------------------------050-02563-0000 INST KIT 297C SOLD 0050-02563-0001 INST KIT 297C CRMP 0

--------------------------------------------------------------------------------------------------------SYMBOL PART NUMBER FIND NO DESCRIPTION UM -0000 -0001-------------------------------------------------------------------------------------------------------- 030-01157-0011 SOCKET CRMP 20G EA . 37.00 030-01175-0000 CONN SUB-D HSG 37S (FEMALE PINS) EA . 1.00 030-01188-0000 PIN POLRZTN FEMALE EA . 1.00 030-02349-0018 CONN SUB-D CA 37S EA 1.00 . 030-02351-0003 HOOD/LVR ASSY ST E EA 1.00 1.00 071-04029-0000 MARION CLAMP EA 1.00 1.00 089-05115-0012 SCR, MACH, 6-32, FH 82, PH, SS, BLK OXD, 3/4 LG EA 4.00 4.00 089-06085-0012 SCR PHP 6-32X3/4 EA 4.00 4.00 155-05551-0000 INST DWG KAS297B/C RF .00 .00

1.5.8 KAP 315A Installation Kits

The KAP 315A Installation Kit (P/N 050-02290-0000/0001/0002/0003) is available in both solder and crimp style connector versions with both gray and black mounting hardware for gray or black bezels. The kit consists of the following items:

PN DESCRIPTION REV-----------------------------------------------------------------------050-02290-0000 INSTALL KIT 0050-02290-0001 INSTALLATION KIT 0

--------------------------------------------------------------------------------------------------------SYMBOL PART NUMBER FIND NO DESCRIPTION UM -0000 -0001-------------------------------------------------------------------------------------------------------- 030-02566-0001 CONN, CIRC, PLG, CRIMP, (16-26SW) EA . 1.00 030-02566-0005 CONNECTOR EA 1.00 . 057-02029-0044 KAP315A CONN LABEL EA 1.00 1.00 089-05115-0012 SCR, MACH, 6-32, FH 82, PH, SS, BLK OXD, 3/4 LG EA 4.00 4.00


--------------------------------------------------------------------------------------------------------SYMBOL PART NUMBER FIND NO DESCRIPTION UM -0002 -0003-------------------------------------------------------------------------------------------------------- 030-02566-0001 CONN, CIRC, PLG, CRIMP, (16-26SW) EA . 1.00 030-02566-0005 CONNECTOR EA 1.00 . 057-02029-0044 KAP315A CONN LABEL EA 1.00 1.00 089-06461-0012 SCR FHP 6-32X3/4 EA 4.00 4.00

VENDOR INFORMATION

030-02566-0001 Bendix PTO6SE1626SW(SR) 030-02566-0005 Bendix PTO6E1626SW(SR)

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1.5.9 KTA 336 Installation Kit

The KTA 336 Installation Kit (P/N 050-03208-0000) is available is crimp style connector only.

PN DESCRIPTION REV-----------------------------------------------------------------------050-03208-0000 KTA336 INSTALL KIT 1

-------------------------------------------------------------------------------------------------SYMBOL PART NUMBER FIND NO DESCRIPTION UM -0000-------------------------------------------------------------------------------------------------REF1 155-06602-0000 KTA336 INSTALL DWG RF .00 030-03249-0000 CONN STRPL EA 1.00

1.5.10 KSA 372/372T/372X Installation Kit

The KSA 372/372T/372X Installation Kit (P/N 050-01246-0000) is available in solder style con-nector only. The kits consist of the following items:

PN DESCRIPTION REV-----------------------------------------------------------------------050-01246-0000 INSTALLATION KIT 11

-------------------------------------------------------------------------------------------------SYMBOL PART NUMBER FIND NO DESCRIPTION UM -0000------------------------------------------------------------------------------------------------- 030-02070-0000 CONN 16-26S PIN FEMALE EA 1.00 089-07017-0001 BLT HHN1/4-28X.531 EA 4.00 089-08068-0030 WSHR FLT STD .257 EA 4.00 155-05086-0000 INST DWG KSA370 AR .00 155-05145-0000 INST DWG KSA370 AR .00

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1.6 ACCESSORIES REQUIRED, BUT NOT SUPPLIEDSome of the following accessories are required, but not supplied as a part of the KFC 275/325 Flight Control System. Consult the appropriate STC Installation Manual for requirements pertain-ing to your aircraft.

A. KCI 310 (P/N 066-3020-XX) Flight Command Indicator and installation kit (P/N 050-01252-00XX).

B. KCI 310A (P/N 066-3082-XX) Flight Command Indicator and installation kit (P/N 050-01252-00XX).

C. KPI 553A (P/N 066-3045-XX) Horizontal Situation Indicator and installation kit (P/N 050-01791-00XX).

D. KPI 553B (P/N 066-3069-XX) Horizontal Situation Indicator and installation kit (P/N 050-02167-00XX).

E. KI 525A (P/N 066-3046-XX) Horizontal Situation Indicator and installation kit (P/N 050-01344-0000).

F. KA 51B (P/N 071-1242-XX) Compass Slaving Accessory and installation kit (P/N 050-01928-0000/0001).

G. KRG 331 (P/N 060-0024-XX) Remote Yaw Rate Gyro and installation kit (P/N 050-01865-00XX).

H. KSG 105 (P/N 060-0013-01) Directional Gyro and installation kit (P/N 050-01410-0000).

I. KMT 112 (P/N 071-1052-XX) Compass Flux Valve and installation kit (P/N 050-01361-0000).

J. KI 256 (P/N 060-0017-XX) Vertical Gyro and installation kit (P/N 050-01518-0000).L. KG 102A (P/N 060-0015-00) Directional Gyro and installation kit (P/N

050-01410-0000).M. KVG 350 (P/N 060-0026-00) Vertical Gyro and installation kit (P/N

050-01873-0000).N. Bench Test Kit (P/N 050-01332-0000)

PN DESCRIPTION REV-----------------------------------------------------------------------050-01332-0000 KSM375BENCHTESTKIT 2

-------------------------------------------------------------------------------------------------SYMBOL PART NUMBER FIND NO DESCRIPTION UM -0000------------------------------------------------------------------------------------------------- 071-06010-0000 SPLINE ADAPTER EA 1.00 071-06011-0000 PLATE MTG EA 1.00

O. Test Stand (P/N 071-06028-0000)P. Adapter Tool (P/N 071-06021-0003)Q. Adapter Pin (P/N 071-06021-0002)

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1.7 RELATED PUBLICATIONSA. KCI 310 Flight Command Indicator maintenance manual (P/N 006-05604-00XX).B. KCI 310A Flight Command Indicator maintenance manual (P/N 006-05666-00XX).C. KPI 553A Horizontal Situation Indicator maintenance manual (P/N

006-05602-00XX).D. KPI 553B Horizontal Situation Indicator maintenance manual (P/N

006-05603-00XX).E. KAS 297C Altitude/Vertical Speed Selector maintenance manual (P/N

006-05663-00XX).F. KCS 305 Compass System maintenance manual (P/N 006-05116-00XX).G. KCS 55A Compass System maintenance manual (P/N 006-05111-00XX).H. KVG 350 Vertical Gyro maintenance manual (P/N 006-05199-00XX).I. KI 256 Vertical Gyro maintenance manual (P/N 006-05146-00XX).J. KRG 331 Remote Yaw Rate Gyro maintenance manual (P/N 006-05515-00XX).K. Honeywell Servo maintenance manual (P/N 006-05557-00XX).

1.8 LICENSE REQUIREMENTSNone.

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1.9 CONTINUED AIRWORTHINESS INSTRUCTIONS

1.9.1 EQUIPMENT

FAR Part 25.1529 Instructions for Continued Airworthiness is met per the following instructions:The instructions for continued airworthiness given in the TC or STC approvals for this product sup-plements or supersedes the instructions for continued airworthiness in this manual.

Most Honeywell products are designed and manufactured to allow "on-condition maintenance." On-condition maintenance is defined as follows: No maintenance is required until the equipment does not properly perform its intended function. When service is required, a complete perfor-mance test should be accomplished following any repair action. Refer to the appropriate unit Maintenance/Overhaul Manual for complete performance test information.However, certain components of Honeywell Flight Control Systems do require routine mainte-nance. In addition, routine inspections or performance testing of Honeywell products may be re-quired to comply with Federal Aviation Administration Regulations. Certain components of BENDIX/KING model KFC 275 and KFC 325 Flight Control Systems re-quire periodic maintenance as outlined in this procedure.

The following maintenance actions should be accomplished at least once each calendar year (13 months maximum) or every 1000 hours (1100 hours maximum) of operation, whichever comes first.

A. Remove all servo capstan assemblies (model KM 275, KM 276, KM 277, KSM 375, KSM 376) from the aircraft and check the slip-clutch torque setting (Refer to 2.4.3 SLIP-CLUTCH ADJUSTMENT). Re-adjust if necessary to the specifications found in the test procedure in the applicable TC or STC Maintenance/Overhaul Manuals.

B. If the aircraft has model KS 270, KS 270A, KS 271, KS 271A, KS 272, KS 272A, KS 273, KSA 373, or KSA 374 Servo Actuators installed, they should be removed from the aircraft.

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C. PERIODIC INSPECTION PROCEDURE for the KS 27XA SERVOModels covered: KS 270A, KS 271A, and KS 272A.

CAUTION

Any disassembly/assembly of these servosMUST be done at a static-safe workstation. Theinspector and bench should be grounded.

Cover Removal1. Remove the two screws that hold the cover on the unit, and

carefully slide the cover off over the wiring harness.2. Place the servo (without its cover) on the bench so that the

inner parts of the unit will not be damaged. Solenoid/Clutch Inspection

1. Inspect the operation of the solenoid. The plunger should move freely in and out of the solenoid body. There should be no dirt, contamination, or corrosion around the solenoid plunger. (This could impede the actuation of the solenoid.)

2. The release spring should pull the plunger out of the sole-noid and against its stop freely and without hesitation.

General Inspection1. Inspect the wiring for evidence of wear or damage to the in-

sulation. This could cause wire shorts. 2. Inspect the entire servo for any loose hardware or other ab-

normalities.Additional Inspection for the KS 270A Pitch Servo

1. Position the KS 270A Servo so that the solenoid plunger is oriented vertically with the motor up.

2. With finger or thumb, apply pressure to the side of the pinion gear. The motor should rock back and forth, activating the 2 trim-sensing microswitches when pressure is applied, and deactivating the switches when pressure is removed. The microswitches should both be deactivated in the hands-off condition. The beryllium copper springs should have with no signs of cracking at corner bend.

Cover Replacement1. Carefully slide the cover back on over the wiring harness

onto the unit to its original position. 2. Install the screws using a low-strength thread-locking com-

pound such as Loctite 222 or Loctite 242.

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D. If the aircraft has model KSA 372, KSA 372T, or KSA 372X Servo Actuators in-stalled, they should be removed from the aircraft. Check the electrical torque-lim-iting circuitry as outlined in the appropriate sections of the KFC 300 Mainte-nance/Overhaul Manuals or the individual servo maintenance manual. The gear train of the servo actuator should be inspected and lubricated as necessary.

E. Reinstall servos (if removed) and servo capstans. Inspect bridle cables for wear, corrosion, and distortion. (Refer to FAA Advisory Circular AC 43.13.1A.) Re-ten-sion the bridle cables to the specifications listed in the applicable STC Maintenance Manual, Installation Manual, or aircraft TC data.

F. Perform preflight checks and flight checks as described in the applicable STC Maintenance Manual, Installation Manual, or aircraft TC data.

Some autopilot installations are included on an aircraft's type certificate. Maintenance information for the autopilot system may be located in the aircraft's Maintenance/Overhaul Manual for autopi-lot instructions that are included on an aircraft type certificate.

Refer to 2.5 KFC 275/325 ALIGNMENT for periodic maintenance procedures.

When service is required, a complete performance test should be accomplished following any re-pair action. Refer to TABLE 2-1 COMPONENT REPLACEMENT ADJUSTMENTS for list of main-tenance requirements by unit. Consult the appropriate unit Maintenance/Overhaul Manual for complete performance test information.

1.9.2 WIRES/COAX CABLES

During on-condition or regularly scheduled maintenance, inspect the wires and coax cables fol-lowing the guidelines listed in AC 43,13-1 Chapter 15 as necessary.

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SECTION IIINSTALLATION

2.1 GENERAL INFORMATIONThis section contains general suggestions and factors to consider before installing the KFC 275/325 Flight Control Systems. Close adherence to these suggestions will assure optimum per-formance from the equipment. Specific installation requirements are contained in the STC Instal-lation Manual that pertains to the particular type of aircraft which the equipment is to be installed.The conditions and test required for the TSO and MOPS approval of this article are minimum per-formance standards. It is the responsibility of those installing this article either on or with a speci-fied type or class of aircraft to determine that the aircraft installation conditions are within the TSO and MOPS standards. These articles must have separate approval for installation in an aircraft. Any features in this equipment outside the requirements of this applicable TSO and MOPS must be evaluated and approved as part of the installation approval. The article may be installed only if performed under 14 CFR part 43 or the applicable airworthiness requirements.

2.2 UNPACKING AND INSPECTING EQUIPMENTExercise extreme care when unpacking the equipment. Make a visual inspection of the unit for evidence of damage incurred during shipment. If a claim for damage is to be made, save the ship-ping container to substantiate the claim. The claim should be promptly filed with the transporta-tion company. It would be advisable to retain the container and packaging material after all equip-ment has been removed in the event that equipment storage or reshipment should become nec-essary.

2.3 EQUIPMENT INSTALLATION

2.3.1 AVIONICS COOLING REQUIREMENTS

The greatest single contributor to increased reliability of all modern day avionics is to limit the max-imum operating temperature of the individual units, such as KCP 220, whether panel mounted or remote mounted. While modern day individual circuit designs consume much less electrical en-ergy, watts per cubic inch dissipated within the avionics unit remains much the same due to high density packaging techniques utilized. Consequently, the importance of providing cooling to the avionics stack is still with us today.

NOTE: The KCP 220 requires force air cooling.

While each individual unit may or may not require forced air cooling, the combined heat load of several units operating in a typical avionics location will significantly degrade the reliability of the avionics if provisions for cooling are not incorporated in the initial installation. Failure to provide cooling to the equipment will lead to increased avionics maintenance costs and may also void the Honeywell warranty.

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2.3.2 KFC 275/325 Installation

The KFC 275/325 installation will conform to standards designated by the customer, installing agency, and existing conditions as to the unit location and type of installation. However, the fol-lowing suggestions will assure a more satisfactory performance from the equipment.

2.3.3 Installation Procedures

Refer to the appropriate STC installation manual.

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FIGURE 2-1 KA 185A CONNECTOR P185A1 PIN FUNCTIONS

PIN I/O NAME

1 I STROBE

2 CHASSIS GROUND

3 I CLOCK

4 I DATA

5 SPARE

6 O ALERT DIMMER BUS

A I +28 VDC INPUT POWER

B I AP LT DRIVE

C SPARE

D SPARE

E I +5VDC INPUT POWER

F POWER GROUND

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* On -15 and above units only

FIGURE 2-2 KCP 220 CONNECTOR J2201 PIN FUNCTIONS (Sheet 1 of 2)

PIN I/O NAME

1 I PITCH AND ROLL (LO) (C)

2 I NAV (+RT)(15mV/DEG VOR)

3 I NAV (+LT)

4 O PRFLIGHT (OPEN/28V)

5 I ROLL CMD BAR ADJUST

6 O PITCH RATE (.1V/DEG/SEC => UP

7 O 4" PIT CMD BAR (1.0V/DEG => UP

8 O 3" CMD BAR RETRACT (15V/OPEN)

9 O PITCH DR (+DN)

10 I R0LL NULL ADJUST

11 I MODE CRTL (CLK)

12 I MODE CRTL (STR)

13 O ROLL DR (+LT)

14 O ROLL DR (+RT)

15 O 4" CMD BAR RETRACT (OPEN/GND)

16 I HDG DAT (+ .55V/DEG => RT)

17 I HDG DAT (-)

18 I ROLL ATT (H)(50mV/DEG OUT 0 => RT)

19 I PITCH ATT (H)(50mV/DEG OUT => UP)

20 I ROLL ATT (- .2V/DEG => RT)

21 O 3" ROLL CMD BAR (-.168V/DEG => RT

22 I LOC ENG (HI/GND)

23 KEY PIN

24 I PITCH CMD BAR ADJUST

25 O PITCH DR (+UP)

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* On -15 and above units only


PIN I/O NAME

26 I PITCH FB (+UP)

27 I CRSCHG (HI/GND) *HDG/SGVAL (0/28)

28 O AP VAL (GND/28V)

29 O 3" PIT CMD BAR (-.453V/DEG => UP)

30 I ROLL FB (+RT)

31 O COMM CLK

32 I CRS DAT (+.21V/DEG => RT)

33 I CRS DAT (-)

34 O G DUMP (HI/GND)

35 O NAV STRG CMD VALID (GND/28V)

36 O NAV 1/NAV 2 (1/0)

37 O AP VALID (OPEN/GND)

38 I COMPASS VALID (HI/GND)

39 O 4" ROLL CMD BAR (.75V/DEG => RT)

40 O PITCH ATT (-.2V/DEG => UP)

41 I PITCH FB (+DN)

42 I ROLL FB (+LT)

43 I VG DEMOD DRIVE

44 O COMM ADR 1

45 O COMM ADR 0

46 O COMM ADR 2

47 O COMM DATA

48 I MAN TRIM ENG (GND/HI) *NAV VAL (-)

49 O MAN TRIM ENG (GND/HI) *NAV VAL (+)

50 O +28V TRIM POWER

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*On -15 and above units only


PIN I/O NAME

1 I +28V SWITCHED

2 O +15VDC

3 O -15VDC

4 CHASSIS GROUND

5 O +5VDC

6 I VERTICAL ACCEL (-)

7 O TRIM DN DR (GND/HI)

8 I TRIM DN FB (GND/HI)

9 O MANUAL TRIM DR

10 I GS VALID (-)

11 I GS DEV (+UP)

12 I ALT OSC INPUT (4.75KHz)

13 O AP LT DRIVE (OPEN/GND)

14 I MODE CTRL DATA

15 I VERT ACCEL (+)(-1.65V/G => UP)

16 O AURAL ALERT (2KHz) OUT

17 I MANUAL TRIM VOLTAGE

18 O TRIM CLUTCH ENGAGE (OPEN/HI)

19 I NAV SOURCE SEL 1

20 I NAV SOURCE SEL 2

21 I RNAV MODE SEL 1

22 KEY PIN

23 I RNAV MODE SEL 2

24 I TRIM UP FB (GND/HI)

25 I YAW GYRO VALID (OPEN/GND)

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*On -15 and above units only


PIN I/O NAME

26 I FLAPS LOGIC (GND/HI)

27 I GS VALID (+)(VALID if > 180mV)

28 I GS DEV (.214V/DEG => UP)

29 O AP ANN (EXT)(OPEN/GND)

30 O *TRIM FAIL ANN (OPEN/GND)

31 I IAS (DC) INPUT (+)

32 I TRIM SENSE UP (OPEN/GND)

33 I TRIM SENSE DN (OPEN/GND)

34 O AP CLUTCH ENGAGE (GND/HI)

35 O YD CLUTCH ENGAGE (GND/HI)

36 O 3" INST VG EXC (10VAC at 400Hz)

37 O RADAR ALT HI

38 I +28VDC

39 O RADAR ALT LO

40 O TRIM UP DR (GND/HI)

41 POWER GROUND

42 SIGNAL GROUND

43 I FLAPS LOGIC (HI/GND)

44 I TRIM SERVO STRAP

45 I OUTER MARKER (GND/HI)

46 I MIDDLE MARKER (GND/HI)

47 O RADAR ALT VALID (0/28V)

48 O FLAPS MTR UP (GND/HI)

49 O FLAPS MTR DN (GND/HI)

50 APR. MLS. CPL (1/0)

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PIN I/O NAME

1 I MAN TRIM UP (PIL)

2 I MAN TRIM UP (CPIL)

3 I MAN TRIM DN (PIL)

4 I MAN TRIM DN (CPIL)

5 I MAN TRIM ARM (PIL)

6 I MAN TRIM ARM (CPIL)

7 O MAN TRIM UP

8 O MAN TRIM DN

9 I CRS DAT (C)

10 I CRS DAT (H)

11 I VG EXCITATION (H)

12 O RUD DR (+LT)

13 O RUD DR (+RT)

14 O +21VDC

15 O -21VDC

16 O YAW SERVO DRIVE (+RT)

17 CAT II REQ (1/0)

18 O YAW RATE GYRO EXC (C)

19 O VG VALID (OPEN/28)

20 I ARINC 429 (EFIS) (A)

21 I PIT & ROLL REF (C)

22 I ARINC 429 (EFIS) (B)

23 I NAV AC REF (H)

24 I NAV AC REF (C)

25 O MAN TRIM ARM (GND/HI)

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PIN I/O NAME

26 O 429 DATA COMM (A) (FLT CNTRL)

27 O 429 DATA COMM (B) (FLT CNTRL)

28 I YAW RATE (-)

29 I YAW RATE (.2V/DEG/SEC => RT)

30 I NAV STEER CMD (HI)

31 I 429 DAT COMM DME A BENDIX

32 KEY PIN

33 I 429 DAT COMM DME B BENDIX

34 I HDG DATUM (H)(393mV/DEG IN PHASE => RT)

35 I HDG DATUM (C)

36 I DG EXCITATION (H)

37 I ROLL ATT (H)(.2V/DEG OUT OF PHASE => RT)

38 I ROLL ATT (C)

39 ARINC 429 (FMS) (A)

40 I RUD FB (+LF)

41 I RUD FB (+RT)

42 I LATERAL ACC (-.18V/DEG => RT)(HI)

43 I PIT ATT (H)(.2V/DEG OUT OF PHASE => UP)

44 I PIT ATT (C)

45 ARINC 429 (FMS) (B)

46 O PIT ATT (H)(50mV/DEG OUT OF PHASE => UP)

47 O ROL ATT (H)(50mV/DEG OUT OF PHASE => RT)

48 I 429 DATA COMM (A) (667)

49 I 429 DATA COMM (B) (667)

50 I NAV STEER CMD (LO)

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FIGURE 2-5 KMC 221 CONNECTOR P2211 PIN FUNCTIONS (Sheet 1 of 2)

PIN I/O NAME

1 POWER GROUND

2 O BACK COURSE ANNUNCIATION

3 I CWS SWITCH

4 I GA SWITCH

5 SIGNAL GROUND

6 O YD ANNUNCIATION

7 I CMP VAL

8 I SWITCH DATA

9 KEY PIN

10 I ANNUNCIATOR CLOCK

11 I SWITCH STROBE

12 O TRIM FAIL ANNUNCIATION

13 SPARE

14 SPARE

15 SPARE

16 SPARE

17 SPARE

18 O CMP VAL

19 CHASSIS GROUND

20 SHIELD GROUND

21 I +5VDC

22 I +28VDC

23 I PANEL LAMPS (+)

24 I PANEL LAMPS (-)

25 O AP LIGHT DRIVE

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PIN I/O NAME

26 O NAV VAL (-)

27 O NAV VAL (+)

28 I SWITCH CLOCK

29 I ANNUNCIATOR STROBE

30 I ANNUNCIATOR DATA

31 O AP/TRIM HORN

32 I +15VDC

33 I -15VDC

34 O PITCH CMD BAR NULL

35 O ROLL CMD BAR NULL

36 O ROLL NULL

37 O LATERAL ACCEL NULL

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FIGURE 2-6 KDC 222 CONNECTOR P2221 PIN FUNCTIONS

PIN I/O NAME

1 O LATERAL ACCEL

2 I LATERAL ACCEL NULL ADJUST

3 I YAW GYRO EXCITATION

4 SPARE

5 I +5VDC

6 KEY PIN

7 O VERTICAL ACCEL

8 SPARE

9 I PRE-FLIGHT TEST

10 O "G" DUMP

11 SPARE

12 SPARE

13 SPARE

14 O ALTITUDE HOLD OSCILLATOR

15 SPARE

16 O INDICATED AIRSPEED DC

17 I PITCH RATE

18 I +28VDC

19 POWER GROUND

20 SPARE

21 SPARE

22 I +15VDC

23 I -15VDC

24 SIGNAL GROUND

25 CHASSIS GROUND

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FIGURE 2-7 KS 270A CONNECTOR J2701A PIN FUNCTIONS

PIN I/O NAME

A O MOTOR SENSE #2

B I SOLENOID STRAP #1

C POWER GROUND

D I CAPSTAN CW COMMAND

E I AUTOPILOT CLUTCH ENGAGE

F SPARE

H I +14VDC/+28VDC

J O CCW TORQUE LIMIT

K SPARE

L I CAPSTAN CCW COMMAND

M I SOLENOID STRAP #2

N CHASSIS GROUND

P O MOTOR SENSE #1

R O CW TORQUE LIMIT

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NOTE: Pins F, J, K, and R are used on the -60 and -61 Units only. They are Spares on all other Units.

FIGURE 2-8 KS 271A CONNECTOR J2711A PIN FUNCTIONS

PIN I/O NAME

A O MOTOR SENSE #2

B I SOLENOID STRAP #1

C POWER GROUND

D I CAPSTAN CCW COMMAND


F I COMMAND RELAY (HI)

H I +14VDC/+28VDC

J O SERVO EFFORT (+)

K I COMMAND RELAY (LO)

L I CAPSTAN CW COMMAND

M I SOLENOID STRAP #2

N CHASSIS GROUND

P O MOTOR SENSE #1

R O SERVO EFFORT (-)

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NOTE: * On Unit versions -01, thru -05, -18, and -19, these lines also serve as engage lines.

FIGURE 2-9 KS 272A CONNECTOR J2721A PIN FUNCTIONS (-41 Versions and below)

PIN I/O NAME

A O MOTOR TRIM VOLTAGE

B I PFT (Not -01 thru -05, -18 or -19)

C I MANUAL TRIM ENGAGE (Not -01 thru -05, -18 or -19)

D I * MANUAL TRIM CW


F O MOTOR FEEDBACK CCW

H CHASSIS GROUND

J POWER GROUND

K I AUTO TRIM CW DRIVE

L O MOTOR FEEDBACK CW

M I +28VDC POWER

N I +14VDC POWER

P I * MANUAL TRIM CCW

R I AUTO TRIM CCW DRIVE

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FIGURE 2-10 KS 272A CONNECTOR J2721A PIN FUNCTIONS (-42 Versions and above)

PIN I/O NAME

A O MOTOR TRIM VOLTAGE

B I PREFLIGHT TEST

C I MANUAL TRIM ENGAGE

D I MANUAL TRIM CW


F O MOTOR FEEDBACK CCW

H CHASSIS GROUND

J POWER GROUND

K I AUTO TRIM CW DRIVE

L O MOTOR FEEDBACK CW

M I +28VDC POWER

N I +14VDC POWER

P I MANUAL TRIM CCW

R I AUTO TRIM CCW DRIVE

S O SERVO FLAVOR STRAP

T SPARE

U SPARE

V I MANUAL TRIM DRIVE SIGNAL

W SPARE

X SPARE

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FIGURE 2-11 KAS 297C CONNECTOR P297C1 PIN FUNCTIONS (Sheet 1 of 2)

PIN I/O NAME

1 I 5V/14V/28V LAMPS

2 ALTITUDE COMMON

3 BAROMETRIC REFERENCE

4 O BAROMETRIC ALTITUDE EXCITATION

5 I ALTITUDE GRAY CODE D4

6 I ALTITUDE GRAY CODE A1

7 I BAROMETRIC ALTITUDE SENSE

8 LAMPS 5V/14V = GND, 28V = OPEN

9 I ALTITUDE OSCILLATOR

10 I ALTITUDE GRAY CODE C2


12 I ALTITUDE GRAY CODE B4


14 I SERIAL ADRESS 1

15 O ALERT BAND SELECT

16 GAIN STRAP #1

17 GAIN STRAP #2

18 I +14VDC/+28VDC INPUT POWER

19 POWER GROUND

20 LAMPS 5V = 5V, 14V = 14V, 28V = GND

21 SPARE

22 GAIN STRAP #4

23 O AURAL ALERT

24 O ALERT LAMP


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FIGURE 2-11 KAS 297C CONNECTOR P297C1 PIN FUNCTIONS (Sheet 2 of 2)

PIN I/O NAME



28 I ALTITUDE VALID

29 KEY PIN


31 O SERIAL CLOCK

32 I SERIAL DATA

33 I SERIAL ADDRESS 0

34 GAIN STRAP #3

35 O SONALERT

36 O VOICE ENABLE

37 CHASSIS GROUND

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FIGURE 2-12 KAP 315A CONNECTOR P315A1 PIN FUNCTIONS (Sheet 1 of 2)

PIN I/O NAME

A SPARE

B SPARE

C SPARE

D SPARE

E SPARE

F SPARE

G SPARE

H SPARE

J SPARE

K SPARE

L SPARE

M SPARE

N SPARE

P SPARE

R SPARE

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FIGURE 2-12 KAP 315A CONNECTOR P315A1 PIN FUNCTIONS (Sheet 2 of 2)

PIN I/O NAME

S O ALERT DIMMER BUS

T POWER GROUND

U CHASSIS GROUND

V I +28VDC

W I +5VDC

X SPARE

Y I CLOCK

Z I DATA

A SPARE

B I STROBE

C O AP DRIVE

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PIN I/O NAME

1 POWER GROUND

2 O BACK COURSE ANNUNCIATION

3 I CWS SWITCH

4 I GA SWITCH

5 SIGNAL GROUND

6 O YD ANNUNCIATION

7 SPARE

8 I SWITCH DATA

9 KEY PIN

10 I ANNUNCIATOR CLOCK

11 I SWITCH STROBE

12 O TRIM FAIL ANNUNCIATION

13 O PAH (Open/0)

14 O CWS (Open/0)

15 O WL (Open/0)

16 O RH (Open/0)

17 SPARE

18 O CMP VAL

19 CHASSIS GROUND

20 SHIELD GROUND

21 I +5VDC

22 I +28VDC

23 I PANEL LAMPS (+)

24 I PANEL LAMPS (-)

25 O AP LIGHT DRIVE

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FIGURE 2-13 KMC 321 CONNECTOR P3211 PIN FUNCTIONS (Sheet2 of 2)

PIN I/O NAME

26 O NAV VAL (-)

27 O NAV VAL (+)

28 I SWITCH CLOCK

29 I ANNUNCIATOR STROBE

30 I ANNUNCIATOR DATA

31 O AP/TRIM HORN

32 I +15VDC

33 I -15VDC

34 O PITCH CMD BAR NULL

35 O ROLL CMD BAR NULL

36 O ROLL NULL

37 O LATERAL ACCEL NULL

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NOTE: * = 16 Gauge Pins, Remainder are 20.

FIGURE 2-14 KTA 336 CONNECTOR J336-1 PIN FUNCTIONS (Sheet 1 of 2)

PIN I/O NAME

A O AUTOTRIM CMD UP (0/28)

B O AUTOTRIM CMD DN (0/28)

C O AUTOTRIM CLU ENG IN (0/28)

D O TRIM STRAP

E O AT FB UP (0/28)

F O AT FB DN (0/28)

G I +15VDC (TEST)

H I TRIM MON FAIL TEST (0/1)

J I TRIM AURAL ALERT (0/1)

K O PILOT MT ENG (IN)

L O COPILOT MT ENG (IN)

M O PFT (0/28)

N O AP ENG (0/28)

P I +7.5V (TEST)

R O CWS (X/0)

S O +28V TRIM (OUT)

T I AT RELAY OK (HI) (0/28)

U I AT RELAY OK (LO) (X/0)

V I CHASSIS GND

W O AIL TRIM LF ENG (0/28)

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NOTE: * = 16 Gauge Pins, Remainder are 20.

FIGURE 2-14 KTA 336 CONNECTOR J336-1 PIN FUNCTIONS (Sheet 2 of 2)

PIN I/O NAME

X O AIL TRIM RT ENG (0/28)

Y I AT MON PFT OK TEST (0/1)

Z I * AUTOTRIM DRIVE DN (0/28)a I * AUTOTRIM DRIVE UP (0/28)b I AUTOTRIM CLU ENG OUT (0/28)

c I/O * TRIM MTR BRAKE ON (28/0)d I +10V (TEST)

e I MAN TRIM VOLTAGE (OUT)

f I TRIM FAIL VISUAL ALERT (OPEN/0)

g I * +28V SWITCHED (OUT) (0/28)h I MAN TRIM ENG TEST (0/1)

i O * +28V SWITCHED (IN) (0/28)j I AP DISC (OPEN/0)

k O * STICK SHAKER ENGAGE #1 (0/28)m O * STICK SHAKER ENGAGE #2 (0/28)n I * TRIM IN MOTION (OPEN/0)p O * MAN TRIM VOLTAGE (IN)q O * EMERGENCY TRIM UP (0/28)r O * EMERGENCY TRIM DN (0/28)s O * +28V TRIM (IN)t O * POWER GROUND

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FIGURE 2-15 KSA 372/X CONNECTOR J3721 PIN FUNCTIONS

PIN I/O NAME

A I +27.5VDC

B POWER CHASSIS GROUND

C I TORQUE ENGAGE SWITCH

D I (+) INPUT COMMAND

E I (-) INPUT COMMAND

F SPARE

G O (+) TACH OUTPUT

H O (-) TACH OUTPUT

J I CLUTCH ENGAGE

K SPARE

L I (+) CW TRIM DRIVE

M SPARE

N I (+) CCW TRIM DRIVE

P O CCW SENSE

R O CW SENSE

S CCW RTL LOW

T O VTL ELEVATOR

U O CCW RTL

V O CW RTL

W CW RTL LOW

X O VTL RUDDER

Y VTL COMMON

Z RTL CW COMMON

a VTL AILERON

b RTL CCW COMMON

c SPARE

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FIGURE 2-16 KSA 372T CONNECTOR J3721 PIN FUNCTIONS

PIN NAME

A +27.5VDC

B POWER/CHASSIS GROUND

C MOTOR CW

D (+) INPUT COMMAND

E (-) INPUT COMMAND

F CCW RTL COMMON

G PFT

H MANUAL TRIM ENGAGE

J AP CLUTCH ENGAGE

K CCW RTL LOW

L MANUAL TRIM DRIVE

M SIGNAL GROUND

N MANUAL TRIM VOLTAGE

P MANUAL TRIM UP CW

R MANUAL TRIM DN CCW

S SERVO FLAVOR STRAP

T CCW RTL

U CW RTL COMMON

V CW RTL

W CW RTL LOW

X CHASSIS GROUND

Y MOTOR CCW

Z MOTOR FEEDBACK CCW

a VTL

b MOTOR FEEDBACK CW

c VTL COMMON

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FIGURE 2-17 KSA 372 -80 AND -81 CONNECTOR J3721 PIN FUNCTIONS

PIN I/O NAME

A I +27.5VDC

B POWER CHASSIS GROUND

C SPARE

D I (+) INPUT COMMAND

E I (-) INPUT COMMAND

F O TRIM RELAY CCW (0/1)

G O (+) TACH OUTPUT

H O (-) TACH OUTPUT

J I CLUTCH ENGAGE

K TRIM RELAY CW (0/1)

L (+) CW TRIM DRIVE

M O TRIM IN MOTION (OPEN/GND)

N (+) CCW TRIM DRIVE

P SPARE

R SPARE

S O TRIM REQ CCW (OPEN/GND)

T O VTL ELEVATOR

U SPARE

V SPARE

W SPARE

X O VTL RUDDER

Y VTL COMMON

Z SPARE

a VTL AILERON

b O TRIM REQ CW (OPEN/GND)

c SPARE

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2.4 REMOVAL AND REINSTALLATIONIn the event that a KFC 275/325 component requires removal for maintenance, alignment or ad-justments may be required. Refer to TABLE 2-1 COMPONENT REPLACEMENT ADJUSTMENTS for requirements of the various components.

NOTEALL AUTOPILOT COMPONENTS MUST BE RE-PLACED WITH THE EXACT SAME UNIT PARTNUMBER.

COMPONENT ADJUSTMENTS NEEDED AFTER COMPONENT REPLACEMENT

KCP 220 The four adapter modules must be removed from the existing flight com-puter and installed in the replacement.The KCP 220 065-00064-0001 only has three adapter modules (No logic module) Refer to FIGURE 2-39 KCP 220 ADAPTER for details.

KFC 275 systems require attitude gyro alignment per section 2.5 KFC 275/325 ALIGNMENTKFC 325 systems using a remote vertical gyro or AHRS unit typically do not need to have the attitude gyro alignment performed as long as the gain pots in the flight computer have not been disturbed since it left the factory. If alignment is required, follow the same procedure as for the KFC 275.

KMC 221 AND KMC 321

There are six adjustments that may need to be set when replacing the Mode Controller.

1. Back Bright: Back light adjustment for mode buttons.2. Nom Brite: Mode annunciator brightness adjustment.3. RN: Roll Null see section 2.4.2 IN-FLIGHT ADJUSTMENTS4. PC: Pitch Command Bar see section 2.4.2 IN-FLIGHT ADJUST-MENTS.5. RC: Roll Command Bar see section 2.4.2 IN-FLIGHT ADJUST-MENTS.6. ACCEL: Lateral Acceleration adjustment see section 2.4.2 IN-FLIGHT ADJUSTMENTS.

KDC 222 1. Lateral acceleration adjustment see section 2.4.2 IN-FLIGHT AD-JUSTMENTS.2. KAS 297C alignment refer to the KAS 297C Installation Manual part number 006-00686-XXXX.

KAS 297C KAS 297C alignment refer to the KAS 297C Installation Manual part number 006-00686-XXXX.

KEA 130A or KEA 346 or AM 250

KAS 297C alignment refer to the KAS 297C Installation Manual part number 006-00686-XXXX.

KTA 336 None

TABLE 2-1 COMPONENT REPLACEMENT ADJUSTMENTS

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KSA 372 None

KSM 275 Slip clutch torque and bridle cable tension must be set to the proper val-ues. See the aircraft TC or STC data for applicable settings and section 2.4.3 SLIP-CLUTCH ADJUSTMENT.

COMPONENT ADJUSTMENTS NEEDED AFTER COMPONENT REPLACEMENT

TABLE 2-1 COMPONENT REPLACEMENT ADJUSTMENTS

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2.4.1 KCP 220 ADAPTER MODULE INSTALLATION

The install the adapter modules, the covers must be removed, which breaks the factory seal. Breaking the factory seal for this purpose does not void the unit warranty.Upon installing the adapter modules and re-installing the KCP 220 in the aircraft, run a functional test as described in the aircraft maintenance manual.Refer to FIGURE 2-18 KCP 220 ADAPTER MODULE REPLACEMENT.

A. Remove four screws from cover. Remove cover. Refer to item A.B. Remove six screws from roll card. Refer to item B.C. Remove two screws from connector end of unit. Refer to item C.

1. Open the roll adapter card to gain access to both the roll and pitch modules.

2. Replace modules and close roll card.3. Replace screws.

E. Remove six screws from the logic card. Refer to item D.1. Open the logic card to gain access to both the logic and op-

tion modules.2. Replace modules and close logic card.3. Replace screws.4. Replace cover.

FIGURE 2-18 KCP 220 ADAPTER MODULE REPLACEMENT (Dwg. No. 11248-11, Rev 0, Sheet 1 of 1)

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2.5 KFC 275/325 ALIGNMENTWhen performing maintenance on the KFC 275 flight control system, it is very important to main-tain the flight computer/attitude gyro alignment. This will insure proper flight characteristics and optimum performance of the system. The KI 256 attitude gyros will vary slightly from unit to unit in their pitch and roll outputs therefore they must be matched to the associated flight computer by way of alignment or the system performance will be degraded.The flight control system must be realigned when either the vertical gyro or the flight computer is replaced with another unit. Realignment must also be done after bench repair of the flight com-puter if the alignment adjustments are changed or if the flight computer is sent to Honeywell for repair as these gains are always reset at the factory.The alignment procedure is always required after the initial system installation and the procedures are listed below.

2.4.1 KFC 275 FLIGHTLINE GYRO ALIGNMENT PROCEDURE

A. Remove the KCP 220 flight computer from the airplane. Connect the KTS 162 Flight Line Tester between the computer and the airplane with the six cables pro-vided.

B. Remove the KMC 221 or KMC 321 Mode Controller from the panel and reconnect it using the extender cable.

C. Mount the vertical gyro in the gyro tilt stand. Place the tilt stand in a convenient location with reference to the autopilot computer and test set. Level the tilt stand using the twist adjust knobs and bubble level. Connect the vertical gyro to the air-plane harness using the KI 256 gyro extender cable. (This cable will also work for KI 254/KG 253 and KG 258/KG 259.) Also connect the vertical gyro to an air source if required.

CAUTION:A Properly regulated and filtered air source is essen-tial for correct gyro operation.

NOTE:When making gyro alignment adjustments, always

have the gyro set to zero degrees tilt in the axis notunder test.

D. Before applying power make sure that the proper adapter modules are installed in the KCP 220 Flight Computer. Apply power to the system. All associated circuit breakers must be activated.

E. After the gyro is fully erected (ten minutes minimum run-up time), engage the Sys-tem Preflight Test function by depressing the TEST button on the Mode Controller.

F. Upon successful passage of Pre-flight Test, engage the Flight Director mode by depressing the FD button on the Mode Controller and proceed with the following.

G. Set the Gyro Stand to zero in both the pitch and roll axis. Adjust the leveling screws for pitch and roll zero visual indication with no parallax.

H. Measure the voltage from J2201 pin 20 with reference to J2202 pin 42 with a digital voltmeter. Adjust the Roll Null adjustment for 0.0 VDC. This potentiometer is ac-cessible through the hole labeled RN on the side of the Mode Controller.

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I. Measure the voltage from J2201 pin 40 with reference to J2202 pin 42 with a digital voltmeter. Adjust the Pitch Null adjustment for 0.0 VDC. This potentiometer is ac-cessible through the hole labeled PN on the bottom of the KCP 220.

J. Measure the voltage again from J2201 pin 20 with respect to J2202 pin 42. Tilt the gyro to a twenty-five degree right bank by turning the tilt stand CW to the detent. Visually adjust to exactly twenty-five degrees bank. Adjust the Roll Gain adjust-ment for -5.0 +/- 0.1 VDC. This potentiometer is accessible through the hole la-beled RG on the bottom of the KCP 220.

K. Tilt the Gyro to a twenty-five degree left bank by turning the Tilt Stand CCW to the detent. Visually adjust to exactly twenty-five degrees bank. The voltage should read +5.0 +/- 0.1 VDC.If the reading in step K exceeds +5.1 VDC, repeat step J and reduce the gain set-ting by one-half the amount exceeded in step K. If step K measured less than +4.9 VDC, repeat step J and increase the gain setting by one-half the amount short in step K. Repeat steps J and K until both the right and left bank voltage measure-ment are within tolerance. The proper total voltage excursion must be 10 +/- 0.2 VDC.

L. With the Gyro Test Stand in the zero pitch position, adjust the leveling screws on the Tilt Stand to obtain a pitch zero visual indication on the vertical gyro. (Horizon line aligned with 90 deg index marks.) Reset the Pitch Null (Step I) after any re-lev-eling is done.

M. Measure the voltage again from J2201 pin 40 with respect to J2202 pin 42. Tilt the Gyro ten degrees nose down with the Tilt Stand by moving the adjustable support bar to the rear slot. Adjust the Pitch Gain adjustment for +2.0 +/- 0.1 VDC. This potentiometer is accessible through the hole labeled PG on the bottom of the KCP 220.

N. Tilt the Gyro ten degrees nose up with the Tilt Stand by moving the adjustable sup-port bar to the forward slot. The voltage should read 2.0 +/- 0.1 VDC.If the meter reading exceeds -2.1 VDC, repeat steps M and reduce the gain by one-half the amount exceeded in step N. If the meter reading is less than -1.9 VDC, repeat step M and increase the gain by one-half the amount short in step N. Repeat steps M and N until both pitch up and down are within tolerance. The prop-er total voltage excursion must be 4 +/- 0.2 VDC.

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2.4.2 IN-FLIGHT ADJUSTMENTS

NOTES:The airplane must be trimmed for straight and level flight with centered ball in the Pitch, Roll, and Yawaxis before the autopilot is engaged and any in-flightadjustments are attempted.

The mode controller should be removed and recon-nected to the airplane with an extender cable tomake the adjustments accessible in-flight.

A. Roll AdjustmentAt a safe altitude and with the airplane trimmed for straight and level flight in smooth air, engage the autopilot. The autopilot should hold the airplane at the pitch angle present when engaged and at a zero roll attitude as indicated on the roll at-titude display. If the airplane does not maintain zero roll attitude, an adjustment of the Roll Null adjustment is required. This potentiometer is accessible through the hole labeled RN located on the side of the mode controller. Adjust this as neces-sary for a zero roll indication. Adjustments should be made slowly to avoid over-compensation.

B. Lateral Acceleration (Yaw) Adjustment

NOTETHE SOCATA TBM 700 & CESSNA CITATION 500DOES NOT USE LATERAL ACCELERATION.THIS ADJUSTMENT IS NOT REQUIRED FORTHOSE AIRCRAFT

With the airplane in the same flight conditions as listed in step A., engage the Head-ing and Altitude Hold modes. The turn coordinator ball should be centered; if it is not then a lateral acceleration adjustment is needed. This potentiometer is acces-sible through the hole labeled ACCEL on the side of the mode controller. Adjust this in small increments and let it settle for 10 sec. or so between adjustments for a cen-tered ball.

C. Command Bar AdjustmentsIn-flight adjustments of the command bars are necessary if, when flying straight and level in Altitude Hold and Heading modes, the command bars are not zeroed in each axis. The pitch and roll command bar potentiometers are accessible through the holes labeled PC and RC respectively on the side of the mode control-ler. Adjust these for zero visual command.

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2.4.3 SLIP-CLUTCH ADJUSTMENT

2.4.3.1 KSM 375 Clutch Adjustment

A. Capstan torque settings are adjustable, and must periodically adjusted. The fixture and tools required to perform these adjustments are indicated in 1.6 ACCESSO-RIES REQUIRED, BUT NOT SUPPLIED paragraph N-Q.

B. Check the STC manual to determine the servo mount part number and setting re-quired for each axis of the aircraft.

C. Remove the six screws and the dust cover from the servo capstan. Lift the slip clutch assembly of the capstan pulley. (Refer to FIGURE 2-19 KSM 375 & 376 CLUTCH ADJUSTMENT DRAWING view A).

D. Mount the slip clutch in the clutch plate PN 071-06011-0000 and clamp the clutch plate in a bench vise. (Refer to FIGURE 2-19 KSM 375 & 376 CLUTCH ADJUST-MENT DRAWING view B).

E. Remove the cotter key from the slip clutch adjust nut. Insert the spline adapter PN 071-06010-0000 into the slip clutch spline. (Refer to FIGURE 2-19 KSM 375 & 376 CLUTCH ADJUSTMENT DRAWING view C).

F. Using a torque wrench (Snap on tools TEP-6FUA or equivalent), check the clutch setting by rotating the torque wrench and reading the torque required to slip the clutch in both clockwise and counterclockwise directions.

NOTEThe torque reading is the maximum torque read on the wrench at breakout. This test should be repeated three times in each direction and then the average of the six readings used to determine the true torque

readings.

G. If the level measured falls below the desired value, rotate the clutch adjust nut clock-wise (30 degrees of nut rotation is approximately 2.5 in-lbs. on the -0000 clutch as-semblies and 8 in-lbs. on the -0001 clutch assemblies).

H. If the level measured falls about the desired value rotate the clutch adjust nut coun-terclockwise. After the nut is adjusted repeat the torque test until the proper value is reached.

I. Install the cotter key as shown in view D of FIGURE 2-19 KSM 375 & 376 CLUTCH ADJUSTMENT DRAWING.

J. Record the slip clutch torque reading, aircraft type, and date on the decal affixed to the slip clutch body.

K. Install clutch assembly in capstan and secure the dust cover with the six screws.

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2.4.3.2 KM 275 Cable Capstan Clutch Adjustment

Refer to FIGURE 2-20 KM 275 & 277 CLUTCH ADJUSTMENT DRAWING sheet 2.

2.4.3.3 KM 277 Chain Capstan Clutch Adjustment

Refer to FIGURE 2-20 KM 275 & 277 CLUTCH ADJUSTMENT DRAWING Sheet 4 and 5.

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FIGURE 2-19 KSM 375 & 376 CLUTCH ADJUSTMENT DRAWING (Dwg No 155-05151-0000 Rev AB)

B KFC 275/325

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FIGURE 2-20 KM 275 & 277 CLUTCH ADJUSTMENT DRAWING (Dwg No 159-08155-5006 Rev 1, Sheet 1 of 5)

B KFC 275/325

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B KFC 275/325

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FIGURE 2-21 KA 185A INSTALLATION DRAWING (Dwg No 155-05611-0000 Rev 2)

B KFC 275/325

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FIGURE 2-22 KCP 220 OUTLINE AND INSTALLATION DRAWING (Dwg No 155-05609-0000 Rev AB)

B KFC 275/325

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FIGURE 2-23 KMC 221 INSTALLATION DRAWING (Dwg No 155-05612-0000 Rev 3)

B KFC 275/325

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FIGURE 2-24 KDC 222 INSTALLATION DRAWING (Dwg No 155-05606-0000 Rev 4)

B KFC 275/325

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FIGURE 2-25 KS 270A/KS 271A AND KM 275 INSTALLATION DRAWING (Dwg No 155-05161-0000 Rev AC)

B KFC 275/325

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FIGURE 2-26 KS 272A AND KM 276 INSTALLATION DRAWING (Dwg No 155-05183-0000/0001 Rev AB)

B KFC 275/325

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FIGURE 2-27 KAS 297C INSTALLATION DRAWING (Dwg No 155-05551-0000 Rev AA)

B KFC 275/325

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FIGURE 2-28 KAP 315A INSTALLATION DRAWING (Dwg No 155-05608-0000 Rev 2)

B KFC 275/325

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FIGURE 2-29 KMC 321 INSTALLATION DRAWING (Dwg No 155-05607-0000 Rev AA)

B KFC 275/325

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FIGURE 2-30 KTA 336 INSTALLATION DRAWING (Dwg. No. 155-06602-0000 Rev 1)

B KFC 275/325

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FIGURE 2-31 KSA 372 & KSM 375 INSTALLATION DRAWING (Dwg No 155-05086-0000 Rev AB) (For Versions 065-0056-XX except -59 and -81)

B KFC 275/325

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FIGURE 2-32 KSA 372 (-0059 & -0081) & KSM 375 INSTALLATION DRAWING (Dwg No 155-05086-0001 Rev B) (For Version 065-00056-0059 & -0081 only)

B KFC 275/325

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FIGURE 2-33 KSA 37X AND KSM 375-50 INSTALLATION DRAWING (Dwg No 155-05086-0050 Rev 3)

B KFC 275/325

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FIGURE 2-34 KSA 372T AND KSM 375-60 INSTALLATION DRAWING (Dwg No 155-05086-0060 Rev 2)

B KFC 275/325

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FIGURE 2-35 KSA 372X AND KSM 375X INSTALLATION DRAWING (Dwg No 155-05086-0070 Rev AA)

B KFC 275/325

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FIGURE 2-36 KFC 275 INTERCONNECT (Dwg No 159-03047-0002 Rev 3, Sheet 1 of 12)

B KFC 275/325

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B KFC 275/325

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FIGURE 2-36 KFC 275 INTERFCONNECT (Dwg No 159-03047-0002 Rev 3, Sheet 9 of 12)

B KFC 275/325

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FIGURE 2-37 KFC 325 INTERFCONNECT (Dwg No 159-03047-0001 Rev 2, Sheet 9 of 12)

B KFC 275/325

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FIGURE 2-38 KFC 325 AFCS EFIS INTERCONNECT (Dwg No 159-03047-0000 Rev 1, Sheet 1 of 12)

B KFC 275/325

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FIGURE 2-39 KCP 220 ADAPTER (Dwg No 155-05629-0000 Rev 1, Sheet 1 of 1)

B KFC 275/325

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FIGURE 2-40 KCP 220 ADAPTER (Dwg No 155-05629-0001 Rev AA, Sheet 1 of 1)

B KFC 275/325

SECTION IIIOPERATION

3.1 GENERALRefer to STC Installation Manual of the particular aircraft in which the system is installed for Op-erating Procedures or the Flight Manual Supplement of the particular aircraft.

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BENDIX/KING KFC 275/325

TSO APPENDIX

ENVIRONMENTAL QUALIFICATION FORMS

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