KRA-405B RADAR ALTIMETER SYSTEM OPTION ICA …

ICA Supplement.dot (Rev. 6/15/2011) Form 2261

CESSNA AIRCRAFT COMPANY

P.O. Box 7704

WICHITA, KANSAS 67277

KRA-405B RADAR ALTIMETER SYSTEM OPTION ICA SUPPLEMENT

MODEL NO: 510

SUPPLEMENT NO: ICA-510-34-00006

SUPPLEMENT

DATE: 5/21/2010

PREPARED BY: RDN

CHECKED BY: TLE

APPROVED BY: JDH

APPROVED BY: JDL

APPROVED BY: MDD

Cessna Aircraft Company Page i P.O. Box 7704 KRA-405B RADAR ALTIMETER SYSTEM OPTION ICA Supplement Wichita, Kansas 67277 Supplement No.: ICA-510-34–00006 Rev A


REVISIONS

Rev Date By Approved By

- 07/30/2009 RDN See Title Page

ECR 063490

Section Description KRA-405B RADAR ALTIMETER OPTION

All Initial Release

Cessna Aircraft Company Page ii P.O. Box 7704 KRA-405B RADAR ALTIMETER SYSTEM OPTION ICA Supplement Wichita, Kansas 67277 Supplement No.: ICA-510-34–00006 Rev A


Rev Date By Approved By

A 2/3/2011 MAW

ECR 063490

Section Description (Rev A) (ECR 063490) 1.1.3 Removed from NOTE: “AND INCORPORATED INTO THE OPERATOR’S

SCHEDULED MAINTENANCE PROGRAM” Table 1 3.3.1 3.3.2 3.3.3

Was: “TBD” Is: “000381”

3.3.3 Was: “…P/N 010-00435-XX), where (XX) at a minimum must contain the -20 software load.” Is: “…P/N 010-00435-21) or latest version with a dash number greater than -21” Was: “010-00435-XX” Is: “010-00435-21”

3.4 Table 2: Was: 9023108, 9011600, 9008104, 9003101 Is: Figure 8 Figure 9, Figure 10, Figure 11, Figure 12, Figure 13

3.4.1 Was: “9016502” Is: “Figure 14” Was: “REFER TO 9008512 FOR WIRE…” Is: “REFER TO FIGURE 15, FIGURE 16, AND FIGURE 17 FOR WIRE…”

3.4.2 Was: “Refer to 7018105 and 9054503 for Wire…” Is: “Refer to Figure 18 and Figure 19 for Wire…” Was: “7018105 IS THE STANDARD…” Is: “FIGURE 18 IS THE STANDARD…” Was: “REFER TO 9008104 FOR WIRE...” Is: “REFER TO FIGURE 10, FIGURE 11, AND FIGURE 12 FOR WIRE…”

3.4.3 Was: “9016506” Is: “Figure 20” 4 Was: “IF APPLICABLE, MAKE SURE THAT THE…”

Is: “MAKE SURE THAT THE…” 4.1.1 Was: “Chapter 34(Navigation), 34-60-00 Maintenance Practices, Section

3…” Is: “…Chapter 34 (Navigation), 34-60-00 Maintenance Practices, under the section titled GDU 1040A PFD Removal/Installation…”

4.1.2 Was: “Chapter 34(Navigation), 34-60-00 Maintenance Practices, Section 3…” Is: “…Chapter 34 (Navigation), 34-60-00 Maintenance Practices, under the section titled GDU 1500 MFD Removal/Installation…”

4.3 Was: “Chapter 34(Navigation), 34-60-00 Maintenance Practices, Section 3…”

Cessna Aircraft Company Page iii P.O. Box 7704 KRA-405B RADAR ALTIMETER SYSTEM OPTION ICA Supplement Wichita, Kansas 67277 Supplement No.: ICA-510-34–00006 Rev A


Is: “…Chapter 34 (Navigation), 34-60-00 Maintenance Practices, under the section titled GIA-63W Integrated Avionics Unit Removal/Installation …”

4.5 1)c) Added Step C to Removal Section 2)b) Was: “…secure with four (4) fasteners.” Is: “…verify that the arrows on the antenna point inboard and the spacers angle the antennas inboard.” 2)c) Was: “Verify bond per CSAM030, Type I.” Is: “Verify that the electrical bond is Type 1. Refer to the Model 510 Maintenance Manual 20-30-30 Maintenance Practices.” 2)d) Was: “Fillet Seal per CSNP035, Type I, Class B.” Is: “Apply a Fillet Seal to the antenna base and the BNC connector with Type 1, Class B sealant. Refer to the Model 510 Maintenance Manual, 20-40-20 Maintenance Practices.”

5 Was: “…P/N 010-00435-XX, WHERE XX SIGNIFIES A MINIMUM THAT A -20 SOFTWARE LOAD MUST BE INSTALLED.” Is: “…P/N 010-00435-21 OR LATEST VERSION WITH A DASH NUMBER GREATER THAN -21”

5.1 Was: “…P/N 600-08292-XXXX.” Is: “…P/N600-08292-0007 or Service Memo with a dash number greater than 0007. Added: “Testing of the system will also require the use of any commercially available one (1) foot square or larger microwave absorber such as Eccosorb® FS Foam”

6.5.7 Was: “…KRA-405B antenna with a one (1)…” Is: “…KRA-405B antenna, copilot side antenna, with a one (1)…”

6.8.3 Was: “…move the Aircraft outdoors and away from any…” Is: “…move the Aircraft away from any…

7.1.2 Was: “The RAD ALT system has no mandatory replacement time, inspection interval, or structural inspection procedures, and has no impact on Cessna Aircraft Company Model 510 Maintenance Manual, Capter 4 Airworthiness Limitations for Citations.” Is: “There are no new or additional airworthiness limitations associated with this equipment and or installation.”

Attachments Removed Cessna Proprietary Data from Drawings. Added Figures 11, 12, 14-20

Cessna Aircraft Company Page iv P.O. Box 7704 KRA-405B RADAR ALTIMETER SYSTEM OPTION ICA Supplement Wichita, Kansas 67277 Supplement No.: ICA-510-34–00006 Rev A


CONTENTS

Section / Title Page

REVISIONS .................................................................................................................................................... i CONTENTS ................................................................................................................................................. iv TABLES ....................................................................................................................................................... vi FIGURES ..................................................................................................................................................... vi 1. INTRODUCTION HEADING ..................................................................................................................... 1

1.1. Purpose .................................................................................................................................................. 1 2. APPLICABILITY ....................................................................................................................................... 2

2.1. Effectivity ................................................................................................................................................ 2 2.2. Complete ICA Documents ..................................................................................................................... 2 3. DESCRIPTION AND OPERATION .......................................................................................................... 3

3.1. Description ............................................................................................................................................. 3 3.2. Operation ............................................................................................................................................... 3 3.3. System Component(s) ........................................................................................................................... 3

3.3.1. KRA-405B Bendix King Radar Altimeter ................................................................... 3

3.3.2. S67-2002-4 Sensor Systems Antenna ..................................................................... 4

3.3.3. G1000 Mustang Software ......................................................................................... 4

3.3.4. Garmin GDU 1040A (PFD) ....................................................................................... 4

3.3.5. Garmin GIA 63W ....................................................................................................... 4

3.3.6. Garmin GDU 1500 (MFD in Reversionary Mode) ..................................................... 5

3.4. Aircraft Wiring ......................................................................................................................................... 5 3.4.1. Wire Routing - Nose .................................................................................................. 5

3.4.2. Wire Routing - Cabin ................................................................................................. 6

3.4.3. Wire Routing - Fairing ............................................................................................... 6

4. REMOVAL AND INSTALLATION ............................................................................................................ 6

4.1. GDU 1040A/1500 (P/N 011-00916-00, P/N 011-01108-00) .................................................................. 6 4.1.1. GDU1040A PFD REMOVAL/RE-INSTALLATION: ................................................... 7

4.1.2. GDU 1500 MFD REMOVAL/RE-INSTALLATION: .................................................... 7

Cessna Aircraft Company Page v P.O. Box 7704 KRA-405B RADAR ALTIMETER SYSTEM OPTION ICA Supplement Wichita, Kansas 67277 Supplement No.: ICA-510-34–00006 Rev A


4.2. G1000 System Software/Configuration Files: ........................................................................................ 7 4.3. GIA 63W REMOVAL/RE-INSTALLATION: ............................................................................................ 7 4.4. Bendix King Radar Altimeter (KRA-405B) Removal/Installation . .......................................................... 7 4.5. Sensor Systems Antenna (S67-2002-4) Removal/Installation . ............................................................ 8 5. MAINTENANCE AND SPECIAL TOOLS ............................................................................................... 10

5.1. Maintenance ......................................................................................................................................... 10 5.2. System Wiring ...................................................................................................................................... 10 6. TESTING, RETURN TO SERVICE AND TROUBLESHOOTING .......................................................... 10

6.1. Testing Setup – RAD ALT .................................................................................................................... 11 6.2. System Calibration ............................................................................................................................... 11 6.3. RAD ALT Normal ON GND Operation ................................................................................................. 12 6.4. RAD ALT Circuit Breaker Operational Test ......................................................................................... 13 6.5. RAD ALT Antenna Operational Test .................................................................................................... 13 6.6. Reconfigure Aircraft ............................................................................................................................. 15 6.7. Return To Service ................................................................................................................................ 15 6.8. Troubleshooting ................................................................................................................................... 15 7. AIRWORTHINESS LIMITATIONS ......................................................................................................... 16

7.1. Limitations and Replacement Intervals ................................................................................................ 16 ATTACHMENT 1 WIRING DIAGRAMS ..................................................................................................... 17

Cessna Aircraft Company Page vi P.O. Box 7704 KRA-405B RADAR ALTIMETER SYSTEM OPTION ICA Supplement Wichita, Kansas 67277 Supplement No.: ICA-510-34–00006 Rev A


TABLES

Table / Title Page

Table 1 Installation ICA Effectivity ................................................................................................ 2 Table 2 Wiring Diagram Manual Updates, Summary .................................................................... 5

FIGURES

Figure / Title Page

Figure 1: Bendix King Radar Altimeter (KRA-405B) Location ........................................ 9 Figure 2: Sensor Systems (S67-2002-4) Antenna Location ........................................... 9 Figure 3: KRA-405B Calibration Switch ........................................................................ 12 Figure 4: RAD ALT Normal On Ground Indication ........................................................ 12 Figure 5: RAD ALT Failure Indication ........................................................................... 13 Figure 6: RA TEST Softkey .......................................................................................... 13 Figure 7: RAD ALT Test Indication ............................................................................... 14 Figure 8: RADIO ALTIMETER CONFIGURATION ....................................................... 17 Figure 9: RADALT WIRE ASSEMBLY .......................................................................... 18 Figure 10: Traffic Trunk (Cabin A) .................................................................................. 19 Figure 11: Traffic Trunk (Cabin B) .................................................................................. 20 Figure 12: Traffic Trunk (Cabin C) .................................................................................. 21 Figure 13: Traffic Options Coaxial Cable ........................................................................ 22 Figure 14: RADALT Wire Coax Routing (Nose) ............................................................. 23 Figure 15: TCAS II Wire Coax Routing (Nose) ............................................................... 24 Figure 16: TCAS II and RADALT Wire Coax Routing (Nose A) ..................................... 25 Figure 17: TCAS II and RADALT Wire Coax Routing (Nose B) ..................................... 26 Figure 18: Standard Main Wire Route (Cabin) ............................................................... 27 Figure 19: Standard Main Wire and Coax Route (Cabin) ............................................... 28 Figure 20: RADALT Wire Route (Fairing) ....................................................................... 29

Cessna Aircraft Company Page 1 P.O. Box 7704 KRA-405B Radar Altimeter System OPTION ICA Supplement Wichita, Kansas 67277 Supplement No.: ICA-510-34–00006 Rev A


1. INTRODUCTION HEADING 1.1. PURPOSE

1.1.1. The purpose of this, Instructions for Continued Airworthiness Supplement, is to

provide the maintenance technician with the information necessary to ensure the

correct functionality and performance of the KRA-405B Radar Altimeter Option

system on the Cessna Model 510.

1.1.2. This supplemental document is designed to satisfy the required 14 CFR 23.1529

“Instructions for Continued Airworthiness” requirements associated with this

installation. This document is a supplement to the Model 510 Maintenance

Manual and may or may not be incorporated.

1.1.3. If this information is incorporated into the Model 510 Maintenance Manual, the

maintenance manual shall take precedence over this supplemental document.

Refer to the application ATA chapter and section of the respective Maintenance

Manual for the status of all ICA Supplements applicable to your model.

NOTE: This document must be placed with the aircraft operator’s Technical Library CD-

ROM or Maintenance Manual and incorporated into the operator’s scheduled

maintenance program.



2. APPLICABILITY 2.1. Effectivity

This Instructions for Continued Airworthiness (ICA) supplement is effective for the following

airplane model(s) and serialization where this KRA-405B Radar Altimeter System Option is

installed:

Table 1 Installation ICA Effectivity

2.2. Complete ICA Documents

2.2.1. The following document(s), in conjunction with this supplement, constitute the

Instructions for Continued Airworthiness for the KRA-405B Radar Altimeter Option

system. All items must be available to the operator at initial delivery.

• Model 510 Wiring Diagram Manual

• Model 510 Maintenance Manual

• 190-00494-03 Rev A or Later Garmin G1000 Pilot’s Guide for the Cessna

Citation Mustang.

• 190-00600-03 Rev A or Later Garmin G1000 Cessna Mustang Cockpit

Reference Guide.

• Avionics Wiring Diagrams as defined in Attachment 1, where 510-TBD is the

serial effectivity of the airplane.

Model Beginning Effectivity

Ending Effectivity

510 000381 and On

Cessna Aircraft Company Page 3 P.O. Box 7704 KRA-405B RADAR ALTIMETER SYSTEM OPTION ICA Supplement Wichita, Kansas 67277 Supplement No.: ICA-510-34–00006 Rev A


3. DESCRIPTION AND OPERATION 3.1. Description

ECR 063490, “RADAR ALTIMETER CERT - MODEL 510”, defines the requirements for

the installation of the RADAR ALTIMETER (RAD ALT) option. The KRA-405B Radar

Altimeter functions as an accurate source for altitude information during the approach

and landing phases of a flight. The RAD ALT provides this information by generating a

4.3 GHz RF signal from its transmitting antenna mounted on the bottom of the airplane.

The generated signal reflects off of the ground/water and the reflected signal is received

by a receive antenna mounted near the transmit antenna. The time delay is used to

calculate the distance the airplane is from the ground/water. This info is sent to the

G1000 system via an ARINC 429 bus to GIA 1 and GIA 2, and TCAS II (if installed).

This info is then presented to the pilot on both Primary Flight Displays. In addition to the

above, when the G1000 system, using the altitude information from the KRA-405B,

determines that the airplane is approaching the ground/water, the altitude strip on both

PFDs will be covered over with a brown background texture similar to the attitude

background texture to inform the pilot that ground/water is approaching (Radio Altitude

Ground Line).

3.2. Operation

RAD ALT is activated from the Primary Flight Display (PFD) using the softkey located

along the bottom edge of the Display. Pressing the softkeys turns the related function on

or off.

3.3. System Component(s)

3.3.1. KRA-405B Bendix King Radar Altimeter

Bendix King supplied KRA-405B Radar Altimeter (P/N 066-01153-0202), (RAD

ALT), is an electronic transmitter/receiver used to determine the altitude above

ground level (AGL). This Radar Altimeter is provided as Optional Equipment at

S/N 510-000381and On for the Model 510 airplane.



3.3.2. S67-2002-4 Sensor Systems Antenna

Sensor Systems supplied Antennas (P/N S67-2002-4), one transmit antenna and

one receive antenna, which are provided as Optional Equipment at S/N

510-000381 and on for the RAD ALT Option on Model 510 Mustang.

3.3.3. G1000 Mustang Software

Garmin supplied SD card (P/N 010-00435-21) or latest version with a dash

number greater than -21. The 010-00435-21 is provided as standard equipment

at 510-000381 and on.

NOTE:

THE 010-00435-21 SOFTWARE IS THE MINIMUM REQUIRED

SOFTWARE NEEDED TO SUPPORT THE RAD ALT OPTION. WHEN

INSTALLING THE RAD ALT OPTION ALWAYS USE THE LATEST

SOFTWARE AS LONG AS IT IS -21 OR GREATER. THE 010-00435-21

SOFTWARE IS INCLUDED AS LOOSE EQUIPMENT ON THE

AIRPLANE.

3.3.4. Garmin GDU 1040A (PFD)

RAD ALT Data is displayed on PFD1 and PFD2 which consists of a 10.4 inch

LCD display with 1024x768 resolution. Both are configured as a Primary Flight

Display (PFD). Both PFD’s link and display all functions of the G1000 System

during flight. The displays communicate throughout the system via a High-Speed

Data Bus (HSDB) connection.

3.3.5. Garmin GIA 63W

RAD ALT Data is taken from the KRA 405B RADAR ALTIMETER, in the form of

ARINC 429 bus and transmitted to the Garmin Integrated Avionics Unit 1 (GIA 1)

and Garmin Integrated Avionics Unit 2 (GIA 2.)



3.3.6. Garmin GDU 1500 (MFD in Reversionary Mode)

RAD ALT Data is displayed on the Multi Function Display (MFD), GDU 1500, in

reversionary mode, which consists of a 15-inch LCD display 1024x768 resolution.

The GDU 1500 is configured as a MFD. The GDU 1500 communicates

throughout the system via a High-Speed Data Bus (HSDB) connection.

3.4. Aircraft Wiring

NOTE:

The Model 510 Wiring Diagram Manual listed in Table 2 below is added in this Instructions

for Continued Airworthiness Supplement. Refer to Attachment 1 for updated wiring

diagrams.

Table 2 Wiring Diagram Manual Updates, Summary

3.4.1. Wire Routing - Nose

Refer to Figure 14 for Wire and Coax routing definition of the RAD ALT System

Option in the Nose.

NOTE:

FIGURE 14 IS FOR THE RAD ALT SYSTEM AS A STANDALONE

OPTION. REFER TO FIGURE 15, FIGURE 16, AND FIGURE 17 FOR

WIRE ROUTING DEFINITION WITH TCAS II AND RAD ALT.

Chapter Description Ref Cessna DWG (REF ECR 63490)

NEW Bendix King KR-405B Radar Altimeter

Figure 8

Figure 9

Figure 10

Figure 11

Figure 12

Figure 13



3.4.2. Wire Routing - Cabin

Refer to Figure 18 and Figure 19 for Wire and Coax routing definition of the RAD

ALT System Option in the cabin.

NOTE: FIGURE 18 IS THE STANDARD MAIN CABIN WIRE ROUTING FOR THE MODEL 510

AIRPLANE. REFER TO FIGURE 10, FIGURE 11, AND FIGURE 12 FOR WIRE SCHEMATIC

DEFINITION.

3.4.3. Wire Routing - Fairing

Refer to Figure 20 for wire routing definition of the RAD ALT System Option in the

fairing.

4. REMOVAL AND INSTALLATION

NOTE:

MAKE SURE THAT THE AIRPLANE IS CONFIGURED FOR

MAINTENANCE AS DEFINED BY THE ASSOCIATED SYSTEM IN THE

MAINTENANCE MANUAL OR IN THIS DOCUMENT, INCLUDING THE

REMOVAL OF ELECTRICAL POWER, AVIONICS POWER,

HYDRAULIC POWER, ETC., PRIOR TO REMOVAL OR INSTALLATION

OF AIRPLANE COMPONENTS.

4.1. GDU 1040A/1500 (P/N 011-00916-00, P/N 011-01108-00)

NOTE:

IF THE PFD/MFD IS REMOVED AND THE SAME ONE REINSTALLED

THEN NO ACTION IS REQUIRED.



4.1.1. GDU1040A PFD REMOVAL/RE-INSTALLATION:

1) Refer to Chapter 34 (Navigation), 34-60-00 Maintenance Practices, under the

section titled GDU 1040A PFD Removal/Installation, or appropriate software

Service Bulletin for parts and instructions on loading system software and

configuration files.

4.1.2. GDU 1500 MFD REMOVAL/RE-INSTALLATION:


section titled GDU 1500 MFD Removal/Installation, or appropriate software

Service Bulletin for parts and instructions on loading system software and

configuration files.

4.2. G1000 System Software/Configuration Files:

1) Anytime the AIRFRAME configuration file is loaded to the G1000 system the

RAD ALT function “unlock” for the PFD(s) and MFD is lost. Refer to Chapter 34

(Navigation), 34-60-00 Maintenance Practices, Section 4 or appropriate software

service Bulletin for parts and instructions on loading system software. Refer to

attachment 1 within this document to unlock RAD ALT functionality.

4.3. GIA 63W REMOVAL/RE-INSTALLATION:


section titled GIA-63W Integrated Avionics Unit Removal/Installation.

4.4. Bendix King Radar Altimeter (KRA-405B) Removal/Installation (located in nose baggage

area, Ref Figure 1).

1) REMOVAL:

a) Detach mating coaxial cables from XMIT (PN1023) and RCVR (PN1024)

TNC connectors on the front of the unit.

b) Detach mating cable (PN803) from Cannon connector on the front of the unit.

c) Loosen fluted retaining screw clamp, located on the front of the mounting

rack, remove triangular keeper from the front lip of the unit, slide unit out of

rack.

2) RE-INSTALLATION:



a) Slide unit into the rack. Hook the triangular keeper over the front lip of the unit

and tighten the fluted retaining screw clamp located on the front of the

mounting rack until secure.

b) Re-attach mating cable (PN803) to Cannon connector on the front of the unit.

c) Re-attach mating coaxial cables to XMIT (PN1023) and RCVR (PN1024)

TNC connectors on the front of the unit.

4.5. Sensor Systems Antenna (S67-2002-4) Removal/Installation (located on removable fairing

panel, Ref Figure 2).

NOTE:

ANTENNA ALIGNMENT IS CRITICAL OF SYSTEM OPERATION. MAKE

SURE ARROWS ON THE TOP OF THE ANTENNA POINT TOWARDS

ONE ANOTHER.

1) REMOVAL:

a) Remove the four (4) fasteners attaching the antenna to the airframe.

b) Detach mating coaxial cable from antenna TNC connector. XMIT (PY1010)

and RCVR (PY1011).

c) Remove the old sealant from the antenna and the mounting surface. Refer to

the Model 510 Maintenance Manual, 20-40-20, Fuel, Weather, Pressure and

High Temp Sealing – Maintenance Practices, Cleaning.

2) RE-INSTALLATION:

a) Re-attach mating coaxial cable to antenna TNC connector. XMIT (PY1010)

and RCVR (PY1011).

b) Align the antenna with the panel mounting holes and verify that the arrows on

the antenna point inboard and the spacers angle the antennas inboard.

Note: The thick part of the spacer is outboard.

c) Verify that the electrical bond is Type I. Refer to the Model 510 Maintenance

Manual 20-30-30 Maintenance Practices.

d) Apply a Fillet Seal to the antenna base and the BNC connector with Type I,

Class B sealant. Refer to the Model 510 Maintenance Manual, 20-40-20

Maintenance Practices.



Figure 1: Bendix King Radar Altimeter (KRA-405B) Location

Figure 2: Sensor Systems (S67-2002-4) Antenna Location



5. MAINTENANCE AND SPECIAL TOOLS

NOTE:

THE G1000 MODEL 510 SOFTWARE LOADER CARD IS REQUIRED

WHEN LOADING SYSTEM SOFTWARE. G1000 MODEL 510

SOFTWARE LOADER CARD P/N 010-00435-21 OR LATEST VERSION

WITH A DASH NUMBER GREATER THAN -21.

5.1. Maintenance

The KRA-405B Radar Altimeter System has been designed for “on-condition”

maintenance. For details relating to “on-condition” maintenance, refer to Honeywell

Service Memo SM #292. P/N 600-08292-0007 or Service Memo with a dash number

greater than 0007.

Testing of the system will also require the use of any commercially available one (1) foot

square or larger microwave absorber such as Eccosorb ® FS Foam.

5.2. System Wiring

Refer to the Wiring Diagram Manual, Chapter 20, Standard Practices, for wiring

maintenance requirements and practices. Refer to Attachment 1 for wiring diagram

definitions.

6. TESTING, RETURN TO SERVICE AND TROUBLESHOOTING

NOTE:

PERFORM A FULL VISUAL INSPECTION, BEFORE BEGINNING ANY

TESTING PROCEDURES. ENSURE THAT CONNECTORS ARE

PROPERLY INSTALLED, ALL CABLES ARE PROPERLY ROUTED AND

TIED DOWN, ALL ROUTED CABLES DO NOT INTERFERE WITH ANY

FLIGHT CONTROLS OR OTHER EQUIPMENT, AND NO

CONNECTORS ARE STRAINED DUE TO THE WAY THE CABLES ARE

ROUTED AND ANCHORED.



6.1. TESTING SETUP – RAD ALT

6.1.1. Before connecting external power source to aircraft, verify that the system power

is off by placing the BATT switch to OFF and AVIONICS master switch to OFF.

6.1.2. Adjust Ground Power Unit (GPU) for +28.5 ± 0.5 VDC and connect to airplane.

6.1.3. Verify or engage all LH and RH power J-box and LH and RH CB panel CBs.

6.1.4. Place BATT switch to BATT and AVIONICS master switch to AVN PWR.

6.2. System Calibration

6.2.1. The following conditions must be met before calibration:

1) The calibration must be accomplished outside of the hanger with no obstacles

surrounding or underneath the aircraft. Extraneous reflections may cause an

incorrect calibration.

2) Allow a minimum of three minutes of warm-up time before initiating the

calibration.

6.2.2. Press the recessed switch (SW 1) on the front of the KRA-405B (see Figure 3:

KRA-405B Calibration Switch). When the calibration is in process, the KRA-

405B will output an altitude of 500 feet. The switch may be released as soon as

the indicator on the PFD’s display 500 feet. If the PFD’s don’t display 500 feet,

the switch has not been pressed for enough time.

NOTE:

THIS SWITCH IS INTENTIONALLY DIFFICULT TO PRESS. IT MUST

BE PRESSED THROUGH A HOLE IN THE FRONT PANEL WITH A

TOOL NO GREATER THAT 0.12 INCHES IN DIAMETER FOR AT

LEAST 0.2 INCHES. HOLD THE SWITCH UNTIL THE KRA-405B

INDICATOR ON THE PFD’S DISPLAY 500 FEET TO ENSURE THAT

THE KRA-405B ACCEPTS THE SWITCH PRESS.



6.2.3. A calibration in an excessively noisy environment will not be accepted by the

KRA-405B. A post calibration altitude of thirty (30) to one hundred (100) feet

indicates a failed calibration. If this condition occurs, the calibration must be

completed in a different location.

Figure 3: KRA-405B Calibration Switch

6.3. RAD ALT Normal ON GND Operation

6.3.1. For normal ON GND operation the RAD ALT display will appear as shown in

Figure 4 below.

Figure 4: RAD ALT Normal On Ground Indication



6.4. RAD ALT Circuit Breaker Operational Test

6.4.1. Pull the RAD ALT Circuit Breaker (CB), (HC037) in the LH CB panel.

6.4.2. Verify that the RA FAIL annunciation appears above the HSI on both PFD’s as

shown in Figure 5.

Figure 5: RAD ALT Failure Indication

6.4.3. Return the system to normal operation by pushing the RAD ALT CB (HC037) in

the LH CB panel.

6.4.4. Verify that the RA FAIL message is replaced by the 0 (+5, -0 tolerance) message

as shown in Figure 4.

6.5. RAD ALT Antenna Operational Test

6.5.1. Go to the MFD AUX – SYSTEM STATUS page. Press the RA TEST softkey as

shown in Figure 6. Verify a 50 ± 5 is shown in the radio altimeter display above

the HSI as shown in Figure 7.

Figure 6: RA TEST Softkey



6.5.2. Pull the NAV/IAU 1 primary and secondary circuit breakers. Verify 50 ± 5 remains

in the radio altimeter display above the HSI.

6.5.3. Close the NAV/IAU 1 primary and secondary circuit breakers. Pull the NAV/IAU 2

primary and secondary circuit breakers. Verify 50 ± 5 remains in the radio

altimeter display above the HSI.

6.5.4. Close the NAV/IAU 2 primary and secondary circuit breakers. Press the RA TEST

softkey again and verify a 0 (+5, -0 tolerance) is shown in the radio altimeter

display above the HSI.

6.5.5. Rotate the Rotary Test Switch to the RADALT position. Verify a 50 ± 5 is shown

in the radio altimeter display above the HSI as shown in Figure 7.

6.5.6. Rotate the Rotary Test Switch back to the OFF position. Verify a 0 (+5, -0

tolerance) is shown in the radio altimeter display above the HSI.

6.5.7. Cover the receive (port) KRA-405B antenna, copilot side antenna, with a one (1)

foot square or larger piece of microwave absorber. The KRA-405B should unlock

and the RA box above the HSI should disappear.

Figure 7: RAD ALT Test Indication

NOTE:

IT MAY BE NECESSARY TO REMOVE THE AIRCRAFT FROM THE

HANGER, AWAY FROM OTHER AIRCRAFT AND/OR OTHER

SOURCES OF REFLECTION IN ORDER TO ACHIEVE AN UNLOCK

CONDITION (RA BOX REMOVED FROM PFD) WITH THE

MICROWAVE ABSORBER.



6.5.8. While still covering the antenna, reconfirm that the self-test is operational by

repeating Section 6.5.1

6.5.9. Press the RA TEST softkey again. Verify the RA box above the HSI disappears.

6.5.10. Move the foam completely away from the antennas and verify that the radio

altimeter display reappears and indicates 0 FT (+5, -0 tolerance).

6.6. Reconfigure Aircraft

6.6.1. Place the BATT switch to OFF and AVIONICS master switch to OFF.

6.6.2. Remove external power.

6.7. Return To Service

6.7.1. The KRA-405B Radio Altimeter system shall conform to the requirements

specified herein. Any part of the system that does not conform shall have parts

replaced or adjusted as necessary and re-tested. Adjustment or repair of supplier

equipment is permitted only with specific supplier approval. Completion of the

requirements of Section 6 defines the minimum acceptance criteria for the KRA-

405B Radio Altimeter system.

6.8. TROUBLESHOOTING

6.8.1. If any of the system components fail to pass the tests specified in Section 6 of this

ICA, then further troubleshooting must be performed to find the root cause of the

failure. After the root cause has been determined and repaired, that component

must be retested using the applicable portion of Section 6 as a guide.

6.8.2. The first step in troubleshooting is to verify aircraft wiring. If, after thorough wiring

verification, the problem still exists, then it may be necessary to replace the errant

system component.

6.8.3. KRA 405B System Troubleshooting

1) If the Radio Altimeter Display indicates a value greater than 5 while the Aircraft is

on the ground, repeat Section 6.4. If calibration still fails, it may be necessary to

move the Aircraft away from any source of interference and repeat Section 6.4

again.

2) If the Radio Altimeter Display indicates 100 when the RA TEST is activated, the

systems transmitter/receiver is inoperative and repair is required.



6.8.4. After completion of troubleshooting, verify the RAD ALT functionality per Section

6.5 of the ICA.

7. AIRWORTHINESS LIMITATIONS 7.1. Limitations and Replacement Intervals

7.1.1. Cessna Aircraft Company Model 510 Maintenance Manual, Chapter 4,

Aiworthiness Limitations for Citation airplanes, contains the system and airframe

limitations for the Model 510.

NOTE:

THE AIRWORTHINESS LIMITATIONS SECTION IS FAA-APPROVED

AND SPECIFIES MAINTENANCE REQUIRED UNDER SECTION 43.16

AND 91.403 OF TITLE 14 CODE OF FEDERAL REGULATIONS,

UNLESS AN ALTERNATIVE PROGRAM HAS BEEN FAA APPROVED.

7.1.2. There are no new or additional airworthiness limitations associated with this

equipment and or installation..



ATTACHMENT 1 WIRING DIAGRAMS

Figure 8: RADIO ALTIMETER CONFIGURATION



Figure 9: RADALT WIRE ASSEMBLY



Figure 10: TRAFFIC TRUNK (CABIN A)



Figure 11: TRAFFIC TRUNK (CABIN B)



Figure 12: TRAFFIC TRUNK (CABIN C)



Figure 13: TRAFFIC OPTIONS COAXIAL CABLE



Figure 14: RADALT WIRE COAX ROUTING (NOSE)



Figure 15: TCAS II WIRE COAX ROUTING (NOSE)



Figure 16: TCAS II AND RADALT WIRE COAX ROUTING (NOSE A)



Figure 17: TCAS II AND RADALT WIRE COAX ROUTING (NOSE B)



Figure 18: STANDARD MAIN WIRE ROUTE (CABIN)



Figure 19: STANDARD MAIN WIRE AND COAX ROUTE (CABIN)



Figure 20: RADALT WIRE ROUTE (FAIRING)