Cessna 750 User manual

CESSNA AIRCRAFT COMPANY
AIRCRAFT DIVISION
WICHITA, KANSAS 67277
Magnetometer Relocation
ICA Supplement
MODEL NO: 750
SUPPLEMENT NO: ICA-750-34-00002
SUPPLEMENT DATE: 11/20/2014
© Cessna Aircraft Company
Form 2261 Rev 1

CESSNA AIRCRAFTCOMPANY
AIRCRAFT DIVISION
WICHITA, KANSAS 67277
REVISIONS
ICA-750-34-00002 Rev: - Date: 11/20/2014
ICA Summary Pages 1-6
Manuals Affected Description Title
Maintenance Manual 34-15-00 pages
1-3
STANDBY INSTRUMENTS - DESCRIPTION AND
OPERATION
• Updates the location where the magnetometer is installed.
Maintenance Manual 34-15-20 pages
401-403
L-3 COMMUNICATIONS MAG-3000 MAGNETOMETER
- REMOVAL/INSTALLATION
• Updates the location where the magnetometer is installed.
Appendix A: Illustrated Parts
Catalog
NOT USED
Appendix B: Wiring Diagram
Manual
NOT USED
1. Export Compliance
A. This publication contains technical data and is subject to U.S. export regulations. This information has
been exported from the United States in accordance with export administration regulations. Diversion
contrary to U.S. law is prohibited.
ECCN: 9E991
2. Revision Bars
A. Revision bars in this ICA supplement identify new ICAs and/or changes to the current ICAs in the
released maintenance manual.
• New ICAs that are not in the current maintenance manual will have a revision bar from top to
bottom along the left margin.
• ICAs that are in the current maintenance manual and have information added, deleted or revised
will have a revision bar(s) in the left margin adjacent to the added, deleted or revised information.
• New or changed illustrations will have a change bar for the entire length of the page.
3. Page Numbering
A. The page number system for ICA included in this supplement have three-element numbers that are
separated by dashes. The three-element number is found at the bottom right corner of the page, left
of the page number. The date is found below the page number.
B. When the chapter/system element number is followed with zeros in the section/subsystem and
subject/unit element number (28-00-00), the information is applicable to the entire system.
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Nov 20/2014
© Cessna Aircraft Company
ICA-750-34-00002 Form 2261 Rev 1

CESSNA AIRCRAFT COMPANY
AIRCRAFT DIVISION
WICHITA, KANSAS 67277
C. When the section/subsystem element number is followed with zeros in the subject/unit element
number (28-21-00), the information is applicable to the subsystems in the system.
D. The subject/unit element number is used to identify information applicable to units in the subsystems.
The subject/unit element number continues in sequence from the number -01- with the number of
subsystem units in which maintenance information is necessary.
E. All system/subsystem/unit (chapter/section/subject) maintenance data is separated into specified
types of information: Description and Operation, Troubleshooting, Maintenance Practices, etc.
Blocks of page numbers that are in sequence are used to identify the type of information:
(1) Description and Operation or Troubleshooting information may not be included if the procedure
is easy. When subtopics are short, they may be put together into the Maintenance Practices
section. Maintenance Practices can have a mix of subtopics that includes information to service,
remove, install, adjust, test, clean, paint or do approved repairs.
(2) Longer procedures that are not as easy to do may be included in a specified section.
Page 1 through 99 - Description and Operation
Page 101 through 199 - Troubleshooting
Page 201 through 299 - Maintenance Practices
Page 301 through 399 - Servicing
Page 401 through 499 - Removal/Installation
Page 501 through 599 - Adjustment/Test
Page 601 through 699 - Inspection/Check
Page 701 through 799 - Cleaning/Painting
Page 801 through 899 - Approved Repairs
F. A typical page number:
G. Illustrations use the same figure numbers as the page block in which they appear. For example, Figure
202 would be the second figure in a Maintenance Practices section.
4. Supplement Revisions
A. Revisions to this supplement may be accomplished if changes to this supplement are required after
release of the original issue and prior to incorporation into the manuals listed in the REVISIONS table.
B. All revisions to this supplement will have changes identified in detail in the revision block(s) above.
C. All pages in this ICA supplement will have the same date and are valid as of the date shown.
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Nov 20/2014
© Cessna Aircraft Company
ICA-750-34-00002 Form 2261 Rev 1

CESSNA AIRCRAFTCOMPANY
AIRCRAFT DIVISION
WICHITA, KANSAS 67277
5. ICA Incorporation into Applicable Manuals
NOTE: Most ICA supplements will be incorporated in the next available revision to the manuals listed
above and should be used in conjunction with those manuals until the next available revision is
released.
A. The ICA Supplement List located in the Introduction section of each manual listed in the REVISIONS
table will indicate the incorporation status as of the release date of the published revision.
B. The manual revision level of the supplement incorporation will be listed in the "Manual Incorporation
Status" column in the ICA Supplement List, when those ICAs associated with that manual have been
incorporated. After ICAs are incorporated, the manual that they are incorporated in must now be used
for those ICAs instead of the supplement.
• Based on revision cycle times for the affected manuals, MM ICAs, WDM ICAs, etc. in this
supplement may be incorporated in the manuals at different times.
• There will not be a revision to this supplement to indicate incorporation in the manuals. Users are
required to check the ICA Supplement List for each manual affected to determine incorporation
status.
C. This supplement will be completely superseded by the manuals listed in the REVISIONS table when
it has been incorporated in all of the manuals.
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Nov 20/2014
© Cessna Aircraft Company
ICA-750-34-00002 Form 2261 Rev 1

CESSNA AIRCRAFT COMPANY
AIRCRAFT DIVISION
WICHITA, KANSAS 67277
INTRODUCTION
1. Purpose
A. The purpose of this Supplement is to provide the maintenance technician with the information
necessary to ensure the correct functionality and performance of the Magnetometer Relocation on
the Cessna Model 750 until this information gets incorporated into the next revision to the manuals
listed in the "REVISIONS" section of this supplement.
B. This ICA supplement is designed to satisfy the requirements of 14 CFR 25.1529 "Instructions for
Continued Airworthiness" associated with this installation. This document is a supplement to the
Model 750 Maintenance Manual and will be incorporated in the next revision to the manual.
C. When this information is incorporated in the next revision to the manuals listed in the "REVISIONS"
section, those manuals shall take precedence over this supplemental document. Refer to the "ICA
Supplement List" in the "Introduction" section of the respective manual for the status of all applicable
ICA Supplements.
D. Revisions to this supplement may occur if there is a change to any of the ICAs in this supplement
prior to incorporation into all of the affected manuals.
NOTE: This document must be placed with the aircraft operator's Technical Library CD-ROM
or Model 750 Maintenance Manual and incorporated into the operator's scheduled
maintenance program.
2. Effectivity
A. These Instructions for Continued Airworthiness (ICA) are effective for the following aircraft model and
serialization.
Model Beginning Effectivity Ending Effectivity
750 -0501 and On.
3. Complete ICA Documents
A. The following document(s), in conjunction with this supplement, constitute the Instructions for
Continued Airworthiness for the Magnetometer Relocation on the Cessna Model 750. All items must
be available to the operator at initial delivery.
(1) Model 750 (0501 & On) Maintenance Manual
(2) Model 750 (0501 & On) Wire Diagram Manual
4. System Components
A. Refer to Appendix A: Illustrated Parts Catalog
Page 4 of 6
Nov 20/2014
© Cessna Aircraft Company
ICA-750-34-00002 Form 2261 Rev 1

CESSNA AIRCRAFTCOMPANY
AIRCRAFT DIVISION
WICHITA, KANSAS 67277
LIST OF INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
1. Model 750 Maintenance Manual
A. Chapter 34 Navigation
(1) Refer to 34-15-00, Standby Instruments - Description and Operation
(2) Refer to 34-15-20, L-3 Communications MAG-3000 Magnetometer - Removal/Installation
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Nov 20/2014
© Cessna Aircraft Company
ICA-750-34-00002 Form 2261 Rev 1

CESSNA AIRCRAFT COMPANY
AIRCRAFT DIVISION
WICHITA, KANSAS 67277
INSPECTION PROGRAM AND AIRWORTHINESS LIMITATIONS
1. Continuous Inspection Program
A. This ICA Supplement does not affect the current inspection program.
2. Airworthiness Limitations
A. Cessna Aircraft Company Model 750 (0501 & On) Maintenance Manual, Chapter 4, Airworthiness
Limitations, contains the system and airframe limitations for the Model 750.
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.
(1) There are no new (or additional) airworthiness limitations associated with this equipment and/or
installation.
Page 6 of 6
Nov 20/2014
© Cessna Aircraft Company
ICA-750-34-00002 Form 2261 Rev 1

CESSNA AIRCRAFT COMPANY
MODEL 750 (SERIAL -0501 AND ON)
MAINTENANCE MANUAL
STANDBY INSTRUMENTS - DESCRIPTION AND OPERATION
1. General
A. This section gives a description and the operation of the standby instrument system. The line
replaceable units (LRU's) in the standby instrument system are the L-3 Communications GH-3900
Secondary Flight Display (SFD), L-3 Communications GH-3900 Detachable Configuration Module
(DCM), L-3 Communications ADC-4000 Standby Air Data Computer (ADC), L-3 Communications
MAG-3000 Magnetometer, standby pitot probe, standby static port, and standby emergency power
supply.
B. Refer to Figure 1 for a general view of the standby instrument system.
2. Description
A. L-3 Communications GH-3900 Secondary Flight Display (SFD)
(1) The SFD is installed in the instrument panel in the cockpit, above the Garmin GDU 1400W
Multifunction Display (MFD).
(2) The SFD has two controls on its face, a BARO knob and an M button. The M button is used to
select or adjust the SFD Menu functions.
(3) The SFD unit is a stand-alone unit that has inertial sensors that give attitude data on an active
matrix color liquid crystal display (AMLCD) screen. Also, it shows:
• Altitude and airspeed data received from the standby air data computer (ADC) through an
ARINC 429 data bus
• Magnetic heading data received from the MAG-3000 Magnetometer through an RS-422
data bus and the internal inertial sensors
• Navigational data received from the Garmin G5000 avionics system through an RS-422
data bus.
(4) Electrical power to the SFD is supplied by the airplane's electrical system. If the airplane's
electrical power is not available, the standby emergency power supply in the nose compartment
will supply the electrical power.
B. L-3 Communications GH-3900 Detachable Configuration Module (DCM)
(1) The DCM is attached to the wiring harness at the rear of the SFD.
(2) The DCM has sufficient memory to record data that is special to the hardware and software
configurations for each installation, such as panel angle, navigation interface, aircraft heading
calibration, and display format. When the SFD is removed from the airplane, the DCM stays
connected to the airplane wiring harness. When the DCM is connected to a new or different
SFD, it is not necessary to configure the unit.
C. L-3 Communications ADC-4000 Standby Air Data Computer (ADC)
(1) The standby ADC is installed on the right side of the airplane, behind the refreshment center,
at approximately FS 150.00. An electrical connector, pitot hose, and static tube connect to the
bottom of the ADC.
(2) The ADC receives pitot-static pressure from the standby pitot probe and the standby static ports.
It sends this data to the SFD through an ARINC 429 data bus.
D. L-3 Communications MAG-3000 Magnetometer
(1) The magnetometer is installed in the vertical stabilizer under the bullet fairing.
(2) The magnetometer is a three-axis magnetic sensor that converts magnetic field data into a digital
format. This digital data is sent to and shown on the SFD.
E. Standby Pitot Probe
(1) The standby pitot probe is installed on the right side of the airplane, behind the refreshment
center, at FS 150.00 and WL 127.08. A hose connects to the rear side of the pitot probe. The
pitot probe supplies pitot pressure to the standby ADC.
(2) The pitot probe is electrically heated. This prevents the formation of ice on the inlet port.
34-15-00 Page 1
© Cessna Aircraft Company Nov 20/2014
ICA-750-34-00002 Form 2261 Rev 1

CESSNA AIRCRAFT COMPANY
MODEL 750 (SERIAL -0501 AND ON)
MAINTENANCE MANUAL
Standby Instrument System
Figure 1 (Sheet 1)
34-15-00 Page 2
© Cessna Aircraft Company Nov 20/2014
ICA-750-34-00002 Form 2261 Rev 1

CESSNA AIRCRAFT COMPANY
MODEL 750 (SERIAL -0501 AND ON)
MAINTENANCE MANUAL
F. Standby Static Port
(1) There is a left and a right standby static port installed on the airplane. They are installed at FS
117.60 and WL 100.23, below the cockpit floorboard panels. They are attached to the fuselage
skin with rivets and have a tube that connects to the rear side of it. The static ports supply static
pressure to the standby ADC.
(2) The static ports have small holes that are flush with the fuselage skin. Each static port directs
atmospheric pressure from ambient air outside of the airplane through the holes and the tubes
to the standby ADC. The static ports are electrically heated. This prevents the formation of ice
over the static ports.
G. Standby Emergency Power Supply
(1) The standby emergency power supply is installed in the nose compartment, behind the left nose
compartment door. It's installed in a mounting tray at approximately FS 75.20 and WL 111.72. It
supplies emergency electrical power for avionics and lighting during airplane operations.
(2) The power supply is a sealed lead-acid battery that incorporates a charging and fault isolation
system. For more data about the power supply, refer to the manufacturer's component
maintenance manual. Refer to the Introduction - Supplier Publication List.
3. Operation
A. Standby Instrument System
(1) The standby instrument system supplies air data to the standby air data computer (ADC). The
standby ADC supplies this air data to the secondary flight display (SFD).
(2) During flight, ram air pressure goes into the standby pitot probe from the forward movement
of the airplane through the air. The force from the ram air pressure in the standby pitot probe
pushes the air pressure through a hose to the standby ADC. The standby ADC changes this into
a digital signal and sends it through an ARINC 429 data bus to the SFD.
(3) During flight and on the ground, static air pressure goes into the standby static ports from the
atmosphere around the airplane. The static air pressure in the standby static ports is sent
through tubes to the standby ADC. The standby ADC changes the static air pressure into
airspeed and altitude data that shows on the SFD.
(4) The SFD gets magnetic heading data from the magnetometer. The magnetic heading data is
sent over an RS-422 serial data bus.
(5) Push the M button below the display screen on the SFD to show the menus. Push or turn the
BARO knob to select submenus or set values.
(6) The secondary flight display (SFD) and the detachable configuration module (DCM) receive
power through the STBY FLIGHT DISPLAY circuit breaker on the left circuit breaker panel.
The standby ADC receives power through the STBY ADC circuit breaker on the left circuit
breaker panel. The magnetometer receives power through the STBY HDG circuit breaker on the
left circuit breaker panel. The standby pitot probe receives electrical power through the STBY
PITOT HEAT circuit breaker on the right circuit breaker panel. The standby static ports receive
electrical power through the STBY STATIC HEAT circuit breaker on the right circuit breaker
panel. The standby emergency power supply stays charged through the STBY BATT CHARGE
circuit breaker on the left circuit breaker panel.
34-15-00 Page 3
© Cessna Aircraft Company Nov 20/2014
ICA-750-34-00002 Form 2261 Rev 1

CESSNA AIRCRAFT COMPANY
MODEL 750 (SERIAL -0501 AND ON)
MAINTENANCE MANUAL
L-3 COMMUNICATIONS MAG-3000 MAGNETOMETER - REMOVAL/INSTALLATION
1. General
A. This section gives the removal and installation procedures for the L-3 Communications MAG-3000
Magnetometer (UV007). For a general description of the magnetometer, refer to Standby Instruments
-Descriptio
n and Operation .
2. Tools and Equipment
NOTE: For the tool, equipment, and special consumable part numbers and the manufacturer data, refer
to Navigation - General. For the supplier publication part number and manufacturer data, refer
to the Introduction - Supplier Publication List.
A. Tools and Equipment
• None.
B. Special Consumables
• None.
C. Reference Material
• Chapter 6, Access Plates and Panels Identification - Description and Operation
• Chapter 20, Electrical Bonding - Maintenance Practices
• Chapter 24, External Electrical Power - Maintenance Practices
•L-3Commu
nications MAG-3000 Magnetometer - Adjustment/Test.
• Chapter 55, Bullet Faring - Removal/Installation
3. Setup
A. Prepare the Airplane for the L-3 Communications MAG-3000 Magnetometer Removal.
(1) Remove the electrical power from the airplane. Refer to Chapter 24, External Electrical Power
- Maintenance Practices.
(2) Disengage the circuit breaker given in Table 401.
Table 401. Circuit Breakers
Circuit Breaker Name Circuit Breaker Location
STBY HDG Left Circuit Breaker Panel
(3) Remove vertical stabilizer panel 342BC to get access to the magnetometer (UV007). Refer to
Chapter 6, Access Plates and Panels Identification - Description and Operation and Chapter 55,
Bullet Faring - Removal/Installation.
4. L-3 Communications MAG-3000 Magnetometer Removal
A. Remove the Magnetometer (Refer to Figure 401).
(1) Disconnect the electrical connector (P1) from the electrical connector (JV303).
(2) Remove the screws and the washers that attach the magnetometer (UV007) to the bracket.
(3) Remove the magnetometer from the airplane.
5. L-3 Communications MAG-3000 Magnetometer Installation
A. Install the Magnetometer (Refer to Figure 401).
(1) Put the magnetometer (UV007) in its position near the bracket.
(2) Connect the electrical connector (P1) to the electrical connector (JV303).
(3)Do the L-3 Communications MAG-3000 Magnetometer Functional Check. Refer to L-3
Communications MAG-3000 Magnetometer - Adjustment/Test.
(4) Put the magnetometer in its position at the bracket.
(a)Make sure that the FORE arrow on the magnetometer points forward.
(b) Install the screws and the washers.
34-15-20 Page 401
© Cessna Aircraft Company Nov 20/2014
ICA-750-34-00002 Form 2261 Rev 1

CESSNA AIRCRAFT COMPANY
MODEL 750 (SERIAL -0501 AND ON)
MAINTENANCE MANUAL
L-3 Communications MAG-3000 Magnetometer Installation
Figure 401 (Sheet 1)
34-15-20 Page 402
© Cessna Aircraft Company Nov 20/2014
ICA-750-34-00002 Form 2261 Rev 1

CESSNA AIRCRAFT COMPANY
MODEL 750 (SERIAL -0501 AND ON)
MAINTENANCE MANUAL
6. L-3 Communications MAG-3000 Magnetometer Post-Maintenance Checks
A. Do the Magnetometer Post-Maintenance Checks
(1) Do an electrical bond check (Type I) between the magnetometer (UV007) and the bracket. Refer
to Chapter 20, Electrical Bonding - Maintenance Practices.
7. Closeout
A. Put the Airplane Back to its Initial Condition.
(1) Install vertical stabilizer panel 342BC. Refer to Chapter 6, Access Plates and Panels
Identification - Description and Operation and Chapter 55, Bullet Faring - Removal/Installation.
34-15-20 Page 403
© Cessna Aircraft Company Nov 20/2014
ICA-750-34-00002 Form 2261 Rev 1

CESSNA AIRCRAFT COMPANY
AIRCRAFT DIVISION
WICHITA, KANSAS 67277
SUPPLEMENT NO: ICA-750-34-00002
APPENDIX A: ILLUSTRATED PARTS CATALOG
NOT APPLICABLE
© Cessna Aircraft Company
Form 2261 Rev 1

CESSNA AIRCRAFT COMPANY
AIRCRAFT DIVISION
WICHITA, KANSAS 67277
SUPPLEMENT NO: ICA-750-34-00002
APPENDIX B: WIRING DIAGRAM MANUAL
NOT APPLICABLE
© Cessna Aircraft Company
Form 2261 Rev 1