C550GT ICA v.8 11-09-2020 copy

MAINTENANCE MANUAL SUPPLEMENT 73-20-00-Engine Fuel & Controls
C550GT-AD016-FU24-0213
Engine Fuel & Controls Revision: Initial Issue DATE: 01/01/2020

Maintenance Practices / Removal and Installation

(12) Connect the rod end (28) to the cambox input-lever (33) with the bolt (29), washers and nut (30). Safety
with a cotter pin.

CAUTION: DO NOT MOVE THE POWER LEVER. YOU CAN DAMAGE THE PROPELLER LINKAGE.
(13) Check the Engine Control rigging and do any necessary adjustments. (Link) Chapter 76-00-00

WARNING: MAKE SURE YOU DO A DUPLICATE INSPECTION OF THE ENGINE CONTROLS.

Figure 73.2 Engine Push-Pull Cables

Page 404

MAINTENANCE MANUAL SUPPLEMENT 73-20-00-Engine Fuel & Controls
C550GT-AD016-FU24-0213
Engine Fuel & Controls Revision: Initial Issue DATE: 01/01/2020

Maintenance Practices / Removal and Installation

3. Fuel Condition Lever - Control Cable Removal.
Ref. Dwg. No: AD-550GT-7600-001-000

In the cockpit.
(1) At the engine control quadrant, disconnect the rear end of the control cable (5) from the Fuel Condition

Lever. See Chp. 73 Control Quadrant Removal.
(2) Remove the control cable rear fork-end (25).
(3) Remove the bolts (16), washers (22) and nuts (23) from the cable clamp (6) to release the cable (5) from

the bracket (14).
(4) At the inside of the firewall, at bracket (7), loosen the control cable jam-nut (18). Remove the jam-nut and

washer (21) from the rear end of the control cable.
(5) Remove the screw (19), washer (22) and nut (23), then remove the P-clamp (24) from the bracket (12).

In the engine compartment (See Figure 73.2)
(6) At the Starting Control bellcrank (35), remove the cotter pin and the nut (30), washers and bolt (34) from

the rod end (28).
(7) Remove the two bolts (17), washers (20) and nuts (30) that attach the cable clamp assembly (6, 32) to the

engine control bracket (4).
(8) Carefully withdraw the control cable (5) forward into the engine compartment and clear of the aircraft.

4. Fuel Condition Lever - Control Cable Installation.
Ref. Dwg. No: AD-550GT-7600-001-000
(1) Make sure the jam-nut (18) and washer (21) is installed on the threaded sleeve of the cable (5).
(2) Put the control cable (5) through the firewall bracket (7).
NOTE: Do not tighten the jam-nut in this step.

In the engine compartment. (See Figure 73.2)
(3) Route the cable to the engine control bracket (4).

NOTE: The minimum bend radius is 4.00 in. for a Cablecraft cable. Make sure the cable cannot chafe.
(4) Attach cable (5) to control bracket (4) using the cable clamp assembly (6, 32) and the two bolts (17),

washers (20) and nuts (30).
NOTE: Do not connect the rod end to the Starting Control lever in this step.

In the cockpit.
(5) At the firewall, install the washer (21) and jam-nut (18) on the cable (5).

NOTE: Do not tighten the jam-nut in this step.
(6) Install the fork-end (25) on the cable (5) inner.
(7) Install the cable (5) outer to the bracket (14) using the clamp (6) and the bolts (16), washers (22) and nuts

(23).
(8) At the quadrant, reconnect the rear end of the control cable (5) to the Fuel Condition Lever. (Link) Control

Quadrant, Removal and Installation.
(9) Install the P-clamp (24) on the cable (5) and to bracket (12) with the screw (19), washer (22) and nut (23).
(10) Make sure the cable routing is correct, then tighten the cable jam-nuts on each side of the firewall at

bracket (7).
(11) Move the Fuel Condition Lever through its full range of motion. Make sure the cable moves smoothly

without binding.

Page 405

MAINTENANCE MANUAL SUPPLEMENT 73-20-00-Engine Fuel & Controls
C550GT-AD016-FU24-0213
Engine Fuel & Controls Revision: Initial Issue DATE: 01/01/2020

Maintenance Practices / Removal and Installation

(12) Connect the rod end (28) to the Starting Control lever (35) with the bolt (34), washers and nut (30).
Safety with a cotter pin.

(13) Check the Engine Control rigging and do any necessary adjustments. See Chp. 76 Rigging Procedures

WARNING: MAKE SURE YOU DO A DUPLICATE INSPECTION OF THE ENGINE CONTROLS.

Required by NZ Civil Aviation Rules Part 43, Amendment 11 of the General Maintenance Rules.
See Rule 43.113 - Duplicate Safety Inspection of Control System.

Page 406

MAINTENANCE MANUAL SUPPLEMENT 73-30-00-Engine Fuel and Control
C550GT-AD016-FU24-0213
Engine Fuel and Control Revision: Initial Issue DATE: 01/01/2020

Description and Operation / Indicating

Indicating
Engine Fuel and Control

73-30-00 Engine Fuel and Control - Indicating

Description and Operation

Indicating System.

The MVP-50T is an integrated system that receives all engine operating parameters and transmits this to a
central processor for crew presentation. It includes items such as transducers, receivers, engine data computer
and a display monitor panel. Refer to 77-40-00 Integrated Engine Instrument Systems for detailed information.
(Link)
The C550GT Fuel Indicating System displays Fuel Pressure on the vertical strip gauge of the MVP-50T Engine
Monitor Panel. The system uses data sourced from a pressure transducer on the LH side of the firewall in the
engine compartment. The transducer is connected with a flexible hose to the modified inlet fitting of the Fuel/Oil
Heater.
There is a separate Fuel Pressure Switch on the LH side of the firewall. The output of the pressure switch
connects to the Engine Data Converter (EDC) and signals when fuel pressure is below 2 psi. This illuminates the
FUEL.P Crew Alert System (CAS) on the Engine Monitor Panel.
A transducer in the main fuel line supplies Fuel Flow data. This transducer transmits flow rate signals to the EDC.
The EDC converts the signal to serial data which displays on the F.FLOW Vertical Strip Gauge on the Engine
Monitor Panel.

Page 1

MAINTENANCE MANUAL SUPPLEMENT 73-30-00- Fuel Transducers
C550GT-AD016-FU24-0213
Fuel Transducers Revision: Initial Issue DATE: 01/01/2020

Removal and Installation Maintenance Practices / Removal and Installation
Fuel Transducers

Removal and Installation

1. Fuel Pressure Transducer.

Ref. Ext. Doc: Electronics International Inc. MVP-50T Instructions for Continued Airworthiness (Doc. 06201101,
latest revision).

These instructions provide Maintenance, Removal, Installation, Adjustment and Test information for the C550GT
Fuel Indicating System components.

2. Fuel Flow Transducer Removal.
Ref. Dwg. No: AD-550GT-2820-005-000

WARNING: OBSERVE ALL FIRE AND SAFETY PRECAUTIONS. MAKE SURE ALL PERSONNEL KNOW THE
DANGERS OF FUEL VAPOUR AND LEAKAGE.

CAUTION: CONNECT A GROUND CABLE TO THE AIRCRAFT TO ELIMINATE THE DANGER OF ELECTROSTATIC
DISCHARGE.

(1) Set the master switch to OFF.
(2) Make sure the Fuel Shut-off Valve tee-handle is in the OFF position.

NOTE: Placard the tee-handle. DO NOT OPERATE.
(3) Drain the fuel filter.
(4) Disconnect the transducer electrical loom.

NOTE: Carefully remove the insulation to access the connectors.
(5) If necessary, remove the P-clamps from the rigid lines.
(6) Disconnect the fuel inlet and outlet rigid lines from the transducer fittings.

NOTE: Cap all open fittings during this procedure to prevent contamination.
(7) Remove the transducer.
(8) Remove the fuel inlet and outlet fittings.

Figure 73.3 Fuel Flow Transducer

Page 401

MAINTENANCE MANUAL SUPPLEMENT 73-30-00-Fuel Transducers
C550GT-AD016-FU24-0213
Fuel Transducers Revision: Initial Issue DATE: 01/01/2020

Maintenance Practices / Removal and Installation

3. Fuel Flow Transducer Installation.
Ref. Dwg. No: AD-550GT-2820-005-000
(1) Install the fuel inlet and outlet fittings into the transducer.
See Figure 73.3

(2) Position the transducer on the bracket (1).
(3) Install with bolts (4), washers (6) and nuts (9).
(4) Connect inlet and outlet rigid lines to the transducer fittings.
(5) If removed, install the P-clamps to the rigid lines.
(6) Connect the electrical loom to the transducer.

NOTE: Insulate the connection. Damage will occur if moisture gets into the connectors.
(7) Remove the temporary Tee Handle placard installed during the removal procedure.
(8) Set the Master Switch to ON.
(9) Set the Fuel Shut-off Valve tee-handle to the ON position.
(10) Do a Fuel Distribution System Leak Test. See Chp. 28 Fuel Distribution Leak Test.
(11) Do a Fuel Flow Test. See Chp. 28 Fuel Flow Test.

CAUTION: MAKE SURE YOU DO A FUEL FLOW INDICATING SYSTEM FUNCTION CHECK.
NOTE: Refer to Electronics International Inc. MVP-50T Instructions for Continued Airworthiness Doc.
06201101. These instructions provide information to correctly function check the C550GT Fuel Flow
Indicating System.

Page 402

MAINTENANCE MANUAL SUPPLEMENT 73-30-00- Engine Fuel & Controls- Indicating
C550GT-AD016-FU24-0213
Engine Fuel & Controls- Indicating Revision: Initial Issue DATE: 01/01/2020

Maintenance Practices / Adjustment and Test

Adjustment and Test
Engine Fuel & Controls- Indicating

Adjustment and Test

Fuel Indicating System components.

Refer to the Electronics International Inc. MVP-50T Instructions for Continued Airworthiness Doc. 06201101.
These instructions provide Maintenance, Removal, Installation, Adjustment and Test information for Fuel
Indicating System components. (link) E.I. Inc. MVP-50T ICA)

Refer to the Glass Panel Engine Monitor MVP-50T (for Turboprops and Jets) Installation Instructions (Doc. II
1211061) for information on Troubleshooting and Adjustment and Test.

Page 501

MAINTENANCE MANUAL SUPPLEMENT 74-00-00 - Engine Ignition System
C550GT-AD016-FU24-0213
Chapter 74 Revision: Initial Issue DATE: 01/01/2020

Chapter 74 Engine Ignition System
Engine Ignition System

Chapter 74 Engine Ignition System

MAINTENANCE MANUAL SUPPLEMENT 74-00-00 - Engine Ignition System
C550GT-AD016-FU24-0213
Chapter Contents Revision: Initial Issue DATE: 01/01/2020

Chapter Contents Engine Ignition System
Engine Ignition System

Chapter Contents

Chapter 74 Engine Ignition System

Applicable Section Guide
74-00-00 Engine Ignition System

Description and Operation
> Engine Ignition System

Components Changed By This STC
74-10-00 Ignition Exciter

Description and Operation
> Ignition Exciter Unit

Maintenance Practices
Removal and Installation
> Ignition Exciter Removal
> Ignition Exciter Installation.
Inspection and Check
> Inspection of Ignition Exciters
> Inspection of Ignition Exciter Attaching Parts

74-20-00 Ignition Cables and Igniters
Description and Operation
Maintenance Practices
> Ignition Cables
> Igniters.
> Adjustment and Test.
> Inspection and Check
> Cleaning.
> Approved Repairs

MAINTENANCE MANUAL SUPPLEMENT 74-00-00 - Manual to Use DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Manual to Use
Chapter Guide
MANUAL TO USE
Chapter Guide
Manual to Use N/A FU24- 954 C550GT

Applicable Section Guide 
SECTION / SUB-SECTION

74-00-00 Engine Ignition System
Description and Operation

Ignition System
Troubleshooting

74-10-00 Ignition Exciter 
Description and Operation

Ignition Exciter 
Maintenance Practices
Removal and Installation

Exciter Removal
Exciter Installation

Inspection and Check 
Inspection of Ignition Exciters 
Inspection of Ignition Exciter Attaching Parts.

74-20-00 Ignition Cables and Igniters 
Description and Operation 

Ignition Cables and Igniters
Removal and Installation 

Ignition Cables and Igniters 
Adjustment and Test 

Cables and Igniters
Operational Test of the Ignition System.
Inspection and Check
Cables and Igniters
Cleaning
Igniters
Cables
Approved Repairs
Ignition Cables and Igniters Repairs

MAINTENANCE MANUAL SUPPLEMENT 74-00-00-Engine Ignition System
C550GT-AD016-FU24-0213
Engine Ignition System Revision: Initial Issue DATE: 01/01/2020

Description and Operation / Ignition System

Engine Ignition System
Ignition System

74-00-00 Engine Ignition System

Description and Operation

Engine Ignition System

The ignition system is capable of quick light-ups over a wide temperature range. The system has an ignition
exciter, two individual high-tension cable assemblies, two igniters, an ignition switch and a starter switch. The
system is energized from the aircraft 28 VDC supply and will operate in the 9 to 30 VDC range.

The two-position IGNITION switch located on the Circuit Breaker and Switch Panel CONTROLS THE Ignition
System. With the ignition switch set to ON, the exciter unit will energise when you hold the starter button on the
Fuel Condition Lever.

Figure 74.4 Ignition Components

Page 1

MAINTENANCE MANUAL SUPPLEMENT 74-00-00 - Components Changed Table
C550GT-AD016-FU24-0213
Components Changed Table Revision: Initial Issue DATE: 01/01/2020

Components Changed Table CCBTS / Ignition System
Ignition System

Components Changed By This STC

Drawing Number Item Part Number Description / Location
Engine Ignition System
AD-550GT-2430-001-000 1 10-381550-1 Ignition Exciter
AD-550GT-2430-001-000 5 AD-550GT-2430-001-010 Bracket

Page 2

MAINTENANCE MANUAL SUPPLEMENT 74-10-00-Exciter Unit
C550GT-AD016-FU24-0213
Exciter Unit Revision: Initial Issue DATE: 01/01/2020

Description and Operation / Ignition Exciter

Exciter Unit
Ignition Exciter

74-10-00 Ignition Exciter

Description and Operation

Ignition Exciter Unit

The ignition exciter mounts to a bracket on the bottom LH firewall structural channels. It is a sealed unit
containing electronic components encased in an epoxy resin. The unit only energizes during the engine starting
sequence to initiate combustion.
The exciter transforms the DC input to a pulsed high voltage output through solid-state circuitry, a transformer
and diodes.

When you energize the unit, a capacitor on the high voltage side of the output transformer charges
progressively. When the energy stored is sufficient to ionize a spark gap, the capacitor discharges across the two
spark igniters using a dividing/step-up transformer network.

The system design ensures that if one igniter is open or shorted, the remaining igniter will continue to function.

For safety, the capacitor discharges automatically when:
i. Either or both igniters becoming inoperative.
ii. There is no input voltage.

Figure 74.5 Ignition Exciter Unit
Page 1

MAINTENANCE MANUAL SUPPLEMENT 74-10-00- Ignition Exciter
C550GT-AD016-FU24-0213
Ignition Exciter Revision: Initial Issue DATE: 01/01/2020

Removal and Installation Maintenance Practices / Removal and Installation
Ignition Exciter

Maintenance Practices
Removal and Installation

WARNING: RESIDUAL VOLTAGE IN THE IGNITION EXCITER MAY BE DANGEROUSLY HIGH. MAKE SURE THE
IGNITION IS SWITCHED OFF. ALWAYS DISCONNECT THE COUPLING NUTS AT THE IGNITION
EXCITER END FIRST. ALWAYS USE INSULATED TOOLS TO REMOVE THE CABLE COUPLING NUTS.
DO NOT TOUCH THE OUTPUT CONNECTORS OR COUPLING NUTS WITH BARE HANDS.

1. Ignition Exciter Removal
Ref. Dwg. No: AD-550GT-2430-001-000
(1) Set the Master Switch to OFF.
(2) Remove the lockwire and disconnect the cannon plug.

CAUTION: IN THE NEXT STEP, DO NOT ALLOW THE IGNITION CABLE BRAIDING OR FERRULE TO ROTATE
WHEN YOU REMOVE THE COUPLING NUTS.

(3) Remove the two ignition cable couplings from the output connectors on the ignition exciter.
(4) Remove the four bolts, self-locking nuts and washers that attach the unit to the bracket.
(5) Remove the ignition exciter.

2. Ignition Exciter Installation.
Ref. Dwg. No: AD-550GT-2430-001-000

(1) Position the Ignition Exciter unit on the bracket.
(2) Attach the Ignition Exciter using the four bolts, washers and self-locking nuts.
(3) Connect the power-supply cannon plug and safety it with lockwire.

CAUTION: IN THE NEXT STEP, DO NOT ALLOW ANY LUBRICANT TO COME IN CONTACT WITH THE CENTRAL
CONDUCTORS OF THE EXCITER CONNECTORS. CONTACT WITH THE CONDUCTORS MAY RESULT
IN A HIGH RESISTANCE PATH WHICH COULD GENERATE HEAT AND OXIDATION.

(4) Lightly coat the threads of the ignition exciter connectors with fluorocarbon spray lubricant.
(5) Connect the two ignition cable couplings to the connectors on the ignition exciter.

CAUTION: DO NOT ALLOW THE IGNITION CABLE BRAIDING OR FERRULES TO ROTATE WHEN YOU TIGHTEN
THE COUPLING NUTS.

(6) Tighten the coupling nuts. Torque to finger-tight, then plus 45°. Safety with lockwire.
(7) Connect the two ignition cable coupling nuts to the spark igniters. Tighten the coupling nuts. Torque to

finger-tight, then plus 45°.
(8) Do an Operational Test of the Ignition System.
Ref. Ext. Doc: P&WC Maintenance Manual, Turboprop Gas Turbine Engine, Model PT6A-15AG Manual Part No.
3030442 (latest revision).

NOTE: See Chapter 74-00-00 - Ignition, B. Operational Check - Spark Ignition System.

Page 401

MAINTENANCE MANUAL SUPPLEMENT 74-10-00- Ignition Exciter Unit
C550GT-AD016-FU24-0213
Ignition Exciter Unit Revision: Initial Issue DATE: 01/01/2020

Inspection and Check Maintenance Practices / Inspection and Check
Ignition Exciter Unit

Inspection and Check

1. Inspection of Ignition Exciters
(1) Examine the ignition exciter unit for damage and general condition.
(2) Examine the input and output connectors for damage and the connector threads for corrosion.

2. Inspection of Ignition Exciter Attaching Parts
(1) Visually examine the bolts and nuts for condition of the threads.
(2) Examine the bracket for cracks, distortion and general condition.

Page 601

MAINTENANCE MANUAL SUPPLEMENT 74-20-00-Cables & Igniters - Description
C550GT-AD016-FU24-0213
Cables & Igniters - Description Revision: Initial Issue DATE: 01/01/2020

Cables & Igniters - Description Description and Operation / Cables & Igniters
Cables & Igniters

74-20-00 Ignition Cables and Igniters

Description and Operation

Description and Operation

The two ignition cables conduct the electrical output from the ignition exciter to the engine igniters. Each cable
consists of an electrical lead contained in a flexible metal braiding. The cables have coupling nuts at each end
that thread onto the connector of the ignition exciter and the igniter.
The flexible outer braiding has mount flanges for attachment to the engine fireseals
The two igniters are at the 4 and 9 o'clock positions on the gas generator case next to the fuel manifold. The
igniters are a threaded plug with a central positive electrode enclosed in an annular semi-conducting material.

Page 1

MAINTENANCE MANUAL SUPPLEMENT 74-20-00- Cables and Igniters
C550GT-AD016-FU24-0213
Cables and Igniters Revision: Initial Issue DATE: 01/01/2020

All Sections Maintenance Practices / All Sections
Cables and Igniters

Maintenance Practices

1. Ignition Cables

Refer to P&WC Maintenance Manual, Turboprop Gas Turbine Engine, Model PT6A-15AG Manual Part No. 3030442
(latest revision). 74-20-00 - Ignition Cables and Spark Igniters, 5. Removal/Installation of Ignition Cables. See
Figure 202.

2. Igniters.

Refer to P&WC Maintenance Manual, Turboprop Gas Turbine Engine, Model PT6A-15AG Manual Part No. 3030442
(latest revision). 74-20-00 - Ignition Cables and Spark Igniters, 5. Removal/Installation of Igniters. See Figure
203.

Adjustment and Test.

Refer to P&WC Maintenance Manual, Turboprop Gas Turbine Engine, Model PT6A-15AG Manual Part No. 3030442
(latest revision). 74-20-00 - Ignition Cables and Spark Igniters, 9. Adjustment and Test, A. Ignition Cables.

Inspection and Check

Ignition Cables and Igniters.
Refer to P&WC Maintenance Manual, Turboprop Gas Turbine Engine, Model PT6A-15AG Manual Part No. 3030442
(latest revision). 74-20-00 - Ignition Cables and Spark Igniters, 7. Inspection/Check, A. Ignition Cables, B.
Spark Igniters. See Figure 204
(3) Then do an Operational Test of the Ignition System.

Refer to P&WC Maintenance Manual, Turboprop Gas Turbine Engine, Model PT6A-15AG Manual Part No. 3030442
(latest revision). Chapter 74-00-00 - Ignition, B. Operational Check - Spark Ignition System.

Cleaning.

Refer to P&WC Maintenance Manual, Turboprop Gas Turbine Engine, Model PT6A-15AG Manual Part No. 3030442
(latest revision). 74-20-00 - Ignition Cables and Spark Igniters. 6. Cleaning, A. Igniters, B. Cables.

Approved Repairs

For Cable Braiding Minor and Major Damage repairs, refer to P&WC Maintenance Manual, Turboprop Gas Turbine
Engine, Model PT6A-15AG Manual Part No. 3030442 (latest revision).. 74-20-00 - Ignition Cables and Spark
Igniters, 8. Approved Repairs.

Page 201

MAINTENANCE MANUAL SUPPLEMENT 75-00-00 - Engine Air DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Engine Air
Chapter 75

Title Page

Chapter 75
Engine Air

Chapter 75 Engine Air

MAINTENANCE MANUAL SUPPLEMENT 75-00-00 - Engine Air DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Engine Air
Chapter Content

Chapter Content
Engine Air

Chapter Contents

Chapter 75 Engine Air

Applicable Section Guide
75-30-00 Engine Bleed & Vent Air Systems

Description and Operation
> Turboprop Engine Vent System

Maintenance Practices
Removal and Installation
> Engine Vent Air System Removal
> Engine Vent Air System Installation
Inspection and Check
> Engine Vent Air System - Inspection

MAINTENANCE MANUAL SUPPLEMENT 75-00-00 - Manual to Use DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Manual to Use
Chapter Guide
MANUAL TO USE
Chapter Guide
Manual to Use N/A FU24- 954 C550GT

Applicable Section Guide 
SECTION / SUB-SECTION

75-30-00 Engine Vent Air 
Description and Operation

Turboprop Engine Vent Air System
Troubleshooting
Maintenance Practices
Removal and Installation

Rear Flexible Hose
Exit Tube

Inspection and Check 
External Visual Inspection 
Internal Inspection- Vent tube Removed

MAINTENANCE MANUAL SUPPLEMENT 75-30-00-Engine Vent Air System-Details
C550GT-AD016-FU24-0213
Engine Vent Air System-Details Revision: Initial Issue DATE: 01/01/2020

Engine Vent Air System-Details Description and Operation / Engine Bleed Air Sys.
Engine Bleed Air Sys.

75-30-00 Engine Vent Air System

Description and Operation

Turboprop Engine Vent System

A centrifugal oil separator in the accessory gearbox separates oil from engine vent air to discharge relatively oil
free air to atmosphere.
This air/oil vapour exits the engine through a flexible hose attached to a fitting on the top RH side of the
accessory housing.
The hose is routed forward through the firewall panels and connects to the Exit Tube.
The Exit Tube attaches to the exhaust stub with a steel link and discharges air/oil vapour into the exhaust.

Version 3, an expanded version of this DO is a work in progress, awaiting input from MFP 16/04/2020

Figure 75.6 Engine Vent Air System

Page 1

MAINTENANCE MANUAL SUPPLEMENT 75-30-00- Vent Air System
C550GT-AD016-FU24-0213
Vent Air System Revision: Initial Issue DATE: 01/01/2020

Vent Air System Maintenance Practices / Removal and Installation
Removal and Installation

Maintenance Practices
Removal and Installation

1. Engine Vent Air System Removal
Ref. Dwg. No: AD-550GT-7100-001-000
Rear flexible hose

(1) Remove the rear hose clamp at the engine outlet fitting.
(2) Remove the forward hose clamp at the connection to the exit tube.
(3) Remove the nuts, washers and screws from the firewall seal plate.
(4) Disconnect the hose from the exit tube and the engine fitting. Then carefully extract the hose forward

through the firewall.

Exit Tube Removal

(1) Remove the bolt and nut that attaches the exit tube link to the exhaust stub.
(2) Remove the nuts, washers and screws from the firewall seal plate.
(3) Move the exit tube aft and away from the engine.

2. Engine Vent Air System Installation
Ref. Dwg. No: AD-550GT-7100-001-000
Exit Tube Installation.
(1) Position the exit tube through the fire wall.
(2) Attach the link to the exhaust stub with the bolt and nut.
(3) Attach the firewall seal plate with the nuts, washers and screws.

Rear Flexible Hose Installation
(1) Position the flexible hose and attach it with the hose clamps.
(2) Attach the firewall seal plate with the nuts, washers and screws.

Page 401

MAINTENANCE MANUAL SUPPLEMENT 75-30-00- Engine Vent Air System
C550GT-AD016-FU24-0213
Engine Vent Air System Revision: Initial Issue DATE: 01/01/2020

Engine Vent Air System Maintenance Practices / Inspection & Check
Inspection & Check

Inspection and Check

Engine Vent Air System - Inspection
See Figure 75.6
External Visual Inspection.

(1) Examine the outer braid of the flexible hose for chaff damage.
(2) Look for oil leakage where the flexible hose connects to the exit tube.

NOTE: If oil is visible, remove the flexible hose and do an internal inspection.
(3) Make sure the clamps are secure.
(4) Examine the exit tube support-link, look for cracks and loose bolts.
(5) Examine the firewall seals for wear and correct fit around the hose and exit tube.

Internal Inspection with the Vent Tube Removed.

CAUTION: INSPECT ENGINE VENT SYSTEM PARTS CAREFULLY. A RESTRICTION IN THE ENGINE VENT AIR
SYSTEM WILL AFFECT AIRFLOW INSIDE THE ENGINE.

(1) Use a bright light to examine the inside lining of the flexible tube. Replace the flexible tube if you find
damage or deterioration.

(2) Make sure there are no obstructions in the flexible hose or the exit tube.

Page 1

MAINTENANCE MANUAL SUPPLEMENT 76-00-00 - Engine Controls DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Engine Controls
Chapter 76

Title Page

Chapter 76
Engine Controls

Chapter 76 Engine Controls

MAINTENANCE MANUAL SUPPLEMENT 76-00-00 - Engine Controls DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Engine Controls
Chapter Contents

Chapter Contents
Engine Controls

Chapter Contents

Chapter 76 Engine Controls

Applicable Section Guide
76-00-00 Engine Controls

Description and Operation
> Chapter 76 Topic Overview
76-10-00 Power Control
Description and Operation
> Rigging Procedures
Maintenance Practices
Removal and Installation
> Engine Control Cables.
> Engine Control Quadrant
Adjustment and Test
> Engine Controls Rigging Procedure.
> Rear Linkage Rigging.
> Reverse Pick-up Point Adjustment – (Deadband gap).
> Forward Linkage Rigging
> Fuel Condition Control Rigging
> Propeller Speed Control Rigging
Inspection and Check
> Identifying the Track Point on the Reversing Cam.

MAINTENANCE MANUAL SUPPLEMENT 76-00-00 - Manual to Use DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Manual to Use
Chapter Guide
MANUAL TO USE
Chapter Guide
Manual to Use N/A FU24- 954 C550GT

Applicable Section Guide 
SECTION / SUB-SECTION

76-00-00 Engine Controls
Description and Operation

Chapter Overview
Troubleshooting

76-10-00 Engine Controls 
Description and Operation

C550GT Engine Power Controls

Maintenance Practices

Servicing

Removal and Installation 
Cables and Linkages 
Control Quadrant

Adjustment and Test 
Rigging Procedures - General 
Rear Linkage Rigging 
Reverse Pick-up Point Adjustment 
Forward Linkage Rigging 

Fuel Condition Lever Rigging – Start Flow Control
Propeller Speed Control Rigging

Inspection and Check 
Identifying the Track Point

MAINTENANCE MANUAL SUPPLEMENT 76-00-00-Chapter 76 Overview
C550GT-AD016-FU24-0213
Chapter 76 Overview Revision: Initial Issue DATE: 01/01/2020

Description and Operation / Engine Controls

Chapter 76 Overview
Engine Controls

76-00-00 Engine Controls

Description and Operation

Chapter 76 Topic Overview

This section describes the systems that control the operation of the engine. Specifically, the procedure for rigging
the engine and propeller controls of the P&WC PT6A-15AG turboprop engine installed in the C550GT.

The information in ATA Chapter 76 typically includes the maintenance, removal and installation of mechanical
linkages and controls to the Fuel Control Unit and Propeller Governor.
However, in line with other manuals for similar aircraft, the C550GT MMS has details of these systems in Chapter
73-20-00 (Link to this section) and 61-20-00 (Link to this section.)
See these sections for details of the Engine and Propeller control quadrant and control cables.

For maintenance information on the engine components, Fuel Control Unit and Propeller Governor, refer to
Chapter 73-00-00 Engine Fuel and Control - Description And Operation in the P&WC Maintenance Manual.

Ref. Ext. Doc: P&WC Maintenance Manual, Turboprop Gas Turbine Engine, Model PT6A-15AG Manual Part No.
3030442 (latest revision).

Information on components and control systems that are specifically included in other chapters are not covered
here.

Page 1

MAINTENANCE MANUAL SUPPLEMENT 76-10-00-Engine Power Control System
C550GT-AD016-FU24-0213
Engine Power Control System Revision: Initial Issue DATE: 01/01/2020

Power Control Description and Operation / Power Control
Engine Power Control System
76-10-00 Power Control
Power Control System
Description and Operation

This section shows the C550GT system that controls the Fuel Control Unit, Starting Control and Constant Speed
Unit.

WARNING: THE ENGINE CONTROL SYSTEM IS CRITICAL TO AIRCRAFT SAFETY. THE PROCEDURES FOR
ADJUSTMENT AND SET-UP MAY ONLY BE SPECIFIC TO THIS AIRCRAFT. MAKE SURE YOU OBEY
ALL RIGGING INSTRUCTIONS. IT IS IMPORTANT THAT YOU DO THE PROCEDURE IN THE
CORRECT ORDER.

The rigging procedure is included in the Adjustment and Test section. Use the Applicable Section Guide for
reference.
The Removal and Installation procedures for specific control linkages and cables are detailed in Chapter 73.
See Chp. 73 Engine and Propeller Control Quadrant.

Rigging Procedures

(1) Rear Linkage Rigging.

(2) Reverse Pick-up Point Adjustment.

(3) Forward Linkage Rigging.

(4) Fuel Condition Lever Rigging - Start Flow Control.

(5) Propeller Speed Control Rigging.

CAUTION: DO NOT MOVE THE CONTROL QUADRANT POWER LEVER AFT OF THE FLIGHT IDLE DETENT. YOU
CAN DAMAGE THE PROPELLER CONTROL LINKAGE. FOR MAINTENANCE, FIRST DISCONNECT THE
REVERSING CABLE BEFORE YOU MOVE THE POWER LEVER.

NOTE: There are references to drawing numbers (Ref.Dwg.No.) and to Figures in the rigging procedures.
The drawings are ‘Top Level’ drawings that identify each part location and show the changes made by
this STC. The Figures are there to show specific dimensions or positions and add clarity to the rigging
procedure.

Page 1

MAINTENANCE MANUAL SUPPLEMENT 76-10-00- Engine Power Controls
C550GT-AD016-FU24-0213
Engine Power Controls Revision: Initial Issue DATE: 01/01/2020

Maintenance Practices / Removal and Installation

Engine Power Controls
Removal and Installation

Maintenance Practices
Removal and Installation

Engine Control Cables.

Refer to Chapter 73-20-00 for Removal and Installation. See Chp. 76 Engine Control Cables.

Engine Control Quadrant

Refer to Chapter 73-20-00 for Removal and Installation See Chp. 73 Engine and Propeller Control Quadrant.

Page 1

MAINTENANCE MANUAL SUPPLEMENT 76-10-00- Engine Controls Rigging
C550GT-AD016-FU24-0213
Engine Controls Rigging Revision: Initial Issue DATE: 01/01/2020

Maintenance Practices / Adjustment and Test

Engine Controls Rigging
Adjustment and Test

Adjustment and Test

Engine Controls Rigging Procedure.

(1) Rear Linkage Rigging.

(2) Reverse Pick-up Point Adjustment.

(3) Forward Linkage Rigging.

(4) Fuel Condition Lever Rigging - Start Flow Control.

Propeller Speed Control Rigging.

1. Rear Linkage Rigging.
Ref. Dwg. No: AD-550GT-7600-001-000

Step A. Check the Power Lever control.
See Figure 76.1
(1) Disconnect the power lever cable from the cambox input lever.
(2) Disconnect the engine reversing cable clevis from the reversing cam lever.

In the Cockpit.
(3) Release all Control Quadrant lever friction.
(4) Move the Power Lever through its full range. Make sure the control moves freely with no binding and

unwanted friction.

Figure 76.1 Cambox input and output levers.
Step B. Identify the Track Point. See Chp. 76 Identifying the Track Point on the Reversing Cam.

With the cam follower pin at the track point, make sure the centreline of the input lever is:
(1) 30° to the engine horizontal axis.
(2) 90° to the push-pull cable axis.
See Figure 76.2

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MAINTENANCE MANUAL SUPPLEMENT 76-10-00-Engine Controls Rigging
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Maintenance Practices / Adjustment and Test

Step C. Check the Power Lever’s range of travel.

Move the cockpit power lever through its full forward and reverse range. Make sure the range of movement of
the end of the power lever cable is more than the cambox input lever range.

Figure 76.2 Input Lever position.
Step D. Set the Flight Idle position of the Power Lever.

At the control quadrant.
(1) Position the Power Lever 7/16 in. forward of the FLIGHT IDLE detent.

NOTE: This is the Flight Idle Rigging Position for the C550GT Power Lever.
(2) Apply the control quadrant friction to lock the Power Lever in this position.

In the engine compartment.
(3) Make sure the cam follower pin is at the track point. (See Step B)
(4) Then connect the power lever control rod end to the input lever.

NOTE: You need 2 personnel to complete tasks 5 to 9.
(5) Release the control quadrant friction.
(6) Move the quadrant control Power Lever forward. This moves the cambox input lever into the forward range

of travel.
(7) Then move the quadrant control Power Lever slowly back toward the Flight Idle position.
(8) While you keep light finger-force forward on the reversing cam, measure the aft movement of the cam lever

against your finger as the cockpit Power Lever reaches the Flight Idle Rigging Position.
NOTE: Coordinate the Power Lever movement and position with the person in the cockpit.
(9) Carefully adjust the input cable length at the rod-end to produce 1/32 in. of reversing cam movement at the
track point just as the Power Lever reaches the Flight Idle Rigging position.
(10) Tighten the rod end jam nut.

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MAINTENANCE MANUAL SUPPLEMENT 76-10-00-Engine Controls Rigging
C550GT-AD016-FU24-0213
Engine Controls Rigging Revision: Initial Issue DATE: 01/01/2020

Maintenance Practices / Adjustment and Test

(11) Tighten the nut (30) that secures the Power Lever cable rod-end to the cambox input lever.
(12) Torque the nut to 32 – 36 in.lbs and safety it with a cotter pin.

Step E. Set the FCU control arm position.
See Figure 76.3
(1) Remove the FCU interconnecting rod from the FCU control arm.
(2) Set the control quadrant fuel condition lever to the CUTOFF position.
(3) Move the FCU control arm clockwise until you feel the “pick-up point”
NOTE: 1. You can feel the internal pick-up point as a slight resistance of the scheduling cam against the
speeder spring tension.
(4) Hold this position, then make sure the centre-line of the control arm is approximately 22.5° below the
engine horizontal centreline.
NOTE: 2. To reset the FCU arm position, mark the FCU arm and vernier coupling with a marker pen. Then
loosen the nut on the FCU control arm and adjust the vernier coupling position. There are 24 teeth
on the inner face and 25 on the outer face of the coupling disc.

Figure 76.3 F.C.U. input arm position.
Step F. Reconnect the FCU interconnecting rod.

(1) Connect the upper end of the FCU interconnecting rod to the top hole in the FCU actuating lever.
(2) Move the FCU control arm 1/8 in. away from the pick-up point (counterclockwise) and connect the FCU

interconnecting rod to the outer hole in the FCU control arm.
NOTE: The nominal length of the FCU control rod is 11.15 in.
(3) Adjust both rod-ends equally and connect the rod.

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MAINTENANCE MANUAL SUPPLEMENT 76-10-00-Engine Controls Rigging
C550GT-AD016-FU24-0213
Engine Controls Rigging Revision: Initial Issue DATE: 01/01/2020

Maintenance Practices / Adjustment and Test

Step G. Check the FCU actuating lever and rod clearance.
Move the FCU control arm clockwise until you feel the “pickup point”. Refer step E. (3).
Check that these dimensions are correct:
(1) There should be approximately 0.030 in. clearance between the cam follower pin and the front face of the
track in the FCU actuating lever. See Figure 76.4

(2) There should be 0.060 to 0.100 in. clearance (Dimension X) between the flat on the interconnect rod and the
FCU arm extension. See Figure 76.5
NOTE: If necessary, rotate the interconnect rod until the flat surface is parallel with the FCU arm extension.

(3) To adjust the FCU arm, see NOTE 2 in step E and then repeat steps F through H.

Figure 76.4 F.C.U. lever to rod clearance.

Step H. Check that the operation of the Power Lever and cambox linkages is correct.
(1) Move the Power Lever through its full range.
(2) Make sure that there is no binding and that the FCU lever contacts the MAXIMUM STOP.
(3) Make sure that the cam follower pin does not bottom-out at either end of the reversing cam track.

WARNING: WARNING: DO A DUPLICATE SAFETY INSPECTION OF THE CONTROL SYSTEM.
Required by NZ Civil Aviation Rules Part 43, Amendment 11 of the General Maintenance Rules.
See Rule 43.113 - Duplicate Safety Inspection of Control System.

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MAINTENANCE MANUAL SUPPLEMENT 76-10-00-Engine Controls Rigging
C550GT-AD016-FU24-0213
Engine Controls Rigging Revision: Initial Issue DATE: 01/01/2020

Maintenance Practices / Adjustment and Test

Figure 76.5 Dimension X clearance.

2. Reverse Pick-up Point Adjustment – (Deadband gap).
(1) Set the Power lever at the Flight Idle Rigging Position, the cam follower pin will be at the track point. Refer to
Section 1, Step D.
(2) Check that the end of the adjustment screw is level with the rear face in the radial portion of the reversing
cam track.
See Figure 76.6
(3) If necessary, loosen the jam-nut and adjust the screw until the threaded end is level with the rear face.
Tighten the jam-nut and safety with lockwire.

Figure 76.6 Reverse Pick-up Point

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MAINTENANCE MANUAL SUPPLEMENT 76-10-00-Engine Controls Rigging
C550GT-AD016-FU24-0213
Engine Controls Rigging Revision: Initial Issue DATE: 01/01/2020

Maintenance Practices / Adjustment and Test

3. Forward Linkage Rigging

CAUTION: DO NOT MOVE THE CONTROL QUADRANT POWER LEVER AFT OF THE FLIGHT IDLE DETENT. YOU
CAN DAMAGE THE PROPELLER CONTROL LINKAGE. FOR MAINTENANCE, FIRST DISCONNECT THE
REVERSING CABLE BEFORE YOU MOVE THE POWER LEVER.

Step A. Disconnect the applicable propeller controls.

(1) Disconnect the push-pull wire rope rear clevis from the propeller reversing-cam lever. See Figure 76.7

(2) Disconnect the propeller governor interconnect-rod from
the governor air-bleed link. See Figure 76.8

(3) Disconnect the reversing-control wire rope terminal from
the propeller reversing lever. See Figure 76.8
NOTE: Retain the small bushing and make sure it is in
place when you reconnect the front terminal.

Figure 76.7 Push-Pull cable rear clevis.

Step B. Check the propeller push-pull control cable rigging.

(1) Pull the propeller push-pull cable forward. Make sure that the push-pull control terminal is against the
internal stop of the low pitch stop adjuster.

(2) Check that the collar is visible through the holes in the low pitch stop adjuster.
(3) Check the push-pull cables range of movement. The total range should be 1.10 in. to 1.20 in.

NOTE: Measure the range of movement by pushing the push-pull cable aft against the stop. Put a piece of
masking tape on the push-pull cable, up against the forward edge the low pitch stop adjuster. Pull
the push-pull cable forward to the stop and measure the distance from the forward edge of the low
pitch stop adjuster to the aft edge of the masking tape.

(4) Reconnect the wire rope cable front terminal to the reversing lever. Make sure you install the small bushing
in the lever.

Figure 76.8 Air-Bleed link connection.

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MAINTENANCE MANUAL SUPPLEMENT 76-10-00-Engine Controls Rigging
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Maintenance Practices / Adjustment and Test

Step C. Check and adjust the Beta Valve position. See Figure 76.9

(1) Set the rear end of the slot in the Beta Valve clevis flush with front face of the cap nut. (Detail A).
(2) To adjust the slot FORWARD, turn the low pitch adjuster CLOCKWISE as viewed from the front of the aircraft.

To adjust the slot AFT, turn the low pitch adjuster COUNTERCLOCKWISE.
(3) Torque the low pitch stop adjuster locknut to 150 to 250 in lbs. and safety it with lockwire.

Figure 76.9 Beta Valve position.

Step D. Check and adjust the interconnect rod to the governor air-bleed. See Figure 76.10
NOTE: Section 3, Step A removed the propeller governor interconnect-rod from the governor air-bleed link.

(1) Pull the propeller reversing lever forward.
(2) Hold the fuel governor air-bleed link forward to the MAX stop.
(3) Adjust the interconnect-rod until the attach bolt aligns with the outer hole on the governor air bleed link.
(4) Then shorten the overall length of the interconnect-rod by turning each rod-end 1/2 turn each.
(5) Reconnect the interconnect-rod.
(6) Torque the interconnect-rod locknut to 32 - 36 in.lbs. and safety it with lockwire.

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MAINTENANCE MANUAL SUPPLEMENT 76-10-00-Engine Controls Rigging
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Maintenance Practices / Adjustment and Test

Figure 76.10 Ar-Bleed interconnect rod.

Step E. Adjust and connect the propeller reversing wire rope clevis to the reversing cam lever at the cambox.
See Figure 76.1 and See Figure 76.7
(1) Move the cambox input lever into the forward power range.
(2) Pull the propeller reversing cam lever firmly aft.
(3) While you apply slight forward pressure on the rear terminal to remove the play, adjust the rear clevis until
the bolt hole aligns with the middle hole in the propeller reversing cam.
(4) Lengthen the rear clevis one-half turn and reconnect it with the clevis pin.
NOTE: Do not install the washer and cotter pin.
(5) Check that the clevis pin is free to rotate in the reversing cam and reversing lever. To get this, lengthen the
rear clevis.
NOTE: If the pilot reports that there is a lot of friction in the power lever, the reason may be that the
compression in the rear end of the reversing cable is too high. The rear clevis should be slightly in
compression, but not to the point where the cam follower pin rides hard against the forward face of
the reverse cam slot.
(6) Check the witness hole for correct thread engagement, then install the washer and cotter pin.
(7) Tighten the rear clevis locknut and safety it with lockwire.

Step F. Check the Power Lever control cable and linkage for full and free movement.

(1) Move the cockpit Power Lever from FLIGHT IDLE to MAX POWER.
(2) Check that the control is free to move and without binding.
(3) Check that there is spring-back at the MAX POWER stop.

NOTE: Spring-back should be 1/8 to 1/4 in.

WARNING: DO A DUPLICATE SAFETY INSPECTION OF THE CONTROL SYSTEM.

Required by NZ Civil Aviation Rules Part 43, Amendment 11 of the General Maintenance Rules.
See Rule 43.113 - Duplicate Safety Inspection of Control System.

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MAINTENANCE MANUAL SUPPLEMENT 76-10-00-Engine Controls Rigging
C550GT-AD016-FU24-0213
Engine Controls Rigging Revision: Initial Issue DATE: 01/01/2020

Maintenance Practices / Adjustment and Test

4. Fuel Condition Control Rigging
See Figure 76.11

Step A. At the cockpit Control Quadrant, move the Fuel Condition Lever to the CUTOFF position.

(1) Check for control lever spring back of 1/8 to 1/4 in.

Step B. Move the Fuel Condition Lever to the GROUND-IDLE position.

(1) Make sure the rigging hole on the Starting Control lever aligns with the 45° slot.
(2) If necessary, adjust the cable length to get this alignment.

Step C. Adjust the telescopic rod to a pre-set gap of 0.60 in.

Step D. Move the Fuel Condition Lever to the FLIGHT-IDLE position.

(1) Check for a control spring back of 1/8 to 1/4 in.

Step E. Do an Engine Ground Run to check the FLIGHT-IDLE Ng speed.

(1) The FLIGHT-IDLE speed must be 69% to 71% Ng.
(2) Adjust the FLIGHT-IDLE stop on the Starting Control to set the correct Ng speed.

NOTE: Refer to the P&WC Maintenance Manual, Turboprop Gas Turbine Engine, Model PT6A-15AG Manual
Part No. 3030442 (latest revision). Chapter 71-00-00, Powerplant Adjustment and Test, Section 11-
Fuel Control Unit Checks.

WARNING: DO A DUPLICATE SAFETY INSPECTION OF THE CONTROL SYSTEM.

Required by NZ Civil Aviation Rules Part 43, Amendment 11 of the General Maintenance Rules.
See Rule 43.113 - Duplicate Safety Inspection of Control System.

Figure 76.11 Starting Control.

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MAINTENANCE MANUAL SUPPLEMENT 76-10-00- Propeller Speed Control Rigging
C550GT-AD016-FU24-0213
Propeller Speed Control Rigging Revision: Initial Issue DATE: 01/01/2020

Propeller Speed Control Rigging Maintenance Practices / Adjustment and Test
Adjustment and Test

Propeller Speed Control Rigging

Ref. Dwg. No: AD-550GT-7600-001-000

(1) At the cockpit control quadrant, set the Propeller Control Lever to FEATHER.
(2) At the Propeller Governor, remove the lever return extension-spring. See Figure 76.12
(3) Set the control lever to the FEATHER STOP.
(4) Attach the front control cable with the connecting link.
(5) Use the cable clamp (Detail C) to connect the aft end of the front control cable to the rear Cablecraft cable

terminal (5, 52). Also See Figure 76.13

(6) The Propeller Control Lever on the cockpit control quadrant must have spring-back when you move the lever

to FEATHER.

NOTE: Adjust the cable length in the cable clamp. Use the Cablecraft cable adjustment (Detail H) to get this
spring-back.

(7) Move the cockpit Propeller Control Lever to MAX RPM.

Figure 76.12 Propeller Governor controls.

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MAINTENANCE MANUAL SUPPLEMENT 76-10-00-Propeller Speed Control Rigging
C550GT-AD016-FU24-0213
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Maintenance Practices / Adjustment and Test

(8) Make sure the control lever on the governor is on the MAX. RPM stop and reconnect the lever return
extension-spring (47).
NOTE: The front control cable (54) will have slight slack when the control lever is on the MAX. RPM stop.

(9) If necessary, repeat steps 6 and 7 to make sure the FEATHER STOP spring-back, MAX. RPM stop position and
cable slack are correct.

WARNING: DO A DUPLICATE SAFETY INSPECTION OF THE CONTROL SYSTEM.

Required by NZ Civil Aviation Rules Part 43, Amendment 11 of the General Maintenance Rules.
See Rule 43.113 - Duplicate Safety Inspection of Control System.

Figure 76.13 Cable connection.

Page 511

MAINTENANCE MANUAL SUPPLEMENT 76-10-00- Engine Controls Rigging
C550GT-AD016-FU24-0213
Engine Controls Rigging Revision: Initial Issue DATE: 01/01/2020

Maintenance Practices / Inspection and Check

Identify the Track Point

Engine Controls Rigging
Inspection and Check

Inspection and Check

Identifying the Track Point on the Reversing Cam.

An important step in the rigging procedure is to establish the correct Flight Idle position of the Power Lever
relative to the Flight Idle position on the cambox. This Flight Idle position on the cambox reversing lever is the
track point.
If you set this correctly from the beginning, the amount of time spent adjusting the rigging after the first engine
run can be significantly reduced.

How to identify the Track Point on the Reversing Cam.

(1) Disconnect the forward end of the FCU Interconnecting Rod from the FCU actuating cam lever.
(2) Hold the FCU Actuating Lever forward, against the return spring, clear of the cam follower pin. (temporarily

secure it with a cable-tie)
(3) Then, by hand, move the cambox input lever into the forward range of travel. The cam follower pin moves

along the circumferential arc.
NOTE: The slot profile in the reversing cam lever is made up of a circumferential arc and a radial portion.

You will see that the reversing cam lever is not moved fore or aft as the cam follower pin slides in the
circumferential slot.
(4) Use your other hand to apply a slight forward pressure on the reverse cam, then slowly move the cambox
input lever aft towards flight idle.
(5) As the cam follower pin reaches the point where the circumferential slot in the reverse cam changes to the
radial portion you should see, and feel, a small aft movement in the reverse cam.
(6) The point where movement of the reversing cam lever just begins to occur is called the Track Point.
(7) Cycle the cambox input lever several times to identify exactly where the track point is.

*Go back to rigging procedure (Go to Page 501)

Figure 76.14 Trackpoint Set-up

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MAINTENANCE MANUAL SUPPLEMENT 76-10-00-Engine Controls Rigging
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Maintenance Practices / Inspection and Check

Figure 76.15 Identifying the Trackpoint
Page 602

MAINTENANCE MANUAL SUPPLEMENT 77-00-00 - Engine Indicating
C550GT-AD016-FU24-0213
Chapter 77 Revision: Initial Issue DATE: 01/01/2020

Title Page Engine Indicating

Chapter 77
Engine Indicating

Chapter 77 Engine Indicating

MAINTENANCE MANUAL SUPPLEMENT 77-00-00 - Engine Indicating
C550GT-AD016-FU24-0213
Chapter Contents Revision: Initial Issue DATE: 01/01/2020

Chapter Contents Engine Indicating
Engine Indicating

Chapter Contents

Chapter 77 Engine Indicating

Applicable Section Guide
77-40-00 Integrated Engine Instrument System

Description and Operation
77-40-01 Fuel Flow

Description and Operation
> Troubleshooting.

Maintenance Practices
> Removal and Installation.
> Adjustment and Test

77-40-02 Fuel Pressure
Description and Operation
> Troubleshooting.
Maintenance Practices
> Removal and Installation
> Adjustment and Test.

77-40-03 Fuel Quantity Indicating
Description and Operation
> Troubleshooting
Maintenance Practices
> Removal and Installation.
> Adjustment and Test

77-40-04 Oil Pressure
Description and Operation
> Troubleshooting.
Maintenance Practices
> Removal and Installation
> Adjustment and Test

77-40-05 Oil Temperature
Description and Operation
> Troubleshooting
Maintenance Practices
> Removal and Installation
> Adjustment and Test

77-40-06 Inter Turbine Temperature
Description and Operation
> Troubleshooting
Maintenance Practices
> Removal and Installation.
> Adjustment and Test

77-40-07 Torque Indicating
Description and Operation
> Troubleshooting
Maintenance Practices
> Removal and Installation.
> Adjustment and Test

77-40-08 Ng and Np Indicating
Description and Operation
> Troubleshooting
Maintenance Practices
> Removal and Installation
> Adjustment and Test

MAINTENANCE MANUAL SUPPLEMENT 77-00-00 - Manual to Use DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Manual to Use
Chapter Guide

Chapter Guide
Manual to Use

Applicable Section Guide MANUAL TO USE
SECTION / SUB-SECTION
N/A FU24- 954 C550GT
77-00-00 Engine Indicating
77-40-00 Integrated Engine Instrument Systems 
77-40-01 Fuel Flow Indicating 
Description and Operation

Fuel Flow Indicating System Description 
Troubleshooting
Maintenance Practices 
Removal and Installation 
Monitor Panel and Engine Data Converter
Fuel Flow Transducer. 
Adjustment and Test 
System Test - E.I. Inc. Field Test Device (FCD)
Calibration 
77-40-02 Fuel Pressure Indicating 
Description and Operation
Fuel Pressure Indicating System Description 
Troubleshooting 
Maintenance Practices
Removal and Installation
Monitor Panel
Fuel Pressure Transducer
Adjustment and Test
System Test - E.I. Inc. Field Test Device (FCD)
Calibration

77-40-03 Fuel Quantity Indicating 
Description and Operation 

Fuel Quantity Indicating System Description 
Troubleshooting 
Maintenance Practices
Removal and Installation 
Engine Monitor Panel 
Fuel Level Capacitive Probes
Adjustment and Test
System Test - E.I. Inc. Field Test Device (FCD)
Calibration

MAINTENANCE MANUAL SUPPLEMENT 77-00-00 - Manual to Use DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Manual to Use
Chapter Guide

Applicable Section Guide MANUAL TO USE
SECTION / SUB-SECTION
N/A FU24- 954 C550GT
77-40-04 Oil Pressure Indicating
Description and Operation 

Oil Pressure Indicating System Description
Troubleshooting 
Maintenance Practices 
Removal and Installation
Monitor Panel 
Oil Pressure Transducer 
Adjustment and Test
System Test - E.I. Inc. Field Test Device (FCD) 
Calibration 
77-40-05 Oil Temperature Indicating System
Description and Operation 
Oil Temperature Indicating System Description 
Troubleshooting
Maintenance Practices 
Removal and Installation 
Monitor Panel
Oil Temperature Probe and Harness. 
Adjustment and Test 
System Test - E.I. Inc. Field Test Device (FCD)
Calibration 
77-40-06 Inter Turbine Temperature Indicating System 
Description and Operation
ITT Indicating System Description 
Troubleshooting 
Maintenance Practices
Removal and Installation 
ITT Probes and Harness. 
Engine Monitor Panel.
Adjustment and Test
System Test - E.I. Inc. Field Test Device (FCD)
Calibration
77-40-07 Torque Indicating System
Description and Operation
Torque Indicating System Description
Troubleshooting

MAINTENANCE MANUAL SUPPLEMENT 77-00-00 - Manual to Use DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Manual to Use
Chapter Guide

Applicable Section Guide MANUAL TO USE
SECTION / SUB-SECTION
N/A FU24- 954 C550GT
Maintenance Practices

Removal and Installation 
Torque Pressure Pipes and Hoses.
Monitor Panel 

Adjustment and Test
System Test - E.I. Inc. Field Test Device (FCD) 
Calibration 

77-40-08 Ng and Np Indicating System 
Description and Operation 

Ng and Np Indicating System Description
Troubleshooting 
Maintenance Practices 
Removal and Installation
Tachometer Generator Removal
Tachometer Generator Installation
Monitor Panel
Adjustment and Test
System Test - E.I. Inc. Field Test Device (FCD)
Calibration

MAINTENANCE MANUAL SUPPLEMENT 77-40-01-MVP-50T System
C550GT-AD016-FU24-0213
MVP-50T System Revision: Initial Issue DATE: 01/01/2020

MVP-50T System Description and Operation / Engine Indicating
Engine Indicating

77-40-00 Integrated Engine Instrument System

Description and Operation

Description and Operation

The C550GT uses the Electronics International Inc. MVP-50T Multifunction Glass Panel Engine Monitor positioned
on the RH Instrument Sub-Panel to display engine parameters to the flight crew. The system performs
monitoring tasks only, it does not perform any engine or aircraft system controlling functions.

The Engine Indicating System has four Sub-Systems:
(1) Display Unit
(2) Engine Data Converter
(3) Probes, Sensors, transducers and modules
(4) Inter-wiring, connectors and cables.

For a detailed Description and Operation of the Engine Indicating System, refer to the MVP-50T Operating
Instructions.
Ref. Ext. Doc: Electronics International Inc. MVP-50T Operating Instructions (Doc. No. 1206067)

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MAINTENANCE MANUAL SUPPLEMENT 77-40-01-Integrated Engine Instrument Systems
C550GT-AD016-FU24-0213
Integrated Engine Instrument Systems Revision: Initial Issue DATE: 01/01/2020

Description Description and Operation / Fuel Flow Indicating

Fuel Flow Indicating
Integrated Engine Instrument Systems

77-40-01 Fuel Flow

Description and Operation

Fuel Flow Indicating - Description

The C550GT has a fuel flow transducer in the fuel supply line. This transducer mounts to a bracket on the cockpit
floor aft of the instrument panel frame.
The FT-180 Fuel Flow Transducer transmits flow rate signals to the
Engine Data Converter (EDC). The EDC converts the signal to serial
data which displays on the F. FLOW Vertical Strip Gauge on the MVP-
50T Multifunction Glass Panel Engine Monitor.

Fuel Flow is colour-coded, green shows the normal operating range and
an arrow marks the current flow rate. A digital value in Litres/hr is
displayed below the vertical bar.

(The configuration of the main screen display is still not defined;
this paragraph will be edited when more information is available.
Would also like to get an illustration of the C550GT configuration, showing Fuel Flow in L/hr. this can be
created from a photo)

A. For Description and Operation of the display,

Ref. Ext. Doc: Electronics International Inc. MVP-50T Operating Instructions (Doc. No. 1206067).
Ref. Ext. Doc: Electronics International Inc. MVP-50T Instructions for Continued Airworthiness (Doc. 06201101,
latest revision).

B. For installation of the Fuel Flow Transducer,
Ref. Dwg. No: AD-550GT-2820-005-000

Troubleshooting.
a. Use the applicable E.I. Inc Field Test Device to test the wiring and correct operation of the components of
the Fuel Flow Indicating System.

Model No. FCD-FF: Fuel Flow Signal.
This device produces a variable fuel flow signal of 50Hz to 350 Hz, 9V Sq Wave.

b. Obey the instructions provided with the Electronics International Inc. FCD to troubleshoot the C550GT Fuel
Flow System and MVP-50T Glass Panel Engine Monitor.

c. For information on Troubleshooting the Fuel Flow Indicating System.
Ref. Ext. Doc: Glass Panel Engine Monitor MVP-50T Installation Instructions (Doc. II 1211061).

NOTE: Refer to Section 7.6 – Troubleshooting.

d. Refer to the EDC-33T Interwiring Diagram.
Ref. Dwg. No: AD-550GT-7700-001-201

e. Refer to the MVP-50T Interwiring Diagram.
Ref. Dwg. No: AD-550GT-7700-001-101

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MAINTENANCE MANUAL SUPPLEMENT 77-40-01- Integrated Engine Instrument Systems
C550GT-AD016-FU24-0213
Integrated Engine Instrument Systems Revision: Initial Issue DATE: 01/01/2020

Fuel Flow Indicating Maintenance Practices / Fuel Flow Indicating
Integrated Engine Instrument Systems

Maintenance Practices

1. Removal and Installation.

Monitor Panel and Engine Data Converter.

For Removal and Installation of the Monitor Panel and associated components,
Ref. Ext. Doc: Electronics International Inc. Glass Panel Engine Monitor MVP-50T (for Turboprops and Jets)
Installation Instructions (II-1211061, Latest Revision)

Fuel Flow Transducer.
Refer to Chapter 28-20-04 of this CMMS for Fuel Flow Transducer Removal and Installation. (Link)

2. Adjustment and Test

(1) System Test.
Use the applicable E.I. Inc Field Test Device to test the wiring and correct operation of the components of the
Fuel Flow Indicating System.
Model No. FCD-FF: Fuel Flow Signal
This device produces a variable fuel flow signal of 50Hz to 350 Hz, 9V Sq Wave.

(2) Calibration.
For field calibration of the Fuel Flow System, use a Field Calibration Device (FCD). These units provide a
calibrated signal that may be used to verify the calibration of a given E.I. instrument.

Universal Field Calibration device.

Model No. FCD-TR-1. (Available from Electronics International Inc. - NIST certified)

a. Use this unit to provide a calibrated signal that may be used to verify the calibration of a given E.I.
instrument.

This Bluetooth® field calibration device will allow wireless data retrieval, test and calibration for all engine
indication systems.

NOTE: NIST traceable calibration is an assurance program that certifies that a laboratory or manufacturer is
fully equipped to calibrate equipment to National Institute of Standards and Technology (NIST)
standards and that any products offered by that manufacturer will match those NIST-maintained
measurement standards.

b. Obey the instructions provided with the Electronics International Inc. FCD to field calibrate the C550GT Fuel
Flow Indicating System and MVP-50T Glass Panel Engine Monitor.

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