C550GT ICA v.8 11-09-2020 copy

MAINTENANCE MANUAL SUPPLEMENT 61-20-00- Overspeed Governor Check
C550GT-AD016-FU24-0213
Overspeed Governor Check Revision: Initial Issue DATE: 01/01/2020

Overspeed Governor Check Maintenance Practices / Inspection and Check
Inspection and Check

Inspection and Check

1. Hydraulic Overspeed Governor Operational Ground Check.

Pre-Check Procedures.
i. Make sure you position the aircraft in an area free of foreign objects that can damage the engine.
ii. Position the aircraft into wind

WARNING: MAKE SURE PERSONNEL, EQUIPMENT AND OTHER AIRCRAFT ARE CLEAR OF THE DANGER ZONE
NEAR THE ENGINE.

(1) Start the engine. Refer to the Approved Flight Manual Supplement STC 14/21E/5. (latest revision)
(2) Set the Propeller Speed Control Lever full forward to the MAX RPM position.
(3) On the switch panel, select and hold the GOVNR RESET switch.
(4) Move the Power Lever forward until the propeller constant speeds.
(5) Make sure the propeller RPM stabilises at approx 4-6% below the MAX RPM %

NOTE: The propeller is now operating on the Overspeed Governor.
(6) Continue to hold the GOVNR RESET switch while you reduce engine power, move the Power Lever to the

Flight Idle position.
(7) Release the GOVNR RESET switch.
Then, to check for correct deactivation and reset of the Overspeed Governor test solenoid,

(8) Move the Power Lever forward until the propeller constant speeds.
(9) Make sure the propeller RPM stabilises at 100% RPM, before you reduce power.
(10) Move the Power Lever to the Flight Idle position.
(11) Shut down the engine. Refer to the Approved Flight Manual Supplement STC 14/21E/5. (latest revision)

Page 601

MAINTENANCE MANUAL SUPPLEMENT 61-20-00- Carbon Block
C550GT-AD016-FU24-0213
Carbon Block Revision: Initial Issue DATE: 01/01/2020

Maintenance Practices / Inspection and Check

Carbon Block
Inspection and Check

Inspection and Check

Carbon Block Assemblies.

CAUTION: INSTRUCTIONS AND PROCEDURES IN THIS SECTION MAY INVOLVE CRITICAL PARTS. REFER TO
THE INTRODUCTION CHAPTER OF THIS MANUAL FOR INFORMATION ABOUT PROPELLER
CRITICAL PARTS. REFER TO THE ILLUSTRATED PARTS LIST CHAPTER OF THE APPLICABLE
OVERHAUL MANUAL(S) FOR THE IDENTIFICATION OF SPECIFIC PROPELLER CRITICAL PARTS.

1. Inspection

The clearance between the yoke pin and the corresponding linkage (beta lever bushing) can become too close
due to a buildup of plating and foreign particles between the two pieces. This can cause a binding action,
resulting in excessive wear to the carbon block, beta ring, and beta linkage.

(1) Inspect the beta lever and carbon block interface for free movement. If there is binding, do the following:

a. Disconnect the beta linkage and remove the carbon block assemblies from the beta ring.
b. Using an abrasive pad, lightly polish the yoke pin to provide adequate clearance and eliminate binding.
c. Reinstall the carbon block assembly into the beta ring.
d. Install, adjust and safety the beta linkage.

2. Replacement
NOTE: This procedure covers replacement of A-3026 Carbon Block Unit in the A-3044 Carbon Block
Assembly.

Replace an A-3026 carbon block unit if the side clearance between the beta ring and carbon block exceeds 0.010
inch (0.25 mm).

(1) Remove the cotter pin from the end of the clevis pin.
(2) Slide the pin from the assembly and remove and discard the carbon block unit.
(3) Inspect the yoke for wear or cracks. Replace the yoke if necessary.
(4) Install a new carbon block unit and slide a new clevis pin into place.
(5) Secure the clevis pin with a T-head cotter pin. See Figure 61.9
(6) Refit the carbon block.
(7) Establish the required clearance by sanding the sides of the carbon block as needed. See Figure 61.10

3. Installation of the A-3044 Carbon Block Assembly.
Refer to the Propeller Installation and Removal. (Go to Page 405)

Page 602

MAINTENANCE MANUAL SUPPLEMENT 61-40-00-Beta Sys. Description
C550GT-AD016-FU24-0213
Beta Sys. Description Revision: Initial Issue DATE: 01/01/2020

Description and Operation / Beta Indicating Sys-

Beta Sys. Description
Beta Indicating System

61-40-00 Beta Indicating System

Description and Operation

Beta Range Indication.

The Beta Indicating System advises the pilot that the control quadrant Power Lever is transitioning through the
position 7/16 in. forward of the Flight Idle detent.

The blue BETA light, on the RH Instrument Sub-Panel, indicates that the propeller is operating in the Beta Range.
The light is a Press-to-Test pedestal type.

The propeller reversing cable terminal activates the beta switch. Moving the Power Lever aft of 7/16 in. forward
of the Flight Idle detent (rig position) activates the reversing cam. The reversing cam moves the cable which
contacts and activates the Beta Switch.

The switch is located on the right side of the engine, forward of the propeller reversing cam. Remove the top
engine cowl to access the switch.

Page 1

MAINTENANCE MANUAL SUPPLEMENT 61-40-00- Beta Switch
C550GT-AD016-FU24-0213
Beta Switch Revision: Initial Issue DATE: 01/01/2020

Removal and Installation Maintenance Practices / Removal and Installation
Beta Switch

Maintenance Practices
Removal and Installation

1. Beta Switch Removal.
Ref. Dwg. No: AD-550GT-7700-001-101
Ref. Dwg. No: AD-550GT-7700-001-000
(1) Make sure aircraft electrical power is OFF.
(2) Remove the top engine cowl. See Chp. 71 Engine Cowling
(3) Disconnect the electrical wiring from the switch.
(4) Remove the screws, washers and nuts that attach the switch to the bracket.
(5) Remove the switch.

2. Beta Switch Installation.
Ref. Dwg. No: AD-550GT-7700-001-101
Ref. Dwg. No: AD-550GT-7700-001-000
(1) Position the switch on the bracket plate and attach it with the screws, washers and nuts.
(2) Connect the electrical wiring to the switch.
(3) Adjust the switch position. See Chp. 61 Beta Switch Adjustment.
(4) Install the top engine cowl. See Chp. 71 Engine Cowling

Figure 61.28 Beta Switch position

Page 401

MAINTENANCE MANUAL SUPPLEMENT 61-40-00- Beta Switch Position
C550GT-AD016-FU24-0213
Beta Switch Position Revision: Initial Issue DATE: 01/01/2020

Adjustment and Test Maintenance Practices / Adjustment and Test
Beta Switch Position

Adjustment and Test

1. Beta Switch Position.

(1) Remove the top engine cowl. See Chp. 71 Engine Cowling
(2) Disconnect the reversing cable terminal from the Beta Valve lever.
(3) Set the Power Lever to a position 7/16 in. forward of the Flight Idle detent.
(4) Set the Master switch to ON.
(5) Move the power lever aft past the position 7/16 in. forward of the Flight Idle detent.

Result.
The blue Beta light should come ON.

If the Beta Light does not illuminate.

(6) Check the position of the Power Lever when the BETA light illuminates. The Power Lever rear edge should be
7/16 in. forward of the Flight Idle detent.

(7) If necessary, loosen the Beta switch attach screws and reposition the switch to make sure the light comes
ON at the correct Power Lever position.

(8) Install the top engine cowl. See Chp. 71 Engine Cowling

2. Beta Switch Adjustment.

(1) Start the engine. Refer to the Pilot Operating Handbook (POH).
(2) Set the Propeller Control Lever to the MAX RPM position.
(3) Move the Power Lever to a position on or about 7/16 in. forward of the Flight Idle detent.
(4) Check that the BETA Light is OFF.
(5) Slowly move the Power Lever aft of the 7/16 in. rig position until the Beta Light comes ON.
(6) Check that this point is within 1/16 in. to 1/8 in. aft of the position 7/16 in. forward of the Flight Idle detent.
(7) Move the Power Lever to a position on or about 7/16 in. forward of the Flight Idle detent and check that the

Beta Light goes OFF.

If the Power Lever position point is not correct.
(8) Make sure the Power Lever IDLE position is correctly rigged. Check the rear linkage. See Chp. 76 Propeller

Speed Control Rigging.
(9) Reposition the Beta switch on the attach plate. Refer to Beta Switch Position, step 7 above.

Page 501

MAINTENANCE MANUAL SUPPLEMENT 71-00-00 - DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue
Powerplant

Title Page

Powerplant
Chapter 71

Chapter 71 Powerplant

MAINTENANCE MANUAL SUPPLEMENT 71-00-00 - Powerplant DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Powerplant
Chapter Contents

Chapter Contents
Powerplant

Chapter Contents

Chapter 71 Powerplant

Applicable Section Guide
71-00-00 Powerplant
Description and Operation
> Powerplant - Description
Maintenance Practices

Removal and Installation
> Engine Removal
> Engine Installation.
Adjustment and Test
> General Engine Testing and Checks
> Engine Operating Limits.
> Pre-Start Checks.
> Engine Starting.
> Engine Shutdown.
> Engine Performance Check .
71-10-00 Cowling
Description and Operation
> Cowling Description
Maintenance Practices
Removal and Installation
> Engine Cowling
> Inspection and Check
71-20-00 Mounts
Description and Operation
> Mounts.

71-20-01 Engine Frame Reinforcements
Description and Operation
> Engine Frame Reinforcements.
Maintenance Practices

Inspection and Check
> Engine Strut Inspection.
> Engine Frame Lower Bracket Inspection.

71-20-02 Mount Frame
Description and Operation
> Mount Frame Description
Maintenance Practices

Removal and Installation
> Engine Mount Frame Removal
> Engine Mount Frame Installation
Inspection and Check
> Engine Mount Frame Inspection.-150 HRS

71-20-03 Isolator Mounts
Description and Operation
> Isolator Description
Maintenance Practices
> Engine Isolator Mount Removal
> Engine Isolator Mount Installation

Inspection and Check
> Isolator Mount Inspection A.- Visual (150hrs)
> Isolator Mount Inspection B. – Disassembled. (600hr)

MAINTENANCE MANUAL SUPPLEMENT 71-00-00 - DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue
Chapter Contents

71-30-00 Engine Fireseals
Description and Operation
> Powerplant Fireseals
Maintenance Practices
Removal and Installation
> Rear Fireseal Removal.
> Rear Fire Seal Installation.
> Forward Fireseal Removal
> Forward Fireseal Installation
Inspection and Check
> Inspection of Fireseal Baffles.

71-50-00 Powerplant Electrical
Description and Operation
> Troubleshooting
> Powerplant Electrical Loom Inspection.

71-60-00 Air Intake System
Description and Operation
Adjustment and Test
> Servicing.
> Adjustment and Test
> Differential Pressure Switch Setting – Filter Dirty Warning Light

71-70-00 Engine Fluid Drains
Description and Operation
> Engine Fluid Drains.
Inspection and Check
> Starting Control Drain.
> Fuel Control Unit (FCU) Seepage Drain.

MAINTENANCE MANUAL SUPPLEMENT 71-00-00 - 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 PWC EMM C550GT

Applicable Section Guide 
SECTION / SUB-SECTION 

71-00-00 Powerplant
Description and Operation

Differences

PT6A-15AG Turboprop Engine

Specifications (Leading Particulars)

Troubleshooting

Maintenance Practices 

Removal and Installation
PT6A-15AG Turboprop Engine Removal 
PT6A-15AG Turboprop Engine Installation

Adjustment and Test 
General Engine Testing and Checks
a. Specific checks after component change 
b. Minimum checks to be done before troubleshooting
c. Engine Operating Limits 
Engine Over-torque and Over-temperature Limits 
Engine Pre-operational Check.
Pre-Start Checks 
Dry Motoring Run
Wet Motoring Run 
Engine Starting 
Engine Shutdown
Post-Shutdown Checks 
Propeller Governor Checks 
Fuel Control Unit Checks
a. Minimum Governing - Ground Idle 
b. Flight-Idle Adjustment 
c. Gas Generator Speed 
d. Deceleration Check 
Oil Pressure Check 
Engine Performance Check 
Acceleration Adjustments 
Torquemetre Function Test 






MAINTENANCE MANUAL SUPPLEMENT 71-00-00 - Manual to Use DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Manual to Use
Chapter Guide
MANUAL TO USE
Applicable Section Guide
SECTION / SUB-SECTION N/A FU24- 954 C550GT

71-10-00 Cowling 
Description and Operation

Cowling- Nomex / Carbon-Fibre 

Maintenance Practices

Removal and Installation
Top Cowl

Bottom Cowl

71-20-00 Mounts 
71-20-01 Engine Struts / Reinforcement Brackets 
Description and Operation

Engine Struts (Top) 
Reinforcement Brackets (Bottom)
Maintenance Practices
Inspection and Check

Engine Strut Inspection.
Engine Frame Lower Bracket Inspection.

71-20-02 Mount Frame 
Description and Operation

PT6A-15AG Engine Mount 
Maintenance Practices
Removal and Installation 

Engine Mount Frame Removal 
Engine Mount Frame Installation 
Inspection and Check 
150 hr Mount Frame Inspection
71-20-03 Isolator Mounts
Description and Operation
Isolator mounts
Maintenance Practices
Removal and Installation

Isolation Mount Removal
Isolation Mount Installation
Inspection and Check

Isolator Mount Inspection

71-30-00 Fireseals 
Description and Operation

Fireseal Description

MAINTENANCE MANUAL SUPPLEMENT 71-00-00 - Manual to Use DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Manual to Use
Chapter Guide
MANUAL TO USE
Applicable Section Guide
SECTION / SUB-SECTION N/A FU24- 954 C550GT

Maintenance Practices 

Removal and Installation
Fireseal Removal

Fireseal Installation

Inspection and Check

71-40-00 Attach Fittings (Powerplant) 
Description and Operation

Ignition Exciter Bracket

Maintenance Practices 

Removal and Installation
Exciter Unit Bracket

71-50-00 Powerplant Electrical 
Description and Operation 

Powerplant Electrical 
Troubleshooting

Electrical
Maintenance Practices
Inspection and Check

Electrical Loom

71-60-00 Air Intake 
Description and Operation

Air Intake System 
Maintenance Practices
Removal and Installation

Adjustment and Test

Differential Pressure Switch Setting
Filter Dirty Warning Light

Inspection and Check

MAINTENANCE MANUAL SUPPLEMENT 71-00-00-Description / Differences
C550GT-AD016-FU24-0213
Description / Differences Revision: Initial Issue DATE: 01/01/2020

Description / Differences Description and Operation / Powerplant
Powerplant

71-00-00 Powerplant

Description and Operation

Powerplant Differences
The zone forward of the C550GT firewall is completely different from the FU24-954. For all maintenance and
inspection, use these Instructions for Continued Airworthiness.

Powerplant - Description

The C550GT is powered by the P&WC PT6A-15AG Turboprop Gas Turbine Engine.
For detailed Description and Operation of the PT6A-15AG Turboprop engine refer to Chapter 72-00-00,
Description and Operation in the P&WC PT6A-15AG Engine Maintenance Manual (No. 3030442 latest revision).
(Link to Publication List)

The tubular steel engine mount is bolted to the firewall structure in four places. Thrust loads are transferred to
the airframe through engine struts and reinforcement brackets on the aft side of the firewall. The turboprop
engine mounts to the frame at three points using isolator mounts.

Figure 71.1 Powerplant Installation.
The C550GT uses a carbon-fibre, two-piece, removable engine cowling. The top and bottom cowl joins at the
horizontal split-line with Camloc® fasteners.
The bottom cowl has a NACA inlet duct on the RH side that forces air into the oil cooler unit.
The engine combustion air inlet cover is flush with the bottom cowl surface and contains the barrier filter. An air
inlet is located forward of the exhaust outlet to supply fresh air to the cockpit.

Page 1

MAINTENANCE MANUAL SUPPLEMENT 71-00-00-Description / Differences
C550GT-AD016-FU24-0213
Description / Differences Revision: Initial Issue DATE: 01/01/2020

Description and Operation / Powerplant

The top cowl has a hinged access door for engine oil servicing.

Figure 71.2 Engine Cowling.
The engine vent system discharges air/oil vapour into the exhaust. Pipes for oil and fuel component drains are
routed overboard from the engine compartment.
Leading Particulars
Refer to Chapter 72-00-00, Description and Operation, Engine Data in the P&WC PT6A-15AG Engine Maintenance
Manual (No. 3030442 latest revision) (Link to Publication List)

Page 2

MAINTENANCE MANUAL SUPPLEMENT 71-00-00 - Components Changed Table
C550GT-AD016-FU24-0213
Components Changed Table Revision: Initial Issue DATE: 01/01/2020

Components Changed Table CCBTS / Powerplant
Powerplant

Components Changed By This STC

Drawing Number Item Part Number Description / Location

Powerplant Installation

AD-550GT-7100-001-000 1 08-51081-1 Bleed Air Tube

AD-550GT-7100-001-000 2 08-51083-1 Gasket

AD-550GT-7100-001-000 3 08-57115-1 Fitting

AD-550GT-7100-001-000 4 11-51053-- Oil Breather Tube

AD-550GT-7100-001-000 5 11-51055-1 Backing Plate

AD-550GT-7100-001-000 6 11-51057-1 Seal

AD-550GT-7100-001-000 7 11-51059-1 Fairlead

AD-550GT-7100-001-000 8 11-51061-1 Oil Breather Exit Tube

AD-550GT-7100-001-000 9 11-51075-1 Link

AD-550GT-7100-001-000 10 11-51063 Support, Drain Pipe

AD-550GT-7100-001-000 11 11-51065 Support, Drain Pipe

AD-550GT-7100-001-000 12 11-57069-1 Combustion Drain Pipe, Fwd.

AD-550GT-7100-001-000 13 11-57071-1 Combustion Drain Pipe, Rear

AD-550GT-7100-001-000 14 193-4-18-0 Hose

AD-550GT-7100-001-000 15 3162-16 Hose

AD-550GT-7100-001-000 16 5906-2SA5 Isolator

AD-550GT-7100-001-000 17 193000-3D-0202 Hose, StartGen. Drain

AD-550GT-7100-001-000 18 193000-4-0390 Hose

AD-550GT-7120-002-000 1 08-51071-1 Engine Mount Assembly

Engine Cowling and Barrier Air Filter

AD-08600-7110-001-000 4 AD-08600-7110-010-000 Crusader Engine Cowls

AD-08600-7110-001-000 9 AD-08600-7110-015-000 Filter Cover

AD-08600-7110-001-000 10 21416T001 Barrier Filter Element

AD-08600-7110-001-000 13 AD-08600-7130-001-000 Fireseals Installation

Fireseals

AD-08600-7130-001-000 5 AD-08600-7130-001-100 Forward Fireseal Assembly

AD-08600-7130-001-000 6 AD-08600-7130-001-200 Rear Fireseal assembly

Propeller Installation

AD-550GT-6100-001-000 5 C-3064-1P Back-Plate Assembly

AD-550GT-6100-001-000 6 C3065-1P Spinner Assembly

AD-550GT-6100-001-000 7 C3317-230 O Ring

Page 1

MAINTENANCE MANUAL SUPPLEMENT 71-00-00- PT6A-15AG Turboprop Engine
C550GT-AD016-FU24-0213
PT6A-15AG Turboprop Engine Revision: Initial Issue DATE: 01/01/2020

PT6A-15AG Turboprop Engine Maintenance Practices / Removal and Installation
Removal and Installation

Maintenance Practices
Removal and Installation

1. Engine Removal

(1) Support the rear fuselage with the aircraft tail stand.
(2) Disconnect the aircraft batteries. See Chp. 24 Battery Removal
(3) In the cockpit, set the fuel valve to OFF and placard it 'DO NOT OPERATE'.
(4) Remove the engine cowling. See Chp. 71 Engine Cowling
(5) Install the wrap-around Air Inlet Protector.

CAUTION: IF ANY OBJECT FALLS INTO THE ENGINE COMPRESSOR INLET, STOP ALL WORK UNTIL THE
OBJECT IS RECOVERED.

(6) Drain the engine’s integral oil tank.

NOTE: Refer to the P&WC Maintenance Manual, Turboprop Gas Turbine Engine, Model PT6A-15AG Manual
Part No. 3030442, Chapter 72-00-00 Servicing, D. 1. and Fig. 301.

(7) Drain the oil cooler.

(8) Remove the propeller. See Chp. 61 Propeller Model No. HC-B3TN-3D – Removal.

(9) Disconnect the engine control cables. See Chp. 73 Engine Control Push-Pull Cables

a. Propeller control at the push-pull cable bracket.
b. Power lever cable at the input lever and bracket.
c. Fuel condition lever at the Starting Control and bracket.
(10) Disconnect and cap the fuel supply hose at the Fuel Heater.

(11) Disconnect and cap the oil cooler lines from the oil scavenge pump and the oil tank.

(12) Disconnect/remove these electrical wires/components.

a. Disconnect the chip detector wire at the underside of the Reduction Gearbox.
b. Disconnect the Inter-Turbine Temperature (ITT) wires at the terminal block.
c. Disconnect the ignition, oil temperature, Ng and Np RPM wiring.
d. Disconnect the Py Anti-Ice heater wiring.
e. Disconnect the wires to the Starter Generator.

NOTE: Tag all wires for reassembly.
(13) If applicable, disconnect and cap the P3 air heater hose and fittings.

(14) Remove the combustion chamber drain lines.

(15) Remove the oil tank vent and drain lines.

(16) Disconnect and cap the oil and fuel lines at the engine. (Indicating systems)

a. Engine oil pressure.
b. Fuel pressure.
c. Torque low/high pressure at the flexible hose connection at the front fireseal baffle.
(17) Remove the rear air-inlet compartment fireseal from the engine mount frame to allow engine to be

removed from the mount frame.

(18) Support the engine with suitable lifting equipment

NOTE: Use the PWC51861-600 sling (or equivalent) and a suitable hoist.
Refer to the P&WC Maintenance Manual, Turboprop Gas Turbine Engine, Model PT6A-15AG Manual Part No.
3030442, Chapter 72-00-00.

WARNING: DO NOT STAND UNDER THE LOAD. MAKE SURE ALL PERSONNEL STAY CLEAR OF THE ENGINE
DURING THE LIFT.

(19) Remove the three engine support bolts from the isolator mounts.
(20) Carefully lower the engine clear of the airframe. Make sure there is no wiring and hoses still connected.

Page 401

MAINTENANCE MANUAL SUPPLEMENT 71-00-00-PT6A-15AG Turboprop Engine
C550GT-AD016-FU24-0213
PT6A-15AG Turboprop Engine Revision: Initial Issue DATE: 01/01/2020

Maintenance Practices / Removal and Installation

2. Engine Installation.

WARNING: MAKE SURE YOU USE THE CORRECT ATTACHMENT BOLTS. CHECK THE PART NUMBER ON THE
REFERENCE DRAWING. REF.DWG.NO. AD-550GT-7100-001-000.

CAUTION: WHEN YOU INSTALL A NEW, NEWLY OVERHAULED OR REPAIRED ENGINE, MAKE SURE THE OIL
COOLER AND OIL COOLER HOSES HAVE BEEN FLUSHED OR REPLACED.

(1) Install the lifting device. Refer to P&WC PT6A-15AG Maintenance Manual, Chapter 72-00-00
(2) Carefully lift and position the engine in the Engine Mount.
(3) Install the 3 bolts through the engine mount and isolators. Make sure the countersunk side of the washer is

against the underside of the bolt head.
NOTE: The top isolator mount uses a longer bolt.
Ref. Dwg. No: AD-550GT-7100-001-000

(4) Hold the bolt and torque the nuts to 450-500 in lbs. Safety the nuts with a cotter pin.
(5) Install the engine rear inlet-fireseal to the engine mount.
(6) Connect the Indicating System flexible hoses.

a. Engine Lubrication Oil Pressure hose.
b. Fuel Pressure
c. Torque low and high pressure connections.

(7) Connect the drains and vent lines.

a. Combustor drains in 2 places.
b. Engine Vent hose.
CAUTION: MAKE SURE THE ENGINE VENT HOSE IS NOT CRIMPED OR RESTRICTED. OIL WILL BE PUMPED

OUT OF THE ENGINE DURING OPERATION IF THE VENT SYSTEM IS RESTRICTED.

c. Accessory mount pad drains.
d. Fuel pump drain.

(8) Connect the Electrical Connectors and wiring supports.

a. Chip Detector.
b. P3 Heater.
c. ITT indicator.

NOTE: Make sure to use the correct terminals. (Large AL, Small CR)
Torque the nuts. Large 10-15 in lb. Small 8-12 in lb.

d. Ignition Exciter connection.
e. Ng and Np speed sensors
f. Starter Generator wiring.
(9) Connect the oil cooler hoses.

a. To oil scavenge pump
b. To oil tank.
(10) Connect the fuel supply hose to the fuel heater.
(11) Connect the engine control cables. See Chp. 73 Engine Control Push-Pull Cables

a. Propeller condition.
b. Power lever.
c. Fuel condition lever.
(12) Install the propeller. See Chp. 61 Propeller Model No. HC-B3TN-3D – Installation.
(13) Service the engine with oil. Refer to P&WC PT6A-15AG Maintenance Manual section 72-00-00.
(14) Rig the Engine Controls. See Chp. 76 Engine Controls Rigging Procedure.
(15) Connect the aircraft batteries. See Chp. 24 Battery Installation.

Page 402

MAINTENANCE MANUAL SUPPLEMENT 71-00-00-PT6A-15AG Turboprop Engine
C550GT-AD016-FU24-0213
PT6A-15AG Turboprop Engine Revision: Initial Issue DATE: 01/01/2020

Maintenance Practices / Removal and Installation

(16) Do an Ignition System Test.
Refer to the applicable procedure in Chapter 74-00-00, Ignition System, Sec. 5. Adjustment and Test in the
P&WC Manual (No. 3030442).

(17) Install the engine cowling. See Chp. 71 Engine Cowling

(18) Do the specific Powerplant checks and adjustments and in the order in which they are to be done after
Engine Replacement.

Refer to the P&WC Maintenance Manual, Turboprop Gas Turbine Engine, Model PT6A-15AG Manual Part No.
3030442 (latest revision). 71-00-00 -Power Plant, Adjustment and Test, 1. General, para. A and Table 501.

CAUTION: MAKE SURE YOU USE THE SPECIFIC ENGINE CHECKS AND OBEY THE SEQUENCE THAT THE
CHECKS ARE DONE. REFER TO THE P&WC ENGINE MAINTENANCE MANUAL FOR THE LIST AND
ORDER OF ENGINE TESTS REQUIRED AFTER A COMPONENT REPLACEMENT.

Page 403

MAINTENANCE MANUAL SUPPLEMENT 71-00-00- General Engine Testing and Checks
C550GT-AD016-FU24-0213
General Engine Testing and Checks Revision: Initial Issue DATE: 01/01/2020

Maintenance Practices / Adjustment and Test

General Engine Testing and Checks
Adjustment and Test

Adjustment and Test

General Engine Testing and Checks

Refer to the P&WC Engine Manual, Chapter71-00-00 -Power Plant, Adjustment and Test for generalized
procedures for ground testing.
Ref. Ext. Doc: P&WC Maintenance Manual, Turboprop Gas Turbine Engine, Model PT6A-15AG Manual Part No.
3030442 (latest revision).

CAUTION: MAKE SURE YOU USE THE SPECIFIC ENGINE CHECKS AND OBEY THE SEQUENCE THAT THE
CHECKS ARE DONE. REFER TO THE P&WC ENGINE MAINTENANCE MANUAL FOR THE LIST AND
ORDER OF ENGINE TESTS REQUIRED AFTER A COMPONENT REPLACEMENT.

NOTE: Where specific procedures applicable to the C550GT STC 14/21E/5 Powerplant installation are
required, these will be detailed in this Crusader Maintenance Manual Supplement (CMMS) and ICA
documents. Use the Applicable Chapter Guide, this will guide you to which publication is applicable.

The P&WC Maintenance Manual, Chp. 71-00-00 has specific procedures for Model PT6A-15AG Engine Testing:
(1) General

a. Specific checks after installation or replacement of components.
b. Minimum checks to be done before troubleshooting.
c. Engine Operating Limits.
(2) Engine Over-torque and Over-temperature Limits.
(3) Engine Pre-operational Check.
(4) Pre-Start Checks.
(5) Dry Motoring Run.
(6) Wet Motoring Run.
(7) Engine Starting.
(8) Engine Shutdown.
(9) Post-Shutdown Checks.
(10) Propeller Governor Checks.
(11) Fuel Control Unit Checks.

a. Minimum Governing
b. Flight-Idle Adjustment
c. Gas Generator Speed
d. Manual Override System Static Check – (Not installed in C550GT)
e. Manual Override System Operational Check- (Not applicable to C550GT)
f. Deceleration Check

(12) Oil Pressure Check.
(13) Engine Performance Check.
(14) Acceleration Adjustments.
(15) Torquemetre Function Test.

NOTE: Use the Applicable Chapter Guide, this will guide you to the applicable document.

Page 501

MAINTENANCE MANUAL SUPPLEMENT 71-00-00- Engine Check Procedures
C550GT-AD016-FU24-0213
Engine Check Procedures Revision: Initial Issue DATE: 01/01/2020

Engine Check Procedures Maintenance Practices / Adjustment and Test
Adjustment and Test

1. Engine Operating Limits.
Ref. Ext. Doc: Crusader 550GT Approved Flight Manual Supplement STC 14/21E/5.

2. Pre-Start Checks.
Ref. Ext. Doc: Crusader 550GT Approved Flight Manual Supplement STC 14/21E/5.

3. Engine Starting.
Ref. Ext. Doc: Crusader 550GT Approved Flight Manual Supplement STC 14/21E/5.

4. Engine Shutdown.
Ref. Ext. Doc: Crusader 550GT Approved Flight Manual Supplement STC 14/21E/5.

5. Engine Performance Check .

(1) Before performing an Engine Performance Check:

a. Make sure that all indicators of engine performance are calibrated.
b. Remove the engine cowling.
c. Secure all disconnected electrical connectors and ducting in the engine compartment to prevent them from

being damaged by the prop wash.
d. Make sure you position the aircraft in an area free of foreign objects that can damage the engine.

WARNING: MAKE SURE PERSONNEL, EQUIPMENT AND OTHER AIRCRAFT ARE CLEAR OF THE DANGER ZONE
NEAR THE ENGINE.

e. Secure the aircraft into wind.

WARNING: TO SECURE THE AIRCRAFT, ATTACH STRAPS OF 2000 KG CAPACITY TO THE MAIN LANDING
GEAR, THEN AFT TO AN ANCHOR OR OBJECT ABLE TO RESIST THE THRUST GENERATED AT FULL
POWER.

(2) Refer to Figure 510, sheet 14, Chapter 71-00-00, Powerplant Adjustment and Test in the P&WC PT6A-15AG
Engine Maintenance Manual (No. 3030442 latest revision.) for engine performance targets.

(3) Do an Engine Performance Check in accordance with Section 13, Chapter 71-00-00, Powerplant Adjustment
and Test in the P&WC PT6A-15AG Engine Maintenance Manual (No. 3030442 latest revision.)

C550GT Engine Performance Check Guidelines.

• Establish the propeller speed at 2200 RPM.
• Advance the Power Lever to the TARGET TORQUE you determined in Step B. Then, do not move the Power

Lever while you allow the instrument indications to stabilise.
• Hold that Power Lever position for 2 minutes, then record the gas generator speed (Ng), interturbine tem-

perature (ITT) and fuel flow (FF).
NOTE: Convert FT-LB to psi using a factor of 30.54 (Example: 1380 ft lb ÷ 30.54 = 45.18 psi.)
NOTE: Convert PPH to Litres/hr by using a factor of 1.76. See Chp. 20 Fuel Conversion Table.

Page 502

MAINTENANCE MANUAL SUPPLEMENT 71-10-00-Cowling
C550GT-AD016-FU24-0213
Cowling Revision: Initial Issue DATE: 01/01/2020

Description and Operation / Cowling

Description / Differences

Cowling
Cowling

71-10-00 Cowling

Description and Operation

Cowling Description

The C550GT uses a carbon-fibre, two-piece, removable engine cowling. This was developed under a separate
STC - 10/21E/17. See Figure 71.2

The cowl structure uses Nomex® Honeycomb with a fire-retardant epoxy resin and a strengthening joggle in the
upper cowl. The top and bottom cowl joins at the horizontal split-line.

Figure 71.3 Bottom Cowl.

The bottom cowl has a NACA inlet duct on the RH side that forces air into the oil cooler unit. The engine
combustion air inlet cover is flush with the bottom cowl surface and contains the barrier filter.
Both cowls have integral structural channels. The Engine Fireseals fit into these channels and seal the Air Intake.
The top cowl has a hinged Oil Service access door.
For further information on the engine cowling,
Ref. Ext. Doc: Instructions for Continued Airworthiness AD016-08600-0239 ISS1, Alternate Engine Cowls STC
10/21E/17.

Page 1

MAINTENANCE MANUAL SUPPLEMENT 71-10-00-Cowling
C550GT-AD016-FU24-0213
Cowling Revision: Initial Issue DATE: 01/01/2020

Description and Operation / Cowling

Figure 71.4 Top Cowl

Page 2

MAINTENANCE MANUAL SUPPLEMENT 71-10-00- Engine Cowling
C550GT-AD016-FU24-0213
Engine Cowling Revision: Initial Issue DATE: 01/01/2020

Removal and Installation Maintenance Practices / Removal and Installation
Engine Cowling
Maintenance Practices
Engine Cowling Removal and Installation

Top Cowl Removal

(1) Loosen the Camloc® fasteners at the split-line and the fuselage.
(2) Carefully lift the top cowl away from the bottom cowl and clear of the aircraft.

Bottom Cowl Removal

(1) Inside the cowl, on the LH side, remove the clamp from the cockpit fresh-air duct and remove the ducting.
(2) On the RH side of the bottom cowl, disconnect the electrical wiring at the connector to the pressure switch.

NOTE: You need a minimum of two people for this task.
(3) Support the cowl and loosen the Camloc® fasteners at the fuselage.
(4) Carefully lower the bottom cowl clear of the aircraft.

Cowling Installation
Use the removal procedure as a guide to install the engine cowling.

Inspection and Check
Refer to Alternate Engine Cowls STC 10/21E/17.

Ref. Ext. Doc: Instructions for Continued Airworthiness AD016-08600-0239 ISS1, Alternate Engine Cowls STC
10/21E/17.

Page 401

MAINTENANCE MANUAL SUPPLEMENT 71-20-00-Mounts General
C550GT-AD016-FU24-0213
Mounts General Revision: Initial Issue DATE: 01/01/2020

Mounts General Description and Operation / Mounts
Mounts
71-20-00 Mounts
Mounts.
Description and Operation

Overview.

This section includes
(1) The one-piece aluminum struts that fasten between the firewall and the fuselage upper-longeron.
(2) The reinforcement brackets fastened to the lower longerons.
(3) The tubular steel frame that attaches the engine to the airframe.
(4) The isolator mounts at the three engine to frame attach points.

Page 1

MAINTENANCE MANUAL SUPPLEMENT 71-20-01-Engine Struts / Brackets
C550GT-AD016-FU24-0213
Engine Struts / Brackets Revision: Initial Issue DATE: 01/01/2020

Engine Struts / Brackets Description and Operation / Powerplant-Mounts
Powerplant-Mounts
71-20-01 Engine Frame Reinforcements
Engine Frame Reinforcements.
Ref. Dwg. No: AD-550GT-7120-001-000 Description and Operation

The turbine engine frame attaches at the same points as the original FU24-954 engine frame. Additional one-
piece aluminium struts fasten between the firewall and the fuselage upper-longeron. These struts give further
reinforcement to the firewall structure and better load transfer.
The engine frames two lower mounts bolt through reinforcement brackets fastened to the lower longerons inside
the fuselage.
Use the CMMS for maintenance of the upper struts and lower brackets and the FU24 MM for inspection and
maintenance of all other firewall structure.

Figure 71.5 Engine Support Struts and Brackets.
Page 1

MAINTENANCE MANUAL SUPPLEMENT 71-20-01- Engine Struts / Brackets
C550GT-AD016-FU24-0213
Engine Struts / Brackets Revision: Initial Issue DATE: 01/01/2020

Inspection and Check Maintenance Practices / Inspection and Check
Engine Struts / Brackets

Maintenance Practices
Inspection and Check

1. Engine Strut Inspection.

Ref. Dwg. No: AD-550GT-7120-001-000

CAUTION: THE ENGINE STRUTS ARE CRITICAL TO THE SAFETY OF THE AIRCRAFT. MAKE SURE YOU
EXAMINE ALL AREAS CAREFULLY.

(1) Remove the LH and RH Instrument Sub-Panels. See Chp. 39 Instrument Panels - Removal and Installation.

(2) Use a mirror and bright light to carefully examine the engine struts.

(3) Look for:

a. Damage to any radiused edge.
b. Loose or broken bolts.
c. Signs of fretting or chafe. (Black dust or stains)
d. Cracks.
e. Signs of cracked paint or deformation of the strut, firewall, horizontal bulkhead and longerons.
(4) Examine the doubler plate for loose bolts, damage, cracks or chafe.

Result.
If you find any damage, contact the Crusader Aircraft Company (CAC) for support.

(5) Re-torque the strut attachment fasteners and engine frame bolts. See Chp. 5 150 hr Maintenance Schedule

2. Engine Frame Lower Bracket Inspection.

CAUTION: THE ENGINE MOUNT BRACKETS ARE CRITICAL TO THE SAFETY OF THE AIRCRAFT. MAKE SURE
YOU EXAMINE ALL AREAS CAREFULLY.

(1) In the cockpit at the firewall, access the LH and RH lower reinforcement brackets.
(2) Use a mirror and bright light to carefully examine each bracket.
(3) Look for:

a. Damage to any radiused edge.
b. Loose or missing rivets.
c. Signs of fretting or chafe. (Black dust or stains)
d. Cracks.
e. Signs of cracked paint or deformation of the bracket, firewall, fuselage skin or stringer.

Result.
If you find any damage, contact the Crusader Aircraft Company (CAC) for support

(4) Re-torque the engine frame lower bolts. See Chp. 5 150 hr Maintenance Schedule

Page 601

MAINTENANCE MANUAL SUPPLEMENT 71-20-02-Description
C550GT-AD016-FU24-0213
Description Revision: Initial Issue DATE: 01/01/2020

Description Description and Operation / Engine Mount Frame
Engine Mount Frame

71-20-02 Mount Frame

Description and Operation

Mount Frame Description
A tubular steel structure attaches the engine to the airframe. The mount frame uses 3 rubber vibration isolators.

The tubular structure is attached to the fuselage at the firewall by 4 bolts.

The two top attach bolts thread into captive nuts in the load transfer struts. See Chp. 71 Engine Frame
Reinforcements.

Figure 71.6 Engine Mount Frame.
Page 1

MAINTENANCE MANUAL SUPPLEMENT 71-20-02- Engine Mount Frame
C550GT-AD016-FU24-0213
Engine Mount Frame Revision: Initial Issue DATE: 01/01/2020

Removal and Installation Maintenance Practices / Removal and Installation
Engine Mount Frame

Maintenance Practices
Removal and Installation

1. Engine Mount Frame Removal
Ref. Dwg. No: AD-550GT-7120-002-000
(1) Support the rear fuselage with the tail-stand. See Chp. 7 Lifting and Shoring.
(2) Remove the engine cowling. See Chp. 71 Engine Cowling
(3) Support the engine with applicable P&WC lifting equipment. Refer to the P&WC PT6A-15AG Maintenance
Manual, Section 72-00-00, Removal and Installation, Special Tools.
(4) Disconnect the isolation mounts. See Chp. 71 Engine Isolator Mount Removal
(5) Disconnect the engine fire seals. See Chp. 71 Rear Fireseal Removal.
(6) Remove the instrument panel for access. See Chp. 39 Instrument Panels - Removal and Installation.
NOTE: Note: The two top bolts thread into nuts held by throat washers. See Figure 71.7
(7) Access the bottom nuts behind the rudder pedals.
(8) Remove the top and bottom bolts that attach the mount frame to the firewall.
(9) Carefully lift the Engine Mount Frame clear of the engine.

Figure 71.7 Engine Frame Strut attachment.
Page 401

MAINTENANCE MANUAL SUPPLEMENT 71-20-02-Engine Mount Frame
C550GT-AD016-FU24-0213
Engine Mount Frame Revision: Initial Issue DATE: 01/01/2020

Maintenance Practices / Removal and Installation

2. Engine Mount Frame Installation

Ref. Dwg. No: AD-550GT-7120-002-000

CAUTION: MAKE SURE YOU USE THE CORRECT ENGINE FRAME MOUNTING BOLTS AND NUTS.

Refer to AD-550GT-7120-002-000 for correct hardware specifications.

Bolts are installed from the engine side. These radius head-bolts (5, 6) have countersunk washers under the
head. Make sure you place the recessed side of the washer against the bolt head. Apply thread lubrication to the
bolt threads before you install them.

WARNING: THE TIGHTENING TORQUE IS CRITICAL. INCORRECT TORQUE LOADS WILL CAUSE BOLT
FATIGUE AND RESULT IN BOLT FAILURE.

Make sure you apply the correct torque. The engine frame mounting bolts and nut run-up torque must be
determined during assembly and added to the required torque load.
CAUTION: A NUT RUN-UP TORQUE MORE THAN 50 IN-LBS SHOULD BE INVESTIGATED.

When torque is applied to the bolt heads, the torque needed to overcome the friction of the bolts in the frame
and struts, must be determined. This torque value plus the run-up torque value must then be added to get the
final required torque.
CAUTION: WHEN TIGHTENING OR HOLDING THE TWO BOTTOM NUTS INSIDE THE FUSELAGE, ENSURE

THAT NO SCRATCHING, DENTING, GOUGING OR SIMILAR DAMAGE IS CAUSED TO THE
REINFORCEMENT BRACKETS. DAMAGE MAY CAUSE CRACKING OF THE BRACKETS.

(1) Make sure the two top nuts are secure in the engine strut throat-washers.
NOTE: If necessary, apply adhesive sealant to retain the nuts in position.

(2) Position the mount frame on the firewall.
(3) Install the two top bolts (5) with countersunk washers (4). Do not tighten the bolts in this step.
(4) Install the two bottom bolts (6) with countersunk washers (4) into the mount frame and bottom brackets.
(5) Inside the fuselage, install the washers (2) and nuts (7).
(6) Torque top bolts (5) and bottom bolts (6) to 160-190 in lbs plus the run-up torque.

NOTE: Carefully hold the bottom nuts (7) while applying the torque.
(7) Install fire seals. need link here
(8) Connect the mount frame to the three isolation mounts. See Chp. 71 Engine Isolator Mount Installation
(9) Remove the P&WC lifting equipment.
(10) Reinstall the instrument panels. See Chp. 39 Instrument Panels - Removal and Installation.
(11) Install the cowling. See Chp. 71 Engine Cowling
(12) Remove the tail stand. See Chp. 7 Lifting and Shoring.

Page 402

MAINTENANCE MANUAL SUPPLEMENT 71-20-02- Engine Mount Frame
C550GT-AD016-FU24-0213
Engine Mount Frame Revision: Initial Issue DATE: 01/01/2020

Inspection and Check Maintenance Practices / Inspection and Check
Engine Mount Frame

Inspection and Check

1. Engine Mount Frame Inspection.-150 HRS

(1) Examine the Mount Frame attachment bolts for shear or fretting damage.
(2) Visually examine all tubular parts for distortion, bowing, chafing, corrosion and cracks.
(3) Visually examine all welds for cracks.

WARNING: CRACKS IN ANY AREA OF THE ENGINE MOUNT FRAME ARE NOT PERMITTED.

Result

(1) If you think there is attachment bolt damage, remove the bolt. See Chp. 71 Engine Mount Frame Removal.
(2) Examine the bolts for defects and find the cause of the damage. Replace damaged bolts.
(3) After the visual examination, if you think the Mount Frame has a crack, inspect the frame by Magnetic

Particle Inspection method to ASTM E1444 (active standard)
NOTE: The NDT process can be done with the Mount Frame installed.
If the Mount Frame has a crack, contact the Crusader Aircraft Company (CAC) for support.

Page 601

MAINTENANCE MANUAL SUPPLEMENT 71-20-03-Description
C550GT-AD016-FU24-0213
Description Revision: Initial Issue DATE: 01/01/2020

Description and Operation / Isolator Mounts

Description
Isolator Mounts

71-20-03 Isolator Mounts

Description and Operation

Isolator Description

The C550GT Powerplant Installation uses isolator mounts at the three engine to frame attach points. Each
isolator is made up of two moulded assemblies and a spacer. Each of the moulded assemblies has a metal washer
with elastomer bonded to it.

Isolators - General

The metal washers provide a mounting point for the
through-bolt and make the mount ‘fail-safe’. If an
engine fire were to burn away the elastomer, the engine
will still be restrained by the metal washers and
through-bolt. The spacer’s purpose is to set the preload on
the elastomer by regulating how much the isolator
is compressed when the through-bolt is torqued.

Figure 71.8 Isolator Mount (typical)

Page 1

MAINTENANCE MANUAL SUPPLEMENT 71-20-03- Isolator Mounts
C550GT-AD016-FU24-0213
Isolator Mounts Revision: Initial Issue DATE: 01/01/2020

Removal and Installation Maintenance Practices / Removal and Installation
Isolator Mounts

Maintenance Practices

1. Engine Isolator Mount Removal

(1) Support the rear fuselage with the tail-stand. See Chp. 07 Lifting and Shoring.
(2) Remove the engine cowling. See Chp. 071 Engine Cowling
(3) Support the engine with applicable P&WC lifting equipment. Refer to the P&WC PT6A-15AG Maintenance

Manual, Section 72-00-00, Removal and Installation, Special Tools.
(4) Remove the cotter pin (2) and nut (3) from each bolt (15) that attaches the isolator to the mount frame.
(5) Remove the bolts (15) and washer (14).

NOTE: The bolts have a countersunk washer. On reassembly, the recess must go against the radius of the
bolt head.

(6) Remove the lockwire from the isolator mount bolts and remove the bolts (8) and washers (9)
(7) Remove the mounts.

Figure 71.9 Engine Isolator Mount

2. Engine Isolator Mount Installation
(1) Use a new gasket (11) under the mount housing.
(2) Install the 4 bolts (8) and washers (9).
(3) Note: Make sure the countersunk face of the washer is against the head of the bolt.
(4) Torque the bolts (9) to 275 - 300 in lbs. and safety with lockwire.
NOTE: Make sure the lockwire cannot chafe on the mount assembly.
(5) Assemble the isolator mount as shown in Figure 71.9
(6) Install the mounting bolts (15) with head to the rear. Install washers (14, 4) and nuts (3).
(7) Torque nuts (3) to 480 - 600 in lbs. and safety with a cotter pin (2).
(8) Remove the lifting equipment.
(9) Install the cowling. See Chp. 71 Engine Cowling
(10) Remove the tail stand. See Chp. 07 Lifting and Shoring.

Page 401

MAINTENANCE MANUAL SUPPLEMENT 71-20-03- Isolator Mounts
C550GT-AD016-FU24-0213
Isolator Mounts Revision: Initial Issue DATE: 01/01/2020

Maintenance Practices / Inspection and Check

Inspection and Check
Isolator Mounts

Inspection and Check

Isolator Mount Inspection A.- Visual (150hrs)

See Figure 71.8
Dirt and hydrocarbons should be removed by wiping with a clean rag, soap and water or isopropyl alcohol.

CAUTION: SOLVENTS SHOULD NOT BE USED AS THEY CAN DAMAGE THE ELASTOMER OR THE ELASTOMER-
TO-METAL BOND. ANY LUBRICANTS OR SOLVENTS SPILLED ONTO THE ISOLATORS SHOULD BE
REMOVED FROM THE ISOLATORS AS SOON AS POSSIBLE.

Inspection.
(Isolators mounted on the aircraft with the isolators supporting the weight of the engine.)
Examine the Isolator for:

(1) Condition of the elastomer. The elastomer should free of damage, cracking, or other deterioration.

(2) Integrity of the metal-to-elastomer bond. The elastomer should remain bonded to the metal washers.

NOTE: Failure of the bond can cause excessive drift of the powerplant. If you suspect delamination,
investigate by probing with a blunt-edged instrument. If more than 30% of the edge of a bonded
interface is debonded over ¼” in depth, the isolator should be replaced.

(3) Inspect the metal washers (as visible) for corrosion or damage.

NOTE: Minor damage can be blended out by hand. The depth of the rework must not exceed 10% of the
material thickness.

(4) Examine the structure around the engine (cowling, prop spinner) for signs of damage caused by excessive

drift of the engine. If damage is found, investigate the cause.

NOTE: Excessive drift can be caused by a too-soft isolator, delamination, or by elastomer creep that occurs
over time.

Result

If you find any of the defects above, disassemble the isolators and do Inspection B.

Isolator Mount Inspection B. – Disassembled. (600hr)
(1) Support the engine and disassemble each isolator mount, one at a time.
See Chp. 71 Engine Isolator Mount Removal

(2) Examine the nylon sleeve (12) for indications of damage.
NOTE: Damage to the nylon sleeve indicates that the isolator has deteriorated. It has deflected and the
mount (10) has contacted the limiting sleeve. The isolator cannot support the powerplant weight or
thrust loads effectively.

Result.

If you find damage to the nylon sleeve (12), replace the isolator (7) and sleeve (12).

(3) Reassemble the Isolator mount. See Chp. 71 Engine Isolator Mount Installation

Page 601

MAINTENANCE MANUAL SUPPLEMENT 71-30-00-Description
C550GT-AD016-FU24-0213
Description Revision: Initial Issue DATE: 01/01/2020

Description and Operation / Engine Fireseals

Description
Engine Fireseals

71-30-00 Engine Fireseals

Description and Operation

Powerplant Fireseals

The PT6A-15AG engine is surrounded by two steel fireseal baffles which form a plenum for engine induction air.
The C550GT powerplant installation has fireseal baffles with outer periphery rubber seals that attach with screws
to these engine fireseal baffles. The rubber seals on the front and rear baffles seal into slots in the cowling.

The Cowling is described fully in STC 10/21E/17 Installation of Filtered Engine Cowl and Instructions for
Continued Airworthiness AD016-08600-0239-ISS1.
Ref. Ext. Doc: Instructions for Continued Airworthiness AD016-08600-0239 ISS1, Alternate Engine Cowls STC
10/21E/17.

Also refer to these drawings,
Ref. Dwg. No: AD-08600-7130-001-100

Ref. Dwg. No: AD-08600-7130-001-200

The rear fireseal baffles have provision for the engine mount frame tubes to pass through them. Six baffle mount
plates are installed on the frame mount tubes. The baffle mount plates support the baffle and provide a seal
around the frame tubes.

Figure 71.10 Powerplant Fireseals
Page 1

MAINTENANCE MANUAL SUPPLEMENT 71-30-00- Fireseals
C550GT-AD016-FU24-0213
Fireseals Revision: Initial Issue DATE: 01/01/2020

Removal and Installation Maintenance Practices / Removal and Installation
Fireseals

Maintenance Practices
Removal and Installation

1. Rear Fireseal Removal.
Ref. Dwg. No: AD-08600-7130-001-200

See Figure 71.11
CAUTION: IF ANY OBJECT FALLS INTO THE ENGINE COMPRESSOR INLET, ALL WORK MUST CEASE UNTIL

THE OBJECT IS RECOVERED.

(1) Disconnect the torque pressure hoses from the LH fireseal and cap them.
(2) Remove the AN3 bolts and hose clamps from the 6 fireseal frame mounts (10, 11, 12, 13, 14, 15).
(3) If installed, disconnect the flexible heater hose from the bulkhead fitting on the LH fireseal.
(4) Remove the screws from the fairleads that support the Engine Vent Air hose. Remove the hose.
(5) Remove the two screws (33) from the top center strap (9) where the fireseals meet.

NOTE: If necessary, cut the rubber seal at top center.
(6) Remove the bolts and nuts necessary to allow removal of the outer fireseal baffles (2, 3, 4, 5, 6, 7 and 8)

from the inner engine fireseals (23, 24).
(7) If necessary, remove the 8/32” screws and nuts that attach the rubber fireseals to the outer fireseal baffles

and remove the rubber fireseals.

Figure 71.11 Rear Fireseal Installation.

Page 1

MAINTENANCE MANUAL SUPPLEMENT 71-30-00-Fireseals
C550GT-AD016-FU24-0213
Fireseals Revision: Initial Issue DATE: 01/01/2020

Maintenance Practices / Removal and Installation

Figure 71.12 Forward and Rear Fireseal Assemblies.

2. Rear Fire Seal Installation.
Ref. Dwg. No: AD-08600-7130-001-200
CAUTION: IF ANY OBJECT FALLS INTO THE ENGINE COMPRESSOR INLET, ALL WORK MUST CEASE UNTIL
THE OBJECT IS RECOVERED.
See Figure 71.11
(1) Position the rear fireseal baffles (2, 3, 4, 5, 6, 7 and 8) on the engine plates (23, 24) and attach with the AN3
bolts and nuts.
(2) Attach the silicon rubber fireseals and backing strips to the outer fireseal baffles with the 8/32” screws and
nuts.
(3) Install the top center strap (9) where the fireseals meet using the two screws (33).
NOTE: If the rubber seal at top center was cut during removal, repair the join with a suitable high
temperature silicone adhesive/sealant.
(4) Position the support fairlead and install the Engine Vent Hose, attach with the screws, washers and nuts.
(5) Reconnect the flexible heater hose to the bulkhead fitting on the LH fireseal.
(6) Install the AN3 bolts and hose clamps to the 6 fireseal frame mounts (10, 11, 12, 13, 14, 15).
(7) Remove the caps and reconnect the torque pressure hoses from the LH fireseal.

Page 2

MAINTENANCE MANUAL SUPPLEMENT 71-30-00-Fireseals
C550GT-AD016-FU24-0213
Fireseals Revision: Initial Issue DATE: 01/01/2020

Maintenance Practices / Removal and Installation

3. Forward Fireseal Removal
Ref. Dwg. No: AD-08600-7130-001-100
(1) Remove the thirty-two 8/32” screws and nuts holding the rubber fireseal seal and support backing strips (4,
5, 6, 7, 8, 9, and 10).
(2) Remove the rubber fireseal seal and support backing strip.
NOTE: If necessary, cut the rubber fireseal at the joining point.
(3) Remove the clamps that support the T5 Wiring (ITT).
(4) Remove the -3 and -4 torque pressure lines from bulkhead fittings.
NOTE: Put caps on the fittings and hoses.
(5) Remove the AN3 bolts and nuts that attach the fireseal to the engine flange.
(6) Remove the LH and RH fireseals from the engine.

4. Forward Fireseal Installation
Ref. Dwg. No: AD-08600-7130-001-100
(1) Position the LH and RH fireseals (2,3) on the engine flanges and attach with the AN3 bolts and nuts.
(2) Reconnect the torque pressure lines.
(3) Install the T5 wiring (ITT) with the P-Clamps.
(4) Attach the rubber fireseal (15) and backing strips (4, 5, 6, 7, 8, 9, and 10) with the thirty-two 8/32” screws
and nuts.

Page 3

MAINTENANCE MANUAL SUPPLEMENT 71-30-00- Fireseal Baffles
C550GT-AD016-FU24-0213
Fireseal Baffles Revision: Initial Issue DATE: 01/01/2020

Inspection and Check Maintenance Practices / Inspection and Check
Fireseal Baffles

Inspection and Check

Inspection of Fireseal Baffles.
Refer to Alternate Engine Cowls STC 10/21E/17.

Ref. Ext. Doc: Instructions for Continued Airworthiness AD016-08600-0239 ISS1, Alternate Engine Cowls STC
10/21E/17.

NOTE: See Section 3.4 for Inspection requirements.

Page 1

MAINTENANCE MANUAL SUPPLEMENT 71-50-00-Electrical
C550GT-AD016-FU24-0213
Electrical Revision: Initial Issue DATE: 01/01/2020

Powerplant Electrical Description and Operation / Powerplant Electrical
Electrical

71-50-00 Powerplant Electrical

Description and Operation

Description and Operation

The Powerplant electrical harness is integrated with the aircraft main electrical loom. Circuits in the engine
compartment control or sense parameters in these systems:

• Starter Generator System.
• Gas Generator RPM (Ng)
• Propeller RPM (Np)
• Torque.
• Gearbox chip detector.
• Air Filter Obstruction warning.
• Beta position.
• Over-speed Governor test.
• Oil Temperature.
• Oil Pressure warning.
• Oil Pressure.
• Fuel Pressure.
• Interturbine Temperature (ITT)
• Ignition System.
• Py Air Anti-Ice.

Troubleshooting
Refer to the applicable Wiring Schematic for Description and Troubleshooting
Ref. Dwg. No: AD-550GT-7700-001-201

Ref. Dwg. No: AD-550GT-2430-001-001

Ref. Dwg. No: AD-550GT-7510-001-001

Powerplant Electrical Loom Inspection.
(1) Examine the wiring for chafing, burns and oil contamination.
(2) Check that terminals and connectors are correctly connected.
(3) Examine the loom support clamps. Make sure the clamps support and contain the loom without strain.
(4) Make sure the loom is clear of all controls, hot components and possible rub points

Page 1

MAINTENANCE MANUAL SUPPLEMENT 71-60-00-Cowling Air Intake
C550GT-AD016-FU24-0213
Cowling Air Intake Revision: Initial Issue DATE: 01/01/2020

Cowling Air Intake Description and Operation / Air Intake System
Air Intake System

71-60-00 Air Intake System

Description and Operation

Adjustment and Test

Description and Operation

Refer to the Engine Cowls STC 10/21E/17E
Ref. Ext. Doc: Instructions for Continued Airworthiness AD016-08600-0239 ISS1, Alternate Engine Cowls STC
10/21E/17.

1. Servicing.

For Air Filter Cleaning and Replacement procedures
Ref. Ext. Doc: Instructions for Continued Airworthiness AD016-08600-0239 ISS1, Alternate Engine Cowls STC
10/21E/17.

2. Adjustment and Test

Differential Pressure Switch Setting – Filter Dirty Warning Light

For pressure switch Adjustment and Test procedures.
Ref. Ext. Doc: Instructions for Continued Airworthiness AD016-08600-0239 ISS1, Alternate Engine Cowls STC
10/21E/17.

Page 1

MAINTENANCE MANUAL SUPPLEMENT 71-70-00-Engine Fluid Drains
C550GT-AD016-FU24-0213
Engine Fluid Drains Revision: Initial Issue DATE: 01/01/2020

Description and Operation / Drains

Engine Fluid Drains
Drains

71-70-00 Engine Fluid Drains

Description and Operation

Engine Fluid Drains.

The compressor section and combustion section drain overboard through the lower cowl.
Drains from the accessory drives are routed overboard through the nose landing gear cut-out at the rear of the
lower cowl.

Figure 71.13 Combustor Drains

Figure 71.14 Accessory Housing Component Drains
Page 1

MAINTENANCE MANUAL SUPPLEMENT 71-70-00- Engine Fluid Drains
C550GT-AD016-FU24-0213
Engine Fluid Drains Revision: Initial Issue DATE: 01/01/2020

Inspection and Check Maintenance Practices / Inspection and Check
Engine Fluid Drains

Inspection and Check

Engine Fluid Drains
Monitor the Accessory Housing and Component drains at the rear of the engine compartment.

Starting Control Drain.

When the Fuel Condition Lever is moved to the CUTOFF position, it is normal for the Starting Control to dump
fuel from the drain. With the Fuel Condition Lever in the GRD-IDLE position and the engine running, make sure
there is no fuel dripping from the drain.

CAUTION: FUEL LEAKAGE FROM THE STARTING CONTROL DRAIN DURING ENGINE OPERATION IS NOT
PERMITTED.

Refer to P&WC Maintenance Manual, Turboprop Gas Turbine Engine, Model PT6A-15AG Manual Part No.3030442
(latest revision) Chapter 73-10-04 Starting Control - Maintenance Practices.

Fuel Control Unit (FCU) Seepage Drain.

Blue dye leaking from the fuel pump seal drain port indicates possible contamination of, or damage to, the FCU
driveshaft bearing by grease/lubricant wash-out.

CAUTION: LEAKAGE OF FUEL OR BLUE DYE IS NOT ACCEPTABLE. IF LEAKS ARE FOUND, REJECT FCU AND
SEND UNIT FOR RECTIFICATION TO AN APPROVED OVERHAUL FACILITY.

Refer to P&WC Maintenance Manual, Turboprop Gas Turbine Engine, Model PT6A-15AG Manual Part No.3030442
(Latest Revision) Chapter 73-20-00 Fuel Control Unit - Maintenance Practices, Section 7 - Inspection/Check, B.
Leakage Inspection.

Page 1

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

Title Page Engine Fuel and Control

Chapter 73
Engine Fuel and Control

Chapter 73 Engine Fuel & Control

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

Chapter Contents Engine Fuel and Controls
Engine Fuel and Controls

Chapter Contents

Chapter 73 Engine Fuel & Control

Applicable Section Guide
73-00-00 Engine Fuel and Control
73-10-00 Distribution
Description and Operation
73-00-00 Engine Fuel and Controls
73-20-00 Controlling
Description and Operation
> General
> Engine Fuel System
> Control Quadrant
> Push-Pull Cables
> Engine Fuel Controls

Components Changed By This STC
Maintenance Practices

Removal and Installation
> Control Quadrant Removal.
> Control Quadrant Installation.
> Power Lever - Control Cable Removal.
> Power Lever - Control Cable Installation.
> Fuel Condition Lever - Control Cable Removal.
> Fuel Condition Lever - Control Cable Installation.
73-30-00 Engine Fuel and Control - Indicating
Description and Operation
> Indicating System.
Removal and Installation
> Fuel Pressure Transducer.
> Fuel Flow Transducer Removal.
> Fuel Flow Transducer Installation.
Adjustment and Test
> Fuel Indicating System components.

MAINTENANCE MANUAL SUPPLEMENT 73-00-00 - 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
73-00-00 Engine Fuel & Controls
Description and Operation 

General 
73-10-00 Distribution 

Fuel Distribution- Firewall Forward 
73-20-00 Controlling
Description and Operation 

Engine Fuel System 
Control Quadrant 
Power Lever 
Fuel Condition Lever 
Maintenance Practices
Removal and Installation
Control Quadrant Removal
Control Quadrant Installation
Power Control Cable Removal
Power Control Cable Installation
Fuel Condition Control Cable Removal
Fuel Condition Control Cable Installation
Adjustment and Test

Inspection and Check

73-30-00 Indicating 
Description and Operation 

MVP-50T Engine Monitor Panel
Fuel Pressure Transducer 
Fuel Flow Transducer 
Maintenance Practices
Removal and Installation 
Fuel Pressure Transducer
Fuel Flow Transducer

Adjustment and Test
Fuel Indicating System Components

MAINTENANCE MANUAL SUPPLEMENT 73-10-00-Engine Fuel- Distribution
C550GT-AD016-FU24-0213
Engine Fuel- Distribution Revision: Initial Issue DATE: 01/01/2020

Engine Fuel- Distribution Description and Operation / Engine Fuel & Control
Engine Fuel & Control

73-00-00 Engine Fuel and Control
73-10-00 Distribution

Description and Operation

Description and Operation
The Engine Fuel Distribution section is the portion of the Fuel System from the firewall forward. This includes all
plumbing, fuel pump, valves, filters, manifold and nozzles. These components are integral parts of the PT6A-
15AG Turboprop Gas Turbine Engine. Refer to the P&WC PT6A-15AG Engine Manual, Chapter 73-00-00 Engine
Fuel and Control.

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

Page 1

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

Control Quadrant Description and Operation / Control Quadrant
Engine Fuel & Controls

73-20-00 Controlling

Description and Operation

Engine Fuel and Controls - Description and Operation

General

The Engine Fuel and Controls are those components that deliver and control metered fuel to the
engine combustion chamber. This includes compensation for changes in ambient temperature, compressor
discharge pressure and Gas Generator RPM.

Engine Fuel System

The PT6A-15AG Fuel System consists of an oil-to-fuel heater, fuel pump, fuel control unit, starting control and
dump valve, dual fuel manifold with 14 simplex nozzles, fuel drain valves and interconnecting pneumatic sense
lines. For Description and Operation refer to P&WC Maintenance Manual, Turboprop Gas Turbine Engine, Model
PT6A-15AG Manual Part No. 3030442 (latest revision). Chapter 73-00-00 Engine Fuel and Control - Description
and Operation.

Control Quadrant

The C550GT Control Quadrant is very similar in construction and mounting to the FU24-954 dual control
configuration. The three levers mount in an engine controls quadrant that attaches in a central position below the
flight instrument panel. The quadrant has an adjustable friction damper that effects all levers.

Push-Pull Cables

All three control levers connect to the applicable engine components using Cablecraft push-pull cables. These
cables are low friction with a minimal loss of motion. The outer jacket is fuel, oil and abrasion resistant and the
inner liner is PTFE. Cablecraft cables do not require lubrication, this will damage the cable.
At the quadrant, each push-pull cable outer-sleeve terminates with a clamp at a re-designed two-piece bracket.

Engine Fuel Controls

Power Lever
The control quadrant power lever connects through airframe linkages to the cambox assembly, mounted in front
of the FCU at the rear of the engine. An interconnect rod from the cambox to the fuel control unit schedules the
full range of operational engine power. It also selects the propeller pitch (Beta control) from reverse selection up
to the constant speed RPM selected by the cockpit propeller control lever.

Fuel Condition Lever
The Fuel Condition Lever connects to the Starting Control to manually control fuel supply and cut-off.
The starting control lever opens and closes a manually operated plunger in the starting flow
control that selects fuel cut-off, starting and run positions. The Start Button is located in the top of the lever.

Propeller Control Lever
Refer to Chapter 61 for information on the Propeller Controls.
Link to this section.

Page 1

MAINTENANCE MANUAL SUPPLEMENT 73-20-00 - Components Changed Table
C550GT-AD016-FU24-0213
Components Changed Table Revision: Initial Issue DATE: 01/01/2020

Components Changed Table CCBTS / Engine Fuel & Controls
Engine Fuel & Controls

Components Changed By This STC

Drawing Number Item Part Number Description / Location

Engine Control Quadrant

AD-550GT-7600-001-000 1 08-47153-1 Bracket, Prop. Control

AD-550GT-7600-001-000 2 08-47183-1 Quadrant Assembly

AD-550GT-7600-001-000 5 580-727-007 Cable

AD-550GT-7600-001-000 6 031804 Clamp

AD-550GT-7600-001-000 7 AD-550GT-7600-001-010 Bracket

AD-550GT-7600-001-000 8 AD-550GT-7600-001-030 Bracket

AD-550GT-7600-001-000 9 AD-550GT-7600-001-040 Doubler

AD-550GT-7600-001-000 10 AD-550GT-7600-001-050 Doubler

AD-550GT-7600-001-000 11 AD-550GT-7600-001-060 Bracket

AD-550GT-7600-001-000 12 AD-550GT-7600-001-070 Bracket

AD-550GT-7600-001-000 13 AD-550GT-7600-001-080 Bracket

AD-550GT-7600-001-000 14 AD-550GT-7600-001-100 Bracket

AD-550GT-7600-001-000 25 11-47001-2 Fork End

AD-550GT-7600-001-000 28 TF3 Rod End

Engine Power and Starting Controls.

AD-550GT-7600-001-000 37 08-47145-1 Control Bracket Clamp

AD-550GT-7600-001-000 3 08-47209-1 Bracket, Power Control

AD-550GT-7600-001-000 4 0847211-1 Bracket, Condition Lever

AD-550GT-7600-001-000 6 031804 Clamp

AD-550GT-7600-001-000 32 08-47217-1 Packer

AD-550GT-7600-001-000 33 08-47139-2 Throttle Lever

AD-550GT-7600-001-000 35 08-47213-1 Bellcrank

Indicating

AD-550GT-2820-005-000 1 AD-550GT-2820-005-001 Bracket

AD-550GT-2820-005-000 2 AD-550GT-2820-005-002 Bracket

AD-550GT-2820-005-000 7 FT-180 Flow Transducer

Page 2

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

Removal and Installation Maintenance Practices / Removal and Installation
Engine Fuel & Controls
Maintenance Practices
Engine and Propeller Control Quadrant. Removal and Installation
See Figure 73.1

1. Control Quadrant Removal.
Ref. Dwg. No: AD-550GT-7600-001-000
(1) Set the master Switch to OFF.
(2) Disconnect the wiring to the Start Button.

CAUTION: WHEN YOU REMOVE OR DISASSEMBLE THE QUADRANT, DO NOT MOVE THE POWER LEVER. YOU
CAN DAMAGE THE PROPELLER LINKAGE.

(3) Remove the cotter pins, washers and clevis pins that attach the control cables to each lever.
(4) Remove the bolts, nuts and washers that attach the quadrant to the channels on the horizontal bulkhead.
(5) Support the quadrant while you remove the two forward screws at the side of the quadrant.
(6) Lift the quadrant clear of the instrument panel bulkhead.

NOTE: Brackets (14) and (8) and associated cable clamps (6) and cables (5) remain in place.

2. Control Quadrant Installation.
Ref. Dwg. No: AD-550GT-7600-001-000
(1) Position the control quadrant inside the two frames on the horizontal bulkhead.
NOTE: The bottom bracket (14) attaches with the same bolts in the next step.
(2) Install the bolts, nuts and washers that attach the quadrant to the horizontal bulkhead channels.
(3) Install the two forward screws at the side of the quadrant.
(4) Position each cable clevis, install the cotter pins, washers and clevis pins that attach the control cables to
each lever.
(5) Connect the wiring to the Start Button.
(6) Check the Engine Control rigging and adjust if necessary. See Chp. 76 Rigging Procedures

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

(7) Do a function test of the Start Button. Motor the engine. Refer to the POH (Link)

Page 401

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

Figure 73.1 Control Quadrant

Page 402

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

Engine Control Push-Pull Cables

1. Power 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 Power 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).
(6) In the engine compartment
(7) At the cambox input lever (33), remove the cotter pin and the nut (30), washers and bolt (29) from the rod

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

engine control bracket (3).
(9) Carefully withdraw the control cable (5) forward into the engine compartment and clear of the aircraft.

2. Power 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.
(3) Route the cable to the engine control bracket (3).

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 (3) 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 cambox input-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 Power Lever. See Chp. 73 Control

Quadrant 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 Power Lever through its full range of motion. Make sure the cable moves smoothly without

binding.

Page 403