C550GT ICA v.8 11-09-2020 copy

MAINTENANCE MANUAL SUPPLEMENT 28-20-00- Fuel Sys. Leak Test
C550GT-AD016-FU24-0213
Fuel Sys. Leak Test Revision: Initial Issue DATE: 01/01/2020

Fuel Sys. Leak Test Maintenance Practices / Adjustment & Test
Adjustment & Test

1. Fuel Distribution Leak Test.

Non-pressurised components.
The Fuel Distribution System between the LE tanks and the outlet of the Fuel Boost Pump functions under gravity
pressure.
(1) Make sure there is sufficient fuel in the Fuel Tanks.

(2) Examine all connections and components in the Component Fuel Bay for signs of fuel leakage.

(3) Examine the area between each LE Fuel tank for fuel leakage.

(4) Check the Curtis drain valves on each LE tank for leakage.

Pressurised Components.
Leak test the remaining components of the Fuel System, up to the engine’s HP Fuel Pump.
(1) Connect the aircraft electrical system to a Ground Power Unit (GPU) during the test.
(2) In the cockpit, set the Condition Lever to the FUEL OFF position.
(3) Set the Fuel Shut-off tee handle to OFF.
(4) Set the Master Switch ON.
(5) Make sure the FUEL P annunciator on the Engine Monitor Panel is ON.
(6) Set the Fuel Shut-off tee handle to ON.
(7) Make sure the FUEL P annunciator on the Engine Monitor Panel goes OFF.

NOTE: The fuel system is now pressurised.
(8) Examine all connections and components up to the inlet of the Fuel/Oil Heater for signs of fuel leakage.
(9) Set the Fuel Shut-off tee handle to OFF.
(10) Set the Master Switch OFF.

Page 504

MAINTENANCE MANUAL SUPPLEMENT 28-00-00 - AF Filter Bypass Test
C550GT-AD016-FU24-0213
AF Filter Bypass Test Revision: Initial Issue DATE: 01/01/2020

AF Filter Bypass Test Adjustment & Test
Adjustment & Test

1. Fuel Filter Switch and Bypass Valve
Operational Test

This test checks that the by-pass valve operates correctly. A partially blocked filter element will cause a
differential pressure switch in the Airframe Filter head assembly to close.
When this switch activates the FUEL FLTR annunciator on the Engine Monitor Panel will come ON. If the filter
element becomes fully blocked a differential pressure activated valve will permit fuel to bypass the filter.

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

Warning Light Test.
(1) In the cockpit, set the Master Switch to ON
(2) Check the annunciator panel. Make sure the FUEL FLTR light is OFF.
(3) Open the RH side access hatch to the Fuel Component bay.
(4) Press the differential pressure switch Test Button on the top of the Airframe Fuel Filter.
(5) The FUEL FLTR annunciator must illuminate.
(6) Set the master switch to OFF.

Bypass Valve Test.
(1) Replace filter element with a clean dummy element. Refer to Airframe Fuel Filter Servicing. See Chp. 28

Airframe Fuel Filter Servicing.
(2) Start and run the engine. (Refer to the POH)
(3) Result
(4) The FUEL FLTR annunciator illuminates and the engine operates normally.
(5) When test is successfully completed, shut down the engine.
(6) Remove the dummy element and install a new filter element. See Chp. 28 Airframe Fuel Filter Servicing.

Page 505

MAINTENANCE MANUAL SUPPLEMENT 28-40-00-System Description
C550GT-AD016-FU24-0213
System Description Revision: Initial Issue DATE: 01/01/2020

Description and Operation / Fuel Quan.Indicating

System Description
Fuel Quan.Indicating

28-40-00 Fuel Quantity Indicating

Description and Operation

Description and Operation

Each LE Fuel Tank has a capacitive fuel quantity probe. The recessed probe housing in the top tank skin has an
aerodynamic cover. The wiring for the probe connects through sealed rigid tubing inside the tank and terminates
at the outboard rib. This design allows removal and installation of the probe without draining fuel.

The Engine Data Converter (EDC) processes fuel level data from each probe for display on the MVP-50T Engine
Monitor Panel. Each LE Tank has a vertical strip type Fuel Quantity indicator.

Refer to Chapter 77-40- Integrated Engine Instrument Systems for configuration of the display and calibration of
the indicating system. (Link to Chp 77-40-00)

Page 1

MAINTENANCE MANUAL SUPPLEMENT 28-40-00- Troubleshooting
C550GT-AD016-FU24-0213
Troubleshooting Revision: Initial Issue DATE: 01/01/2020

Troubleshooting / Fuel Quantity Indicating

Troubleshooting
Fuel Quantity Indicating

Troubleshooting

Fuel Quantity Indicating System.

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

NOTE: For troubleshooting, refer to Section 7.0 of the Electronics International Inc. Glass Panel Engine
Monitor MVP-50T (for Turboprops and Jets) Installation Instructions (II-1211061, Latest Revision)

Page 101

MAINTENANCE MANUAL SUPPLEMENT 28-40-01- Fuel Quantity Probe
C550GT-AD016-FU24-0213
Fuel Quantity Probe Revision: Initial Issue DATE: 01/01/2020

Removal & Installation Maintenance Practices / Removal & Installation
Fuel Quantity Probe

Maintenance Practices
Removal and Installation

1. Fuel Quantity Probe Removal.
Ref. Dwg. No: AD-550GT-2840-001-000

WARNING: OBSERVE ALL FIRE AND SAFETY PRECAUTIONS. MAKE SURE ALL PERSONNEL KNOW THE
DANGERS OF FUEL VAPOUR AND LEAKAGE WHILE WORKING ON AN OPEN FUEL TANK.

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

(1) Set the master switch to OFF.
(2) Place a placard on the switch panel. DO NOT TURN MASTER SWITCH ON.
(3) To access the fuel probe, remove the domed cover (2).
(4) Disconnect the wiring to the probe.

NOTE: Carefully remove the insulation to access the connectors.

WARNING: TO ELIMINATE THE DANGER OF FIRE, MAKE SURE TO REINSULATE THE CONNECTORS BEFORE
ANY FURTHER WORK IS DONE ON THE FUEL SYSTEM.

(5) Carefully loosen the probe. Remove it from the housing and the fuel tank.

2. Fuel Quantity Probe Installation.
Installation of a capacitive fuel probe is different for Inboard and Outboard Tanks.

Inboard LE Fuel Tanks have 5 internal ribs. The probe support fairlead is in the first rib that the probe passes
through.
Ref. Dwg. No: AD-550GT-2810-001-000

Outboard LE Tanks have 3 internal ribs. The probe support fairlead is in the last rib that the probe passes
through.
Ref. Dwg. No: AD-550GT-2810-003-000

(1) Apply a small amount of fuel compatible thread sealant to the probe (19).
(2) Carefully insert the probe (19) into the fuel tank through the threaded hole in the housing.

NOTE: Make sure you angle the probe, so it passes through the fairlead in the rib support bracket.
(3) Tighten the probe.

CAUTION: DO NOT OVER-TIGHTEN THE PROBE. DAMAGE TO THE BONDING OF THE THREADED COUPLER
CAN OCCUR.

(4) Connect the wiring.
NOTE: Insulate the connection. Damage will occur if moisture gets into the connectors.

(5) Calibrate the Fuel Quantity Indicating System See Chp. 28 Fuel Quantity Indicating Calibration
(6) Install the domed cover (2).

Page 401

MAINTENANCE MANUAL SUPPLEMENT 28-40-01- Fuel Quantity Indicating Calibration
C550GT-AD016-FU24-0213
Fuel Quantity Indicating Calibration Revision: Initial Issue DATE: 01/01/2020

Fuel Quantity Indicating Calibration Maintenance Practices / Adjustment & Test
Adjustment & Test

Adjustment and Test

1. Fuel Quantity Indicating Calibration
If a fuel probe is replaced, calibrate the Fuel Quantity Indicating System.

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

NOTE: Section 7.0 of these instructions provide information to correctly calibrate the C550GT Fuel Quantity
Indicating System.

Page 501

MAINTENANCE MANUAL SUPPLEMENT 31-00-00 - Indicating and Reporting Systems
C550GT-AD016-FU24-0213
Chapter 31 Revision: Initial Issue DATE: 01/01/2020

Title Page Indicating and Reporting Systems

Chapter 31
Indicating and Reporting Systems

Chapter 31 Indicating and Reporting
Systems

MAINTENANCE MANUAL SUPPLEMENT 31-00-00 - Indicating and Reporting Systems
C550GT-AD016-FU24-0213
Chapter Content Revision: Initial Issue DATE: 01/01/2020

Chapter Content Indicating and Reporting Systems
Indicating and Reporting Systems

Chapter Contents

Chapter 31 Indicating and Reporting Systems

Applicable Section Guide
31-30-00 Reporting Systems

Description and Operation
> G-Meter.
> Troubleshooting.
> Removal and Installation.
> Adjustment and Test.

31-50-00 Lift Detector System
Description and Operation
> Lift Detector Components
Troubleshooting
Maintenance Practices
> Lift Detector Switch Removal.
> Lift Detector Switch Installation.
Adjustment and Test
> Lift Detector System- Functional Test.
> Lift Detector Switch- Position Check and Adjustment.

MAINTENANCE MANUAL SUPPLEMENT 31-00-00 - 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
31-00-00 Indicating and Recording Systems
31-30-00 G-Meter 
Description and Operation 

G-Meter 
Troubleshooting 

Vendor Manual Reference
Maintenance Practices
Removal and Installation

Vendor Manual Reference
Adjustment and Test

Vendor Manual Reference

31-50-00 Lift Detector 
Description and Operation 

Lift Detector 
Troubleshooting 

Wiring Schematic 
Maintenance Practices
Removal and Installation

Lift Detector Removal
Lift Detector Installation
Adjustment and Test
Functional Test
Position Adjustment

MAINTENANCE MANUAL SUPPLEMENT 31-30-01-E.I. Inc G-Meter
C550GT-AD016-FU24-0213
E.I. Inc G-Meter Revision: Initial Issue DATE: 01/01/2020

E.I. Inc G-Meter Description and Operation / Reporting Systems
Reporting Systems

31-30-00 Reporting Systems

Description and Operation

1. G-Meter.

Description and Operation

The G-Meter value displays in the lower LH side of the MVP-50T Engine Monitor Panel main screen.
The system has a module that measures 3 axes of g-force. This module mounts to a vertical bracket behind the
instrument panel.
The MVP-50T uses the G-Meter function to record g-forces in all stages of flight.

Troubleshooting.
Ref. Ext. Doc: Electronics International Inc. Glass Panel Engine Monitor MVP-50T (for Turboprops and Jets)
Installation Instructions (II-1211061, latest revision).

NOTE: Refer to Section 7.0 Troubleshooting
Removal and Installation.
Ref. Ext. Doc: Electronics International Inc. Glass Panel Engine Monitor MVP-50T (for Turboprops and Jets)
Installation Instructions (II-1211061, latest revision)
Adjustment and Test.
Ref. Ext. Doc: Electronics International Inc. MVP-50T Instructions for Continued Airworthiness (Doc. 06201101,
latest revision).

NOTE: These instructions provide information to configure the system and calibrate the sensors.

Page 1

MAINTENANCE MANUAL SUPPLEMENT 31-50-01-Lift Detector System
C550GT-AD016-FU24-0213
Lift Detector System Revision: Initial Issue DATE: 01/01/2020

Lift Detector System Description and Operation / Warning Systems
Warning Systems

31-50-00 Lift Detector System

Description and Operation

Lift Detector Components

The Lift Detector System is an electrical audio warning that tells the pilot of an impending stall. The warning horn
will sound approximately 5 knots prior to a stall condition.

The system has 4 components.

(1) A 5 AMP Circuit breaker on the Switch Panel.
(2) A lift detector switch on the leading edge of the centre wing RH side.
(3) A warning horn on the upper surface of the horizontal bulkhead.
(4) Related wiring and connectors.

For wiring,
Ref. Dwg. No: AD-550GT-3340-001-000

For Installation,
Ref. Dwg. No: AD-550GT-3100-001-000

Page 1

MAINTENANCE MANUAL SUPPLEMENT
C550GT-AD016-FU24-0213
Lift Detector

Troubleshooting

Troubleshooting Figure 31.1 Lift De
Lift Detector

31-50-01-Lift Detector DATE: 01/01/2020
Revision: Initial Issue
Troubleshooting

etector Sys. Wiring

Page 101

MAINTENANCE MANUAL SUPPLEMENT 31-50-01- Lift Detector Switch
C550GT-AD016-FU24-0213
Lift Detector Switch Revision: Initial Issue DATE: 01/01/2020

Removal and Installation Maintenance Practices / Removal and Installation
Lift Detector Switch

Maintenance Practices

1. Lift Detector Switch Removal.
Ref. Dwg. No: AD-550GT-3340-001-001
(1) Set the battery Master switch to OFF.
(2) Project the position of the switch vane onto the front plate of the component to provide a datum for
installation. See Figure 31.2
(3) Remove the four screws (1) and carefully remove the lift detector switch (2) from the leading edge.
NOTE: The wiring connects at the rear of the switch.
(4) Disconnect wires W3 (ground) and W2 (power) and insulate the connector on W2.
(5) Remove the lift detector switch (2).

2. Lift Detector Switch Installation.
Ref. Dwg. No: AD-550GT-3340-001-001
(1) Connect the wiring to the terminals at the rear of the Lift Detector Switch.
(2) Make sure that the vane aligns with the datum line on the front cover, then use the screws (1) to install the
lift detector switch. See Figure 31.2
(3) Do a Functional Test of the Lift Detector System. See Chp. 31 Lift Detector System- Functional Test.
(4) Do a Position Check and Adjustment of the lift detector switch. See Chp. 31 Lift Detector Switch- Position
Check and Adjustment.

Figure 31.2 Lift Detector System.

Page 401

MAINTENANCE MANUAL SUPPLEMENT 31-50-01- Lift Detector System
C550GT-AD016-FU24-0213
Lift Detector System Revision: Initial Issue DATE: 01/01/2020

Adjustment and Test Maintenance Practices / Adjustment and Test
Lift Detector System

Adjustment and Test

1. Lift Detector System- Functional Test.

(1) Set the Battery Master switch to ON.
(2) Lift the vane of the lift detector switch, the stall warning horn will sound immediately.
(3) Release the vane of the lift detector switch.
(4) Set the Battery Master switch to OFF.

2. Lift Detector Switch- Position Check and Adjustment.
See Figure 31.2

NOTE: Adjustment of the lift detector switch will require flight testing the aircraft.
(1) Flight test the aircraft.
Note the airspeed that the stall warning horn sounds and the speed that the stall occurs.

NOTE: The stall warning horn should sound 5 knots before a stall.
(2) If necessary, adjust the switch.
(3) Loosen the two screws (3) sufficiently to reposition the switch (4). Move the switch slightly upwards to

decrease speed that the warning horn sounds, or downwards to increase the speed that the warning horn
sounds.
(4) Tighten the two screws (3).
(5) Repeat these steps until the position of the switch is correct.
Title Page

Page 501

MAINTENANCE MANUAL SUPPLEMENT 32-00-00 - Landing Gear DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Landing Gear
Chapter 32

Title Page

Chapter 32
Landing Gear

Chapter 32 Landing Gear

MAINTENANCE MANUAL SUPPLEMENT 32-00-00 - Landing Gear DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Landing Gear
Chapter Content

Chapter Content
Landing Gear

Chapter Contents

Chapter 32 Landing Gear

Applicable Section Guide
32-00-00 Landing Gear
> Description and Operation

Components Changed By This STC
32-10-00 Main Landing Gear

Description and Operation
> Description / Differences.

Maintenance Practices
Removal and Installation
> Reassembly and Installation.

32-10-01 MLG Torque Link
> MLG Torque Link Removal.
> MLG Torque Link Installation.

32-10-02 MLG Axle & Brake Torque Plate
> MLG Axle and Brake Torque Plate Removal
> MLG Axle and Brake Torque Plate Installation
Inspection and Check
> Wing Rib Inspection.
> Main Landing Gear-Cylinder Inspection.

32-20-00 Nose Landing Gear
Description and Operation
> Description and Operation / Differences.
Maintenance Practices
> Nose Landing Gear Disassembly.
> Nose Landing Gear Reassembly.
Removal and Installation
> Nose Landing Gear Removal.
> Nose Landing Gear Installation.

32-20-01 Steering Torque Tube
> Steering Torque Tube Removal.
> Steering Torque Tube Installation.

32-20-02 NLG Steering Linkage
> Nose landing Gear Steering Link Removal.
> Nose Landing Gear Steering Link Installation.

32-20-03 NLG Mudguard
> Mudguard Removal.
> Mudguard Installation.

32-40-00 Wheels & Brakes
> Description and Operation / Differences.

Maintenance Practices
Removal and Installation
> Main Landing Gear Wheel Removal.
> Main Landing Gear Wheel Installation.
> Nose Landing Gear Wheel Removal.
> Nose Landing Gear Wheel Installation.

32-40-02 Wheel Brakes
> Wheel Brakes Removal.
> Wheel Brakes Installation.

MAINTENANCE MANUAL SUPPLEMENT 32-00-00 - Landing Gear DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Landing Gear
Chapter Content

32-40-03 Brake Master Cylinders
Description and Operation
> Master Cylinder Disassembly.
> Master Cylinder Reassembly.
Maintenance Practices
Removal and Installation
> Cleveland Model 10-95 Brake Master Cylinder.
> Grove 678-3 Master Cylinder Removal.
> Grove 678-3 Master Cylinder Installation.
Adjustment and Test
> Brake System Bleeding.
Inspection and Check
> Brake Master Cylinder Inspection. (Installed)
> Brake Master Cylinder Inspection. (Removed)

MAINTENANCE MANUAL SUPPLEMENT 32-00-00 - 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
32-00-00 Landing Gear N/A FU24-954 C550GT
Description and Operation
Main Landing Gear Description 
Nose Landing Gear Description 
32-10-00 Main Landing Gear
Description and Operation 
Main Landing Gear - Description / Differences
Maintenance Practices 

Servicing
Lubrication

Disassembly and Reassembly

Replacement

Nylon Bumper Replacement 
Piston Bearing Replacement 
Torque Link Spacer/Bush Replacement 

Removal and Installation 
MLG Torque Link Removal 
MLG Torque Link Installation 
Axle & Brake Torque plate 
Main Landing Gear Removal 
Main Landing Gear Reassembly and Installation

Adjustment and Test
Operational Test
Functional Test
System Test

Inspection/Check 
Shock Strut Oil and Air Charging 
Steering Alignment
Main Landing Gear - Wing Rib Inspection 
MLG Cylinder Inspection

MAINTENANCE MANUAL SUPPLEMENT 32-00-00 - 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
32-20-00 Nose Landing Gear N/A FU24-954 C550GT
Description and Operation
Nose Lading Gear - Description & Operation 
Nose Landing Gear - Description / Differences 
Troubleshooting
Maintenance Practices

Disassembly and Reassembly.

Nose Landing Gear Disassembly 
Nose Landing Gear Reassembly 

Replacement

Lower Steering Link Bushing Replacement 

Servicing

Removal and Installation 
Steering Torque Tube Removal 
Steering Torque Tube Installation 
Steering Linkage Removal 
Steering Linkage Installation 
Mudguard Removal 
Mudguard Installation

32-40-00 Wheels and Brakes 
32-40-01 Wheels 
Description and Operation 

Wheels - Description 
Wheels and Brakes - Description / Differences
Maintenance Practices
Removal and Installation
Wheels
32-40-02 Wheel Brakes
Description and Operation
Brakes
Maintenance Practices
Removal and Installation
Brakes - Removal and Installation

MAINTENANCE MANUAL SUPPLEMENT 32-00-00 - 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
32-40-03 Brake Master Cylinders
Description and Operation

Brake Master Cylinders
Maintenance Practices
Removal and Installation

Disassembly and Reassembly

Adjustment and Test

Inspection and Check

MAINTENANCE MANUAL SUPPLEMENT 32-00-00-Landing Gear Description
C550GT-AD016-FU24-0213
Landing Gear Description Revision: Initial Issue DATE: 01/01/2020

Description and Operation / Landing Gear

Landing Gear Description
Landing Gear

32-00-00 Landing Gear

Description and Operation

The FU24A-954 landing gear design supports the aircraft on the ground at MTOW during taxi, take-off, and
landing. It is a heavy-duty critical system and requires the correct inspection and maintenance to prevent
structural failure and damage to the aircraft.

Main Landing Gear.

The Crusader Aircraft Company (CAC) made important changes to the Main Landing Gear (MLG) of the Crusader
550GT. The intent was to mitigate the affect the higher MTOW has on the landing gear, increase resilience, and
improve reliability.
Each MLG attaches to the aluminium casting that is part of the centre wing structure, using standard PAL parts
used in the Cresco configuration. This includes stronger bolts and double hex nuts to attach the shock strut
cylinders.
The cylinders are the PAL Cresco thick-walled type that have an improved two-stage coating process to increase
the corrosion and wear resistance. The cylinder bearing that holds the piston has an improved oil seal installed at
the bottom on the inner surface, it is more resistant to rolling and wear.
The modification includes an improved lug bolted to the cylinders bottom flange with 6 high-strength bolts that
use special radius washers. The thick-wall steel piston and bottom socket, wheel axle, torque link brackets and
the bolts that attach these, are all PAL 750XL parts. The brake torque plate, a C550GT part, centres the brake
assembly on the brake disc.
Landing gear torque links modifications are available and make the torque links more resilient to wear. The
Approved Repairs section of this supplement describes the NZCAA approved modifications that are applicable to
the C550GT. The improvements are optional.
The Crusader 550GT uses the standard PAL Cresco mainwheel assembly.

Nose Landing Gear.

Although the overall layout is the same as the FU24A-954, the Crusader 550GT Nose Landing Gear (NLG) has
some important changes included in its design.
To compensate for the larger mainwheels and give increased propeller ground clearance, the C550 uses the PAL
Cresco NLG configuration. The strut is 3 inches longer than the MLG cylinders and keeps the aircraft in a level
ground attitude. A longer steering control tube compensates for the longer NLG shock strut.
The Crusader 550GT NLG attaches to the same firewall structural angles with the same hardware as the FU24A-
954. The C550GT uses the Cresco nosewheel assembly.
A C550GT mudguard assembly protects the engine air intake from mud that could block the particle separator.
There is an option to install the Cresco nosewheel shimmy damper.

Wheels.

The wheels and tyres used on the C550GT follow the PAL Cresco configuration. The table below and the
applicable drawings show the components installed as part of this modification.
For Maintenance Practices refer to Chapter 32 of the basic FU24A-954 Maintenance Manual.
Refer to the Cleveland Maintenance Manual, Technicians Service Guide and the Tyre manufacturers manuals for
detailed maintenance practices.
You can find links to these publications in Chapter 32-40-01 of this supplement.Link to this section

Braking System.

Changes in the Landing Gear due to the increased MTOW, has also required improvements to the Braking
System.
The C550GT uses a larger Cleveland brake assembly, compatible with the larger Cresco wheel and brake disc
configuration.
Crusader Aircraft have modified the FU24A-954 brake hydraulic system, re-routing the rigid fluid lines inside the
fuselage and wing structure. This change makes the system more resilient to damage and requires less
maintenance. Inspection is possible using additional wing access panels.
The applicable C550GT drawings show the location details of the rigid fluid lines.
For Maintenance Practices and procedures for the brake assembly use the Cleveland Component Maintenance
Manual and the Technicians Service Guide. You can find links to these publications in Chapter 32-40-02 of this
supplement. Link to this section
Refer to Chapter 32 of the basic FU24A-954 Maintenance Manual for all other maintenance.

Page 1

MAINTENANCE MANUAL SUPPLEMENT 32-00-00 - Components Changed Table
C550GT-AD016-FU24-0213
Components Changed Table Revision: Initial Issue DATE: 01/01/2020

Components Changed Table CCBTS / Landing Gear
Landing Gear

Components Changed By This STC

Drawing Number Item Part Number Description / Location

32-10-00 Main Landing Gear

AD-550GT-3210-001-000 1 08-40087-1 Clamp-set

AD-550GT-3210-001-100 5 08-40085-1 Main Landing Gear Cylinder

AD-550GT-3210-001-100 6 0840091-1 Lower Torque Link

AD-550GT-3210-001-100 1 08-40035-3 Bearing / MLG Cylinder

AD-550GT-3210-001-100 14 11-40031-1 Lug

AD-550GT-3210-001-100 12 11-40025-1 Torque Link Brackets

AD-550GT-3210-001-100 28 550GT-3210-001-110 Brake Torque Plate

AD-550GT-3210-001-100 9 11-40009-1 Piston

AD-550GT-3210-001-100 11 11-40023-1 Socket

AD-550GT-3210-001-100 10 11-40021-1 Axle

AD-550GT-3210-001-100 16 067-06700 Spacer

AD-550GT-3210-001-100 2 08-40039-1 Reinforcing Plate / Lug

AD-550GT-3210-001-100 3 08-40041-2 Bushing / lower torque link

AD-550GT-3210-001-100 4 08-40045-1 Shim / cylinder bearing

AD-550GT-3210-001-100 7 8.5-10M Inner Tube

32-20-00 Nose Landing Gear

AD-550GT-3220-001-100 2 08-40051-3 Nose Landing Gear Cylinder

AD-550GT-3220-001-100 6 08-40037-1 Bearing / NLG Cylinder

AD-550GT-3220-001-100 4 11-40009-1 Piston

AD-550GT-3220-001-100 1 08-04173-2 Nosewheel Fork

AD-550GT-3220-001-100 5 40-140A Nosewheel Assembly

AD-550GT-3220-001-100 30 550GT-3220-001-120 Mudguard Assembly

32-40-00 Wheels & Brakes

AD-550GT-3210-001-100 15 40-101 Mainwheel Assembly

AD-550GT-3220-001-100 5 40-140A Nosewheel Assembly

AD-550GT-3220-001-100 15 164-03006 Brake disc

AD-550GT-3240-001-000 2 30-89E (LH &RH) Brake Assembly

Page 1

MAINTENANCE MANUAL SUPPLEMENT 32-10-00-MLG - Differences
C550GT-AD016-FU24-0213
MLG - Differences Revision: Initial Issue DATE: 01/01/2020

Description and Operation / Main Landing Gear

MLG - Differences
Main Landing Gear

32-10-00 Main Landing Gear

Description and Operation

Description / Differences.

The FU24A-954 landing gear design supports the aircraft on the ground at MTOW during taxi, take-off, and
landing. It is a heavy-duty critical system and requires the correct inspection and maintenance to prevent
structural failure and damage to the aircraft.

The Crusader Aircraft Company (CAC) made important changes to the Main Landing Gear (MLG) of the Crusader
550GT. The intent was to mitigate the affect the higher MTOW has on the landing gear, increase resilience, and
improve reliability.
Each MLG attaches to the aluminium casting that is part of the centre wing structure, using standard PAL parts
used in the Cresco configuration. This includes stronger bolts and double hex nuts to attach the shock strut
cylinders.
The cylinders are the PAL Cresco thick-walled type that have an improved two-stage coating process to increase
the corrosion and wear resistance. The cylinder bearing that holds the piston has an improved oil seal installed at
the bottom on the inner surface, it is more resistant to rolling and wear.
The modification includes an improved lug bolted to the cylinders bottom flange with 6 high-strength bolts that
use special radius washers. The thick-wall steel piston and bottom socket, wheel axle, torque link brackets and
the bolts that attach these, are all PAL 750XL parts. The brake torque plate, a C550GT part, centres the brake
assembly on the brake disc.
Landing gear torque links modifications are available and make the torque links more resilient to wear. The
Approved Repairs section of this supplement describes the NZCAA approved modifications that are applicable to
the C550GT. The improvements are optional.
The Crusader 550GT uses the standard PAL Cresco mainwheel assembly.

Page 1

MAINTENANCE MANUAL SUPPLEMENT 32-10-00- Main Landing Gear
C550GT-AD016-FU24-0213
Main Landing Gear Revision: Initial Issue DATE: 01/01/2020

Reassembly & Install Maintenance Practices / Reassembly & Install
Main Landing Gear

Maintenance Practices
Removal and Installation

1. Reassembly and Installation.
Ref. Dwg. No: AD-550GT-3210-001-000

Ref. Dwg. No: AD-550GT-3210-001-100

(1) Lift the aircraft.
NOTE: Use the Single Lift or Double Lift method. See Chp. 07 Lifting and Shoring.

WARNING: MAKE SURE THAT YOU LIFT AND TRESTLE THE AIRCRAFT ON LEVEL GROUND, AWAY FROM
WIND GUSTS AND JET OR PROP WASH. THE AIRCRAFT CAN FALL OFF THE JACKS AND CAUSE
INJURY OR DEATH.

CAUTION: BEFORE YOU INSTALL THE MLG, MAKE SURE YOU EXAMINE THE WING RIB AND BRACKET
WHERE THE MLG TOUCHES.

Refer to the Wing Rib Inspection procedure. See Chp. 32 Wing Rib Inspection.

(2) Install the cylinder.

Ref. Dwg. No: AD-550GT-3210-001-000

a. Carefully move the MLG cylinder up through the wing access and support it in position.
NOTE: In the next steps, apply a small quantity of CA 1010 Mastinox Jointing Compound (or equivalent) to
each bolt shank only.

b. Install the two top bolts (10), washers (9), (8) and nuts (11). Do not tighten the nuts during this step.
c. Install the clamp-set (1), with the bottom bolts (10) washers (9), (8) and nuts (11).

NOTE: In the next step, there is limited access to the top nuts.

d. Hold the bolt heads while you tighten the two top nuts as much as possible by hand.
NOTE: Use a 7/16 AF long-series ring wrench, or box wrench.

e. Hold the bolt heads and use a torque wrench to tighten the two bottom nuts to 210 - 250 in lbs.

CAUTION: MAKE SURE THAT THE NUT DOES NOT BOTTOM OUT ON THE BOLT SHANK. INSTALL MORE
WASHERS SO THAT THERE IS A MINIMUM 1 AND MAXIMUM 3 BOLT THREADS VISIBLE.

(3) Install the cylinder bearing and lug.

Ref. Dwg. No: AD-550GT-3210-001-100

a. Install the oil seal (52) into the external groove on the cylinder bearing (1).
b. Install the oil seal (51) into the internal groove of the cylinder bearing (1).

NOTE: Lubricate the seals with MIL-H-5606G. (or equivalent)

c. Apply Petroleum Jelly to the internal surface of the cylinder where the bearing will touch.
d. Install the bearing into the cylinder.
e. Apply CA 1010 Mastinox Jointing Compound (or equivalent) to the external surface of the cylinder where

the lug will touch.
f. Install the scraper ring (53) with the stepped face down, into the lug (14).
g. Install the lug (14) and reinforcement plate (2) with the 6 bolts (57, 58), special radius washers (34)

washers (34) and nuts (38). (See Note 7 on Dwg.No. AD-550GT-3210-001-100)

CAUTION: MAKE SURE TO SET THE RADIUSED OUTER EDGES OF THE SPECIAL WASHERS AGAINST THE
RADIUS OF THE CYLINDER FLANGE.

CAUTION: MAKE SURE TO USE THE LONGER BOLTS TO ATTACH THE REINFORCEMENT PLATE. TORQUE ALL
THE LUG ATTACH BOLTS TO 100-140 IN LBS.

CAUTION: MAKE SURE THERE IS NO CLEARANCE BETWEEN THE CYLINDER FLANGE AND THE LUG.

NOTE: If you can see a space between the cylinder flange and the lug, measure the distance for reference,
then remove the lug. The end float permitted is between 0.000 and 0.050. Do not use more
shimming than necessary to set the end float to this range.

h. Remove excessive end float shimming (shim 08-40045-1) from between the lug and the cylinder bearing
(08-40037-1).

i. To reassemble the lug and cylinder go back to steps (e thru g).

Page 401

MAINTENANCE MANUAL SUPPLEMENT 32-10-00-Main Landing Gear
C550GT-AD016-FU24-0213
Main Landing Gear Revision: Initial Issue DATE: 01/01/2020

Maintenance Practices / Reassembly & Install

(4) If necessary, install the socket (11) on to the piston (9).

NOTE: If the piston and socket is an assembly, go to step 5.

a. Put the socket (11) in an oven. Heat for one hour to 100°C (212°F).

CAUTION: TO PREVENT PERSONAL INJURY PUT ON PROTECTIVE GLOVES WHEN YOU HANDLE HOT PARTS.

b. Apply CA 1010 Mastinox Jointing Compound (or equivalent) to the external surface of the piston where the
socket will touch.

c. Press the piston (9) into the socket (11).
NOTE: Use a hydraulic press.

d. Drill the piston (9) using the socket (11) as a guide. 29/64” (0.4531") (11.50mm).
NOTE: Use a drill-press or mill and a diamond tip drill. Remove all burrs and drilling swarf after drilling.

e. Install the bolt (31), special washer (21) and nut (47). Torque nut to 450-500 in lbs.

CAUTION: MAKE SURE TO CORRECTLY SEAT THE SPECIAL WASHER IN THE RADIUS OF THE PISTON TUBE.

(5) Install the piston into the cylinder assembly.

a. Lubricate the oil seal (51) and the bearing with MIL-H-5606G (or equivalent).
NOTE: To prevent damage to the seal, lubricate the piston with Lubriplate 130-AA.

b. Carefully install the piston assembly (9) into the cylinder assembly.
c. Support the MLG piston assembly under the socket.
d. Install the torque link assembly. See Chp. 32 MLG Torque Link Installation.
e. Install the mainwheel assembly.See Chp. 32 Main Landing Gear Wheel Installation.
f. Install the brake calliper. See Chp. 32 Wheel Brakes Installation.
g. Install the clip that attaches the brake hose to the top torque link arm.
h. Install the charging-valve (54).
i. Service the shock strut. See Chp. 12 MLG Strut Servicing.
j. Lower the aircraft from the jacks. See Chp. 07 Lifting and Shoring.

CAUTION: MAKE SURE ALL TRESTLES AND SUPPORTS ARE CLEAR OF THE AIRCRAFT BEFORE YOU LOWER
THE JACK.

k. Install the two wing access panels. See Chp. 12 Access Panel Diagram.

Page 402

MAINTENANCE MANUAL SUPPLEMENT 32-10-01- MLG Torque Links
C550GT-AD016-FU24-0213
MLG Torque Links Revision: Initial Issue DATE: 01/01/2020

Removal & Installation Maintenance Practices / Removal & Installation
MLG Torque Links

32-10-01 MLG Torque Link

1. MLG Torque Link Removal.
Single Side Lift the aircraft. See Chp. 7 Lifting and Shoring.

WARNING: BEFORE YOU DISASSEMBLE THE LANDING GEAR LEG, DEFLATE THE SHOCK STRUT PRESSURE.
THE VERY HIGH PRESSURE INSIDE THE STRUT CAN CAUSE INJURY OR DEATH.

Ref. Dwg. No: AD-550GT-3210-001-100

(1) Deflate the shock strut. See Chp. 12 MLG Strut Servicing.
(2) Remove the clip that attaches the brake hose to the top torque link arm.
(3) Support the MLG piston assembly under the socket.
(4) Remove cotter pin, nut (42) and washer (36) from bottom pivot bolt (60).
(5) Remove bolt (60) and washer (43).
(6) Move the bottom torque link away from the torque link brackets.
(7) Remove the bottom pivot washers (24) and shims (25).
(8) Remove bushing (3).
(9) Remove cotter pin (50), nut (41) and washer (35) from centre pivot bolt (30).
(10) Remove centre pivot bolt (30), washer and special washers (23).
(11) Remove the centre bushing (22) from the top link assembly (26).
(12) Remove the bottom torque link (6).
(13) Remove the nut (46) and washer (35).
(14) Remove the top pivot bolt (49).
(15) Remove the two spacers (19).
(16) Remove the top link (26) from the lug (14).
(17) Remove the top pivot bushing (20).

Figure 32.1 MLG Torque Link

Page 401

MAINTENANCE MANUAL SUPPLEMENT 32-10-01-MLG Torque Links
C550GT-AD016-FU24-0213
MLG Torque Links Revision: Initial Issue DATE: 01/01/2020

Maintenance Practices / Removal & Installation

2. MLG Torque Link Installation.

Ref. Dwg. No: AD-550GT-3210-001-100

(1) Install the top pivot bushing (20) into the top torque link.
NOTE: Refer to FU24-954 MM Chp. 32, Servicing para. (v) on page 5.

(2) Install the top torque link into the lug (14) with spacers (19) either side.
NOTE: Spacers (2) are manufactured in two thicknesses (0.107/0.109 and0.110/0.112) and should be
installed in a suitable combination to achieve 0.004-0.006 gap each side to allow grease penetration.

(3) Install the top pivot bolt (48) with washer (35).
(4) Install the washer (35), and nut (46).
(5) Hold the bolt head and tighten the top pivot nut.
(6) Install the centre pivot bushing (22) into the top link.

NOTE: Refer to FU24-954 MM Chp. 32, Servicing para. (v) on page 5.
(7) Install the bottom link to the top link with special washers (23), centre pivot bolt (30) with washer (35).
(8) Install nut (41) and washer to centre pivot bolt.
(9) Hold the bolt head and tighten the nut. Install the cotter pin.
(10) Install bushing (3) into bottom link (6).

NOTE: Refer to FU24-954 MM Chp. 32, Servicing para. (v) on page 5.
(11) Move the torque link assembly so that the bottom link aligns with the torque brackets.
(12) Install the bottom pivot washers (24) and shims (25).
(13) Install the bottom pivot bolt (59) with washer (42), nut (41) and washer (36).
(14) Hold the bolt head and tighten nut. Install the cotter pin.

NOTE: Adjust thickness of shims to minimise any end float of the bush. Do not tighten the bolt (59) too
much. This will damage the bushing, washers and shims and stop grease entering the gap between
the bottom torque link arm (6) and brackets (10).

NOTE: Install the alternate lower torque link P/N 08-40031-4 with wearable parts (P/N 08-40093-1 and P/N
08-40041-2) as an alternative to the P/N 08-40091-1 lower torque link assembly.

NOTE: The P/N 08-40091-1 lower torque link assembly can also be reworked to P/N 08-40031-4 in
accordance with AD-550GT-3210-001-100.

Page 402

MAINTENANCE MANUAL SUPPLEMENT 32-10-02- MLG Axle & Brake Torque Plate
C550GT-AD016-FU24-0213
MLG Axle & Brake Torque Plate Revision: Initial Issue DATE: 01/01/2020

Removal & Installation Maintenance Practices / Removal & Installation
MLG Axle & Brake Torque Plate

32-10-02 MLG Axle & Brake Torque Plate

1. MLG Axle and Brake Torque Plate Removal
Ref. Dwg. No: AD-550GT-3210-001-100
(1) Lift the aircraft until the wheels are clear of the ground. Single or Double lift. See Chp. 07 Lifting and
Shoring.

WARNING: BEFORE YOU DO ANY WORK ON THE LANDING GEAR LEG, DEFLATE THE SHOCK STRUT
PRESSURE. THE VERY HIGH PRESSURE INSIDE THE STRUT CAN CAUSE INJURY OR DEATH.

(2) Deflate the shock strut. See Landing Gear Strut Servicing. Chp.12 page 316
(3) Remove the charging valve (54).
(4) Remove the Brake Assembly. See Chp. 32 Wheel Brakes Removal.
(5) Remove the mainwheel. See Chp. 32 Main Landing Gear Wheel Removal.
(6) Support the MLG piston assembly under the socket.
(7) Remove cotter pin, nut (42) and washer (36) from the bottom pivot bolt (60). See Figure 32.1
(8) Remove the bolt (60) and washer (43).
(9) Move the bottom torque link away from the torque link brackets.
(10) Remove the bottom pivot washers (24) and shims (25).
(11) Remove the 4 bolts (57), special washers (43) and torque link bracket (12).
(12) Remove the 4 bolts (56) and the washer plate (13) that attach the brake torque plate (28), axle (10) and

torque link bracket (12).

Figure 32.2 MLG Axle & Torque Plate

Page 403

MAINTENANCE MANUAL SUPPLEMENT 32-10-02-MLG Axle & Brake Torque Plate
C550GT-AD016-FU24-0213
MLG Axle & Brake Torque Plate Revision: Initial Issue DATE: 01/01/2020

Maintenance Practices / Removal & Installation

2. MLG Axle and Brake Torque Plate Installation
Ref. Dwg. No: AD-550GT-3210-001-100

(1) Install the outboard torque link bracket (12), axle (10), brake torque plate (28) and washer plate (13) with
the four bolts (56).

(2) Install inboard torque link bracket (12), with the four bolts (57) and radiused washers (43).
NOTE: Apply MIL-T-5544C (or equivalent) to the bolt threads.

CAUTION: MAKE SURE THE RADIUS FACE OF THE SPECIAL WASHER IS AGAINST THE BOLT HEAD.

(3) Torque to 520-625 in lbs. Safety the bolt heads with lockwire.
(4) Move the torque link assembly so that the bottom link aligns with the torque brackets.
(5) Install the bottom pivot washers (24) and shims (25).
(6) Install the bottom pivot bolt (60) with washer (43), nut (42) and washer (36).
(7) Hold the bolt head and tighten the nut. Install the cotter pin (50).

NOTE: Adjust thickness of shims to minimise any end float of the bush. Do not tighten the bolt (59) too
much. This will damage the bushing, washers and shims and stop grease entering the gap between
the bottom torque link arm (6) and brackets (12).

(8) Install the mainwheel assembly. See Chp. 32 Main Landing Gear Wheel Installation.
(9) Install the brake calliper. See Chp. 32 Wheel Brakes Installation.
(10) If removed, install the P-clamp that attaches the brake hose to the top torque link arm.
(11) Install the charging-valve (54). See Chp. 12 MLG Strut Servicing.
(12) Service the shock strut. See Landing Gear Strut Servicing. See Chp. 12 MLG Strut Servicing.
(13) Lower the aircraft from the jacks. See Chp. 07 Lifting and Shoring.

CAUTION: MAKE SURE ALL TRESTLES AND SUPPORTS ARE CLEAR OF THE AIRCRAFT BEFORE YOU LOWER
THE JACK.

Page 404

MAINTENANCE MANUAL SUPPLEMENT 32-10-00- Wing Rib Inspection
C550GT-AD016-FU24-0213
Wing Rib Inspection Revision: Initial Issue DATE: 01/01/2020

Wing Rib Inspection Maintenance Practices / Inspection & Check
Inspection & Check
Inspection and Check
1. Wing Rib Inspection.

(1) Lift the aircraft on jacks. See Chp. 07 Lifting and Shoring.
(2) Remove the two wing access panels (W8) and (W9). See Chp. 12 Access Panel Diagram.

CAUTION: THE LANDING GEAR IS CRITICAL TO AIRCRAFT SAFETY. MAKE SURE YOU EXAMINE LANDING
GEAR PARTS CAREFULLY.

NOTE: Use a mirror and bright light.
(3) Examine the area where the bottom clamp touches the wing rib. Look for signs that the bottom clamp has

moved forward and aft against the wing rib. See Figure 32.4
(4) If you find signs of movement the bolts may have lost torque, go to step (8).
(5) If there are no signs of movement, torque the bottom clamp set nuts (1) to 210-250 in lb.

NOTE: Use a calibrated torque wrench and use a smooth even pull when applying the torque.
NOTE: In this next step, there is limited access to the top nuts (1)
(6) Hold the bolt head (3) while you tighten the two top nuts (1) as much as possible by hand.
NOTE: Use a 7/16 AF long series ring spanner, or box wrench.
(7) Install the wing access panels (W8) and (W9).
(8) If you find signs of movement, do these steps.

a. Do the MLG Cylinder Inspection. See Chp. 32 Main Landing Gear-Cylinder Inspection.
b. Examine the wing rib for wear in the area where the bottom clamp touches. If the wing rib surface is

chaffed contact CAC Support.
c. Remove the access panel (W9). Examine the Landing Gear Attachment P/N 241151-2R and 241151-2L for

damage or elongation of the bolt holes. If you find damage, contact CAC Support.

Figure 32.3 Wing Rib/MLG Clamp Access.

Page 601

MAINTENANCE MANUAL SUPPLEMENT 32-10-00-Wing Rib Inspection
C550GT-AD016-FU24-0213
Wing Rib Inspection Revision: Initial Issue DATE: 01/01/2020

Maintenance Practices / Inspection & Check

Figure 32.4 Wing Rib Inspection.

Page 602

MAINTENANCE MANUAL SUPPLEMENT 32-10-00- MLG Cylinder Inspection
C550GT-AD016-FU24-0213
MLG Cylinder Inspection Revision: Initial Issue DATE: 01/01/2020

MLG Cylinder Inspection Maintenance Practices / Inspection and Check
Inspection and Check

1. Main Landing Gear-Cylinder Inspection.

WARNING: THE LANDING GEAR IS CRITICAL TO AIRCRAFT SAFETY. MAKE SURE YOU EXAMINE LANDING
GEAR PARTS CAREFULLY.

Cylinder P/N 08-400085-1
Ref. Dwg. No: AD-550GT-3210-001-000
(1) Remove the access panels. See Chp. 12 Access Panel Diagram.
(2) Remove the bottom clamp-set (1). Refer to the FU24-954 MM Chp. 32, Page 7, Para. 2 (v).
(3) Use a bright light and a 10x loupe to carefully look for damage.
(4) Make sure that chafing by the bottom clamp set (1) has not cracked or removed the silver-metallic or light-

green ceramic coating.
NOTE: Damage to the white nylon topcoat is possible. This is not a problem.

Result.
If you see damage to the silver or light-green ceramic coating, you must remove the cylinder for repair.
(Remove with reference to FU24-954 MM Chp. 32, Page 7, Para. 2 (v).)

NOTE: An approved facility can assess and may repair the cylinder. Contact CAC for support.
(5) Do a Wing Rib Inspection to examine the area where the bottom clamp touches the wing rib.
See Chp. 32 Wing Rib Inspection.

Result.
If you do not find damage, go to step 6.

(6) Install the clamp-set (1), with bottom bolts (10) washers (8) and (9) and nuts (11).
(7) Hold the bolt head while you use a torque wrench to tighten the two bottom nuts to 210 - 250 in lbs.

CAUTION: MAKE SURE THAT THE NUT DOES NOT BOTTOM OUT ON THE BOLT SHANK. INSTALL MORE
WASHERS SO THAT THERE IS A MINIMUM 1 AND MAXIMUM 3 BOLT THREADS VISIBLE.

(8) Install the access panels.

Page 603

MAINTENANCE MANUAL SUPPLEMENT 32-20-00-NLG - Differences
C550GT-AD016-FU24-0213
NLG - Differences Revision: Initial Issue DATE: 01/01/2020

Description and Operation / Nose Landing Gear

NLG - Differences
Nose Landing Gear

32-20-00 Nose Landing Gear

Description and Operation

Description and Operation / Differences.

The FU24A-954 landing gear design supports the aircraft on the ground at MTOW during taxi, take-off, and
landing. It is a heavy-duty critical system and requires the correct inspection and maintenance to prevent
structural failure and damage to the aircraft.

Although the overall layout is the same as the FU24A-954, the Crusader 550GT Nose Landing Gear (NLG) has
some important changes included in its design.
To compensate for the larger mainwheels and give increased propeller ground clearance, the C550 uses the PAL
Cresco NLG configuration. The strut is 3 inches longer than the MLG cylinders and keeps the aircraft in a level
ground attitude. A longer steering control tube compensates for the longer NLG shock strut.
The Crusader 550GT NLG attaches to the same firewall structural angles with the same hardware as the FU24A-
954.
The C550GT uses the Cresco nosewheel assembly.
A C550GT mudguard assembly protects the engine air intake from mud that could block the particle separator.
There is an option to install the Cresco nosewheel shimmy damper.

Page 1

MAINTENANCE MANUAL SUPPLEMENT 32-20-00- Disassembly
C550GT-AD016-FU24-0213
Disassembly Revision: Initial Issue DATE: 01/01/2020

Disassembly Maintenance Practices / Nose Landing Gear
Nose Landing Gear

Maintenance Practices

1. Nose Landing Gear Disassembly.

Use the FU24-954 Maintenance Manual Chapter 32 - Landing Gear, Maintenance Practices, 2. Removals &
Installations para. (xv) Page 10, steps (A) thru (K) for Disassembly procedures including these tasks below.

Applicable FU24 Manual section.
FU24-954 Maintenance Manual Chapter 32.
Section 2. Removals and Installations, para. (xv), page 10
Nose Landing Gear Disassembly (Refer Figure 32.08)

Reason.

The C550GT is fitted with a NLG Mudguard which must be removed first.

Change to step.

Before Step (A), remove the Mudguard Assembly. See Chp. 32 Mudguard Removal.

Additional Information.

See Chp. 32 Components Changed By This STC

Page 201

MAINTENANCE MANUAL SUPPLEMENT 32-20-00- Nose Landing Gear
C550GT-AD016-FU24-0213
Nose Landing Gear Revision: Initial Issue DATE: 01/01/2020

Reassembly Maintenance Practices / Reassembly
Nose Landing Gear

1. Nose Landing Gear Reassembly.
Ref. Dwg. No: AD-550GT-3220-001-100
Ref. Dwg. No: AD-550GT-3220-001-000
(1) If necessary, install the socket (7) on the piston (5).
(2) Put the socket (7) in an oven. Heat for one hour to 100°C (212°F).

CAUTION: PUT ON PROTECTIVE GLOVES WHEN YOU HANDLE HOT PARTS TO PREVENT PERSONAL INJURY.

(3) Coat the mating surfaces with CA 1010 Mastinox Jointing Compound (or equivalent)
(4) Press the piston (5) into the socket (7).

NOTE: Use a hydraulic press.
(5) Install the nosewheel fork (1) on to the socket (7) with bolts (4) washers (39) and nuts (46).

NOTE: Tighten nuts to the standard torque. See Chp. 20 Standard Fastener Torques
(6) Install the oil seal (50) into the external groove on the cylinder bearing (2).
(7) Install the oil seal (49) into the internal groove of the cylinder bearing (2).

NOTE: Lubricate the seals with Mil-H-5606G. (or equivalent)
(8) Apply Petroleum Jelly to the internal surface of the cylinder where the bearing will touch.
(9) Install the bearing (2) into cylinder (3).
(10) Install the steering tube yoke (10) in position with two bolts (34), bolt and nut (33) and two short spacers

(25).
NOTE: Use CA 1010 Mastinox Jointing Compound (or equivalent) on mating surfaces.
(11) Install the scraper ring (51) with the stepped face down, into the plate (14).
(12) Install the plate (14), with scraper, onto the cylinder assembly using the two installed rear bolts (34) and
the third front bolt (34) and spacer (16).
(13) Install the three nuts (45) and washers (38). Torque bolts to 100-140 in lbs.
(14) Lubricate the oil seal (49) in the cylinder bearing with MIL-H-5606G (or equivalent).
NOTE: Lubricate the piston with Lubriplate 130-AA to prevent damage to the seal.
(15) Install the piston assembly (5) into the cylinder (3).
(16) Attach the two limit cables (27).

Page 202

MAINTENANCE MANUAL SUPPLEMENT 32-20-00- Removal & Installation
C550GT-AD016-FU24-0213
Removal & Installation Revision: Initial Issue DATE: 01/01/2020

Removal & Installation Maintenance Practices / Nose Landing Gear
Nose Landing Gear

Removal and Installation

1. Nose Landing Gear Removal.
Refer to the FU24-954 Maintenance Manual, Chapter 32, page 9 for removal instructions.

2. Nose Landing Gear Installation.
Ref. Dwg. No: AD-550GT-3220-001-000
(1) Before you install the Nose Landing Gear (NLG), inspect the mating faces on the firewall angles for damage.
NOTE: In the next step, use CA 1010 Mastinox Jointing Compound (or equivalent) on the mating surfaces.
(2) Support the NLG in position.
(3) Install the two top attach bolts (13) and washers (16).
(4) Install the bottom clamp-set (7) with the two bolts (14) and washers (16).
(5) Inside the cockpit at the firewall, install the four washers (16) and nuts (20).
(6) Hold the bolt heads while you tighten the four nuts.
NOTE: Torque the nuts to 160 - 260 in lbs.
(7) Install the Steering Tube. See Steering Torque Tube Installation. on page 401
(8) Install the Steering Linkage. See Chp. 32 Nose Landing Gear Steering Link Installation.

WARNING: DO A DUPLICATE SAFETY INSPECTION OF THE NLG STEERING 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.

(9) Install the Nosewheel assembly. See Chp. 32 Nose Landing Gear Wheel Installation.
(10) Install the Mudguard assembly. See Mudguard Installation. on page 401
(11) Service the NLG shock strut. See Chp. 12 NLG Strut Servicing.

Page 401

MAINTENANCE MANUAL SUPPLEMENT 32-20-01- Steering Torque Tube
C550GT-AD016-FU24-0213
Steering Torque Tube Revision: Initial Issue DATE: 01/01/2020

Removal & Installation Maintenance Practices / Removal & Installation
Steering Torque Tube

32-20-01 Steering Torque Tube

1. Steering Torque Tube Removal.
Ref. Dwg. No: AD-550GT-3220-001-000
Also refer to FU24-954 MM Fig. 32.07, Pg. 9
(1) Make sure the nosewheel is neutral and secure the rudder.
(2) Remove the closing panel from the fuselage steering tube opening.

Refer to: FU24-954 MM Fig. 32.07 in the next two steps.

(3) Remove the cotter pin, nut, washer and bolt (1), disengage the link assembly (2) and remove top bush (3)
and bottom bush (4).

(4) Remove two cotter pins, two nuts, two bolts (5), two thick washers (6), two washers (7) and disengage both
push rods (8).

Refer to AD-550GT-3220-001-000 in the next five steps.

(5) Remove the nut (21) and remove cotter bolt (25) from the steering tube (1)

CAUTION: USE A COTTER PIN PRESS TOOL. USING A DRIFT CAN DAMAGE THE STEERING TORQUE TUBE
AND BEARING.

(6) Remove the grease nipple (22) from the pivot bolt (2)
(7) Remove the nut (19), washer (3) shim washers (4) and pivot bolt (9).
(8) Move the upper link assembly away from the steering tube.
(9) Remove lockwire, two bolts (12), washers (15), bearing cap (9) and four split washers (8).

NOTE: Use the clamp-set marks for correct assembly of the bearing block.

Refer to: FU24-954 MM Fig. 32.07 in the next three steps.

NOTE: Support the steering torque tube during the next steps.
(10) Remove the two nuts, washers and bolts (11) from bearing assembly (12).
(11) Remove the bearing cap (27).

NOTE: Use the clamp-set marks for correct assembly of the bearing block.
(12) Remove the steering tube by carefully lifting it into the cockpit.

2. Steering Torque Tube Installation.
Ref. Dwg. No: AD-550GT-3220-001-000
Also refer to FU24-954 MM Fig. 32.07, Pg. 9.
(1) Make sure the nosewheel is neutral and secure the rudder.

Refer to: FU24-954 MM Fig. 32.07 in the next four steps.

(2) In the cockpit, carefully put the steering tube through the opening in the fuselage.
(3) Support and temporarily position the tube in the bottom bearing.
(4) Install the top bearing assembly (12) on the tube.
(5) Install the bolts, washers and nuts (11) through the firewall and the bearing assembly. Tighten to the

standard torque. ((link) Chp 91)

Page 401

MAINTENANCE MANUAL SUPPLEMENT 32-20-01-Steering Torque Tube
C550GT-AD016-FU24-0213
Steering Torque Tube Revision: Initial Issue DATE: 01/01/2020

Maintenance Practices / Removal & Installation

Refer to AD-550GT-3220-001-000 in the next two steps.

(6) Trial fit the split washers (8) and bearing cap (9). Use bolts (12) and washers (15).
NOTE: The P/N 245157 split washers are of different thickness, 0.063" thru 0.077". Use split washers of the
correct thickness necessary to get a free rotational fit with NO end float.

(7) When you have the end float set correctly, tighten the bolts (12). Safety the bolt heads with lockwire.

CAUTION: MAKE SURE THAT THE STEERING TUBE IS FREE TO MOVE IN ITS BOTTOM BEARING AND HAS NO
END-FLOAT.

Refer to: FU24-954 MM Fig. 32.07 in the next five steps.

(8) Position the rudder cable link assembly (2), top bush (3) and bottom bush (4) in the top bracket of the
torque tube (15).

(9) Install bolt (1) through the bracket and bushings.
(10) Install washer and nut. Tighten the nut and install the cotter pin.

NOTE: Make sure heads of the eyebolt attachment screws are on the top of the link assembly (2). Install the
longer bush (3) at the top with the shorter bush (4) at the bottom.

(11) Install the two push rods (8). Use the bolts, nuts (5) and washers (6,7). Tighten the nuts and install the
cotter pins.

(12) Install the closing panel over the fuselage steering tube opening.
Refer to: AD-550GT-3220-001-000 in the next steps.

(13) Install the upper link to the steering torque tube (1).

a. Trial fit the upper link clevis on to the torque tubes lower fitting (1). Use pivot bolt (2), shims (4), special
washer (3) and nut (19).

b. Measure the end float between the upper link clevis (23) and the steering torque tube lower fitting. Adjust
shims (4) to get 0.004 to 0.008 end float.

c. Align the pivot bolt keyway and trial fit the cotter bolt (5) with washer (17) and nut (21). In this step, do not
tighten the nut on the cotter bolt fully.

d. Make sure the end float between the upper link clevis and the steering torque tubes lower fitting (1) is
correct.

(14) Tighten the nut (21) on the cotter bolt (5). Torque to 20 25 in lbs
(15) Tighten the pivot bolt nut (19) Torque to 30 - 40 in lbs
(16) Install the pivot bolt grease nipple (22)
(17) Lubricate the steering tube with grease. See Chp. 12 12-20-00 Scheduled

WARNING: MAKE SURE YOU REMOVE THE RUDDER STOP.

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.

Page 402

MAINTENANCE MANUAL SUPPLEMENT 32-20-02- NLG Steering Linkage
C550GT-AD016-FU24-0213
NLG Steering Linkage Revision: Initial Issue DATE: 01/01/2020

Removal & Installation Maintenance Practices / Removal & Installation
NLG Steering Linkage

32-20-02 NLG Steering Linkage

1. Nose landing Gear Steering Link Removal.
(1) Lift the nose of the aircraft and put a padded support under the instrument panel frame at STA 64.57 to
support the forward fuselage. See Chp. 07 Lifting and Shoring.

WARNING: DO NOT USE THE STRUTS SAFETY CABLES TO LIMIT THE MOVEMENT OF THE PISTON AND FORK
ASSY. THE VERY HIGH PRESSURE INSIDE THE STRUT CAN CAUSE INJURY OR DEATH.

(2) Deflate the shock strut. See Chp. 12 NLG Strut Servicing.

CAUTION: MAKE SURE THE NOSEWHEEL IS NEUTRAL AND SECURE THE RUDDER.

In the next step,
Ref. Dwg. No: AD-550GT-3220-001-100

(3) Remove the nut (46) washers (39), special washers (20) and bolt (36) that attach the bottom link arms (19)
to the piston socket (7).

In the next five steps,
Ref. Dwg. No: AD-550GT-3220-001-000

(4) Remove the nut (21) and remove cotter bolt (5) from the steering tube (1)

CAUTION: USE A COTTER PIN PRESS TOOL. USING A DRIFT CAN DAMAGE THE STEERING TORQUE TUBE
AND BEARING.

(5) Remove the grease nipple (22) from the pivot bolt (2)
(6) Remove the nut (19), washer (3) shim washers (4) and pivot bolt (9).
(7) Move the upper link assembly away from the steering tube.
(8) Remove the Steering Link Assembly

Figure 32.5 Extract from NLG Assy. Dwg. AD-550GT-3220-001-000
Page 401

MAINTENANCE MANUAL SUPPLEMENT 32-20-02-NLG Steering Linkage
C550GT-AD016-FU24-0213
NLG Steering Linkage Revision: Initial Issue DATE: 01/01/2020

Maintenance Practices / Removal & Installation

2. Nose Landing Gear Steering Link Installation.

CAUTION: THE LANDING GEAR IS CRITICAL TO AIRCRAFT SAFETY. MAKE SURE YOU EXAMINE LANDING
GEAR PARTS CAREFULLY.

(1) Before you install the steering link, examine the steering torque tube installation.
NOTE: Make sure that the steering tube is free to move in its bottom bearing and has NO end-float.

Ref. Dwg. No: AD-550GT-3220-001-100
(2) Lubricate link tube (23.2), put clevis (23.1), special washers (23.3), and collar (23.4) on tube, insert clevis

pin (23.5).
NOTE: Set the end float to 0.001" - 0.004". Use the special washer (23.3) to get this clearance.
(3) Safety clevis pin (23.5) with a cotter pin.
(4) Put block (8) on tube (23.2). Insert clevis pin (44) and safety with a cotter pin.
NOTE: Make sure the clevis pin is a tight fit in the block.
(5) Install the nylon bumper (21).
NOTE: This assembly is now an "upper link" assembly (23).

Ref. Dwg. No: AD-550GT-3220-001-000
(6) Position the upper link (23) on the steering torque tube (1).
(7) Trial fit the upper link clevis on the steering torque tube fitting. Use shims (4), pivot bolt (2), special washer

(3) and nut (19).
NOTE: Measure the end float between the upper link clevis (23.1) and the steering torque tube fitting (1).

Adjust shims (4) to get 0.004 to 0.008 end float.
(8) Align the pivot bolt keyway and trial fit the cotter bolt (5) with washer and nut (21). In this step, do not

tighten the cotter bolt nut fully.
(9) Make sure the end float between the upper link clevis (23.1) and the steering torque tubes lower fitting (1)

is correct.
(10) Tighten nut (21) on cotter bolt (5). Torque to 20 25 in lbs
(11) Tighten pivot bolt nut (19) Torque to 30-40 in lbs.
(12) Install the pivot bolt grease nipple.

Ref. Dwg. No: AD-550GT-3220-001-100
(13) Install the two bottom link arms (19) to the upper link block (8). Use the AN6-34A bolt (35), spacer (17)

special washers (20), washers (39) and nut (46).
NOTE: Make sure the end float between bottom link arms and the upper link block is 0.001" to 0.002".

Replace or reduce the length of the spacer (8) to get this clearance.
(14) Tighten nut. Torque nut to the standard bolt torque. See Chp. 20 Standard Fastener Torques
(15) Use configuration A or B to install the two links (19) to the NLG fork socket (7).
Config. A
(1) Use the bolt (36), washers (39), special washers (20), and nut (46).

NOTE: Make sure the bushing (18) extends 0.005" clear of the socket bushes (22).
(2) Tighten nut (46) while holding bolt (36).

NOTE: Torque nut to the standard bolt torque. Refer Chp. 20 (link)

Config. B. Standard FU24 series configuration:- stud bolt and special nuts for tow bar attachment.
(1) Use the stud bolt (245229 - FU24), washers (39), special washers (20), and two ESNA nuts (12B-064).

NOTE: Make sure the bushing (18) extends 0.005" clear of the socket bushes (22).

Page 402

MAINTENANCE MANUAL SUPPLEMENT 32-20-02-NLG Steering Linkage
C550GT-AD016-FU24-0213
NLG Steering Linkage Revision: Initial Issue DATE: 01/01/2020

Maintenance Practices / Removal & Installation

(2) Tighten the two nuts.
NOTE: Torque nut to the standard bolt torque. Refer Chp. 20 (link)

Figure 32.6 Extract from NLG Assy. Dwg. AD-55GT-3220-001-100
Page 403

MAINTENANCE MANUAL SUPPLEMENT 32-20-03- NLG Mudguard
C550GT-AD016-FU24-0213
NLG Mudguard Revision: Initial Issue DATE: 01/01/2020

Removal & Installation Maintenance Practices / Removal & Installation
NLG Mudguard

32-20-03 NLG Mudguard

1. Mudguard Removal.
Ref. Dwg. No: AD-550GT-3220-001-100
(1) Remove the cotter pins, nuts (43,48) and washers (37) from both bottom mounting arms.
(2) Remove the bolts (31) with washer (37) from both sides of the nosewheel fork.
NOTE: There is an AN960-10 washer (37) between the arm and the fork on both sides.
(3) Remove the cotter pins and castellated nuts (43,48), and the two bolts (30) with washers (41) from the top
mounting arms and bracket (28).
(4) Remove the mudguard assembly.

2. Mudguard Installation.
Ref. Dwg. No: AD-550GT-3220-001-100

(1) Position the mudguard assembly behind the nosewheel.
(2) Use the two bolts (30) with washers (41) and castellated lock-nuts (43) to attach the top mounting arms to

the bracket (28).
NOTE: Put the mount arm on top of the bracket.
(3) Safety the nuts with cotter pins (48).
(4) Use the two bolts (31) with washers (37) and castellated nuts (43) to attach the bottom mounting arms to
the outside of the fork (1).
NOTE: Make sure you put the bolt head on the inside of the fork. Put an AN960-10 washer between the arm

and the fork on both sides.
(5) Safety the lock-nuts with cotter pins (48).

Figure 32.7 NLG Mudguard

Page 401

MAINTENANCE MANUAL SUPPLEMENT 32-40-00-Wheels and Brakes- Differences
C550GT-AD016-FU24-0213
Wheels and Brakes- Differences Revision: Initial Issue DATE: 01/01/2020

Wheels and Brakes- Differences Description and Operation / Wheels and Brakes
Wheels and Brakes
32-40-00 Wheels & Brakes
Description and Operation / Differences.

Wheels.

The wheels and tyres used on the C550GT follow the PAL Cresco configuration. Go to Components Changed By
This STC (CCBTS) and the applicable drawings which show the components installed as part of this modification.

For Maintenance Practices refer to Chapter 32 of the basic FU24A-954 Maintenance Manual.
Refer to the Cleveland Maintenance Manual, Technicians Service Guide and the Tyre manufacturers manuals for
detailed maintenance practices.

Ref. Ext. Doc: Cleveland Wheels & Brakes Manual AWBCMM0001-22/USA.
Refer to Chapter 32 of the basic FU24A-954 Maintenance Manual for all other maintenance.

Wheel Brakes.

Changes in the Landing Gear due to the increased MTOW, has also required improvements to the Braking
System.
The C550GT uses a larger Cleveland brake assembly, compatible with the larger Cresco wheel and brake disc
configuration.
Crusader Aircraft have modified the FU24A-954 brake hydraulic system, re-routing the rigid fluid lines inside the
fuselage and wing structure. This change makes the system more resilient to damage and requires less
maintenance. Inspection is possible using additional wing access panels.
The applicable C550GT drawings show the location details of the rigid fluid lines.

For Maintenance Practices and procedures for the brake assemblies, use the Cleveland Component Maintenance
Manual and the Technicians Service Guide.

Ref. Ext. Doc: Cleveland Wheels & Brakes Manual AWBCMM0001-22/USA.

Refer to Chapter 32 of the basic FU24A-954 Maintenance Manual for all other Wheel Brake maintenance.

Page 1

MAINTENANCE MANUAL SUPPLEMENT 32-40-01- Wheels
C550GT-AD016-FU24-0213
Wheels Revision: Initial Issue DATE: 01/01/2020

Removal & Installation Maintenance Practices / Removal & Installation
Wheels

Maintenance Practices
Removal and Installation

1. Main Landing Gear Wheel Removal.

For Wheel Removal instructions and procedures, refer to,
Ref. Ext. Doc: Cleveland Wheels & Brakes Manual AWBCMM0001-22/USA.
Ref. Dwg. No: AD-550GT-3210-001-100

NOTE: The C550GT mainwheel has a spacer between the wheel nut and the outer bearing.

1. Make sure you install the spacer (16) P/N 067-06700 on the axle correctly.

Figure 32.8 Main Wheel Installation.

2. Main Landing Gear Wheel Installation.
For Mainwheel Installation instructions and procedures, refer to,
Ref. Ext. Doc: Cleveland Wheels & Brakes Manual AWBCMM0001-22/USA.
Ref. Dwg. No: AD-550GT-3210-001-100
NOTE: The C550GT mainwheel has a spacer between the wheel nut and the outer bearing.
1. Make sure you install the spacer (16) P/N 067-06700 on the axle correctly.

3. Nose Landing Gear Wheel Removal.
Refer to the FU24-954 MM Chapter 32, Sec. 2, para. iii. and the Cleveland Wheels & Brakes Manual.
Ref. Ext. Doc: Cleveland Wheels & Brakes Manual AWBCMM0001-22/USA.
For Mudguard removal. See Chp. 32 Mudguard Removal.

4. Nose Landing Gear Wheel Installation.
Refer to the FU24-954 MM Chapter 32, Sec. 2, para. iii. and the Cleveland Wheels & Brakes Manual.
Ref. Ext. Doc: Cleveland Wheels & Brakes Manual AWBCMM0001-22/USA.
For Mudguard installation. See Chp. 32 Mudguard Installation.

Page 401

MAINTENANCE MANUAL SUPPLEMENT 32-40-02- Wheel Brakes
C550GT-AD016-FU24-0213
Wheel Brakes Revision: Initial Issue DATE: 01/01/2020

Removal and Installation Maintenance Practices / Removal and Installation
Wheel Brakes

32-40-02 Wheel Brakes

1. Wheel Brakes Removal.
Ref. Dwg. No: AD-550GT-3210-001-100
Ref. Ext. Doc: Cleveland Wheels & Brakes Manual AWBCMM0001-22/USA.

2. Wheel Brakes Installation.
Ref. Dwg. No: AD-550GT-3210-001-100
Ref. Ext. Doc: Cleveland Wheels & Brakes Manual AWBCMM0001-22/USA.

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.

Page 401

MAINTENANCE MANUAL SUPPLEMENT 32-40-03-Description and Differences
C550GT-AD016-FU24-0213
Description and Differences Revision: Initial Issue DATE: 01/01/2020

Description and Operation / Brake Cylinders

Description and Differences
Brake Cylinders

32-40-03 Brake Master Cylinders

Description and Operation

Changes in the Landing Gear due to the increased MTOW, has also required improvements to the Braking

System.The C550GT uses a larger Cleveland brake assembly, compatible with the larger Cresco wheel and brake

disc configuration.

To support the larger wheel brakes, four high volume, high pressure brake master cylinders give increased

braking force. The C550GT uses larger 1 inch bore cylinders with a maximum operating pressure of 1200 psi.

There are two types in use.
The Cleveland Model 10-95 and the Grove 678-3. These cylinders are installed in the same way as the Dunlop®
brake master cylinders, original equipment in the FU24-954.
Refer to the applicable section of this CMMS for maintenance information. Go to Applicable Section Guide

Crusader Aircraft re-route the rigid fluid lines inside the fuselage and wing structure. This change makes the
system more resilient to damage and requires less maintenance. Inspection is possible using added wing access
panels. The applicable C550GT drawings show the location details of the rigid fluid lines.

Page 1

MAINTENANCE MANUAL SUPPLEMENT 32-40-03- Grove Brake Master Cylinders
C550GT-AD016-FU24-0213
Grove Brake Master Cylinders Revision: Initial Issue DATE: 01/01/2020

Disassembly/Reassembly Maintenance Practices / Disassembly/Reassembly
Grove Brake Master Cylinders

Disassembly & Reassembly

1. Master Cylinder Disassembly.

(1) Disassembly, inspection and repair of the master cylinder should be done in a clean environment on a
smooth flat working surface.

(2) Remove the snap ring from the top of the master cylinder. Apply sufficient downward pressure on the piston
rod to remove the pre-loaded spring compressive force on the snap ring and rod support. Use snap-ring
pliers to remove the snap ring while keeping the downward pressure on the piston. Then slowly release the
pressure on the piston rod.

(3) Slide the piston rod, attached parts and compression spring out of the master cylinder body.
(4) Using pliers, unscrew the spring guide from the lower end of the piston rod.
(5) Slide the piston and spring off the lower end of the piston rod.
(6) Remove the clevis and jam nut from the top of the piston rod.
(7) Slide the rod support off the upper end of the piston rod.
(8) Remove the O-rings from the piston, piston rod and rod support.

2. Master Cylinder Reassembly.
NOTE: Use hydraulic fluid as a lubricant during reassembly.

(1) Carefully install new O-rings inside the rod support and on the outside in the upper groove of the rod
support.

(2) The groove without the slots.
(3) Lubricate the piston rod O-ring and install it on the lower end of the piston rod.
(4) Install the O-ring on the piston, then slide the piston onto the lower end of the piston rod with the chamfer

facing the piston rod O-ring.
(5) Clean the lower threads of the piston rod and spring guide with alcohol or acetone.
(6) Apply Loctite® 262 to the lower threads of the piston rod.

NOTE: Allow to dry for 24 hours before exposing the area to hydraulic fluid.
(7) Install the small spring on the bottom of the piston rod and the spring guide with the large end upward. Use

pliers to tighten the spring guide.
(8) Lubricate the piston rod with hydraulic fluid, then slide the rod support onto the piston rod from the top with

the O-ring groove toward the clevis end.
(9) Lubricate the interior of the cylinder body with hydraulic fluid and insert the compression spring and piston

rod assembly.
(10) Install the snap ring. To do this, apply pressure to the piston rod, this will compress the compression

spring. Insert the rod support further into the body until the snap ring groove is exposed.
(11) Reinstall the jam nut and clevis.

Page 201

MAINTENANCE MANUAL SUPPLEMENT 32-40-03- Cleveland Brake Master Cylinders
C550GT-AD016-FU24-0213
Cleveland Brake Master Cylinders Revision: Initial Issue DATE: 01/01/2020

Cleveland Brake Master Cylinders Maintenance Practices / Removal and Installation
Removal and Installation

Maintenance Practices
Removal and Installation

1. Cleveland Model 10-95 Brake Master Cylinder.

For Description, Operation, Maintenance Practices and procedures for the Cleveland 10-95 brake master
cylinders.
Ref. Ext. Doc: Parker/Hannifin Repair Kit 199-518 Instructions for Overhaul and Repair.

Refer to Chapter 32 of the FU24A-954 Maintenance Manual for all other maintenance.

Page 401

MAINTENANCE MANUAL SUPPLEMENT 32-40-03- Grove Brake Master Cylinders
C550GT-AD016-FU24-0213
Grove Brake Master Cylinders Revision: Initial Issue DATE: 01/01/2020

Grove Brake Master Cylinders Maintenance Practices / Removal and Installation
Removal and Installation

1. Grove 678-3 Master Cylinder Removal.

(1) Drain the hydraulic fluid from the system by loosening the bleeder valve on the brake caliper. Collect the
drained fluid and dispose of it safely. Pumping the master cylinder will help this process.

(2) Disconnect the hydraulic lines from the master cylinder.
NOTE: Cap the hydraulic lines to prevent contamination.c. Disconnect the attach bolts from the top and
bottom of the master cylinder and remove the master cylinder.

2. Grove 678-3 Master Cylinder Installation.

(1) Reinstall the upper and lower attach bolts.
NOTE: Do not over-tighten the nuts. This may prevent freedom of travel of the master cylinder.

(2) Check that the clevis is adjusted to allow full travel of the master cylinder piston rod from the brake pedal
and that the adjustment allows the piston rod to fully extend.

(3) Remove the caps and attach the hydraulic hoses to the master cylinder.
(4) Bleed the Brake System. See Chp. 32 Brake System Bleeding.

Page 402