C550GT ICA v.8 11-09-2020 copy

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

Brake System Bleeding Maintenance Practices / Adjustment and Test
Adjustment and Test

Adjustment and Test

1. Brake System Bleeding.
NOTE: Use MIL-H-5606 hydraulic fluid (or equivalent).

(1) Remove the vent plug from the brake system reservoir.
(2) Connect a clean hydraulic pressure source such as a hydraulic hand pump, to the bleeder valve on the lower

end of the wheel cylinder.
(3) Open the bleeder valve one-half turn.
(4) Pump hydraulic fluid into the system while you monitor the level in the brake system reservoir. When the

reservoir is almost full, tighten bleeder fitting and remove hydraulic pressure source.
(5) Replace and tighten brake system reservoir vent plug.
(6) Apply hard pressure to the brake pedal. Make sure that you have a “hard pedal” and that there are no leaks.

You may have to pump the brake pedal several times.
NOTE: If a “soft pedal” condition exists, repeat steps (1) though (6).

Page 501

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

Brake Master Cylinder Maintenance Practices / Inspection and Check
Inspection and Check

Inspection and Check

1. Brake Master Cylinder Inspection. (Installed)
Check the master cylinders periodically for:

Cleanliness.

Visually inspect the master cylinder and surrounding area for signs of hydraulic fluid and/or other contamination.
NOTE: Make sure that the piston rod is free of contamination which can cause damage to the O-ring.

Leaks.

If there are signs of leakage at the fittings, tightening or replacement of the fittings should remedy the problem.
If the master cylinder has been overfilled, evidence of leakage will be present, but no action is necessary other
than cleaning the leaked fluid. If the cylinder is leaking around the piston rod, remove the cylinder and do an
inspection with reference to the Master Cylinder Inspection section below. Complete all maintenance with
reference to the applicable sections of this CMMS.

Failure to hold pressure.

If the master cylinder does not hold pressure, bleed the system with reference to Brake System Bleeding.
See Chp. 32 Brake System Bleeding.
If this does not correct the problem, the master cylinder should be removed, inspected and repaired as outlined
below.

2. Brake Master Cylinder Inspection. (Removed)
See Chp. 32 Grove 678-3 Master Cylinder Removal.
CAUTION: REPAIR IS LIMITED TO CLEANING AND INSTALLATION OF NEW PARTS ONLY.
(1) Inspect cylinder body for evidence of severe corrosion, cracks, nicks or scoring. If you find these defects,
replace the parts.
(2) Replace any part that has signs of severe corrosion, or other damage that would make it unserviceable.
(3) Inspect the O-rings for wear, brittleness and damage.
NOTE: It is recommended that all O-rings be replaced whenever the master cylinder is disassembled.
(4) Clean all metal parts in solvent and dry with compressed air. O-rings should be cleaned with hydraulic fluid
and wiped clean.

Page 601

MAINTENANCE MANUAL SUPPLEMENT 33-00-00 - Lights DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Lights
Chapter 33

Title Page

Chapter 33
Lights

Chapter 33 Lights

MAINTENANCE MANUAL SUPPLEMENT 33-00-00 - Lights DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Lights
Chapter Content

Chapter Content
Lights

Chapter Contents

Chapter 33 Lights

Applicable Section Guide
33-00-00 Lights
33-40-00 Exterior Lights

Description and Operation
> Wing Tip Navigation and Anti-collision Lights
> Troubleshooting

Components Changed By This STC

Maintenance Practices
Removal and Installation
> Wing Tip Navigation and Anti-collision Lights.

MAINTENANCE MANUAL SUPPLEMENT 33-00-00 - Manual to Use DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Manual to Use
Chapter Guide
MANUAL TO USE
Chapter Guide
Manual to Use N/A FU24- 954 C550GT

Applicable Section Guide X
SECTION / SUB-SECTION X

33-00-00 Lights 
33-10-00 Interior Lights
Description and Operation X
X
Panel Lights X
Dimmer Switch
Cockpit Wander Light (if installed) 
Maintenance Practices
Removal and Installation
Bulb Replacement
Panel Light
Dimmer Switch
Cockpit Wander Light (if installed)

33-40-00 Exterior Lights X 
Description and Operation 
X
Navigation Lights X 
Anti-Collision Lights X
Landing Light X 
Troubleshooting X
Wing Tip Navigation and Anti-collision Lights
Maintenance Practices
Removal and Installation
Navigation Light (Wing Tip navigation and Anti-collision)
Navigation Light (Tail)
Flashing Beacon and Flasher Unit
Strobe Light
Landing Light
Adjustment and Test
Landing Light

MAINTENANCE MANUAL SUPPLEMENT 33-40-00-Lighting System Description
C550GT-AD016-FU24-0213
Lighting System Description Revision: Initial Issue DATE: 01/01/2020

Description and Operation / Lights

Lighting System Description
Lights

33-00-00 Lights
33-40-00 Exterior Lights

Description and Operation

Wing Tip Navigation and Anti-collision Lights

Each wing tip of the C550GT has a Whelen ORION™ 600 Position and Anti-Collision Light.
The unit has a rear white position light, a red or green navigation light and a white strobing anti-collision light. All
are encased in a replaceable clear polycarbonate lens.
The system uses LED technology and 28 VDC that does not require a separate power supply.

Troubleshooting

For Troubleshooting, electrical wiring codes and information on connectors.
Ref. Dwg. No: AD-550GT-3340-001-001

Page 1

MAINTENANCE MANUAL SUPPLEMENT 33-40-00 - Components Changed Table
C550GT-AD016-FU24-0213
Components Changed Table Revision: Initial Issue DATE: 01/01/2020

Components Changed Table CCBTS / Lights
Lights

Components Changed By This STC

Drawing Number Item Part Number Description / Location
Exterior Lights
AD-550GT-3340-001-000 1 01-0771733-11 Wingtip Light (Red)
AD-550GT-3340-001-000 2 01-0771733-12 Wingtip Light (Green)

Page 2

MAINTENANCE MANUAL SUPPLEMENT 33-40-00- Lights
C550GT-AD016-FU24-0213
Lights Revision: Initial Issue DATE: 01/01/2020

Maintenance Practices / Removal and Installation

Removal and Installation
Lights

Maintenance Practices
Removal and Installation

Wing Tip Navigation and Anti-collision Lights.

For Wing Tip Lights Description, Removal, Installation and Inspection.
Ref. Ext. Doc: Whelen™ Form 14661C Installation Guide/ICA for Aviation models OR6002G, OR6002R P/N 01-
0771733-11, 01-0771733-12 Orion 600 Wingtip PTA.

Or go to: www.flyWAT.com

Page 401

MAINTENANCE MANUAL SUPPLEMENT 34-00-00 - Navigation and Pitot Static Systems
C550GT-AD016-FU24-0213
Chapter 34 Revision: Initial Issue DATE: 01/01/2020

Title Page Navigation and Pitot Static Systems

Chapter 34
Navigation and Pitot Static Systems

Chapter 34 Navigation and Pitot Static
Systems

MAINTENANCE MANUAL SUPPLEMENT 34-00-00 - Navigation & Pitot System
C550GT-AD016-FU24-0213
Chapter Content Revision: Initial Issue DATE: 01/01/2020

Chapter Content Navigation & Pitot System
Navigation & Pitot System

Chapter Contents

Chapter 34 Navigation and Pitot Static Systems

Applicable Section Guide
34-10-00 Pitot System

Description and Operation
> Pitot System

34-10-02 Outside Air Temperature
Description and Operation
> Outside Air Temperature Indicator.
Troubleshooting
> Troubleshooting.

Components Changed By This STC

Maintenance Practices
Removal and Installation
> OAT Probe Removal.
> OAT Probe Installation.
Adjustment and Test.
> OAT Indication and Probe

34-20-00 Attitude and Direction
34-20-01 Magnetic Compass
Description and Operation
> Magnetic Compass
Troubleshooting
Maintenance Practices
Removal and Installation
> Magnetic Compass
Adjustment and Test
> Compass Calibration

34-50-00 Navigation Systems
Description and Operation
> Bendix/King KT76A Transponder.
> Troubleshooting
> Removal and Installation
> Adjustment and Test

MAINTENANCE MANUAL SUPPLEMENT 34-00-00 - 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
34-10-00 Flight Environment Data
Description and Operation 

Pitot System 
Static System 
Airspeed Indicator 
Altimeter
Vertical Speed Indicator 
Troubleshooting
Chart 
Maintenance Practices 
Servicing
Pitot Static System Line cleaning
Removal and Installation
Pitot Static System Instruments. (Typical)
Pitot Head (Heated)

Adjustment and Test 
Pitot Static System Leak Test 
Pitot Head Alignment Check

34-20-00 Attitude and Direction 
Description and Operation 

Magnetic Compass 
Troubleshooting 

SIRS Navigation-(Vendor) reference
Maintenance Practices
Removal and Installation

Magnetic Compass Removal
Magnetic Compass Installation

Adjustment and Test 
SIRS Navigation-(Vendor) reference

MAINTENANCE MANUAL SUPPLEMENT 34-00-00 - Manual to Use DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Manual to Use
Chapter Guide

Applicable Section Guide MANUAL TO USE
SECTION / SUB-SECTION
N/A FU24- 954 C550GT
34-50-00 Dependent Positioning Determining
Description and Operation X

GPS Navigation - (Varies with Aircraft- see Form 2129)
Transponder
Maintenance Practices
Servicing

Removal and Installation 
Transponder

Adjustment and Test 
Transponder

MAINTENANCE MANUAL SUPPLEMENT 34-10-01-Description
C550GT-AD016-FU24-0213
Description Revision: Initial Issue DATE: 01/01/2020

Description and Operation / Pitot System

Description
Pitot System

34-10-00 Pitot System

Description and Operation

Pitot System

Refer to the Description and Operation section in FU24-954 Maintenance Manual Chapter 34, Page 7 to 9 as the
system is unchanged.

Use this information and the FU24-954 Maintenance Manual Chapter 34- Removal and Installation page 11. This
shows the heated type Pitot Head.
For the applicable Pitot Head part number:
Ref. Dwg. No: AD-550GT-3410-001-000

Page 1

MAINTENANCE MANUAL SUPPLEMENT 34-10-02-Outside Air Temperature System
C550GT-AD016-FU24-0213
Outside Air Temperature System Revision: Initial Issue DATE: 01/01/2020

Description and Operation / O.A.T System

Outside Air Temperature System
O.A.T System

34-10-02 Outside Air Temperature

Description and Operation

Outside Air Temperature Indicator.

The Engine Data Converter (EDC) processes air temperature data from a remote sensor installed in the fuselage,
forward of the windscreen. The Engine Monitor Panel (MVP-50T) receives this data and digitally displays the
temperature on the main screen.

Troubleshooting

Troubleshooting.

(1) General Faultfinding

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

(2) For Electrical Schematic.
Ref. Dwg. No: AD-550GT-7700-001-201

Page 1

MAINTENANCE MANUAL SUPPLEMENT 34-10-02 - Components Changed Table
C550GT-AD016-FU24-0213
Components Changed Table Revision: Initial Issue DATE: 01/01/2020

Components Changed Table CCBTS / Navigation & Pitot Static System
Navigation & Pitot Static System

Components Changed By This STC

Drawing Number Item Part Number Description / Location
AD-550GT-3410-002-000
AD-550GT-3910-001-000 1 P-128 OAT Probe
AD-550GT-3910-001-000
20 NV2C-28V-SH Magnetic Compass

20 NV2-21S Compass Mount

Page 2

MAINTENANCE MANUAL SUPPLEMENT 34-10-02- Outside Air Temperature Indication
C550GT-AD016-FU24-0213
Outside Air Temperature Indication Revision: Initial Issue DATE: 01/01/2020

Removal and Installation Maintenance Practices / Removal and Installation
Outside Air Temperature Indication

Maintenance Practices
Removal and Installation

1. OAT Probe Removal.

Ref. Dwg. No: AD-550GT-3410-002-000

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

2. OAT Probe Installation.

Ref. Dwg. No: AD-550GT-3410-002-000

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

Page 401

MAINTENANCE MANUAL SUPPLEMENT 34-10-02- O.A.T Indication
C550GT-AD016-FU24-0213
O.A.T Indication Revision: Initial Issue DATE: 01/01/2020

Adjustment and Test Maintenance Practices / Adjustment and Test
O.A.T Indication

Adjustment and Test.

1. OAT Indication and Probe

For adjustment and test of the probe:
Ref. Ext. Doc: Electronics International Inc. MVP-50T Instructions for Continued Airworthiness (Doc. 06201101,
latest revision).

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

Title Page

Page 501

MAINTENANCE MANUAL SUPPLEMENT 34-20-01-Magnetic Compass Description
C550GT-AD016-FU24-0213
Magnetic Compass Description Revision: Initial Issue DATE: 01/01/2020

Description and Operation / Magnetic Compass

Magnetic Compass Description
Magnetic Compass

34-20-00 Attitude and Direction
34-20-01 Magnetic Compass

Description and Operation

Magnetic Compass

The modification installs a Model NV2C-28V-SH magnetic compass on the lower inside of the windscreen
centreline. The compass is an autonomous unit and has an integral compensation system. This system lets you
compensate for the magnetic disturbances created by the mechanical and electrical characteristics of the
aircraft.

Troubleshooting

Troubleshooting.

Technical Help provided by SIRS Navigation Ltd.
Refer to the SIRS Navigation-(Vendor) Instructions for Continued Airworthiness in the Associated Publications
section of this document. Link to this section
Ref. Ext. Doc: SIRS Navigation ICA.

Page 1

MAINTENANCE MANUAL SUPPLEMENT 34-20-01- Magnetic Compass
C550GT-AD016-FU24-0213
Magnetic Compass Revision: Initial Issue DATE: 01/01/2020

Maintenance Practices / Removal and Installation

Removal and Installation
Magnetic Compass

Maintenance Practices
Removal and Installation

Magnetic Compass

Install Compass NV2C-28V-SH with reference to the SIRS NAVIGATOR AIRCRAFT COMPASS Installation and
Removal Instructions.
Ref. Ext. Doc: SIRS Navigation ICA.

Ref. Dwg. No: AD-550GT-3910-001-000 Adjustment and Test
NOTE: See Note 3 on this drawing for information on Magnetic Compass Installation.

Adjustment and Test

1. Compass Calibration

For compass adjustment and correction, refer to the SIRS NAVIGATOR’ AIRCRAFT COMPASS Installation
Instructions.
Ref. Ext. Doc: SIRS Navigation ICA.

Page 401

MAINTENANCE MANUAL SUPPLEMENT 34-50-02-Transponder
C550GT-AD016-FU24-0213
Transponder Revision: Initial Issue DATE: 01/01/2020

Description and Operation / Navigation Systems

Transponder
Navigation Systems

34-50-00 Navigation Systems

Description and Operation

Bendix/King KT76A Transponder.

NOTE: ALL INSTALLATIONS OF COMMUNICATION AND NAVIGATION SYSTEMS ARE THE SUBJECT OF
MODIFICATION ACTION TO THE BASIC AIRCRAFT.

This section of the CMMS describes the system, location of components and reference to removal and
installation.
Refer to the aircraft's Approved Aircraft Radio Station and Equipment Approval Levels NZCAA - Form 2129 for
equipment applicable and modification references. Refer to the Form CAA 337 for the specific equipment’s
installation data and electrical schematics.

Description and Operation
The LH Instrument Sub-panel has a Bendix/King KT76A Transponder transmitter/receiver unit.

The KT76A enables ATC computers to display the aircraft identification, altitude and ground speed enroute. The
units IDENT facility will positively identify the aircraft to ATC.

The Altitude Encoder/Configuration Module mounts to the horizontal shelf behind the Instrument Panel.

The Transponder antenna is located on the underside of the fuselage below the cockpit.

Troubleshooting

Ref. Ext. Doc: KT76A Bendix/King Transponder Installation Manual.
Go to Aviation Support at www.honeywell.com or see the Publications List in the Preliminary Section of this
CMMS.

For wiring codes, specifications, connector layout and detailed wiring diagrams, see the applicable CAA Form 337
for modification reference data.

Removal and Installation

Ref. Ext. Doc: KT76A Bendix/King Transponder Installation Manual.
See the applicable CAA Form 337 for modification reference data.

Adjustment and Test

Ref. Ext. Doc: KT76A Bendix/King Transponder Installation Manual.

Page 1

MAINTENANCE MANUAL SUPPLEMENT 39-00-00 - Instrument and Electrical Panels
C550GT-AD016-FU24-0213
Chapter 39 Revision: Initial Issue DATE: 01/01/2020

Title Page Instrument and Electrical Panels

Instrument and Electrical Panels
Chapter 39

Chapter 39 Instrument and Electrical Panels

MAINTENANCE MANUAL SUPPLEMENT 39-00-00 - Instrument & Electrical Panels
C550GT-AD016-FU24-0213
Chapter Contents Revision: Initial Issue DATE: 01/01/2020

Chapter Contents Instrument & Electrical Panels
Instrument & Electrical Panels

Chapter Contents

Chapter 39 Instrument and Electrical Panels

Applicable Section Guide
39-10-00 Instrument Panels
Description and Operation.
> Instrument Panel

Components Changed By This STC
Maintenance Practices
> Instrument Panels - Removal and Installation.
Inspection and Check.
> Inspection of Centre Panel Isolation Mounts.

MAINTENANCE MANUAL SUPPLEMENT 39-00-00 - Manual to Use DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Manual to Use
Chapter Guide
MANUAL TO USE
Chapter Guide
Manual to Use N/A FU24- 954 C550GT

Applicable Section Guide 
SECTION / SUB-SECTION 

39-00-00 Instrument and Control Panels
General

39-10-00 Instrument Panels
Description and Operation

Main Instrument Panel
Instrument Sub-Panels

Maintenance Practices 

Removal and Installation
Instrument Panels- Main and Sub-panels

Inspection and Check 
Centre Panel Mounts

MAINTENANCE MANUAL SUPPLEMENT 39-10-00-Instrument Panel Description
C550GT-AD016-FU24-0213
Instrument Panel Description Revision: Initial Issue DATE: 01/01/2020

Instrument Panel Description Description and Operation / Electrical Panels
Electrical Panels
39-10-00 Instrument Panels
Instrument Panel
Description and Operation.
The C550GT has five instrument panels.

The LH Sub-Panel contains the Navigation
and Communication head units. This panel
also houses the Hour Meter and E.L.T.
Control Head. Two isolation-mounted Centre
Panels contain the essential and optional
flight instruments.
Below the Centre Panel is the Circuit
Breaker/Switch panel.

The RH Sub-Panel has the MVP-50T Turboprop Engine Monitor and
annunciator lights, the Elevator Trim Indicator and USB receptacles.

The LH and RH Sub-Panels and Circuit Breaker / Switch Panel fasten
directly to the instrument panel structure with screws. Access to
components and the area behind the instrument panel is by separate
removal of Panels and Sub-Panels.

The Centre Panels are the only isolation mounted panels. Each panel
has four supporting rubber mounts. Cap nuts fasten the panels to the
mounts.

Page 1

MAINTENANCE MANUAL SUPPLEMENT 39-10-00 - Components Changed Table
C550GT-AD016-FU24-0213
Components Changed Table Revision: Initial Issue DATE: 01/01/2020

Components Changed Table CCBTS / Electrical Panels
Electrical Panels

Components Changed By This STC

Drawing Number Item Part Number Description / Location

39-00-00 Electrical Panels

AD-550GT-3910-001-000 1 1/4 UNC Commercial Isolator Mount

AD-550GT-3910-001-000 4 AD-550GT-3910-001-060 Top Panel

AD-550GT-3910-001-000 8 AD-550GT-3910-001-200 LH Sub-Panel

AD-550GT-3910-001-000 9 AD-550GT-3910-001-300 Flight Inst. Panel

AD-550GT-3910-001-000 10 AD-550GT-3910-001-400 RH Sub-Panel

AD-550GT-3910-001-000 19 NDB14N Dome Nut

AD-550GT-3910-001-000 7 AD-550GT-3910-001-100 Centre Panel

AD-550GT-3910-001-000 11 AD-550GT-3910-001-500 LH Bracket Assy.

AD-550GT-3910-001-000 12 AD-550GT-3910-001-600 RH Bracket Assy.

AD-550GT-3910-001-000 13 AD-550GT-3910-001-700 Stand Off Bracket

AD-550GT-3910-001-000 14 AD-550GT-3910-001-800 Stand Off Bracket

AD-550GT-3910-001-000 6 AD-550GT-3910-001-080 Blanking Panel Assy.

Page 2

MAINTENANCE MANUAL SUPPLEMENT 39-10-00- Instrument Panels
C550GT-AD016-FU24-0213
Instrument Panels Revision: Initial Issue DATE: 01/01/2020

Instrument Panels Maintenance Practices / Removal and Installation
Removal and Installation

Maintenance Practices

1. Instrument Panels - Removal and Installation.

Ref. Dwg. No: AD-550GT-3910-001-000

CAUTION: BEFORE YOU WORK ON THE ELECTRICAL SYSTEM MAKE SURE YOU ISOLATE THE BATTERY AND
DISCONNECT GROUND POWER.

LH and RH Sub-Panel Removal.
(1) Set the Battery Master switch to OFF.
(2) Support the panel and remove the perimeter screws.
(3) Carefully move the Sub-Panel away from the frame.

NOTE: Support the panel to prevent damage to the wiring or components.

LH and RH Sub-Panel Installation.
(1) Set the Battery Master switch to OFF.
(2) Position the Panel and install the perimeter screws.

Figure 39.1 Instrument Panel

Centre Panels Removal.
(1) Set the Battery Master switch to OFF.
(2) Support the panel and remove the four cap nuts.
(3) Carefully move the panel away from the mount structure.

NOTE: Support the panel to prevent damage to the wiring or components.

Centre Panels Installation.
(1) Set the Battery Master switch to OFF.
(2) Support the panel and install the four cap nuts.

Circuit Breaker and Switch Panel Removal.
(1) Set the Battery Master switch to OFF.
(2) Support the panel and remove the perimeter screws.
(3) Carefully move the Switch Panel away from the frame.

NOTE: Support the panel to prevent damage to the wiring or components.
(4) Circuit Breaker and Switch Panel Installation.
(5) Set the Battery Master switch to OFF.
(6) Position the Panel and install the perimeter screws.

Page 401

MAINTENANCE MANUAL SUPPLEMENT 39-10-00- Panel Isolation Mounts
C550GT-AD016-FU24-0213
Panel Isolation Mounts Revision: Initial Issue DATE: 01/01/2020

Panel Isolation Mounts Maintenance Practices / Inspection & Check
Inspection & Check

Inspection and Check.

1. Inspection of Centre Panel Isolation Mounts.
(1) Remove the Centre Panels. See Chp. 39 Instrument Panels - Removal and Installation.
(2) Set the Battery Master switch to OFF.
(3) Support the panel and remove the four cap nuts.
(4) Carefully move the panel away from the mount structure.
NOTE: Support the panel to prevent damage to the wiring or components.

Inspection.

a. Inspect all bonded isolation mounts for metal-to-rubber bond separations, flex cracks, rubber
deterioration and mechanical damage.
b. Replace any isolation mounts that have signs of damage.

Centre Panels Installation.
(1) Set the Battery Master switch to OFF.
(2) Support the panel and install the four cap nuts.

Page 601

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

Title Page

Chapter 40
Hopper

Chapter 40 Hopper

Title Page

MAINTENANCE MANUAL SUPPLEMENT 40-00-00 - Hopper DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Hopper
Chapter Contents

Chapter Contents
Hopper

Chapter Contents

Chapter 40 Hopper

Applicable Section Guide
40-00-00 Hopper

Description and Operation

Components Changed By This STC

Maintenance Practices
Removal and Installation
> Hopper Removal.
> Hopper Installation.
> Hopper Window

MAINTENANCE MANUAL SUPPLEMENT 40-00-01 - Chapter Guide DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Manual to Use
Chapter Guide
MANUAL TO USE
Chapter Guide
Manual to Use N/A FU24- 954 C550GT

Applicable Section Guide 
SECTION / SUB-SECTION 

40-00-00 Hopper
Description and Operation

62.5 cubic ft. Hopper

Hopper Bottom Closing Structure

Hopper Light and Window

Troubleshooting

Maintenance Practices X
X
Servicing X
Hopper- Visual Examination
Hopper Light 
Hopper Window 

Removal and Installation
Hopper Removal X
Hopper Installation
Closing Structure 
Light
Window

Adjustment and Test X
Hopper Leak Test

Inspection and Check

Page i

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

Description / Differences Description and Operation / Hopper
Hopper

40-00-00 Hopper

Description and Operation

Hopper Description

The hopper is a removable prefabricated container for agricultural chemicals central to the aircraft’s role of
spreading dry chemicals. It has a capacity of 62.5 cubic feet and is constructed in upper and lower sections from
moulded reinforced fiberglass. It has a loading aperture formed in the top section and a 42” wide rectangular
reinforced outlet in the bottom section. The top and bottom sections are first bonded together then bolted at the
front and rear flanges. The hopper is then attached by bolts through the side flanges to the fuselage upper
longerons.
A structural sheetmetal cover, shaped to the top contour of the fuselage and reinforced by frames, stringers and
longerons is fitted over the fibreglass hopper and forms part of the hopper installation (Refer Chapter 53).
A fibreglass loading-aperture extension, attached to the hopper cover, improves loading and an integral lid
prevents spillage.
The hopper and cover are located between STA 98.50 and 166.53. The cover is attached to the hopper loading
aperture, fuselage side and upper skins by screws. Gaps between the hopper outlet and the surrounding
fuselage belly structure are closed by fore, aft, LH and RH closing strips and panels.
The hopper has a Perspex® window in the front face of the top section. Through a cut-out in the removable
bulkhead, the pilot can see the level of chemical in the hopper.

Page 1

MAINTENANCE MANUAL SUPPLEMENT 40-00-00 - Components Changed Table
C550GT-AD016-FU24-0213
Components Changed Table Revision: Initial Issue DATE: 01/01/2020

Components Changed Table CCBTS / Hopper
Hopper

Components Changed By This STC

Drawing Number Item Part Number Description / Location

40-00-00 Hopper Installation

AD-550GT-9250-001-000 1 08-14017-1 Hopper Sealing Strip-Rear

AD-550GT-9250-001-000 2 08-14017-2 Hopper Sealing Strip-Front

AD-550GT-9250-001-000 3 0814019-1 Side Sealing Strip

AD-550GT-9250-001-000 4 08-14021-1 Side Cover

AD-550GT-9250-001-000 5 08-14023-1 Front Closing Panel

AD-550GT-9250-001-000 6 08-90011-13 Hopper Top

AD-550GT-9250-001-000 7 08-90043-2 Closing Panel-Rear

AD-550GT-9250-001-000 8 08-90045 Closing Panel Front

AD-550GT-9250-001-000 9 08-90111-11 Hopper Bottom (wide)

AD-550GT-9250-001-000 10 08-90117-1 Clamp Bar

AD-550GT-9250-001-000 11 AD-550GT-9250-001-14 Doubler

AD-550GT-9250-001-000 12 AD-550GT-9250-001-15 Doubler

AD-550GT-9250-001-000 13 AD-550GT-9250-001-16 5mm Perspex Window

AD-550GT-9250-001-000 14 AD-550GT-9250-001-17 Cork gasket

AD-550GT-9250-001-000 31 AD-A11-5350-778-100 Fairing (ACL)

40-00-01 Hopper Outlet Valve Installation

AD-550GT-9250-003-000 1 08-48081-1 Outlet Valve (Stainless Steel)

AD-550GT-9250-003-000 2 AD-A11-5350-777-100 Fairing (ACL)

Page 2

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

Removal and Installation Maintenance Practices / Removal and Installation
Hopper

Maintenance Practices
Removal and Installation

1. Hopper Removal.
Ref. Dwg. No: AD-550GT-9250-003-000
Ref. Dwg. No: AD-550GT-9250-001-000
(1) Remove the cockpit canopy. Refer to FU24-954 MM Chp. 52, Para. 2 (iii)
(2) Inside the cockpit, disconnect the crew restraint harness posts. Refer to FU24-954 MM Chp. 25, Safety
Harnesses, Page 9, Para. 2 (i) and Fig. 25.03
(3) Remove the Detachable Bulkhead. See FU24-954 MM, Chp. 25 Page 6, Para. (v) and Fig. 25.02.
NOTE: If attached, remove the electrical loom from the bulkhead.

WARNING: PERSONNEL HANDLING COMPONENTS INSTALLED ON, OR REMOVED FROM AGRICULTURAL
AIRCRAFT MUST EXERCISE EXTREME CARE TO AVOID PHYSICAL CONTACT WITH SURFACES
THAT MAY BE CONTAMINATED BY HIGHLY TOXIC OR CORROSIVE CHEMICALS. USE
PROTECTIVE CLOTHING AND BREATHING EQUIPMENT OR DISPOSABLE FACIAL MASKS AT ALL
TIMES UNTIL COMPONENTS ARE SATISFACTORILY DECONTAMINATED BY WATER WASHING.

(4) Remove the hopper inlet lid and its operating system from the Hopper Cover.
NOTE: In the next steps, use a second person inside the hopper or fuselage to hold the nuts with a wrench.

(5) Remove the Hopper Cover Extension fasteners from around the hopper opening.
NOTE: It is not necessary to remove the extension from the hopper top.

(6) Remove the screws at the rear and sides of the Hopper Cover.
(7) Carefully remove the Hopper Cover from the fuselage and lift it clear of the aircraft.

NOTE: You need 2-3 personnel for this task.
(8) Under the aircraft, remove the outlet valve fairing.
In the next steps;
Ref. Dwg. No: AD-550GT-9250-001-000

(9) Remove the front closing panel (5).
(10) Remove the bolts (16) that attach the side covers (4).
(11) Remove the fairing (31).
(12) Remove the front closing panel (8) and rear closing panel (7).
In the next steps;
Ref. Dwg. No: AD-550GT-9250-003-000

(13) Remove the 42 bolts (5) that attach the hopper outlet valve (1) to the bottom of the hopper.
(14) Remove the RH and LH sealing strips and clamp bars.

NOTE: Mark the two sealing strips (3) and the two clamp-bars (10) for reassembly.
(15) In the cockpit, disconnect the flap cable (2) at the flap operating lever. Refer to FU24-954 MM Chp. 27, Flap

Control System, page 52, Para. 2 (i)
(16) Attach a 3-metre draw-cord to the disconnected cable end.
(17) Remove the flap cable pulley at the rear of the cockpit.
(18) Carefully pull the flap cable aft through the LH hopper beam.

NOTE: Stow the cable in the cargo bay. Do not pull the draw-cord out of the hopper beam.
In the next steps; See Figure 40.1
(19) Remove the bolts that attach the lateral beam and remove the beam down and out of the aircraft.
(20) Remove the bolts at front and rear of each hopper beam.

NOTE: Do not remove the hopper beams from the hopper tunnels.
(21) Remove the bolts that attach the hopper to the fuselage side longerons (WL 66.0)
(22) Pass a lift strap with a capacity of >250 kg down through the hopper inlet. Attach the lift strap to a suitable

Page 401

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

Maintenance Practices / Removal and Installation

piece of timber positioned fore and aft under the hopper outlet.
NOTE: The timber can be 250 mm x 50 mm and long enough to span the bottom opening of the hopper.

WARNING: DO NOT STAND UNDER THE LOAD. MAKE SURE ALL PERSONNEL STAY CLEAR OF THE HOPPER
DURING THE LIFT. USE ROPE TAG-LINES TO CONTROL THE HOPPER POSITION.

CAUTION: AS YOU LIFT THE HOPPER, MAKE SURE THE TIMBER DOES NOT CONTACT THE FUSELAGE
OPENING.

(23) Use a lifting device, with >250 kg capacity, to slowly raise the hopper.
NOTE: Carefully break the sealant bond between the WL 66.0 longerons and the hopper mounting flange.

(24) As the hopper starts to lift, remove the two hopper beams rearwards from the hopper tunnels.
NOTE: Keep the spacers and packers with the beams. Do not dislodge the draw-cord from the LH hopper
beam.

(25) Lift the hopper out of the fuselage, then move it to one side of the aircraft. Put it down on a level surface.

Figure 40.1 Hopper Beam Detail.

2. Hopper Installation.

Ref. Dwg. No: AD-550GT-9250-003-000
Ref. Dwg. No: AD-550GT-9250-001-000
A. Hopper Installation.
(1) Prepare the LH and RH fuselage WL 66.0 longerons. Remove all the remaining sealant and make sure the

longerons are clean.
(2) Apply low-adhesive sealant MIL-S-8784B (or equivalent) to the hopper support flange and fuselage

longerons.
(3) Pass a lift strap with a capacity of >250 kg down through the hopper inlet. Attach the lift strap to a suitable

piece of timber positioned fore and aft under the hopper outlet.
NOTE: The timber can be 250 mm x 50 mm and long enough to span the bottom opening of the hopper.
WARNING: DO NOT STAND UNDER THE LOAD. MAKE SURE ALL PERSONNEL STAY CLEAR OF THE HOPPER

DURING THE LIFT. USE ROPE TAG-LINES TO CONTROL THE HOPPER POSITION.
(4) Use a lifting device, with >250 kg capacity, to slowly raise the hopper clear of the ground.
CAUTION: MAKE SURE THE HOPPER IS LEVEL AND STABLE ON THE LIFTING DEVICE.

Page 402

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

Maintenance Practices / Removal and Installation

(5) Position the hopper over the hopper bay.
(6) Slowly lower the hopper until the hopper mounting flange is approx. 300 mm above the longerons.
(7) Put the LH and RH hopper beams into the hopper tunnels.

NOTE: Make sure the flap cable draw-cord is in position through the LH hopper beam.
(8) Carefully lower the hopper onto the fuselage longerons.
(9) Remove the lift strap.
(10) Position the hopper and install with bolts (19).
(11) Install the Lateral, LH and RH hopper beams.
(12) Attach the flap cable to the draw-cord and pull it forward through the LH hopper beam.
(13) Install the flap cable pulley at the rear of the cockpit.
(14) Connect the flap cable (2) to the flap operating lever. Refer to FU24-954 MM Chp. 27, Flap Control System.

Para. 2 (iv)
(15) Do a Duplicate Safety Inspection of the Flap Control system.

B. Hopper Cover Installation.

(1) Prepare the structural Hopper Cover for installation. Make sure the doublers and seal strips are clean.
Remove all the remaining sealant.

(2) Apply low-adhesive sealant MIL-S-8784B (or equivalent) to the mating surfaces.
(3) Position the hopper cover over the hopper and align the screw holes.

NOTE: You need 2-3 personnel for this task.
(4) Install the screws through the sides and rear of the hopper cover.

NOTE: Clean off excess sealant.

C. Hopper Top Extension Installation.

(1) If removed, prepare the structural hopper cover extension for installation. Remove all the remaining sealant.
(2) Apply low-adhesive sealant MIL-S-8784B (or equivalent) to the mating surfaces of the hopper top extension.
(3) Install the extension to the hopper cover with the screws, bolts and nuts.

NOTE: Clean off excess sealant.
(4) Install the hopper lid and operating mechanism to the hopper cover.

D. Hopper Outlet Valve and Closing Panels Installation.

Ref. Dwg. No: AD-550GT-9250-003-000
Ref. Dwg. No: AD-550GT-9250-001-000
(1) Install the LH and RH side sealing strips (3) and the clamp bars (10).
(2) Apply low-adhesive sealant MIL-S-8784B (or equivalent) to the bottom hopper flange.
(3) Install the hopper outlet valve (1) to the bottom hopper flange and attach with the bolts (5).
(4) Install the front (8) and rear (7) closing panels.

NOTE: Use low-adhesive sealant MIL-S-8784B (or equivalent).
(5) Install the fairing (31).
(6) Install the side covers (4) with bolts (16).
(7) Install the front closing panel (5).
(8) Install the outlet valve fairing (2).

Page 403

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

Maintenance Practices / Removal and Installation

E. Cockpit Furnishing and Canopy Installation.

(1) Install the Detachable Bulkhead. Refer to FU24-954 MM, Chp. 25 Page 6, Para. (vi) and Fig. 25.02.
(2) Inside the cockpit, install the crew restraint harness posts. Refer to FU24-954 MM Chp. 25, Safety

Harnesses, Page 9, Para. 2 (ii).
(3) Install the canopy. Refer to FU24-954 MM Chp. 52, Page 6, Para. 2 (iv).

Page 404

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

Hopper Window Maintenance Practices / Removal and Installation
Removal and Installation

Hopper Window
For Removal and Installation,
Ref. Dwg. No: AD-550GT-9250-001-000

Title Page

Page 405

MAINTENANCE MANUAL SUPPLEMENT 52-00-00 - Doors DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Doors
Chapter 52

Title Page

Chapter 52
Doors

Chapter 52 Doors

MAINTENANCE MANUAL SUPPLEMENT 52-00-00 - Doors DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Doors
Chapter Content

Chapter Content
Doors

Chapter Content

Chapter 52 Doors

Applicable Section Guide
52-00-00 Doors
52-10-00 Crew Doors

Description and Operation
> Cargo Door
> Internal access Door.
> Cockpit Canopy

Components Changed By This STC

MAINTENANCE MANUAL SUPPLEMENT 52-00-00 - Manual to Use DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Manual to Use
Chapter Guide
MANUAL TO USE
Chapter Guide
Manual to Use N/A FU24- 954 C550GT

Applicable Section Guide 
SECTION / SUB-SECTION 

52-00-00 Doors
Description and Operation 

Cargo Door 
Internal Access Door 
Cockpit Canopy
Maintenance Practices
Servicing
Lubrication
Transparency Cleaning
Transparency Minor Repair
Transparency Replacement

Removal and Installation 
Cargo Door, Hinges & Latches 
Canopy & Canopy Rails 
Canopy Lock Handle & Latch

Adjustment and Test 
Canopy Track Adjustment 
Canopy Roller Adjustment 
Canopy Latch Pin Adjustment

Inspection and Check

MAINTENANCE MANUAL SUPPLEMENT 52-10-00-Canopy- Differences
C550GT-AD016-FU24-0213
Canopy- Differences Revision: Initial Issue DATE: 01/01/2020

Description and Operation / Doors

Canopy- Differences
Doors

52-00-00 Doors
52-10-00 Crew Doors

Description and Operation

Cargo Door

The C550GT Cargo Door is unchanged from the FU24-954 aircraft. Refer to the FU24-954 Maintenance Manual,
Chapter 52 for Description, Operation, Removal, Installation, Inspection an Adjustment.

Internal access Door.

The C550GT rear fuselage Internal Access Door is unchanged from the FU24-954 aircraft. Refer to the FU24-954
Maintenance Manual, Chapter 53 for Description and page 12, Fig. 53.04 for Removal and Installation.

Cockpit Canopy

The basic layout and function of the C550GT cockpit canopy remains the same as the FU24-954. However, the
functionality of the dual control configuration in the C550GT is improved by the inclusion of the 08-600 Dual
Control Canopy. The simplicity of the FU24-954 canopy is retained while a wider canopy frame, blown perspex
side panels and a narrow aluminium centre panel increases cockpit volume and enhances visibility for the flight
crew.

Canopy tracks, seals and latches are unchanged; therefore maintenance and adjustments are the same as with
the baseline FU24-954 aircraft.

Applicable Manual.
Refer to the Chapter 52 Components Changed by This Modification table (CCBTS) for changed part numbers.
Use the FU24-954 Maintenance Manual Chapter 52 - Doors, Page 3 thru 7, for description, operation and all
maintenance procedures except as shown below.

Chapter 52 – Doors, Description and Operation
FU24-954 Manual section not applicable.
FU24-954 Maintenance Manual Chapter 52.
Description and Operation, Cockpit Canopy paragraph, page 3,

Reason the FU24-954 Manual section is not applicable.
The Description/Operation section states; an opaque fibre-glass top panel. The C550GT has a canopy top panel
fabricated in aluminium sheet.
Applicable Manual section.
Refer to the Components Changed by This Modification table (CCBTS) for applicable part number.
Additional Information.
Refer to the Cresco 08-600 Illustrated Parts Manual Chapter 56 – Windows, Figure 3, page 7, item 18

Page 1

MAINTENANCE MANUAL SUPPLEMENT 52-10-00 - Components Changed Table
C550GT-AD016-FU24-0213
Components Changed Table Revision: Initial Issue DATE: 01/01/2020

Components Changed Table CCBTS / Doors
Doors

Components Changed By This STC

Drawing Number Item Part Number Description / Location

Cockpit Canopy

08-600 IPM, Chp.56, Fig.3 28 08-15015-1 Frame Assembly, Dual

08-600 IPM, Chp.56, Fig.3 19 08-15017-1 Panel, Side, LH Dual

08-600 IPM, Chp.56, Fig.3 19 08-15018-1 Panel, Side, RH Dual

08-600 IPM, Chp.56, Fig.3 18 08-15019-1 Panel, Centre, Dual

Page 2

MAINTENANCE MANUAL SUPPLEMENT 53-00-00 - DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue
Fuselage

Title Page

Fuselage
Chapter 53

Chapter 53 Fuselage

MAINTENANCE MANUAL SUPPLEMENT 53-00-00 - Fuselage DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Fuselage
Chapter Contents

Chapter Contents
Fuselage

Chapter Contents

Chapter 53 Fuselage

Applicable Section Guide
53-10-00 Fuselage Main Frame

Description and Operation
> Fuselage Differences
> Hopper Bay Description / Differences

53-40-00 Attach Fittings
53-40-01 Elevator Brackets
Description and Operation
> Stabilator Hinge Reinforcement Brackets.
Maintenance Practices
Inspection and Check
> Elevator Reinforcement Bracket Inspection.
53-40-02 Engine Struts
Description and Operation
> Engine Frame Reinforcements. (Engine Struts)
Maintenance Practices
Inspection and Test
> Engine Strut Inspection.
> Lower Engine Mount Bracket Inspection.
53-60-01 Cockpit Access
Description and Operation
> Cockpit Entry Steps
Removal and Installation
> Cockpit Steps

MAINTENANCE MANUAL SUPPLEMENT 53-00-00 - 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
53-00-00 Fuselage N/A FU24-954 C550GT
Description and Operation
C550GT Fuselage Description / Differences 
Forward Fuselage
Firewall X
Instrument Panel Frame X
Cockpit Area X
Cockpit Rear Bulkhead X
Hopper/Cargo Area (Hopper Bay) X
Rear Wing Attachment Frame
Rear Fuselage 
Rear Bulkhead
Cargo Area X
X
X
X

Elevator Attachment Reinforcement Brackets 
Troubleshooting
Maintenance Practices X
Disassembly and Reassembly X
Replacement
Servicing X
X
Structural Corrosion X
Battery Box Cleaning X
Removal and Installation X
Stressband X
Cockpit Floor Rails
Cockpit Flight Controls Access Panels 
Flight Controls Access Panels
Cargo Floor and Tie Downs X
Internal Access Door (STA 240.5) X
Battery Box
Tailcone 
Tail Bumper 
Hopper Cover (Structural)
Cockpit Entry Steps

MAINTENANCE MANUAL SUPPLEMENT 53-00-00 - 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
53-00-00 Fuselage Cont’d N/A FU24-954 C550GT

Inspection/Check 
Engine to Fuselage Struts 
Elevator Attachment Reinforcement Brackets

Cleaning and Painting
Approved Repairs

MAINTENANCE MANUAL SUPPLEMENT 53-10-00-Fuselage Differences
C550GT-AD016-FU24-0213
Fuselage Differences Revision: Initial Issue DATE: 01/01/2020

Description and Operation / Fuselage

Fuselage Differences
Fuselage

53-10-00 Fuselage Main Frame

Description and Operation

Fuselage Differences

You will find there are changes in the position of some fuselage Station Numbers. This is due to the fuselage
extension and the increase in the dimensions of the powerplant installation. The Rear Fuselage station numbers
from the Wing Rear Attachment (STA 166.6) through to the Rear Bulkhead (STA 355.0) are unchanged. Refer to
the C550GT Station Diagram in Chapter 6. (Link)

See Figure 53.1, this gives an overall view of the fuselage areas that change with this modification. Much of the
FU24-954 Maintenance Manual remains applicable, use the Applicable Section Guide. Link to this section

Figure 53.1 Fuselage Changes - Overview.

The fuselage firewall through to the cockpit rear bulkhead is unchanged. Use the FU24-954 Maintenance Manual
Chp. 53 Pg. 3 para i, ii, iii, iv for description and structural information.

The C550GT has aluminium struts and brackets to add resilience to the critical area where engine frame
transfers loads to the fuselage. See Section 53-40-02

The fuselage extension is a significant primary-structure design change. Therefore, para (v) Pg. 5 of the FU24-
954 Maintenance Manual Chp. 53 is not applicable. Refer to the Hopper Bay (Hopper/Cargo Area) of this
Crusader Maintenance Manual Supplement (CMMS) for details of changes. See Chp. 53 Hopper Bay Description /
Differences

The Rear Fuselage from the Wing Rear Attachment (STA 166.6) through to the Rear Bulkhead (STA 355.0) is
unchanged. Refer to Chp. 53 Pg. 5 of the FU24-954 Maintenance Manual.

On the inside of the fuselage the rear bulkhead has additional reinforcement brackets that support the elevator
attachment. Use the CMMS for inspection, removal and installation of these components. See Chp. 53 Stabilator
Hinge Reinforcement Brackets.

The fuselage modification makes space for a Wide Outlet type hopper. Removable load beams pass through
integral tubes in the larger fibreglass hopper. These beams replace the fixed fuselage longerons so that removal
of the hopper is possible. For maintenance of the hopper and supporting fuselage structure, use the CMMS. For
all other maintenance use the FU24 MM.

Page 1

MAINTENANCE MANUAL SUPPLEMENT 53-10-00-Hopper Bay Differences
C550GT-AD016-FU24-0213
Hopper Bay Differences Revision: Initial Issue DATE: 01/01/2020

Description and Operation / Hopper Bay Structure

Hopper Bay Differences
Hopper Bay Structure

Hopper Bay Description / Differences

An 18-inch Fuselage Extension section, added forward of STA 115.34, is a design change that allows for a larger
Cresco 08-600 hopper. This change moves the existing FU24-954 fuselage frame at STA 115.34 forward to STA
97.34. A replacement frame, installed at STA 115.34, has clips that attach it to the upper longerons.

The larger hopper bay extends from STA 97.34 to a heavy-duty frame at STA 166.53. The bay has two longer
upper longerons at WL 66 at R and L, two mid longerons at WL 46 at R and L and two lower longerons and
hopper beams at WL 32.0.

The position of the fuselage partial frame at STA 143.0 changes, moving aft to STA 153.65. This frame has
brackets to attach the removable hopper beams as does the frame at STA 115.34.

Removable load beams, that pass through integral tubes in the larger fibreglass hopper, replace the lower
fuselage longerons. These beams allow for the removal of the hopper. (Link) Load Beam 53-20-01

The modification also adds two frames, one on each side at STA 135.0. These frames are a narrow section to
make room for the larger hopper.

The modification introduces a reinforced structural Hopper Cover that fits over the fibreglass hopper. Fasteners
attach it to the top of the hopper, the upper fuselage longerons and fuselage frames. The Hopper Cover closes
and seals the top of the hopper bay, retaining the fuselage contour.

Closing panels at front and rear of the hopper outlet-valve seal the base of the hopper bay.

The fuselage structural components added by this modification are of the same material standards as the basic
aircraft. Maintenance, Servicing and Inspection is the same as the FU24-954 except where specified in the
Chapter 53 Guide.

Page 2

MAINTENANCE MANUAL SUPPLEMENT 53-40-01-Elevator Brackets Description
C550GT-AD016-FU24-0213
Elevator Brackets Description Revision: Initial Issue DATE: 01/01/2020

Elevator Brackets Description Description and Operation / Elevator Brackets
Elevator Brackets
53-40-00 Attach Fittings
Stabilator Hinge Reinforcement Brackets. 53-40-01 Elevator Brackets

Description and Operation

The C550GT fuselage extension gives the stabilator greater leverage and control. This creates increased loads on
specific areas of the existing structure.
On the inside of the fuselage rear bulkhead, CAC adds reinforcement brackets that support the stabilator
attachment. The brackets bolt to the existing fuselage stringers, rear bulkhead and hinge bracket. They give
more load transfer capability and structural redundancy.

Use the C550GT Maintenance Manual Supplement (CMMS) for Inspection of these components.See Chp. 53
Elevator Reinforcement Bracket Inspection.

Figure 53.2 Stabilator Hinge Reinforcement.
Page 1

MAINTENANCE MANUAL SUPPLEMENT 53-40-01- Elevator Reinforcement Brackets
C550GT-AD016-FU24-0213
Elevator Reinforcement Brackets Revision: Initial Issue DATE: 01/01/2020

Inspection & Check Maintenance Practices / Inspection & Check
Elevator Reinforcement Brackets

Maintenance Practices
Inspection and Check

1. Elevator Reinforcement Bracket Inspection.
Ref. Dwg. No: AD-550GT-5310-003-000

CAUTION: MAKE SURE THE TAIL STAND IS IN POSITION BEFORE YOU ENTER THE REAR FUSELAGE.

In the Cargo Bay.
Remove the Internal Access Door to the rear fuselage.
(1) Locate the two elevator reinforcement brackets at the rear bulkhead frame. See Figure 53.2
(2) Carefully examine the elevator brackets for signs of:

a. Looseness of the bracket.
b. Loose or damaged fasteners.
c. Cracks in the radiused corners.
d. Cracks from fastener holes.

If you find any damage or cracks, contact Crusader Aircraft Company for support.

Page 601