C550GT ICA v.8 11-09-2020 copy

MAINTENANCE MANUAL SUPPLEMENT 53-40-02-Overview and attachment
C550GT-AD016-FU24-0213
Overview and attachment Revision: Initial Issue DATE: 01/01/2020

Overview and attachment Description and Operation / Engine Struts
Engine Struts

53-40-02 Engine Struts

Description and Operation

Engine Frame Reinforcements. (Engine Struts)
Ref. Dwg. No: AD-550GT-7120-001-000

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

Figure 53.3 Engine Mount struts and brackets.
Page 1

MAINTENANCE MANUAL SUPPLEMENT 53-40-02- Engine Frame attachment
C550GT-AD016-FU24-0213
Engine Frame attachment Revision: Initial Issue DATE: 01/01/2020

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

Maintenance Practices
Inspection and Test

1. Engine Strut Inspection.

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

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

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

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

(3) Look for:

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

(4) Examine the doubler plate for loose bolts, damage, cracks or chafe.

Result.
If you find any damage, contact CAC for support.
(5) Re-torque the strut attachment fasteners and engine frame bolts. (Link) Chp. 5 Scheduled Inspection

2. Lower Engine Mount Bracket Inspection.

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

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

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

Result.

If you find any damage, contact CAC for support.

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

Page 601

MAINTENANCE MANUAL SUPPLEMENT 53-60-00-Description / Differences
C550GT-AD016-FU24-0213
Description / Differences Revision: Initial Issue DATE: 01/01/2020

Description and Operation / Cockpit Entry Steps

Description / Differences
Cockpit Entry Steps

53-60-01 Cockpit Access

Description and Operation

Cockpit Entry Steps

The fuselage extension changes the position of the wing in relation to the cockpit entry door and does not permit
safe entry to the cockpit. The modification adds upper and lower cockpit entry steps on each side of the fuselage
for crew access to the cockpit.

Figure 53.4 Cockpit Steps. Removal and Installation

Removal and Installation.
Cockpit Steps
Use the drawing referenced below for removal and installation.
Ref. Dwg. No: AD-550GT-5340-001-000

Page 1

MAINTENANCE MANUAL SUPPLEMENT 55-00-00 - Stabilisers DATE: 01/01/2020
Revision: Initial Issue Stabilisers
C550GT-AD016-FU24-0213

Chapter 55

Title Page

Chapter 55
Stabilisers

Title Page

Chapter 55 Stabilisers

MAINTENANCE MANUAL SUPPLEMENT 55-00-00 - Stabilisers DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Stabilisers
Chapter Contents

Chapter Contents
Stabilisers

Chapter Contents

Chapter 55 Stabilisers

Applicable Section Guide
55-10-00 Stabilator

Description and Operation
> Terminology
> Stabilator
> Stabilator Trim Tab (Anti-servo Tab)

Maintenance Practices
Removal and Installation
> Stabilator Removal
> Stabilator Installation
> Counter Balance Tube
> Stabilator Trim Tab (Anti-Servo Tab)
Adjustment and Test
> Stabilator (In-Situ) Balancing with Counter Balance Tube

55-30-00 Vertical Stabilisers
55-30-01 Fin
Description and Operation
> Vertical Stabiliser (Fin) Differences
Maintenance Practices
Removal and Installation
> Vertical Stabiliser (Fin)
Inspection and Check
> Vertical Stabiliser
55-30-02 Dorsal Fin
Description and Operation
Maintenance Practices
> Dorsal Fin Removal.
> Dorsal Fin Installation.

55-40-00 Rudder
Description and Operation
> Servicing
Maintenance Practices
> Removal and Installation
> Adjustment and Test

MAINTENANCE MANUAL SUPPLEMENT 55-00-00 - 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
55-10-00 Stabilator
Description and Operation 

Stabilator (Elevator) Description
Stabilator Description and term change

Maintenance Practices 

Removal and Installation 
Stabilator Removal 
Stabilator Installation
Counter Balance Tube 
Anti-Servo Tab

Adjustment and Test
Stabilator balancing

55-30-00 Vertical Stabilisers 
55-30-01 Fin 
Description and Operation

Vertical stabiliser (Fin) 
Vertical Stabiliser Options
Maintenance Practices 
Removal and Installation 
Vertical Stabiliser
Vertical Stabiliser Tip 
Inspection and Check
Visual Inspection - Forward Attachment 
Visual Inspection - Stabiliser to Fuselage Sealing 
55-30-02 Dorsal Fin
Description and Operation
Dorsal Fin
Maintenance Practices
Removal and Installation

Dorsal Fin Removal
Dorsal Fin Installation

MAINTENANCE MANUAL SUPPLEMENT 55-00-00 - DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue
Chapter Guide
MANUAL TO USE
Applicable Section Guide
SECTION / SUB-SECTION N/A FU24- 954 C550GT

55-40-00 Rudder 
Description and Operation

Rudder
Maintenance Practices 
Servicing 

Lubrication
Removal and Installation

Rudder

Adjustment and Check
Rudder Static out of Balance Check

MAINTENANCE MANUAL SUPPLEMENT 55-10-00-Description/Differences
C550GT-AD016-FU24-0213
Description/Differences Revision: Initial Issue DATE: 01/01/2020

Description/Differences Description and Operation / Stabilator
Stabilator
55-10-00 Stabilator
Terminology
Description and Operation

The FU24-954 Manufacturers Maintenance Manual describes the pitch control surface as an Elevator or 'flying
tail'.
The Crusader Aircraft Company considers it is more correct to define this C550GT control surface as a Stabilator.

A stabilator is a surface which combines the function of the horizontal stabiliser and elevator in one by allowing
the entire horizontal stabiliser to move and control the pitch of the aircraft.
Stabilators are designed to pivot about their aerodynamic center and therefore very little pilot effort is required
to make a control input. This amount of effort does not vary with airspeed or angle of attack. To prevent over-
controlling, the stabilator is fitted with an anti-servo tab on its trailing edge. Control input causes the anti-servo
tab to deflect in the same direction as, but further than the stabilator. This additional deflection induces an
aerodynamic force which resists the pilot input.

In the Fletcher FU24-954 design, applicable to the C550GT, the anti-servo tab also acts as an electrically
operated trim tab.

In this supplement to the FU24 Maintenance Manual, when descriptive information and maintenance procedures
specific to the C550GT aircraft are required, the term 'Stabilator' will be used.

NOTE: Applicable information and procedures in the FU24-954 Manual Chapter 27 are referenced.

Stabilator

Description and Operation
Refer to the FU24-954 Maintenance Manual, Chp. 27 page 31, 32

Stabilator Trim Tab (Anti-servo Tab)

Refer to the FU24-954 Maintenance Manual, Chp. 27 page 34 (i)

Page 1

MAINTENANCE MANUAL SUPPLEMENT 55-10-00- Stabilator and components
C550GT-AD016-FU24-0213
Stabilator and components Revision: Initial Issue DATE: 01/01/2020

Stabilator and components Maintenance Practices / Removal and Installation
Removal and Installation

Maintenance Practices
Removal and Installation

1. Stabilator Removal
Refer to the FU24-954 Maintenance Manual, Chp. 27 page 39 (v)

2. Stabilator Installation
Refer to the FU24-954 Maintenance Manual, Chp. 27 page 39 (vi) and Figure 27.21

3. Counter Balance Tube
Refer to the FU24-954 Maintenance Manual, Chp. 27 page 40 (vii)

4. Stabilator Trim Tab (Anti-Servo Tab)

Refer to the FU24-954 Maintenance Manual, Chp. 27 Sec. 2 (xviii) page 43, 44, Fig. 27.34.

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.

Page 401

MAINTENANCE MANUAL SUPPLEMENT 55-10-00- Stabilator Balance
C550GT-AD016-FU24-0213
Stabilator Balance Revision: Initial Issue DATE: 01/01/2020

Stabilator Balance Maintenance Practices / Adjustment and Test
Adjustment and Test

Adjustment and Test

1. Stabilator (In-Situ) Balancing with Counter Balance Tube
Refer to the FU24-954 Maintenance Manual, Chp. 27 page 46, 3. (iii)

Page 501

MAINTENANCE MANUAL SUPPLEMENT 55-30-01-Description / Differences
C550GT-AD016-FU24-0213
Description / Differences Revision: Initial Issue DATE: 01/01/2020

Description / Differences Description and Operation / Vertical Stabiliser
Vertical Stabiliser

55-30-00 Vertical Stabilisers
55-30-01 Fin

Description and Operation

Vertical Stabiliser (Fin) Differences

Vertical Stabilizer P/N 08-32005-2
CAC prefers the PAC Vertical Stabilizer P/N 08-32005-2 installed in accordance with PACSB/FU/094/ISSUE 4.

NOTE: For Continued Airworthiness, reference Service Bulletin PACSB/FU/094/ISSUE 4 and Chapter 55 of
the FU24A-954 MM.

Vertical Stabilizer P/N SA2-55-03-1
Super Air Ltd Vertical Stabilizer P/N SA2-55-03-1 installed in accordance with Super Air Ltd Installation
Instructions in STC 8/21E/11.

NOTE: For Continued Airworthiness reference the Super Air Ltd. STC, associated Instructions for Continued
Airworthiness and Chapter 55 of the FU24A-954 MM.

Title Page

Page 1

MAINTENANCE MANUAL SUPPLEMENT 55-30-01 - Components Changed Table
C550GT-AD016-FU24-0213
Components Changed Table Revision: Initial Issue DATE: 01/01/2020

Components Changed Table CCBTS / Vertical Stabiliser
Vertical Stabiliser

Components Changed By This STC

Drawing Number Item Part Number Description / Location

Vertical Stabiliser Options

PACSB/FU/094/ISSUE 4 - 08-32005-2 Vertical Stabiliser, option 1

Super Air Ltd. STC 8/21E/11 - SA2-55-03-1 Vertical Stabiliser, option 2

Page 2

MAINTENANCE MANUAL SUPPLEMENT 55-30-01- Vertical Stabiliser
C550GT-AD016-FU24-0213
Vertical Stabiliser Revision: Initial Issue DATE: 01/01/2020

Removal and Installation Maintenance Practices / Removal and Installation
Vertical Stabiliser

Maintenance Practices
Removal and Installation

1. Vertical Stabiliser (Fin)
Refer to the ICA for the Vertical Stabiliser installed on the aircraft.

(1) Vertical Stabilizer P/N 08-32005-2 installed in accordance with PACSB/FU/094/ISSUE 4.

NOTE: For Continued Airworthiness reference Service Bulletin PACSB/FU/094/ISSUE 4 and Chapter 55 of the
FU24A-954 MM.

(2) Vertical Stabilizer P/N SA2-55-03-1 installed in accordance with Super Air Ltd Installation Instructions in

STC-8/21E/11.

NOTE: For Continued Airworthiness reference the Super Air Ltd. STC, associated Instructions for Continued
Airworthiness and Chapter 55 of the FU24A-954 MM.

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.

Page 401

MAINTENANCE MANUAL SUPPLEMENT 55-30-01- Vertical Stabiliser
C550GT-AD016-FU24-0213
Vertical Stabiliser Revision: Initial Issue DATE: 01/01/2020

Inspection and Check Maintenance Practices / Inspection and Check
Vertical Stabiliser

Inspection and Check

1. Vertical Stabiliser
For Inspection procedures, refer to the FU24-954 Maintenance Manual, Chp. 55, 1. Servicing (i), (ii), page 4.

(1) Vertical Stabilizer P/N 08-32005-2 installed in accordance with PACSB/FU/094/ISSUE 4.

NOTE: For Continued Airworthiness reference Service Bulletin PACSB/FU/094/ISSUE 4 and Chapter 55 of the
FU24A-954 MM.

(2) Vertical Stabilizer P/N SA2-55-03-1 installed in accordance with Super Air Ltd Installation Instructions in

STC-8/21E/11.

NOTE: For Continued Airworthiness reference the Super Air Ltd. STC, associated Instructions for Continued
Airworthiness and Chapter 55 of the FU24A-954 MM.

Title Page

Page 601

MAINTENANCE MANUAL SUPPLEMENT 55-30-02-Description
C550GT-AD016-FU24-0213
Description Revision: Initial Issue DATE: 01/01/2020

Description Description and Operation / Dorsal Fin
Dorsal Fin
55-30-02 Dorsal Fin
Description and Operation
Description and Operation

The C550GT STC adds a Dorsal Fin forward of the vertical stabiliser. This dorsal fin improves the directional
stability of the aircraft and strengthens the forward attachment of the Fin. A single pre-formed wrap around skin
and two internal reinforcement frames give the dorsal strength and rigidity. The dorsal fin screws to the leading
edge of the vertical stabiliser and the flange on its bottom edge attaches to the fuselage with rivets.

There is an access panel for inspection of the Fin forward attach-bracket and removal of the attach bolt. It is
important to correctly seal the access panel and all gaps between edges of the dorsal fin and the vertical
stabiliser.

Figure 55.5 Dorsal Fin.

Page 1

MAINTENANCE MANUAL SUPPLEMENT 55-30-02 - Components Changed Table
C550GT-AD016-FU24-0213
Components Changed Table Revision: Initial Issue DATE: 01/01/2020

Components Changed Table CCBTS / Stabilisers
Stabilisers

Components Changed By This STC

Drawing Number Item Part Number Description / Location
Dorsal Fin
AD-550GT-5530-001-000 1 AD-550GT-5530-001-100 Dorsal Fin Assembly

Page 2

MAINTENANCE MANUAL SUPPLEMENT 55-30-02- Removal and Installation
C550GT-AD016-FU24-0213
Removal and Installation Revision: Initial Issue DATE: 01/01/2020

Removal and Installation Maintenance Practices / Removal and Installation
Dorsal Fin
Maintenance Practices
Removal and Installation

1. Dorsal Fin Removal.
Ref. Dwg. No: AD-550GT-5530-001-000

(1) Remove the screws that attach to the vertical stabilizer.
(2) Remove the rivets from the flange on its bottom edge.
(3) Carefully lift the dorsal fin off the fuselage.

NOTE: The edges of the dorsal fin have adhesive sealant applied. Carefully break the sealant bond so you do
not damage the flange.

2. Dorsal Fin Installation.
Ref. Dwg. No: AD-550GT-5530-001-000
(1) Apply a small quantity of CA 1010 Mastinox Jointing Compound (or equivalent) to the mating surfaces.
(2) Position the Dorsal Fin on fuselage upper surface.
(3) Install the screws loosely to the vertical stabiliser.
(4) Attach the Dorsal Fin to the fuselage upper surface with skin pins (Cleco Fasteners- or equivalent)
(5) Attach to fuselage upper surface with rivets.
(6) Tighten the 10 screws.
(7) Clean surfaces and apply a sealant compound to all mating joints.

WARNING: MAKE SURE YOU SEAL ALL EDGES OF THE DORSAL FIN. CORROSION CAUSED BY MOISTURE
AND CONTAMINATION CAN DAMAGE THE FORWARD ATTACH BRACKET. FAILURE OF THE
BRACKET CAN CAUSE INJURY OR DEATH.

Figure 55.6 Dorsal Fin attachment.

Page 401

MAINTENANCE MANUAL SUPPLEMENT 55-40-00-Rudder
C550GT-AD016-FU24-0213
Rudder Revision: Initial Issue DATE: 01/01/2020

Rudder Description and Operation / Maint. Practices
Maint. Practices

55-40-00 Rudder

Description and Operation

Description Maintenance Practices
Refer to the FU24-954 Maintenance Manual, Chp. 27 page 19, 20.
Servicing
Refer to the FU24-954 Maintenance Manual, Chp. 27 page 21, 22.

Removal and Installation
Refer to the FU24-954 Maintenance Manual, Chp. 27 Sec. 2. (xi) page 27, 28.

Adjustment and Test

Rudder Static out of Balance Check
Refer to the FU24-954 Maintenance Manual, Chp. 27 Sec. 3. (iii) page 30.

Page 1

MAINTENANCE MANUAL SUPPLEMENT 57-00-00 - Wing DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Wing
Chapter 57

Title Page

Chapter 57
Wing

Chapter 57 Wing

MAINTENANCE MANUAL SUPPLEMENT 57-00-00 - Wing DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Wing
Chapter Contents

Chapter Contents
Wing

Chapter Contents

Chapter 57 Wing

Applicable Section Guide
57-00-00 Wing

Description and Operation
> Wing - Description and Operation

Components Changed By This STC
57-10-00 Centre Wing
> Centre Wing Description and Differences.
57-10-01 Wing Access Panels

Description and Operation
> Extra Access Panels.

57-20-00 Outer Wing Panel
Description and Operation
> Outer Wing Panels and Wing Tips.
Maintenance Practices
Removal and Installation
> Outer Wing Panel Removal
> Outer Wing Panel Installation

MAINTENANCE MANUAL SUPPLEMENT 57-00-00 - 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

57-00-00 Wing 
Description and Operation

General 
Maintenance Practices
Inspection and Check 

Structural Corrosion
Wing Attachments - Visual Inspection 
57-10-00 Centre Wing 
Description and Operation
General 
Centre Wing
Maintenance Practices 
Removal and Installation 
Centre Wing Removal
Centre Wing Installation
57-20-00 Outer Panels
Description and Operation
Outer Panels
Outer Panel changes
Fairings and Gap Strips
Maintenance Practices
Removal and Installation
Outer Panel Removal
Outer Panel Installation

57-30-00 Wing Tips 
Description and Operation

Wing Tips 
Maintenance Practices
Removal and Installation

Wing Tip Removal
wing Tip Installation

MAINTENANCE MANUAL SUPPLEMENT 57-00-00-Wing Description
C550GT-AD016-FU24-0213
Wing Description Revision: Initial Issue DATE: 01/01/2020

Wing Description Description and Operation / Wing
Wing
57-00-00 Wing
Wing - Description and Operation
Description and Operation

General

There are changes introduced that improve the wing reliability, fatigue life and performance. However,
maintenance tasks typically stay the same.

Use the FU24-954 Maintenance Manual pages 2 thru 5 for the description of the primary structure. The structural
changes made by this STC and the affect they have on maintenance, are shown in Section 57-10-00 Centre Wing
and 57-20-00 Outer Wing Panels.

In addition to the information in this Chapter, refer to the drawing list for details of the changes made to the wing
structure by implementation of this STC

Drawing List - Modifications to the Wing Centre Section and Outer Wing Panels

AD-550GT-5700-001-000 Installation Wing Outer Panel Lugs
AD-550GT-5710-006-000 Installation Wing Access Panels
AD-550GT-5710-005-000 Installation Wing Lower Spar Straps
AD-550GT-5710-004-000 Installation Wing Former Spreaders
AD-550GT-5710-003-000 Installation Wing Spanwise Tank Strips
AD-550GT-5710-002-000 Installation Wing Upper Spar Carry Through
AD-550GT-5710-001-000 Installation Wing Spar Outboard Web
AD-550GT-5720-001-000 Installation Shear Strips
AD-550GT-5740-001-000 Installation Wing Leading Edge Inserts
AD-550GT-5740-002-000 Installation Gap Strips

Page 1

MAINTENANCE MANUAL SUPPLEMENT 57-00-00 - Components Changed Table
C550GT-AD016-FU24-0213
Components Changed Table Revision: Initial Issue DATE: 01/01/2020

Components Changed Table CCBTS / Wing
Wing

Components Changed By This STC

Drawing Number Item Part Number Description / Location

57-00-00 Wing

AD-550GT-5700-001-000 1 AD-550GT-5700-001-001-1 Fitting, RH

AD-550GT-5700-001-000 2 AD-550GT-5700-001-001-2 Fitting, LH

AD-550GT-5700-001-000 3 AD-550GT-5700-001-003 Fitting

AD-550GT-5700-001-000 4 AD-550GT-5700-001-004 Fitting

AD-550GT-5700-001-000 5 AD-550GT-5700-001-005-1 Bottom Lug, LH

AD-550GT-5700-001-000 6 AD-550GT-5700-001-005-2 Bottom Lug, RH

AD-550GT-5700-001-000 7 AD-550GT-5700-001-007-1 Top Lug, LH

AD-550GT-5700-001-000 8 AD-550GT-5700-001-007-2 Top Lug, RH

57-10-00 Centre Section

AD-550GT-5710-001-000 1 AD-550GT-5710-001-010 Spar Web, LH

AD-550GT-5710-001-000 2 AD-550GT-5710-001-020 Spar Web, RH

AD-550GT-5710-001-000 3 AD-550GT-5710-001-030 Stiffeners

AD-550GT-5710-002-000 1 AD-550GT-5710-002-001 Forward Angle

AD-550GT-5710-002-000 2 AD-550GT-5710-002-002 Aft Angle

AD-550GT-5710-003-000 1 AD-550GT-5710-003-010-1 Lower Spanwise Strip, RH

AD-550GT-5710-003-000 2 AD-550GT-5710-003-010-2 Lower Spanwise Strip, LH

AD-550GT-5710-003-000 3 AD-550GT-5710-003-030-1 Upper Spanwise Strip, LH

AD-550GT-5710-003-000 4 AD-550GT-5710-003-030-2 Upper Spanwise Strip, RH

AD-550GT-5720-001-000 1 AD-550GT-5720-001-001 Shear Strip, Fuel Tank

57-10-00 Former Spreader Modification

AD-550GT-5710-004-000 1 08-03065-12 Main Spar Bracket

AD-550GT-5710-004-000 2 08-03065-14 Main Spar Bracket

AD-550GT-5710-004-000 3 08-03065-15 Rear Spar Bracket

AD-550GT-5710-004-000 4 08-03065-16 Gusset, Main Spar

AD-550GT-5710-004-000 5 08-03065-17 Gusset, Main Spar

AD-550GT-5710-004-000 6 08-03065-18 Stiffener

AD-550GT-5710-004-000 7 08-03066-12 Main Spar Bracket

AD-550GT-5710-004-000 8 08-03066-14 Main Spar Bracket

AD-550GT-5710-004-000 9 08-20257-1 Bracket

AD-550GT-5710-004-000 10 241177 Fairlead

Leading Edge Inserts

AD-550GT-5740-001-000 1 AD-550GT-5740-001-200 RH Leading Edge Insert

AD-550GT-5740-001-000 2 AD-550GT-5740-001-300 LH Leading Edge Insert

Page 1

MAINTENANCE MANUAL SUPPLEMENT 57-00-00-Components Changed Table
C550GT-AD016-FU24-0213
Components Changed Table Revision: Initial Issue DATE: 01/01/2020

Wing

Components Changed By This STC

Drawing Number Item Part Number Description / Location

Wing Lower Spar Straps

AD-550GT-5710-005-000 1 AD-550GT-5710-005-001 Doubler

AD-550GT-5710-005-000 2 AD-550GT-5710-005-002 Doubler

AD-550GT-5710-005-000 3 AD-550GT-5710-005-003 Doubler

AD-550GT-5710-005-000 4 AD-550GT-5710-005-004 Doubler

AD-550GT-5710-005-000 5 AD-550GT-5710-005-005 Doubler

AD-550GT-5710-005-000 6 AD-550GT-5710-005-006 Doubler

AD-550GT-5710-005-000 7 AD-550GT-5710-005-007 Doubler

Wing Access Panels

AD-550GT-5710-006-000 1 AD-550GT-5710-006-010 Cover Plate

AD-550GT-5710-006-000 2 AD-550GT-5710-006-011 Doubler

Gap Strips

AD-550GT-5740-002-000 1 AD-550GT-5740-002-300 LH Gap Strip Assembly

AD-550GT-5740-002-000 2 AD-550GT-5740-002-400 RH Gap Strip Assembly

Page 2

MAINTENANCE MANUAL SUPPLEMENT 57-10-00-Centre Wing Section Differences
C550GT-AD016-FU24-0213
Centre Wing Section Differences Revision: Initial Issue DATE: 01/01/2020

Description and Operation / Centre Wing

Centre Wing Section Differences
Centre Wing

57-10-00 Centre Wing

Description and Operation

Centre Wing Description and Differences.

Implementation of this STC introduces changes to the wing centre section that improve the fatigue life of the
wing spar and allow for an increased MTOW. These structural improvements raise the level of resistance to
fatigue cracks and wear, giving the centre section better reliability.

Spar Cap Doublers.

There is an increase in the thickness and number of the 4130 steel spar-cap doublers. Two more lower spar-cap
doublers are installed. The wing spar assembly now has seven 0.050 in. steel lower-spar straps.

Carry Through Angles.

The wing spar upper cap has two additional aluminum angle reinforcements. These two Carry Through Angles,
each bolted forward and aft of the upper cap, support the centre of the spar where the spar web joins at the
aircraft’s centreline.

Flat Wing Spar Outer Web.

The fluted outer web of the FU24-950 series wing main spar was susceptible to fatigue cracking and working
rivets. The C550GT has a flat 0.040 in. main spar outer-web that prevents the problems with the fluted
design.The front face of the main spar web is further reinforced by the fuel tank shear strips that support the
Leading Edge (LE) Fuel Tanks.

Figure 57.1 Wing main spar web
Former spreaders.
The wing centre section also benefits from selected parts of PAC Former Spreader Modification PAC/FU/0299. The
wing skin formers and leading-edge formers were susceptible to fatigue cracking caused by wing flex under
normal operating loads.
The modification uses brackets riveted at each end of four of the top and bottom wing skin formers in the outer
bay of the wing centre section. The brackets flanged edges are attached to the rear wing spar and the main spar
web. This design ties the formers to the spars and distributes the load to these more robust structures,
contributing to better overall stiffness of the centre section. The problems with cracking in the leading-edge
formers are eliminated in the C550GT through the redesign of the leading-edge fuel tanks and the integral
inserts.
Wing LE Inserts.
Wing LE Inserts, installed outboard of the Fuel Tanks, complete the leading-edge profile. See Figure 57.2
Gap strips cover the leading-edge areas from tank to insert and between each fuel tank. See Figure 57.4

Page 1

MAINTENANCE MANUAL SUPPLEMENT 57-10-00-Centre Wing Section Differences
C550GT-AD016-FU24-0213
Centre Wing Section Differences Revision: Initial Issue DATE: 01/01/2020

Description and Operation / Centre Wing

Figure 57.2 Leading Edge Insert

Spanwise tank strips
These 0.063 in. Alclad strips act as doublers to the top and bottom spar caps and hold the LE Fuel Tanks in
position on the shear strips.

Access Panels.
On the lower wing skins, four removable panels give access to the aileron control cables for installation and
inspection. (Link to 57-10-01 Access Panels)

Aileron-Direct Pulleys.
Smaller diameter aileron-direct pulleys are installed in the centre wing spar web. Refer to Chapter 27 for more
information. See Chp. 27 Aileron Control System.

Wing Outer Panel Lugs.
The top and bottom Outer Wing Panel attach lugs are redesigned using 4130 steel and reinforce the main spar
attachment points. The lugs attach to the main spar with Hi-Lok® shear pins. Larger diameter Outer Wing Panel
attach bolts have a higher torque and increase the wear resistance of the bearing area. See Figure 57.3
The Outer Wing Panel rear spar fitting is standard FU24 but a larger NAS1306 bolt replaces the stepped shear
bolt.

Figure 57.3 Wing Outer Panel attach.

Page 2

MAINTENANCE MANUAL SUPPLEMENT 57-10-00-Centre Wing Section Differences
C550GT-AD016-FU24-0213
Centre Wing Section Differences Revision: Initial Issue DATE: 01/01/2020

Description and Operation / Centre Wing

Figure 57.4 Leading Edge Gap Strip

Page 3

MAINTENANCE MANUAL SUPPLEMENT 57-10-01-Centre Section - Access Panels
C550GT-AD016-FU24-0213
Centre Section - Access Panels Revision: Initial Issue DATE: 01/01/2020

Centre Section - Access Panels Description and Operation / Wing Access Panels
Wing Access Panels
57-10-01 Wing Access Panels
Description and Operation.
Description and Operation

1. Extra Access Panels.

The FU24-954 had two access panels in the RH Inboard bottom wing skin. The C550GT STC 14/21E/5 introduces
two added access panels into the LH Inboard bottom wing skin. These panels improve access to the aileron
cables and the internal wing bay.

NOTE: All four panels are shown as W.6 in the Access Panel Diagram. See Chp. 12 Access Panel Diagram.

NOTE: THIS CONTENT IS NOT APPROVED - submitted 29/08/2020

Figure 57.5 Centre Wing Access Panels.
Page 1

MAINTENANCE MANUAL SUPPLEMENT 57-20-00-Outer Wing Panel- Differences
C550GT-AD016-FU24-0213
Outer Wing Panel- Differences Revision: Initial Issue DATE: 01/01/2020

Description and Operation / Outer Wing Panel

Outer Wing Panel- Differences
Outer Wing Panel

57-20-00 Outer Wing Panel

Description and Operation

Outer Wing Panels and Wing Tips.

Except for the attachment lugs, the Outer Wing Panels are unchanged. The redesigned fittings are fabricated in
4310 steel and attached to the spar with Hi-Lok® shear pins. The attach bolts require a higher torque, refer to
the Removal and Installation procedures in this chapter. Link to this section
The FU24-954 has vortex generators and modified wing and aileron tips. This existing modification reduces stick
forces and improves the rate of roll.
For information on Wing Tip, Aileron Tip and Vortex Generator Installation, Part Numbers, and Aileron Static
balance.
Ref. Ext. Doc: ASB/FU/052 Revised Wing and Aileron Fairings and Vortex Generators.

Page 1

MAINTENANCE MANUAL SUPPLEMENT 57-20-02- Outer Wing Panel
C550GT-AD016-FU24-0213
Outer Wing Panel Revision: Initial Issue DATE: 01/01/2020

Outer Wing Panel Maintenance Practices / Removal and Installation
Removal and Installation

Maintenance Practices
Removal and Installation

1. Outer Wing Panel Removal
Ref. Dwg. No: AD-550GT-5700-001-000

(1) Make sure all electrical power is OFF.
(2) Remove the centre wing to outer panel gap strips.

NOTE: Refer to the FU24-954 Maintenance Manual, Chapter 57, Maintenance Practices, Removal and
Installation, Sec. 2, para. (iii) Gap Strips Removal.

(3) Disconnect the aileron push/pull rod from the aileron.
NOTE: Refer to the FU24-954 Maintenance Manual, Chapter 27, Maintenance Practices, Removal and
Installation, Sec. 2, para. (xv) Aileron Removal.
NOTE: Support the aileron push/pull rod. Tie it to the centre wing.

(4) Disconnect the electrical connector.
NOTE: Connector No. 3310P21(RH) or No. 3310P11(LH)

(5) At the rear spar fitting, remove nut (22) and washer (9) See Figure 57.6
(6) At the front spar fittings, remove two nuts (23) and washers (10).
(7) Support the outer panel.

NOTE: You need 2-3 personnel for this task.
CAUTION: IN THE NEXT STEP YOU MUST SUPPORT THE LUGS TO PREVENT THEM SPRINGING.

(8) Carefully drift out rear bolt (24) and front bolts (25).
(9) Remove the outer panel and put it on a suitable support stand.

Figure 57.6 Rear Spar Attachment Fittings.

Page 401

MAINTENANCE MANUAL SUPPLEMENT 57-20-02-Outer Wing Panel
C550GT-AD016-FU24-0213
Outer Wing Panel Revision: Initial Issue DATE: 01/01/2020

Maintenance Practices / Removal and Installation

2. Outer Wing Panel Installation
Ref. Dwg. No: AD-550GT-5700-001-000

(1) Do a visual inspection of the Outer Panel attachment lugs.
NOTE: Refer to the FU24-954 Maintenance Manual, Chapter 57, Maintenance Practices, 1. Servicing, para.
(ii) (A) Visual Examination.

(2) Apply CA 1010 Mastinox Jointing Compound (or equivalent) to the mating surfaces of the attachment lugs
and the bolts (24, 25)

(3) Support the Outer Panel in position and carefully engage the lugs at the main spar.
NOTE: You need 2-3 personnel for this task.

(4) Use bullets to align the bolt holes, then put the bolts (25) in the main spar and bolt (24) in the rear spar
positions. See Figure 57.7

(5) Install the washers (10) and nuts (23) on the main spar bolts (25). Torque nuts to 300 - 400 in.lb
(6) Install the washers (9) and nuts (22) on the rear spar bolt (24). Torque nut to 120 - 150 in.lb.
(7) Reconnect the electrical connector No. 3310P21(RH) or No. 3310P11(LH).

NOTE: Make sure the wiring cannot chafe.
(8) Do a functional test of the Wing Tip Strobe, Navigation lights and Landing Lights.
(9) Connect the aileron push/pull rod to the aileron.

NOTE: Refer to the FU24-954 Maintenance Manual, Chapter 27, Maintenance Practices, Removal and
Installation, Sec. 2, para. (xv) Aileron Removal.

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

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

(10) Install the centre wing to outer panel gap strips.
NOTE: Refer to the FU24-954 Maintenance Manual, Chapter 57, Maintenance Practices, Removal and
Installation, Sec. 2, para. (iv) Gap Strips Installation.

Figure 57.7 Main Spar Attachment Fittings.

Page 402

MAINTENANCE MANUAL SUPPLEMENT 61-00-00 - Propeller DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Propeller
Chapter 61

Title Page

Chapter 61
Propeller

Chapter 61 Propeller

MAINTENANCE MANUAL SUPPLEMENT 61-00-00 - Chapter Content DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Propeller
Chapter Content

Chapter Content
Propeller

Chapter Contents

Chapter 61 Propeller

Chapter Contents
Applicable Section Guide
Components Changed By This STC

61-00-00 Propeller
Introduction
> Purpose
> Airworthiness Limitations
> Airframe or Engine Modifications
> Restrictions and Placards
> General
> Continued Airworthiness
> Propeller Critical Parts
> Reference Publications
> References to Hartzell Propeller Inc. Publications
> Definitions
> Abbreviations
> Hartzell Propeller Inc. Product Support
> Warranty Service
> Hartzell Propeller Inc. Recommended Facilities

61-10-00 Propeller
Description and Operation
> Feathering and Reversing Propeller- HC-B3TN-3D
> Model Designation.
> Aluminum Blade Model Identification.
Troubleshooting
> Hunting and Surging.
> Engine Speed Varies with Airspeed.
> Loss of Propeller Control
> Failure to Feather (or feathers slowly).
> Failure to Unfeather.
> Vibration
> Propeller Overspeed.
> Propeller Underspeed
> Oil or Grease Leakage.
Maintenance Practices
Servicing
> Servicing.
> Lubrication Intervals.
> Lubrication Procedure.
> Approved Lubricants.
> Tooling, Consumables and Expendables.
Removal and Installation
> Propeller Model No. HC-B3TN-3D – Removal.
> Pre-Installation.
> Propeller Model No. HC-B3TN-3D – Installation.
> Spinner Dome Removal.
> Spinner Dome Installation.
Adjustment and Test
> Operational Tests.
> Dynamic Balance.
> Tachometer Calibration
Inspection and Check
> Pre-Flight Checks .
> Post-Flight Checks.

Page 1

MAINTENANCE MANUAL SUPPLEMENT 61-10-01-Chapter Content DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Propeller
Chapter Content

> Operational Checks.
> Required Periodic Inspections and Maintenance.
> Periodic Inspections.
> Periodic Maintenance.
> Compliance Inspections.
> Airworthiness Limitations.
> Overhaul Periods.
Inspection and Check
> Inspection Procedures.
> Blade Damage.
> Grease or Oil Leakage.
> Vibration.
> Blade Track.
> Loose Blades.
> Corrosion.
> Spinner Damage.
> Special Inspections.
> Overspeed/Overtorque.
> Lightning Strike .
> Foreign Object Strike.
> Fire Damage or Heat Damage.
> Long Term Storage.
Cleaning and Painting
> Cleaning.
> General Cleaning.
> Spinner Cleaning and Polishing.
> Painting After Repair.
> General.
> Painting of Aluminum Blades.
Approved Repairs
> Blade Repairs.
> Repair of Nicks and Gouges.
> Repair of Bent Blades.
61-20-00 Propeller Control
Description and Operation
> Cockpit Control Quadrant Levers.
> Propeller Governing System Overview.
> Servo-piston Oil Supply.
> Constant Speed Section.
> Feathering.
> Power Turbine Governing Section (Fuel Topping Governor)
> Beta Control Valve.
> Propeller Over-Speed Governor.
Maintenance Practices
Removal and Installation
> Propeller Control Cables Removal.
> Propeller Control Cables Installation.
> Propeller Governor Removal.
> Propeller Governor Installation.
> Propeller Overspeed Governor Removal.
> Propeller Overspeed Governor Installation.
Adjustment and Test
> Primary Blade Angle Check.
> Pre-checks and Nominal Settings.
> C550GT Primary Blade Angle (PBA) Dynamic Check.
> Operational Proving Flight.
> Beta Valve Position Check.
> Beta Nut Nominal Position Check.
> PBA Target Torque Adjustment.

Page 2

MAINTENANCE MANUAL SUPPLEMENT 61-00-00 - Chapter Content DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue
Chapter Content Propeller

> Propeller Governor Checks and Adjustments.
> Power Turbine Governing Section (Fuel Topping Governor)
Inspection and Check
> Hydraulic Overspeed Governor Operational Ground Check.
Inspection and Check
> Carbon Block Assemblies.
> Inspection
> Replacement
> Installation of the A-3044 Carbon Block Assembly.
61-40-00 Beta Indicating System
Description and Operation
> Beta Range Indication.
Maintenance Practices
Removal and Installation
> Beta Switch Removal.
> Beta Switch Installation.
Adjustment and Test
> Beta Switch Position.
> Beta Switch Adjustment.

Page 3

MAINTENANCE MANUAL SUPPLEMENT 61-00-00 - 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
61-00-00 Propeller General
Introduction 

61-10-00 Propeller Assembly 
Description and Operation 

Feathering and Reversing Propeller- HC-B3TN-3D 
Model Designation 
Troubleshooting 
Hunting and Surging 
Engine Speed Varies with Airspeed 
Loss of Propeller Control 
Failure to Feather or Unfeather 
Vibration 
Propeller Over-Speed
Propeller Under-Speed 
Oil or Grease Leakage 
Maintenance Practices
Lubrication 
Approved Lubricants 

Removal and Installation 
Tooling, Consumables and Expendables. 
Propeller Removal 
Pre-Installation
Propeller Installation 
Spinner Dome Removal 
Spinner Dome Installation 

Adjustment and Test 
Operational Tests 
Dynamic Balance 
Tachometer Calibration 

Inspection and Check 
Pre-Flight Checks 
Post-Flight Checks
Operational Checks
Required Periodic Inspections and Maintenance
Inspection Procedures
Special Inspections
Long Term Storage

MAINTENANCE MANUAL SUPPLEMENT 61-00-00 - 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
61-10-00 Propeller Assembly cont’d

Cleaning and Painting 

General Cleaning
Painting After Repair 
Painting of Aluminum Blades

Approved Repairs 
Blade Repairs 

61-20-00 Propeller Control 
Description and Operation 

Introduction 
Cockpit Control Quadrant Levers 
Propeller Governing System 
Power Turbine Governing Section (Fuel Topping Governor)
Beta Control Valve 
Over Speed Governor 
Maintenance Practices 
Removal and Installation 
Propeller Control Cables 
Propeller Governor 
Propeller Over Speed Governor
Adjustment and Test 
Primary Blade Angle Check 
Operational Proving Flight
Beta Valve Position 
Beta Nuts Nominal Position
Propeller Governor 
Power Turbine Governing Section (Fuel Topping Governor)
Inspection and Check 
Hydraulic Overspeed Governor Operational Ground Check. 
Carbon Block Assembly
61-40-00 Beta Indicating System
Description and Operation
Beta Indicating
Removal and Installation
Beta Switch
Adjustment and Test
Beta Switch Position
Beta Switch Adjustment

MAINTENANCE MANUAL SUPPLEMENT 61-00-00 - Components Changed Table
C550GT-AD016-FU24-0213
Components Changed Table Revision: Initial Issue DATE: 01/01/2020

Components Changed Table Propeller
Propeller

Components Changed By This STC

Drawing Number Item Part Number Description / Location
61-00-00 Propeller
AD-550GT-6100-001-000 8 HC-B3TN-3D-T10282 Propeller
AD-550GT-6100-001-000 6 C3065-1P Spinner
AD-550GT-6100-001-000 5 C-3064-1P Spinner Backplate
AD-550GT-7600-001-000 1 08-47153-1 Bracket, Propeller Control
AD-550GT-7600-001-000 5 580-727-007 Cable (Cablecraft)
AD-550GT-7600-001-000 6 031804 Clamp
AD-550GT-7600-001-000 44 MS9600-048 Bracket
AD-550GT-7600-001-000 46 08-47157-1 Lever, spring
AD-550GT-7600-001-000 47 08-47161-1 Tension Spring
AD-550GT-7600-001-000 48 08-47159-1 Link
AD-550GT-7600-001-000 52 242996-3 Eye (alt.no. 08-47189-2)
AD-550GT-7600-001-000 51 SW1-12-3 Swivel Kit
AD-550GT-7600-001-000 55 08-47201-11 Cable Guide Tube

Page 1

MAINTENANCE MANUAL SUPPLEMENT 61-00-00 - Introduction DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Propeller
Introduction
61-00-00 Propeller
Introduction
Propeller Introduction

1. Purpose

a. This manual has been reviewed and accepted by the CAA. Additionally, the Airworthiness Limitations
Section of this manual has been approved by the CAA.

CAUTION: THE PROPELLER LOGBOOK RECORD MUST BE MAINTAINED, RETAINED CONCURRENTLY, AND
BECOME A PART OF THE AIRCRAFT AND ENGINE SERVICE RECORDS.

b. This manual supports the reversing steel hub turbine propeller with aluminum blades installed on the
Crusader 550GT.

c. The purpose of this Crusader 550GT Maintenance Manual Supplement is to enable qualified personnel to
install, operate, and maintain a Hartzell Propeller Inc. Constant Speed Feathering and Reversing Steel Hub
Propeller. Separate manuals are available concerning overhaul procedures and specifications for the
propeller.

NOTE: This manual only includes the HC-B3TN-3D design type. Samples of different hub and blade model
numbers within this design are included in the Description and Operation Chapter of this manual.

2. Airworthiness Limitations

Refer to the Airworthiness Limitations chapter of the Crusader 550GT Instructions for Continued Airworthiness
(ICA) for Airworthiness Limitations information.

3. Airframe or Engine Modifications

a. Propellers are approved vibrationwise on airframe and engine combinations based on tests or analysis of
similar installations. This data has demonstrated that propeller stress levels are affected by airframe
configuration, airspeed, weight, power, engine configuration, and approved flight maneuvers. Aircraft
modifications which can effect propeller stress include, but are not limited to: aerodynamic changes ahead
of or behind the propeller, realignment of the thrust axis, increasing or decreasing airspeed limits,
increasing or decreasing weight limits (less significant on piston engines), and the addition of approved
flight maneuvers (utility and aerobatic).

b. Engine modifications can affect the propeller. The two primary categories of engine modifications are those
that affect structure and those which affect power. An example of a structural engine modification is the
alteration of the crankshaft or damper of a piston engine. Any change to the weight, stiffness, or tuning of
rotating components could result in a potentially dangerous resonant condition that is not detectable by the
pilot. Most common engine modifications affect the power during some phase of operation. Some increase
the maximum power output, while others improve the power available during hot and high operation (flat
rating) or at off-peak conditions. Examples of such engine modifications include, but are not limited to:
changes to the compressor, power turbine or hot section of a turboprop engine; and on piston engines, the
addition or alteration of a turbocharger or turbonormalizer, increased compression ratio, increased RPM,
altered ignition timing, electronic ignition, full authority digital electronic controls (FADEC), or tuned
induction or exhaust.

NOTE: All such modifications must be reviewed and approved by the propeller manufacturer prior to
obtaining approval on the aircraft.

4. Restrictions and Placards

The propeller covered by this manual may have a restricted operating range that requires a cockpit placard.
Review the propeller and aircraft type certificate data sheet (TCDS), Pilot Operating Handbook (POH), and any
applicable Airworthiness Directives for specific information.

Page 1

MAINTENANCE MANUAL SUPPLEMENT 61-00-00-Introduction DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Propeller
Introduction

5. General

Personnel Requirements
a. Inspection, Repair, and Overhaul

Compliance to the applicable regulatory requirements established by the Federal Aviation Administration (FAA) or
foreign equivalent is mandatory for anyone performing or accepting responsibility for any inspection and/or
repair and/or overhaul of any Hartzell Propeller Inc. product. (b) Personnel performing maintenance on steel hub
propellers are expected to have sufficient training and certifications (when required by the applicable Aviation
Authority) to accomplish the work required in a safe and airworthy manner.

b. Maintenance Practices
• The propeller and its components are highly vulnerable to damage while they are removed from the engine.

Properly protect all components until they are reinstalled on the engine.
• Never attempt to move the aircraft by pulling on the propeller.
• Avoid the use of blade paddles. Put the blade paddle in the thickest area of the blade. Use one blade paddle

per blade.
• Use only the approved consumables, e.g., cleaning agents, lubricants, etc.

c. Safe Handling of Paints and Chemicals
• Always use caution when handling or being exposed to paints and/or chemicals during propeller overhaul and

maintenance procedures.
• Before using paint or chemicals, always read the manufacturers label on the container and follow specified

instructions and procedures for storage, preparation, mixing, and application.
• Refer to the products Material Safety Data Sheet (MSDS) for detailed information about physical properties,

health, and physical hazards of any chemical.
d. Observe applicable torque values during maintenance.
e. Before installing the propeller on the engine, the propeller must be statically balanced. New propellers are

statically balanced at Hartzell Propeller Inc. Overhauled propellers must be statically balanced by a certified
propeller repair station with the appropriate rating before return to service.
NOTE: Dynamic balance is recommended. Dynamic balancing is to be accomplished in accordance with the

procedures and limitations in this manual (CMMS).

f. As necessary, use a soft, non-graphite pencil or crayon to make identifying marks on components.
g. As applicable, follow military standard NASMS33540 for safety wire, safety cable, and cotter pin general

practices. Use 0.032 inch (0.81 mm) diameter stainless steel safety wire unless otherwise indicated.

WARNING: DO NOT USE OBSOLETE OR OUTDATED INFORMATION. PERFORM ALL INSPECTIONS OR WORK
IN ACCORDANCE WITH THE MOST RECENT REVISION OF THIS MANUAL. INFORMATION
CONTAINED IN THIS MANUAL MAY BE SIGNIFICANTLY CHANGED FROM EARLIER REVISIONS.
FAILURE TO COMPLY WITH THIS MANUAL OR THE USE OF OBSOLETE INFORMATION MAY
CREATE AN UNSAFE CONDITION THAT MAY RESULT IN DEATH, SERIOUS BODILY INJURY, AND/
OR SUBSTANTIAL PROPERTY DAMAGE. FOR THE MOST RECENT REVISION LEVEL OF THIS
MANUAL, REFER TO THE PRELIMINARY SECTION OF THIS CMMS IN THE CRUSADER 550GT ICA.

h. The information in this manual revision supersedes data in all previous published revisions of this manual.
Other manuals are used in addition to the information in this manual, see the Preliminary section of this
CMMS for a list of applicable publications.

i. The propeller is not equipped with an ice protection system.
j. Propeller components not supplied by Hartzell Propeller Inc. are controlled by the applicable TC or STC

holder Instructions for Continued Airworthiness (ICA).
k. Approved corrosion protection followed by approved paint must be applied to all aluminum blades. For

information about the application of corrosion protection and paint, refer to the Maintenance Practices
chapter of this manual. Operation of blades without the specified coatings and finishes, i.e. polished blades
is not permitted.

6. Continued Airworthiness
Operators are urged to stay informed of Airworthiness information using Hartzell Propeller Inc. Service Bulletins
and Service Letters that are available from Hartzell Propeller Inc. distributors, or from the Hartzell Propeller Inc.
factory by subscription. Selected information is also available on the Hartzell Propeller Inc. website at
www.hartzellprop.com.

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MAINTENANCE MANUAL SUPPLEMENT 61-00-00-Introduction DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Propeller
Introduction

7. Propeller Critical Parts

a. The following maintenance procedures may involve propeller critical parts. These procedures have been
substantiated based on Engineering analysis that expects this product will be operated and maintained
using the procedures and inspections provided in the Instructions for Continued Airworthiness (ICA) for this
product. Refer to the Illustrated Parts List chapter of the applicable maintenance manual for the applicable
propeller model for the identification of specific Critical Parts.

b. Numerous propeller system parts can produce a propeller Major or Hazardous effect, even though those
parts may not be considered as Critical Parts. The operating and maintenance procedures and inspections
provided in the ICA for this product are, therefore, expected to be accomplished for all propeller system
parts.

8. Reference Publications

• Hartzell Propeller Inc. Publications Active Hartzell Propeller Inc. Service Bulletins, Service Letters, Service
Instructions, and Service Advisories.

• Hartzell Propeller Inc. Manual No. 118F (61-10-18) - Three and Four-Blade Steel Hub Turbine Propeller Main-
tenance Manual

• Hartzell Propeller Inc. Manual No. 127 (61-16-27) - Metal Spinner Assembly Maintenance Manual - Available
on the Hartzell Propeller Inc. website at www.hartzellprop.com

• Hartzell Propeller Inc. Manual No. 132A (61-10-32) - Five-Blade Steel Hub Turbine Propellers Hartzell Propel-
ler Inc. Manual No. 133C (61-13-33) - Aluminum Propeller Blade Maintenance Manual

• Hartzell Propeller Inc. Manual No. 159 (61-02-59) - Application Guide - Available on the Hartzell Propeller
Inc. website at www.hartzellprop.com

• Hartzell Propeller Inc. Manual 165A (61-00-65) - Illustrated Tool and Equipment Manual - Available on the
Hartzell Propeller Inc. website at www.hartzellprop.com

• Hartzell Propeller Inc. Manual No. 180 (30-61-80) - Propeller Ice Protection System Manual - Available on the
Hartzell Propeller Inc. website at www.hartzellprop.com

• Hartzell Propeller Inc. Manual No. 181 (30-60-81) - Propeller Ice Protection System Component Maintenance
Manual - Available on the Hartzell Propeller Inc. website at www.hartzellprop.com

• Hartzell Propeller Inc. Manual No. 182 (61-12-82) - Propeller Electrical De-ice Boot Removal and Installation
Manual - Available on the Hartzell Propeller Inc. website at www.hartzellprop.com

• Hartzell Propeller Inc. Manual No. 183 (61-12-83) - Propeller Anti-icing Boot Removal and Installation Man-
ual - Available on the Hartzell Propeller Inc. website at www.hartzellprop.com

• Hartzell Propeller Inc. Manual No. 202A (61-01-02) - Standard Practices Manual, Volumes 1 through 11 (Vol-
ume 7, Consumable Materials and Packaging and Storage is available on the Hartzell Propeller Inc. website at
www.hartzellprop.com)

• Hartzell Propeller Inc. Service Letter HC-SL-61-61Y - Overhaul Periods and Service Life Limits for Hartzell
Propellers Inc. Aviation Components - Propellers, Governors, and Propeller Damper Assemblies - Available on
the Hartzell Propeller Inc. website at www.hartzellprop.com

9. References to Hartzell Propeller Inc. Publications

NOTE: Specific Hartzell Propeller Inc. manuals and service documents are available on the Hartzell website
at www.hartzellprop.com. Refer to the section Required Publications in this chapter for the
identification of these publications.

a. Special tooling is required for procedures throughout this manual. For further tooling information, refer to
Hartzell Propeller Inc. Illustrated Tool and Equipment Manual 165A (61-00-65).
NOTE: Tooling references appear with the prefix ‘TE’ directly following the tool name to which they apply. For
example, a template which is reference number 133 will appear as: template TE133.

b. Consumable materials are referenced in certain sections throughout this manual. Specific approved
materials are listed in the Consumable Materials chapter of Hartzell Propeller Inc. Standard Practices Manual
202A (61-01-02).
NOTE: The reference number for consumable materials appear with the prefix ‘CM’ directly following the
material to which they apply. For example, an approved adhesive that is reference number 16 will
appear as: approved adhesive CM16. Only those items specified may be used.

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MAINTENANCE MANUAL SUPPLEMENT 61-00-00-Introduction DATE: 01/01/2020
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Introduction

10. Definitions

Definitions
A basic understanding of the following terms will assist in maintaining and operating Hartzell Propeller Inc.
propeller systems.

TERM DEFINITION
Annealed
Blade Angle Softening of material due to overexposure to heat

Brinelling Measurement of blade airfoil location described as the angle between the blade
Chord airfoil and the surface described by propeller rotation
Cold Rolling
A depression caused by failure of the material in compression
Constant Force
Constant Speed A straight line distance between the leading and trailing edges of an airfoil

Corrosion Compressive rolling process for the retention area of single shoulder blades
Crack that provides improved strength and resistance to fatigue

Depression A force that is always present in some degree when the propeller is operating
Distortion
Erosion A propeller system that employs a governing device to maintain a selected
Exposure engine RPM
Feathering
Gradual material removal or deterioration due to chemical action
Gouge
Hazardous Propeller Effect Irregularly shaped separation within a material, sometimes visible as a narrow
Horizontal Balance opening at the surface
Impact Damage
Surface area where the material has been compressed but not removed.
Major Propeller Effect
Nick Alteration of the original shape or size of a component
Onspeed
Gradual wearing away or deterioration due to action of the elements
Overhaul
Leaving material open to action of the elements
Overspeed
The capability of blades to be rotated parallel to the relative wind, thus
Overspeed Damage reducing aerodynamic drag

Pitch Surface area where material has been removed
Pitting
The hazardous propeller effects are defined in Title 14 CFR section 35.15(g)(1)

Balance between the blade tip and the center of the hub

Damage that occurs when the propeller blade or hub assembly strikes, or is
struck by, an object while in flight or on the ground

The major propeller effects are defined in Title 14 CFR section 35.15(g)(2)

Removal of paint and possibly a small amount of material

Condition in which the RPM selected by the pilot through the propeller control
lever and the actual engine (propeller) RPM are equal

The periodic disassembly, inspection, repair, refinish, and reassembly of a
propeller assembly to maintain airworthiness

Condition in which the RPM of the propeller or engine exceeds predetermined
maximum limits; the condition in which the engine (propeller) RPM is higher
than the RPM selected by the pilot through the propeller control lever

Damage that occurs when the propeller hub assembly rotates at a speed
greater than the maximum limit for which it is designed

Same as “Blade Angle”

Formation of a number of small, irregularly shaped cavities in surface material
caused by corrosion or wear

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MAINTENANCE MANUAL SUPPLEMENT 61-00-00-Introduction DATE: 01/01/2020
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Introduction

TERM DEFINITION
Propeller Critical Parts
A part on the propeller whose primary failure can result in a hazardous
Reversing propeller effect, as determined by the safety analysis required by Title 14 CFR
Scratch section 35.15
Single Acting
Superseded The capability of rotating blades to a position to generate reverse thrust to
Synchronizing slow the aircraft or back up
Synchrophasing
Same as “Nick”
Track
Hydraulically actuated propeller that utilizes a single oil supply for pitch control
Underspeed
Variable Force Parts that are considered airworthy for continued flight but may no longer be
Vertical Balance available
Windmilling
Adjusting the RPM of all the propellers of a multi-engine aircraft to the same
RPM

A form of propeller sychronization in which not only the RPM of the engines
(propellers) are held constant, but also the position of the propellers in relation
to each other

In an assembled propeller, a measurement of the location of the blade tip with
respect to the plane of rotation, used to verify face alignment and to compare
blade tip location with respect to the locations of the other blades in the
assembly

The condition in which the actual engine (propeller) RPM is lower than the RPM
selected by the pilot through the propeller control lever

A force that may be applied or removed during propeller operation

Balance between the leading and trailing edges of a two-blade propeller with
the blades positioned vertically

The rotation of an aircraft propeller caused by air flowing through it while the
engine is not producing power.

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MAINTENANCE MANUAL SUPPLEMENT 61-00-00-Introduction DATE: 01/01/2020
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Introduction

11. Abbreviations Term
Aircraft Maintenance Manual
Abbreviation Air Force-Navy (or Army-Navy)
AMM Aircraft on Ground
AN Federal Aviation Administration
AOG Foot-Pound
FAA Instructions for Continued Airworthiness
FT-Lb Inside Diameter
ICA Inch-Pound
ID Inches Per Second
In-Lb Pounds
IPS Military Specification
Lbs Major Periodic Inspection (Overhaul)
MIL-X-XXX Military Standard
MPI Material Safety Data Sheet
MS Outside Diameter
MSDS National Aerospace Standards
OD National Aerospace Standards, Military
NAS Newton-Meters
NASM Pilot’s Operating Handbook
Nm Pounds per Square Inch
POH Revolutions per Minute
PSI Time Between Overhaul
RPM Type Certificate
TBO Time Since New
TC Time Since Overhaul NOTE: TSN/TSO is considered as the time accumulated
TSN between rotation and landing, i.e., flight time.
TSO

12. Hartzell Propeller Inc. Product Support

a. Hartzell Propeller Inc. is ready to assist you with questions concerning your propeller system. Hartzell
Propeller Inc. Product Support may be reached during business hours (8:00 a.m. through 5:00 p.m., United
States Eastern Time) at (937) 778-4379 or at (800) 942-7767, toll free from the United States and Canada.
Hartzell Product Support can also be reached by fax at (937) 778-4215, and by email at
[email protected].

b. After business hours, you may leave a message on the 24 hour product support line at (937) 778-4376 or
at (800) 942-7767, toll free from the United States and Canada. A technical representative will contact you
during normal business hours. Urgent AOG support is available 24 hours per day, seven days per week via
this message service.

c. Additional information is available on the website at www.hartzellprop.com.

NOTE: When calling from outside the United States, dial (001) before dialing the above telephone numbers.

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MAINTENANCE MANUAL SUPPLEMENT 61-00-00-Introduction DATE: 01/01/2020
C550GT-AD016-FU24-0213 Revision: Initial Issue Propeller
Introduction

13. Warranty Service

If you believe you have a warranty claim, it is necessary to contact Hartzell Propellers Warranty Administrator.
Hartzell Propellers Warranty Administrator will provide you with a Warranty Application form. It is necessary to
complete this form and return it to the Warranty Administrator for evaluation before proceeding with repair
or inspection work. Upon receipt of this form, the Warranty Administrator will provide instructions on how to
proceed.
Hartzell Propeller Inc. Warranty may be reached during business hours (8:00 a.m. through 5:00 p.m., United
States Eastern Time) at 937-778-4379, or toll free at (800) 942-7767. Hartzell Propeller Inc. Warranty
Administration can also be reached by fax, at (937) 778-4215, or by email at [email protected].

NOTE: When calling from outside the United States, dial (001) before dialing the above telephone numbers.

1. Hartzell Propeller Inc. Recommended Facilities

Hartzell Propeller Inc. recommends using Hartzell Propeller Inc. approved distributors and repair facilities for the
purchase, repair, and overhaul of Hartzell Propeller Inc. propeller assemblies or components.
Information about the Hartzell Propeller Inc. worldwide network of aftermarket distributors and approved repair
facilities is available on the Hartzell Propeller Inc. website at www.hartzellprop.com.

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MAINTENANCE MANUAL SUPPLEMENT 61-10-00-Propeller Description
C550GT-AD016-FU24-0213
Propeller Description Revision: Initial Issue DATE: 01/01/2020

Description and Operation / Propeller

Propeller Description
Propeller

61-10-00 Propeller

Description and Operation

Feathering and Reversing Propeller- HC-B3TN-3D

See Figure 61.1
The propeller described in this section is a three blade, constant speed, feathering and reversing type, Model No.
HC-B3TN-3D. It uses a single oil supply from a governing device to hydraulically actuate a change in blade angle.
Propeller blades and bearing assemblies are mounted on the arms of a steel hub unit (Figure 61.x) and are held
in place by two-piece blade clamps. A cylinder is threaded onto the hub, and a feathering spring assembly is
installed in the cylinder. A piston is placed over the cylinder and is connected by a link arm to each blade clamp.
Propeller blade angle change is accomplished through the linear motion of the hydraulically actuated piston that
is transmitted to each blade through the link arms and blade clamps.
While the propeller is operating, the following forces are constantly present: 1) spring force, 2) counterweight
force, 3) centrifugal twisting moment of each blade, and 4) blade aerodynamic twisting forces. The spring and
counterweight forces attempt to rotate the blades to higher blade angle, while the centrifugal twisting moment of
each blade is generally acting toward lower blade angle. Blade aerodynamic twisting force is usually very small in
relation to the other forces and can attempt to increase or decrease blade angle

Figure 61.1 Hartzell Propeller cut-away

The summation of the propeller forces is toward higher pitch (low RPM) and is opposed by a variable force
toward lower pitch (high RPM). The variable force is oil under pressure from a governor with an internal pump,
which is mounted on and driven by the engine. The oil from the governor is supplied to the propeller and
hydraulic piston through a hollow engine shaft. Increasing the volume of oil within the piston and cylinder will
decrease the blade angle and increase propeller RPM. Decreasing the volume of oil will increase blade angle and
decrease propeller RPM. By changing the blade angle, the governor can vary the load on the engine and maintain
constant engine RPM (within limits), independent of where the power lever is set. The governor uses engine
speed sensing mechanisms that allow it to supply or drain oil as necessary to maintain constant engine speed
(RPM).

If governor supplied oil is lost during operation, the propeller will increase pitch and feather. Feathering occurs
because the summation of internal propeller forces causes the oil to drain out of the propeller until the feather
stop position is reached.

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MAINTENANCE MANUAL SUPPLEMENT 61-10-00-Propeller Description
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Description and Operation / Propeller

Normal in-flight feathering is accomplished when the pilot retards the propeller condition lever past the feather
detent. This allows control oil to drain from the propeller and return to the engine sump. Engine shutdown is
normally accomplished during the feathering process.

Normal in-flight unfeathering is accomplished when the pilot positions the propeller condition lever into the
normal flight (governing) range and restarts the engine. As engine speed increases, the governor supplies oil to
the propeller, and the blade angle decreases.
In reverse mode of operation, the governor operates in an underspeed condition to act strictly as a source of
pressurized oil, without attempting to control RPM. Control of the propeller blade angle in reverse is
accomplished through the beta valve.

NOTE: The beta valve is built into the base of the governor.

The propeller is reversed by manually repositioning the cockpit-control to cause the beta valve to supply oil from
the governor pump to the propeller. An external propeller feedback mechanism, which include a beta ring and
carbon block assembly, communicate propeller blade angle position to the beta valve.
When the propeller reaches the desired reverse position, movement of the beta ring and carbon block assembly,
initiated by the propeller piston, causes the beta valve to shut off the flow of oil to the propeller. Any additional
unwanted movement of the propeller toward reverse, or any movement of the manually positioned beta valve
control toward high pitch position will cause the beta valve to drain oil from the propeller to increase pitch.

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MAINTENANCE MANUAL SUPPLEMENT 61-10-00-Model Designation
C550GT-AD016-FU24-0213
Model Designation Revision: Initial Issue DATE: 01/01/2020

Description and Operation / Propeller

Model Designation
Propeller

Model Designation.

The C550GT uses the Hartzell Propeller HC-B3TN-3D propeller.
Hartzell Propeller Inc. uses a model designation to identify specific propeller and blade assemblies.

HC - Hartzell Controllable
B - Single Shoulder Retention (T and M shank)
3 - Three Blades
N - Mounting Flange is 4.25 in. bolt circle, 2 x ½” Dowels, 8 x 9/16" Bolts.
3 - Constant Speed, Feathering, Reversing, PT-6 with External Beta Ring
D – The B-3475A-2 Low Stop Rod Unit (alternate B-3475-2, B-3002-2), 831-33 Spring Assembly, New Rods.

Last Identification Letter

HC - B 3 T N - 3 (xx) The last two letters indicate Minor Modifications.
A - 831-23A, -47, -46 SPRING ASSEMBLY 3 SPRINGS, OLD RODS
B - B-3475A-2 LOW STOP ROD UNIT ALTERNATE B-3475-2, B-3002-2
C - SAME AS -3B EXCEPT 831-23A,-47, -46 SPRING ASSEMBLY 3 SPRINGS NEW RODS
D - SAME AS -3C EXCEPT 831-33 SPRING ASSEMBLY.

Figure 61.2 Propeller Model Designation

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MAINTENANCE MANUAL SUPPLEMENT 61-10-00-Model Designation
C550GT-AD016-FU24-0213
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Description and Operation / Propeller

Aluminum Blade Model Identification.

The blade designation is impression stamped on the blade butt end (internal) and is either on a decal or ink
stamped on the blade camber side (external).

Figure 61.3 Propeller Blade Designation
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MAINTENANCE MANUAL SUPPLEMENT 61-10-00- Propeller Troubleshooting
C550GT-AD016-FU24-0213
Propeller Troubleshooting Revision: Initial Issue DATE: 01/01/2020

Propeller Troubleshooting Troubleshooting / Propeller
Propeller
Troubleshooting
Troubleshooting.

1. Hunting and Surging.

Hunting is characterized by a cyclic variation in engine speed above and below desired speed. Surging is
characterized by a large increase/decrease in engine speed, followed by a return to set speed after one or two
occurrences.

(1) If propeller is hunting, an appropriately licensed propeller repair station should check:

a. Governor
b. Fuel control
c. Synchrophaser or synchronizer

(2) If propeller is surging:

a. Perform the steps 1.A.(1) through 1.A.(5) in the Operational Tests section of this chapter to release trapped
air from the propeller. If surging reoccurs, it is most likely due to a faulty governor.

b. Hunting and/or surging may also be caused by friction or binding within the governor control, or by internal
propeller corrosion, which causes the propeller to react slower to governor commands.
NOTE: The propeller must be tested on a test bench at an appropriately licensed propeller repair facility to
isolate these faults.

2. Engine Speed Varies with Airspeed.
(1) Constant speed propeller models will experience small variances in engine speed that are normal and are no
cause for concern.
(2) Increase in engine speed while descending or increasing airspeed:
a. Governor is not reducing oil volume.
b. Friction in propeller.

(3) Decrease in engine speed while increasing airspeed:
a. Governor pilot valve is stuck and is excessively decreasing oil volume.
b. Feathering command engaged on propeller pitch control.

(4) Increase in engine speed while decreasing airspeed:
a. Governor pilot valve is stuck and is excessively increasing oil volume.

(5) Decrease in engine speed while decreasing airspeed:
a. Governor is not increasing oil volume in propeller.
b. Friction in propeller.

3. Loss of Propeller Control

(1) Propeller goes to uncommanded high pitch (or feather).

a. Loss of propeller oil pressure - check:
i. Governor pressure relief valve.
ii. Governor drive.
iii. Engine oil supply.

(2) Propeller goes to uncommanded low pitch (high RPM).

a. Governor pilot valve sticking.

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