C-295 MAINTENANCE MANUAL

CHAPTER 76

LIST OF EFFECTIVE PAGES

CHAPTER CHAPTER
SUBJECT PAGE DATE SUBJECT PAGE DATE

List of 505 Jul. 15/03

Effective 506 Jul. 15/03
Page 1 Jul. 15/03 507 Jul. 15/03
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Table of 510 Jul. 15/03
Contents 1 Jul. 15/03 511 Jul. 15/03
2 Jul. 15/03 512 Jul. 15/03
513 Jul. 15/03
76-00-00 514 Jul. 15/03
CONFIG.1 1 May 31/03 515 Jul. 15/03
2 May 31/03 516 Jul. 15/03

76-10-00 CONFIG.1 601 Jul. 15/03

CONFIG.1 1 May 31/03 602 Jul. 15/03
2 May 31/03 603 Jul. 15/03
604 Jul. 15/03
76-11-00 605 Jul. 15/03
CONFIG.1 1 May 31/03 606 Jul. 15/03
2 May 31/03 607 Jul. 15/03
3 May 31/03 608 Jul. 15/03
4 May 31/03
5 May 31/03 76-11-51
6 May 31/03 CONFIG.1 401 May 31/03
7 May 31/03 402 May 31/03
8 May 31/03 403 May 31/03
9 May 31/03 404 May 31/03
10 May 31/03 405 May 31/03
11 May 31/03 406 May 31/03
12 May 31/03
76-11-61
CONFIG.1 101 May 31/03 CONFIG.1 401 May 31/03
102 May 31/03 402 May 31/03
103 May 31/03 403 May 31/03
104 May 31/03 404 May 31/03
105 May 31/03 405 May 31/03
106 May 31/03 406 May 31/03
407 May 31/03
CONFIG.1 501 Jul. 15/03 408 May 31/03
502 Jul. 15/03
503 Jul. 15/03 76-11-62
504 Jul. 15/03 CONFIG.1 401 May 31/03

Effectivity: All
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CHAPTER CHAPTER
SUBJECT PAGE DATE SUBJECT PAGE DATE

402 May 31/03

403 May 31/03 CONFIG.1 501 May 31/03
404 May 31/03 502 May 31/03
405 May 31/03 503 May 31/03
406 May 31/03 504 May 31/03
505 May 31/03
76-11-64 506 May 31/03
CONFIG.1 401 May 31/03
402 May 31/03
403 May 31/03
404 May 31/03
405 May 31/03
406 May 31/03
407 May 31/03
408 May 31/03

76-11-65
CONFIG.1 401 May 31/03
402 May 31/03
403 May 31/03
404 May 31/03
405 May 31/03
406 May 31/03

76-11-66
CONFIG.1 401 May 31/03
402 May 31/03
403 May 31/03
404 May 31/03

76-11-67
CONFIG.1 401 May 31/03
402 May 31/03
403 May 31/03
404 May 31/03

76-14-00
CONFIG.1 1 May 31/03
2 May 31/03
3 May 31/03
4 May 31/03
5 May 31/03
6 May 31/03
7 May 31/03
8 May 31/03

CONFIG.1 101 May 31/03

102 May 31/03

Effectivity: All
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 C-295 MAINTENANCE MANUAL

CHAPTER 76

TABLE OF CONTENTS

CHAPTER/
SUBJECT SECTION PAGE EFF.

ENGINE CONTROLS 76-00-00 EA03, PO01, RJ01

Description/Operation CONFIG.1 1

POWER CONTROL 76-10-00 EA03, PO01, RJ01

Description/Operation CONFIG.1 1

POWER AND FUEL FEATHER CONTROL 76-11-00 EA03, PO01, RJ01

SYSTEM

Description/Operation CONFIG.1 1

Troubleshooting CONFIG.1 101

Adjustment/Test CONFIG.1 501

Inspection/Check CONFIG.1 601

CONTROL QUADRANT ZD133 76-11-51 EA03, PO01, RJ01

Removal/Installation CONFIG.1 401

FLIGHT COMPARTMENT CONTROL CABLES 76-11-61 EA03, PO01, RJ01

Removal/Installation CONFIG.1 401

FUSELAGE TO CENTER WING CONTROL 76-11-62 EA03, PO01, RJ01

CABLES

Removal/Installation CONFIG.1 401

CENTER WING TO NACELLE CONTROL 76-11-64 EA03, PO01, RJ01

CABLES

Effectivity: All
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CHAPTER/
SUBJECT SECTION PAGE EFF.

Removal/Installation CONFIG.1 401

LEVER ASSEMBLY 76-11-65 EA03, PO01, RJ01

Removal/Installation CONFIG.1 401

PULLEY ASSEMBLY 76-11-66 EA03, PO01, RJ01

Removal/Installation CONFIG.1 401

SUPPORT ASSEMBLY 76-11-67 EA03, PO01, RJ01

Removal/Installation CONFIG.1 401

BETA LOCKOUT SYSTEM 76-14-00 EA03, PO01, RJ01

Description/Operation CONFIG.1 1

Troubleshooting CONFIG.1 101

Adjustment/Test CONFIG.1 501

Effectivity: All
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 C-295 MAINTENANCE MANUAL
ENGINE CONTROLS

DESCRIPTION/OPERATION

1. General

The control of each engine and its propeller is from:

- Two lever groups which control mechanically each engine and its
propeller. Each one is independently to the other. These levers are:
· The Power Lever (PL), and

· The Fuel-Feather Lever (FFL).

These levers are on the control quadrant in the center console of the
flight compartment (Ref. 76-11-00, P. Block 1).
- Two EMERGENCY fuel shut-off valves controlled from two fire levers
(LH/RH) installed on the overhead panel of the flight compartment
(Ref. 26-21-00, P. Block 1).

A switch on the control unit KC50 controls electrically the synchrophasing

and propellers speed. This control unit is on the overhead panel
(Ref. 61-20-00, P. Block 1).

The Electrical Control Unit controls electronically each engine. This unit
controls the start and the fuel flow in the Np Bottoming Governing System
and Np Overspeed Protection System.

The condition signals come from:

- The exhaust gas temperature thermocouples at the power turbine inlet
- The Np sensor (high pressure), and
- The torque and overspeed sensor.

The Electrical Control Unit changes the condition signals into output
signals to the related system indicators in the flight compartment.

Effectivity: See TOC CONFIG. 1

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INTENTIONALLY LEFT BLANK

Effectivity: See TOC CONFIG. 1

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 C-295 MAINTENANCE MANUAL
POWER CONTROL

DESCRIPTION/OPERATION

1. General

The primary components of the power control system are the controls of the
flight compartment. These are:
- Two power levers (PL)
- Two fuel-feather levers (FFL), and
- One power rating selector switch.

The functions of these levers are:

A. Power Levers (PL)

The positive and reverse thrust modulation with the power control of
each engine, through the MFCU (Mechanical Fuel Control Unit), and the
pitch of each propeller through the PVM (Propeller Valve Module).

B. Fuel-Feather Levers (FFL)

The selection of the related propeller speed and engine power to each
flight rate, as follows:

(1) MCT: Maximum Continuous (100% Np)

(2) TOGA: Take Off Go Around (100% Np)

(3) CLB: Climb (95% Np)

(4) CRZ1: Cruise 1 to 90% Np

(5) CRZ2: Cruise 2 to 80% Np

The power control quadrant in the flight compartment has:

- A friction brake, which lets adjust the power levers forces.
- A Beta Lockout System, which prevents to set the power levers below
the FI position (Flight Idle) in flight, with an override switch.
- The gust lock lever, which gives a limit of the power levers (PL)
movement to the GI position (Ground Idle).

Effectivity: See TOC CONFIG. 1

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Effectivity: See TOC CONFIG. 1

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 C-295 MAINTENANCE MANUAL
POWER AND FUEL FEATHER CONTROL SYSTEM

DESCRIPTION/OPERATION

1. General

The power levers (PL) and the fuel-feather levers (FFL) are on the control
quadrant, at the center console of the flight compartment. A system of
cables and pulleys transmits the movement of the levers to the engines and
propellers. These cables and pulleys are:
- Through the front area of the instruments center panel,
- Along the center windshield side frames,
- Along the inside of the fuselage, and
- Through the pressure seals to the center wing front spar.

On the control quadrant, between the power levers (PL) and fuel-feather
levers (FFL), is a friction brake device. A selector switch operates the
friction brake device.

The gust lock lever of the flight controls system is on the control
quadrant, on the left side of the power levers (PL).

2. Component Location (Fig. 1)

ITEM FIN DESIGNATION ZONE ACCESS REFERENCE

PANEL

1. ZD133 Control Quadrant 213 - 76-11-51

2. Levers and Bottom 213 211CL 76-11-62
Support Assembly 212BR
211BL
212AR
3. Flight Compartment 213 76-11-61
Control Cables 211
(212)
221
(222)
4. Support Clamp 414 414AT
(424) (424AT)
5. Cables Assembly 413 413AL
Support (423) (423AL)

Effectivity: See TOC CONFIG. 1

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 C-295 MAINTENANCE MANUAL
Power and Fuel-Feather Controls - Component Location

EM1.76.11.00.0AO.01.01-00

Fig. 1 Power and Fuel-Feather Controls - Component Location (Sheet 1 of 3)

Effectivity: See TOC CONFIG. 1

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 C-295 MAINTENANCE MANUAL

EM1.76.11.00.0AO.02.01-00

Fig. 1 Power and Fuel-Feather Controls - Component Location (Sheet 2 of 3)

Effectivity: See TOC CONFIG. 1

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 C-295 MAINTENANCE MANUAL

EM1.76.11.00.0AO.03.01-00

Fig. 1 Power and Fuel-Feather Controls - Component Location (Sheet 3 of 3)

Effectivity: See TOC CONFIG. 1

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 C-295 MAINTENANCE MANUAL
ITEM FIN DESIGNATION ZONE ACCESS REFERENCE
PANEL

6. Bulkhead 414 414AT 76-11-64

(424) (424AT)
7. Levers and Pulleys 941 941AL 76-11-64
Assembly - (942) (942AL)
Fuel-Feather
8. Levers and Pulleys 941 941AL 76-11-64
Assembly - Power (942) (942AR)
9. PL and FFL Cable 413 413AL 76-11-64
Assembly (423) (423AL)

3. Description (Fig. 2) and (Fig. 3)

The control quadrant for the two engines is in the center console of the
flight compartment, at the STA 3343. It has:
- The power levers (PL) (2)
- The fuel-feather levers (FFL) (4)
- The selector knob of the friction brakes (3)
- The gust lock lever (11) of the flight controls system
- The override switch (10) and beta lockout of the propellers
- The power rating selector (5), and
- Two fire warning indicators.

The PL levers (2) and the FFL levers (4) connect with the gearbox and
interface of the fuel and power of the two engines, through the rods and
levers assemblies (7) and (8) and a cables and pulleys system.

The PL levers (2) and the FFL levers (4) connect with the gearbox and
interface of the fuel and power of the two engines through:
- The rods and levers assemblies (7) and (8)
- The cables and pulleys system.

Effectivity: See TOC CONFIG. 1

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 C-295 MAINTENANCE MANUAL
The power levers operation range has these marks (from front to rear):
- MAX MAN
- MAX AUTO
- FI
- GI
- REV.

The flight idle position (FI) and ground idle position (GI) have lock
detent to prevent the accidental movement of the controls to a incorrect
adjustment.

The operation of the gust lock lever (11) gives a limit of the movement of
the power levers (PL) (2) to the GI position.

The selector knob (3) operates the friction damping for the power levers
(PL) (2). When the friction lever turns to the right, the damping effect
increases. The travel range has a mark (+) to the right and (-) to the
left. The FRICTION legend is on the bottom of the knob.

The operation range of the fuel-feather levers (FFL) (4) has these marks,
from the front to the rear:
- RUN
- START
- OFF.

The power rating selector has the PRS legend in the bottom and these marks
from the left to the right:
- MCT
- TOGA
- CLB
- CRZ1
- CRZ2.

The propeller synchronization switch is in the control unit KC50

(Ref. 61-00-00, P. Block 1). This control unit is on the overhead panel.

The unit of flaps control is on the right side of the control quadrant.

Effectivity: See TOC CONFIG. 1

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 C-295 MAINTENANCE MANUAL
Power and Fuel-Feather Controls - Flight Compartment

EM1.76.11.00.0BO.00.01-00

Fig. 2 Power and Fuel-Feather Controls - Flight Compartment

Effectivity: See TOC CONFIG. 1

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 C-295 MAINTENANCE MANUAL
Typical Assembly of the Cable and Pulley

EM1.76.11.00.0CO.00.01-00

Fig. 3 Typical Assembly of the Cable and Pulley

Effectivity: See TOC CONFIG. 1

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 C-295 MAINTENANCE MANUAL
In the inner of the control quadrant there is a microswitch assembly
operated with the levers movement through drive gears. These microswitches
connect to the aircraft systems. The different adjustments of the power,
fuel or gust lock cause an effect on these systems.

The adjustable control rods (7), connected to one of the PL and FFL levers
ends, transmit the levers movement to a bracket and levers assembly (8).
This assembly is on the floor panel and the inner side of the center
console, at the STA 3105. A teleflex push/pull control linkage (9)
transmits the movement from the bracket and lever assembly (8), through
the flexible control cables, to the pulley assemblies. These pulley
assemblies are on the supports of the fuselage frames, at STA 4309.

A cables and pulleys system transmits the movement from the pulley
assembly (at the STA 4309) to the fuselage ceiling and along the ceiling
to the STA 9708. In this station, the cables go through the pressure seals
and along the center wing front spar to the lever and pulley assembly. The
lever and pulley assembly is on the front spar, at wing STA 3100 (LH) and
STA 4100 (RH).

Two turnbuckles (5) adjust the cable tension. Two locksprings safety these
turnbuckles.

The cables (Fig. 3) are assemblies with end fittings that have:
- Threads (4) to engage to the turnbuckles (5) installed at strategic
positions in the cable routing, or
- Swage-end (1) to engage to the pulley assemblies.

The cable guards (2) are between the flanges of the cable pulley brackets
to prevent that the cables go out of the pulleys. The cables have a
diameter of 2,4 mm (0,1 in).

A teleflex push/pull control transmits the movement from the front spar to
the flexible control cables. These cables go through the engine firewall
to connect to a gearbox (9) (Fig. 1) installed at the MFCU of the engine
accessory gearbox at STA 245,84. Other flexible control cables (9) (Fig.
1) connect the control gearbox to the propeller valve module (PVM) on the
propeller gearbox (PGB) casing at engine STA 206. A support clamp (4)
(Fig. 1), installed on the engine front mounting assembly, attaches these
cables.

4. Operation (Fig. 4)

The transmission of the movement of the power levers (PL) is to:

- The HMU on the accessory gearbox
- The PCU on the propeller reduction gearbox.

Effectivity: See TOC CONFIG. 1

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 C-295 MAINTENANCE MANUAL
The power levers (PL) control the engines power and, in the Beta mode,
directly control the propeller pitch and the reverse.

The transmission of the movement of the fuel-feather levers (FFL) is to:

- The HMU on the accessory gearbox
- The PCU on the propeller reduction gearbox.

The functions of the fuel-feather levers (FFL) are to:

- Close mechanically the fuel flow
- Remove the vapors of the fuel system
- Give the lock of the governor system in the ECU
- Set the propeller speed, and
- Feather and unfeather the propeller.

5. Interfaces

The power and fuel controls, through the control quadrant, ZD133, have
interfaces with these systems:
- Pressurization Control System (Ref. 21-31-00, P. Block 1)
- Flaps - Mechanical and Electrical Control (Ref. 27-51-00, P. Block 1)
- Unsafe Takeoff Warning System (Ref. 31-52-00, P. Block 1)
- Propeller Control (Ref. 61-20-00, P. Block 1)
- Power Plant (Ref. 71-00-00, P. Block 1).

Effectivity: See TOC CONFIG. 1

76-11-00 Pag. 10
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 C-295 MAINTENANCE MANUAL
Power and Fuel Controls - Schematic

EM1.76.11.00.0DO.00.01-00

Fig. 4 Power and Fuel Controls - Schematic

Effectivity: See TOC CONFIG. 1

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Effectivity: See TOC CONFIG. 1

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 C-295 MAINTENANCE MANUAL
POWER AND FUEL FEATHER CONTROL SYSTEM

TROUBLESHOOTING

WARNING: MAKE SURE THAT YOU ISOLATE ALL THE CIRCUITS IN MAINTENANCE BEFORE
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

WARNING: PUT WARNING NOTICES IN THE CORRECT POSITION BEFORE YOU START THE
ENGINES. THIS WILL PREVENT THE ACCIDENTAL ENGINES GROUND OPERATION.

WARNING: MAKE SURE THAT THE CORRECT FIRE-FIGHTING EQUIPMENT IS AVAILABLE

NEAR, BUT NOT ADJACENT TO, THE WORK AREA.

WARNING: MAKE SURE THAT NO TRESTLES, STEPS OR EQUIPMENT ARE IN THE AREA OF
THE PROPELLERS OPERATION.

1. General

This section gives the troubleshooting procedures for the Power and
Fuel-Feather Control System. To do the troubleshooting that follows, It is
necessary to start and operate the aircraft engines
(Ref. 71-00-00, P. Block 201).

Referenced Procedures:

- 24-34-11, P. Block 401 - SYSTEM TEST Control Unit, ZD118

- 61-21-00, P. Block 101 - Propeller Controlling
- 61-40-00, P. Block 101 - Indicating
- 71-00-00, P. Block 201 - Power Plant
- 73-23-11, P. Block 401 - Electronic Status Control (ESC)
- 73-23-31, P. Block 401 - Electronic Engine Control (EEC)
- 76-11-51, P. Block 401 - Control Quadrant
- 77-11-17, P. Block 401 - Np Speed Sensor

A.

THE RPM INDICATION DOES NOT SUPPORT EQUIPMENT REQUIRED:

AGREE WITH THE POSITION OF THE - MULTIMETER
POWER LEVERS (PL).

1 SEE NEXT PAGE

Effectivity: See TOC CONFIG. 1

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 C-295 MAINTENANCE MANUAL

1 FROM PREVIOUS PAGE

EXAMINE THE ELECTRONIC ENGINE REPLACE THE EEC, KB5 (KB6)

CONTROL (EEC), KB5 (KB6). (Ref.73-23-31, P. Block 401).
YES
IS THE EEC DEFECTIVE?

NO

EXAMINE THE CONTROL QUADRANT, REPLACE THE CONTROL QUADRANT,

ZD133. ZD133
YES (Ref. 76-11-51, P. Block 401).
IS THE CONTROL QUADRANT
DEFECTIVE?

NO

EXAMINE THE Np SPEED SENSOR, REPLACE THE Np SPEED SENSOR,

EA1 (EA2). EA1 (EA2)
YES
(Ref. 77-11-17, P. Block 401).
IS THE SPEED SENSOR DEFECTIVE?

NO

EXAMINE THE ELECTRICAL WIRING REPLACE THE DEFECTIVE WIRING

BETWEEN THE EEC UNIT, KB5 (Ref. WDM).
(KB6), AND THE Np SPEED SENSOR,
YES
EA1 (EA2).

IS THE WIRING DEFECTIVE?

NO

DO THE TROUBLESHOOTING
PROCEDURES FOR THE PROPELLER
INDICATING SYSTEM
(Ref. 61-40-00, P. Block 101).

Effectivity: See TOC CONFIG. 1

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 C-295 MAINTENANCE MANUAL

B.

WITH THE PLs SET BELOW THE FI SUPPORT EQUIPMENT REQUIRED:

POSITION, ONE WARNING LIGHT OF - NONE
THE BETA LOCKOUT SYSTEM (BLS),
DOES NOT COME ON.

EXAMINE THE BETA LIGHT THAT REPLACE THE DEFECTIVE BETA

DOES NOT COME ON. LIGHT.
YES
IS THE BETA LIGHT DEFECTIVE?

NO

DO THE TROUBLESHOOTING
PROCEDURES FOR THE PROPELLER
INDICATING SYSTEM
(Ref. 61-40-00, P. Block 101).

C.

WITH THE PLs SET BELOW THE FI SUPPORT EQUIPMENT REQUIRED:

POSITION, THE TWO WARNING - MULTIMETER
LIGHTS OF THE BETA LOCKOUT
SYSTEM (BLS), DO NOT COME ON.

DO A CHECK OF: CLOSE OR REPLACE THE CIRCUIT

-THE WARN 2 CIRCUIT BREAKER BREAKER FD31 AND KB21.
FD31 ON SYSTEMS 2, PC12, C/B
PANEL. FIND THE CAUSE FOR THE OPEN
-THE WARN 1 CIRCUIT BREAKER CIRCUIT BREAKERS BEFORE YOU
YES
KB21 ON SYSTEMS 1, PC13, C/B CLOSE THEM.
PANEL.

ARE THE CIRCUIT BREAKERS OPEN

OR DEFECTIVE?

NO

1 SEE NEXT PAGE

Effectivity: See TOC CONFIG. 1

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 C-295 MAINTENANCE MANUAL

1 FROM PREVIOUS PAGE

NO

EXAMINE THE BETA LIGHTS. REPLACE THE DEFECTIVE BETA

LIGHTS.
YES
ARE THE TWO BETA LIGHTS
DEFECTIVE?

NO

EXAMINE THE CONTROL QUADRANT, REPLACE THE CONTROL QUADRANT,

ZD133. ZD133
YES (Ref. 76-11-51, P. Block 401).
IS THE CONTROL QUADRANT
DEFECTIVE?

NO

DO THE TROUBLESHOOTING
PROCEDURES FOR THE PROPELLER
INDICATING SYSTEM
(Ref. 61-40-00, P. Block 101).

D.

WITH THE PLs SET BELOW THE FI SUPPORT EQUIPMENT REQUIRED:

POSITION, THE PROPELLER DOES - MULTIMETER
NOT FEATHER.

EXAMINE THE ELECTRONIC STATUS REPLACE THE ELECTRONIC STATUS

CONTROL (ESC) UNIT, ZD162 CONTROL (ESC) UNIT, ZD162
YES
(Ref. 73-23-11, P. Block 401).
IS THE ESC UNIT DEFECTIVE?

NO

1 SEE NEXT PAGE

Effectivity: See TOC CONFIG. 1

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 C-295 MAINTENANCE MANUAL

1 FROM PREVIOUS PAGE

NO

EXAMINE THE SYSTEM TEST CONTROL REPLACE THE SYSTEM TEST CONTROL
UNIT, ZD118. UNIT, ZD118
YES (Ref. 24-34-11, P. Block 401).
IS THE CONTROL UNIT, ZD118,
DEFECTIVE?

NO

DO THE TROUBLESHOOTING
PROCEDURES FOR THE PROPELLER
CONTROLLING SYSTEM
(Ref. 61-21-00, P. Block 101).

Effectivity: See TOC CONFIG. 1

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Effectivity: See TOC CONFIG. 1

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 C-295 MAINTENANCE MANUAL
POWER AND FUEL FEATHER CONTROL SYSTEM

ADJUSTMENT/TEST

1. Adjustment of the Power and Fuel-Feather Controls System

A. Reason for the Job

- To set the power and fuel-feather controls to the correct position
to get the sufficient engine power and propeller pitch for all the
flight conditions.
- To do the 76.10.00.02 MRB task, "Functional check of Power and
Condition Control Cable Tension".

B. Equipment and Material

ITEM DESIGNATION

1. ITEM 20-15-01 Circuit Breaker Safety Clips and Tags

2. ITEM 27-00-01 Tensiometer
3. ITEM 71-00-26 Rigging Pin
4. - Servicing Platform, 2 m (7 ft)
5. - Warning Notices
6. - Storage Bag
7. - Turnbuckle Lockspring
8. - Cotter Pin
9. - Stainless Steel Lockwire

Referenced Procedures:

- 06-20-00, P. Block 1 - Zoning

- 06-41-53, P. Block 1 - Access Provisions - Fuselage
- 06-41-54, P. Block 1 - Access Provisions - Nacelles
- 06-41-57, P. Block 1 - Access Provisions - Wings
- 24-40-00, P. Block 201 - External Power
- 77-31-11, P. Block 401 - POWERPLANT MAINTENANCE Control Unit

Effectivity: See TOC CONFIG. 1

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 C-295 MAINTENANCE MANUAL

C. Procedure

(1) Job Set-Up

(a) Put warning notices in the flight compartment to prevent the

operation of controls system.

(b) Open, safety and tag this circuit breaker:

PANEL SERVICE FIN

SYSTEMS 1 START KA1

(c) Put the servicing platform in the correct position near the
engine.

(d) Put the servicing platform in the correct position near

leading edge of the center wing.

(e) Remove the access panels 941AL (942AR)

(Ref. 06-41-57, P. Block 1).

(f) Remove the access panels 413AL (413AR), 423AL (423AR) and
414AT (424AT) (Ref. 06-41-54, P. Block 1).

(g) Remove the access panels 211BL (212AR)

(Ref. 06-41-53, P. Block 1).

(h) Remove the applicable ceiling panels between the STA 3826
and STA 4309.

(2) Do the adjustment of the Power Levers (PL) in the flight

compartment and the nacelle (Fig. 501)

(a) Make sure that there are no rigging pins installed in the
system.

(b) Set the two levers (1) to the maximum power position (MAX
MAN). Then, move them slowly and smoothly to the FI position
(rigging).

(c) Set the PL stops (14) to the full position (away from the
PL).

(d) Remove the cotter pin, nut (3), washer (4) and bolt (5) from
the rod (2) and lever arm (9).

(e) Install a rigging pin in the support (6) and lever arm (9).

Effectivity: See TOC CONFIG. 1

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 C-295 MAINTENANCE MANUAL

(f) Set the rod (2) length until you can easily install the bolt
(5) and washer (4) in the rod and lever arm (9).

(g) Remove the rigging pin. Move the PL lever slowly to the MAX
MAN position, and again to the FI position. Make sure that
the rigging pin installation is easy.

(h) If you can not install the rigging pin easily, do again the
steps (d) thru (g) until you can do it.

(j) Install the nut (3). Tighten the nut.

(k) Safety the nut with a new cotter pin.

(l) Make sure that the rigging pin stays installed.

(m) Remove the rigging pin, nut (10), washer (8) and bolt (7)
from the rod (11) and lever arm (9).

(n) Install the rigging pins in the supports (19) and quadrants
(17) and (16).

(p) Set the length of the flexible cable (11) with the nut (12)
and locknut (13). Do this until you can install the bolt (7)
and washer (8) easily in the rod (11) and lever arm (9).

(q) Remove all the rigging pins.

(r) Move the PL lever to the MAX MAN position. Then, move the PL
lever again to the FI position. Make sure that the you can
easily install the rigging pins again.

(s) If you cannot easily install the rigging pins, do the steps
(k) thru (r) again until you can install them.

(t) Install the nut (10). Tighten the nut.

(u) Safety the nut with a new cotter pin.

(v) Remove all the rigging pins.

Effectivity: See TOC CONFIG. 1

76-11-00 Pag. 503
Jul. 15/03
 C-295 MAINTENANCE MANUAL
Power and Fuel-Feather Controls System

EM1.76.11.00.5AO.01.01-00

Fig. 501 Power and Fuel-Feather Controls System (Sheet 1 of 2)

Effectivity: See TOC CONFIG. 1

76-11-00 Pag. 504
Jul. 15/03
 C-295 MAINTENANCE MANUAL

EM1.76.11.00.5AO.02.01-00

Fig. 501 Power and Fuel-Feather Controls System (Sheet 2 of 2)

Effectivity: See TOC CONFIG. 1

76-11-00 Pag. 505
Jul. 15/03
 C-295 MAINTENANCE MANUAL

(w) Turn the quadrants (16) and (17) until you can install the
rigging pin (22) in the pulley assembly (25).

NOTE: Turn the quadrant to the forward direction. Then,

turn it to the rearward direction until the rigging
pin hole aligns.

(x) Install the rigging pins (22) and (34).

(y) If you cannot install the rigging pin (34), adjust the
quadrant (25) micro-regulator until you can install the
rigging pin (34).

(z) Install the rigging pin (34).

(aa) If you cannot install the rigging pin (34), adjust the rod
(33) until you can install it.

(ab) Remove the rigging pins (22), (34) and (32).

(3) Do the adjustment of the cable tension (Fig. 501 and Fig. 502)

(a) Calculate the cable tension on the cable tension/temperature

graph.

(b) Set the two levers (1) to the maximum power position (MAX
MAN). Then, move them slowly and smoothly to the FI position
(rigging).

(c) Install the rigging pins in the quadrants (16) and (17).

(d) Remove and discard the locksprings (36) and (37) from the
turnbuckles (38).

(e) Adjust the cable tension until you get the correct tension
calculated in the step (a).

NOTE: Adjust equally the two cables at each side of the

pulley.

(f) When the cable tension is correct, remove the rigging pins
from the quadrants (16) and (17).

(g) Set the two PL levers (1) to the maximum power position (MAX
MAN). Then, move them slowly and smoothly to the FI position
(rigging).

(h) Make sure that the cables tension is correct. If not, do the
steps (c) thru (g) again until you get the correct tension.

Effectivity: See TOC CONFIG. 1

76-11-00 Pag. 506
Jul. 15/03
 C-295 MAINTENANCE MANUAL
Cable Tension/Temperature Graph

EM1.76.11.00.5BO.00.01-00

Fig. 502 Cable Tension/Temperature Graph

Effectivity: See TOC CONFIG. 1

76-11-00 Pag. 507
Jul. 15/03
 C-295 MAINTENANCE MANUAL

(j) Do the step (g) three times to apply the loads equally to
the quadrants (16) and (17).

(k) Set the two PL levers (1) again to the maximum power
position (MAX MAN). Then, move them slowly and smoothly to
the FI position (rigging).

(l) Install the rigging pins in the quadrants (16) and (17).

(m) Make sure that you can install the rigging pin (22). If not,
do the steps (c) thru (l) again.

(n) Remove all the rigging pins.

(4) Last Check

(a) Make sure that all rigging pins are removed.

(b) Do the step (3) (g) three times.

(c) Make sure that you can install all rigging pins.

(d) If necessary, do the step (3) again until you can install
the rigging pins.

(e) Adjust the PL stops (loosened) until they touch the PL

levers at the position ends.

(f) Safety the PL stops with lockwire.

(g) Safety the turnbuckles with new spring clips.

(5) Do the adjustment of the Fuel-Feather Lever (FFL) controls in the

flight compartment and the nacelle (Fig. 501)

(a) Make sure that there are no rigging pins installed in the
system.

(b) Set the two FFL levers to the OFF position. Then, move them
slowly and smoothly to the START position (rigging).

(c) Remove the cotter pin, nut (3), washer (4) and bolt (5) from
the rod (2) and lever arm (9).

(d) Install a rigging pin in the support (6) and lever arm (9).

(e) Adjust the rod (2) length until you can easily install the
bolt (5) and washer (4) in the rod (2) and lever arm (9).

Effectivity: See TOC CONFIG. 1

76-11-00 Pag. 508
Jul. 15/03
 C-295 MAINTENANCE MANUAL

(f) Remove the rigging pin. Move slowly the FFL lever to the OFF
position. Then, move it again to the START position. Make
sure that you can easily install the rigging pin.

(g) If you cannot install the rigging pin easily, do the steps
(d) thru (f) again until you can install it.

(h) Install the nut (3). Tighten the nut.

(j) Safety the nut with a new cotter pin.

(k) Make sure that the rigging pin stays installed in the
support (6) and lever arm (9).

(l) Remove the cotter pin, nut (10), bolt (7) and washer (8)
from the rod (11) and lever arm (9).

(m) Install the rigging pins in the support (19) and quadrants
(15) and (18).

(n) Adjust the length of the flexible cable (11) with the nut
(13) and locknut (12). Do this until you can easily install
the bolt (7) and washer (8) in the rod (11) and lever arm
(9).

(p) Remove all the rigging pins.

(q) Move the FFL lever slowly to the OFF position. Then, move it
again to the START position. Make sure that you can easily
install the rigging pins.

(r) If you cannot install the rigging pin easily, do the steps
(k) thru (q) again until you can install it.

(s) Install the nut (10). Tighten the nut.

(t) Safety the nut with a new cotter pin.

(u) Remove all the rigging pins.

Effectivity: See TOC CONFIG. 1

76-11-00 Pag. 509
Jul. 15/03
 C-295 MAINTENANCE MANUAL

(v) Turn the quadrants (15) and (18) until you can install the
rigging pin (23) in the pulley assembly (24).

NOTE: Turn the quadrant to the rearward direction. Then,

turn it to the forward direction until the rigging
pin hole aligns.

(w) Install the rigging pins (23) and (31).

(x) If you cannot install the rigging pin (31), adjust the
quadrant (24) micro-regulator until you can install the
rigging pin (31).

(y) Remove the rigging pins (23) and (31).

(z) Turn the quadrant to the rearward direction. Then, turn it

to the forward direction and, after this, to the rigging
position. Install the rigging pins (23) and (31).

(aa) If you can not install the rigging pins (23) and (31), do
again the steps (w) thru (y).

(6) Do the adjustment of the cable tension (Fig. 501 and Fig. 502)

(a) Calculate the cable tension on the cable tension/temperature

graph.

(b) Set the two FFL levers to the OFF position. Then, move them
slowly and smoothly to the START position (rigging).

(c) Install the rigging pins in the quadrants (15) and (18).

(d) Remove and discard the locksprings (36) and (37) from the
turnbuckles (38).

(e) Adjust the cable tension until you get the correct tension
calculated in step (a).

NOTE: Adjust equally the two cables at each side of the

pulley. Adjust the cable that gives the advance
input first and, then, the opposite cable.

(f) When the cable tension is correct, remove the rigging pins.

(g) Set the two FFL levers to the OFF position. Then, move them
slowly and smoothly to the START position (rigging).

(h) Make sure that the cables tension is correct. If not, do the
steps (c) thru (g) again until you get the correct tension.

Effectivity: See TOC CONFIG. 1

76-11-00 Pag. 510
Jul. 15/03
 C-295 MAINTENANCE MANUAL

(j) Do the step (g) three times to apply the loads equally to
the quadrants (15) and (18).

(k) Set the two FFL levers to the OFF position again. Then, move
them slowly and smoothly to the START position (rigging).

(l) Install the rigging pins in the quadrants (15) and (18).

(m) Make sure that you can install the rigging pin (22). If not,
do the steps (c) thru (l) again.

(n) Remove all the rigging pins.

(7) Last Check

(a) Make sure that all rigging pins are removed.

(b) Move the FFL levers slowly to the OFF position. Make sure
that you can install the rigging pin in the OFF rigging
hole.

(c) If you can not get the OFF rigging point, do the rigging
procedure again.

(d) Do the step (6) (g) three times.

(e) Make sure that you can install all rigging pins.

(f) If necessary, do the step (3) again until you can install
the rigging pins.

(g) Safety the turnbuckles (38) with new spring clips (36) and
(37).

(8) Do the last verification of the system adjustment

(a) Connect the GPU. Set the aircraft electrical system to ON

(Ref. 24-40-00, P. Block 201).

(b) Set the INT switch to the EEC position on the POWERPLANT
MAINTENANCE control unit in the flight compartment
(Ref. 77-31-11, P. Block 401),

(c) On the IEDS panel, push (into) and hold the C and UP lighted
pushbuttons during a minimum of 4 seconds. The IEDS panel is
in the flight compartment.

(d) On the IEDS, set the ENGINE TEST INFORMATION page.

(e) Move the left (right) PL lever to the MAX REV position.
Then, move it to the MAX MAN position a minimum of 5 times.

Effectivity: See TOC CONFIG. 1

76-11-00 Pag. 511
Jul. 15/03
 C-295 MAINTENANCE MANUAL

(f) From the MAX MAN position, move the left (right) PL lever to
the FI detent.

(g) On the IEDS, make sure that the left (right) RAW PLA
indication shows 35,5 deg ±0,5 deg.

(h) If the RAW PLA indication is not correct, do the steps (2)
thru (4) again.

(j) Move the left (right) PL lever to the MAX AUTO position.
Then, move it to the FI position.

(k) Make sure that the left (right) RAW PLA indication is in the
limits. If not, do the steps (2) thru (4) again until the
RAW PLA indication is correct.

(l) Move the left (right) PL lever to the MAX AUTO position.
Then, move it quickly to the FI position.

(m) On the IEDS, make sure that the left (right) RAW PLA
indication is not less than 34,0 deg.

(n) Move the left (right) PL lever to the MAX REV position.

(p) On the IEDS, make sure that the left (right) RAW PLA
indication is not less than 2,00 deg.

(q) Move quickly the left (right) PL lever to the MAX REV
position. Make sure that the left (right) RAW PLA indication
is not less than -5,0 deg.

(r) If the RAW PLA indication is less than -5,0 deg, adjust the
PL stop (10) to the minimum position. Do this, until the
indication is correct.

(s) Move the left (right) PL lever from the MAX REV position to
the MAX AUTO position.

(t) Make sure that the left (right) RAW PLA indication shows
80,0 deg ±3,0 deg and the PL WITHIN RANGE shows YES.

(u) If the indications are incorrect, do a check of the engine

controls for a correct installation.

(v) Move the left (right) PL lever to the FI position. Then,

move it quickly to the MAX AUTO position. Make sure that:
- The RAW PLA indication shows 80,0 deg ±3,0 deg
- The PL lever is in its range.

Effectivity: See TOC CONFIG. 1

76-11-00 Pag. 512
Jul. 15/03
 C-295 MAINTENANCE MANUAL

(w) Move the left (right) PL lever from the MAX AUTO position to
the FI position and then, to the MAX MAN position.

(x) On the IEDS, make sure that the left (right) RAW PLA
indication is between 95 and 100 deg. If the indication is
less than 95 degrees, do a check of the engine controls for
a correct installation.

(y) If the indication is more than 100 degrees, adjust the PL

stop (10) to the maximum position. Do this, until the
indication is correct.

(z) On the IEDS, set the LEFT PROP (RIGHT PROP) page.

(aa) On the PMP, set the INT switch to the EPC position.

(ab) Move the left (right) PL lever from the MAX MAN position to
the FI position.

(ac) On the IEDS, make sure that the left (right) PLA indication
is 36 deg ±1,0 deg.

(ad) On the IEDS, make sure that the PL (FI) indication shows
YES.

(ae) If the indication is incorrect, adjust the end of the

telescopic rod (35) until the indications are in the limits.

(af) Move the left (right) PL lever to the MAX AUTO position.
Then, move it to the FI position.

(ag) Make sure the indications in the steps (ac) and (ad) are in
the limits. If not, do the steps (ae) thru (ag) again until
the indications are correct.

(ah) Move the left (right) PL lever to the MAX AUTO position.
Then, move it quickly to the FI position.

(aj) On the IEDS, make sure that:

- The left (right) PLA indication is 33,6 deg
- The PL (FI) indication shows YES.

(ak) Move the left (right) PL lever to the MAX AUTO position.

(al) On the IEDS, make sure that the PL (MAX AUTO) indication
shows YES.

(am) Make sure that the ends of the rod (35) are tightened and
safetied.

Effectivity: See TOC CONFIG. 1

76-11-00 Pag. 513
Jul. 15/03
 C-295 MAINTENANCE MANUAL

(9) Close-Up

(a) Remove all tools and equipment from the work area. Make sure
that the work area is clean.

(b) Install the applicable ceiling panels between the STA 3826
and STA 4309.

(c) Install the access panels 211BL (212AR)

(Ref. 06-41-53, P. Block 1).

(d) Install the access panels 413AL (423AR), 423AL (423AR) and
414AT (424AT) (Ref. 06-41-54, P. Block 1).

(e) Install the access panels 941AL (942AR)

(Ref. 06-41-53, P. Block 1).

(f) Remove the servicing platforms.

(g) Remove the warning notices.

(h) Set the aircraft electrical system to OFF. Disconnect the

GPU (Ref. 24-40-00, P. Block 201).

(j) Remove the safety clips and tags. Close this circuit
breaker:

PANEL SERVICE FIN

SYSTEMS 1 START KA1

2. Operational Test of the Engine Controls and Gust Lock Position

Electronic Rigging

A. Reason for the Job

To make sure that the system operates in the set limits.

B. Equipment and Material

N/A

Effectivity: See TOC CONFIG. 1

76-11-00 Pag. 514
Jul. 15/03
 C-295 MAINTENANCE MANUAL
Referenced Procedures:

- 24-40-00, P. Block 201 - External Power

C. Procedure

(1) Job Set-Up

(a) Connect the GPU. Set the aircraft electrical system to ON

(Ref. 24-40-00, P. Block 201).

(2) Test

ACTION RESULT

(a) On the PMP in the flight

compartment, set the INT
switch to the EEC position.

(b) On the control quadrant in

the flight compartment, set
the power rating switch to
the TOGA position.

(c) On the IEDS, push (into) and The IEDS display shows the
hold the C and UP lighted maintenance primary menu.
pushbuttons during 4 seconds.

(d) On the IEDS, set the ENGINE The IEDS display shows the
TEST INFORMATION page. ENGINE TEST INFORMATION page.

(e) Set the left (right) PL lever On the IEDS display, the PL
to the MAX REV position, and WITHIN RANGE indication shows
then, to the MAX AUT YES.
position.

(f) On the PMP, set the TRIM On the IEDS display, the TRIM
switch to the L (R) position. RESULTS indication shows OK.
Hold it in this position
during 5 sec.

(g) On the control quadrant, set

the gust lock lever to the up
position (gust lock engaged).

Effectivity: See TOC CONFIG. 1

76-11-00 Pag. 515
Jul. 15/03
 C-295 MAINTENANCE MANUAL
ACTION RESULT

(h) On the control quadrant, move The PL lever stops

the left (right) PL lever immediately after the FI
until it touches the gust position.
lock.
On the IEDS, the TRIM PLA
value is 45,0 deg ±3,0 deg.

(j) Move the left (right) PL

lever to the GI position.

(k) Set the gust lock lever to

the down position
(disengaged).

(3) Close-Up

(a) Set the aircraft electrical system to OFF. Disconnect the

GPU (Ref. 24-40-00, P. Block 201).

Effectivity: See TOC CONFIG. 1

76-11-00 Pag. 516
Jul. 15/03
 C-295 MAINTENANCE MANUAL
POWER AND FUEL FEATHER CONTROL SYSTEM

INSPECTION/CHECK

WARNING: PUT WARNING NOTICES IN THE FLIGHT COMPARTMENT BEFORE YOU START THE
MAINTENANCE WORK ON THE ENGINE CONTROL SYSTEMS. THIS WILL PREVENT
THE ACCIDENTAL CONTROL LEVERS OPERATION.

WARNING: DO NOT RUN THE BARE HANDS ALONG THE CABLE DURING THE INSPECTION.
THE BROKEN STRANDS CAN CAUSE INJURY.

1. Visual Inspection of the Power and Fuel-Feather Controls System

A. Reason for the Job

- To do the 76.10.00.01 MRB task,"Detailed visual inspection for
general condition and lubrication of Power and Condition Control
Cables (wire rope type) located between upper fuselage (Frame 9) and
engine nacelle"
- To do the 76.10.00.03 MRB task, "Detailed visual inspection of
Control Quadrant and Adjustable Control Rods for general condition".

B. Equipment and Material

ITEM DESIGNATION

(1) ITEM 12-00-11 Servicing Platform, 2 m (6,5 ft)

(2) ITEM 20-15-01 Circuit Breaker Safety Clips and Tags
(3) Z-24.930 Lint-free Cloth
(4) - Inspection Mirror
(5) - Micrometer, 0 thru 25 mm (0 thru 1,00 in)
(6) - Warning Notices
(7 - Storage Bag

Referenced Procedures:

- 06-41-53, P. Block 1 - Access Provisions - Fuselage

- 12-22-76, P. Block 301 - Engine Controls
- 25-11-11, P. Block 401 - Pilot and Copilot Seats
- 25-86-61, P. Block 401 - Flight Compartment Ceiling Panels
- 25-86-65, P. Block 401 - Main Compartment Ceiling Panels
- 25-89-61, P. Block 401 - Flight Compartment Armor
- 57-41-11, P. Block 401 - Center Wing Leading Edge

Effectivity: See TOC CONFIG. 1

76-11-00 Pag. 601
Jul. 15/03
 - 71-11-14, P. Block 401 - Aft Upper Cowling

C-295 MAINTENANCE MANUAL

- 76-11-00, P. Block 501 - Power and Fuel-Feather Controls System

C. Procedure

(1) Job Set-Up

(a) Put warning notices in the correct position to prevent the

operation of the related control lever.

(b) Open, safety and tag this circuit breaker:

PANEL SERVICE FIN

SYSTEMS 1 START KA1

(c) Put the servicing platform ITEM 12-00-11 in the correct

position.

(d) Remove the necessary ceiling panels

(Ref. 25-86-61, P. Block 401 and 25-86-65, P. Block 401).
Keep the screws in a storage bag for the subsequent
installation.

(e) Remove the pilot and copilot seats

(Ref. 25-11-11, P. Block 401).

(f) Remove the lateral armor plates from the center console, if
necessary (Ref. 25-89-61, P. Block 401).

(g) Remove the lateral access panels 211CL, 211BL, 212AR and
212BR from the center console (Ref. 06-41-53, P. Block 1).
Keep the screws in a storage bag for the subsequent
installation.

(h) Remove the related center wing leading edge

(Ref. 57-41-11, P. Block 401).

(j) Remove the aft upper cowling (Ref. 71-11-14, P. Block 401).

(k) Lift the related left lateral cowling.

(2) Inspection (Fig. 601)

(a) At the center console in the flight compartment, examine:

- The control rods (4), levers (1) and (3) and control cables
(9), for:
· Range and free movements

Effectivity: See TOC CONFIG. 1

76-11-00 Pag. 602
Jul. 15/03
 C-295 MAINTENANCE MANUAL

· Correct installation and locking

· Corrosion

· Safety conditions.

- The connectors (7) for:

· Correct installation

· Damaged wires.

(b) Examine the control rod ends (8) for too much wear.

(c) Examine all the control rod ends (8) for safety conditions.
Make sure that all nuts are correctly tightened and
safetied.

(d) On the control quadrant, operate the friction lock (2). Make
sure that you sense a damping effect on the power levers (1)
and the fuel-feather levers (3).

(e) Release the friction lock (2). Make sure that the controls
operate free and smoothly for all the range.

(f) Examine the assembly (5) and (6) for signs of damage, wear,
distortion or corrosion.

(g) Examine all cables for too much wear, corrosion, broken wire
strands, kinks, scratches or wear on the structure or
adjacent components. Do this inspection from the STA 4309.

NOTE: For the check of broken wire strands, apply a

lint-free cloth along the cable.

(h) In all the pulley installations, move the controls slowly in

their full range of travel. Examine each pulley assembly for
a correct and smooth operation.

(j) Examine the pulleys (10), cable guides, supports and cable
ends for safety condition, too much side play and correct
installation.

(k) Examine the cables turnbuckles (12) for correct installation

and locking. Examine the locksprings for correct
installation and the cable ends for safety conditions. For
this, make sure that no more than three threads go out from
the turnbuckle body.

Effectivity: See TOC CONFIG. 1

76-11-00 Pag. 603
Jul. 15/03
 C-295 MAINTENANCE MANUAL
Power and Fuel-Feather Controls

EM1.76.11.00.6AO.01.01-00

Fig. 601 Power and Fuel-Feather Controls (Sheet 1 of 2)

Effectivity: See TOC CONFIG. 1

76-11-00 Pag. 604
Jul. 15/03
 C-295 MAINTENANCE MANUAL

EM1.76.11.00.6AO.02.01-00

Fig. 601 Power and Fuel-Feather Controls (Sheet 2 of 2)

Effectivity: See TOC CONFIG. 1

76-11-00 Pag. 605
Jul. 15/03
 C-295 MAINTENANCE MANUAL

(l) Make sure that the retaining collars and safety clips are
installed correctly on the pressure seals (11). Examine the
assembly for safety condition. Examine the cable routing for
signs of friction or seizure.

(m) Make sure that the pressure seals (11) are clean.

(n) If you think that the cable is worn or distorted, measure

the cable diameter with the micrometer. The nominal cable
diameter is 2,4 mm (0,1 in).

(p) Discard all the cables that have some of these defects:
- Kinks or distortion
- Corrosion (see NOTE)
- Cable diameter decreased or worn cable with a flat area
shape
- Cable with more than three broken wires for one strand and
in one inch length. Cable with a total of six broken wires
in a length of two inches.

NOTE: You can remove the light surface corrosion with a

lint-free cloth soaked with grease AEROSHELL 7 or
equivalent.

(q) In the nacelle, examine the pulley assemblies for signs of

damage, corrosion, distortion and safety of the cable
connection sleeves.

(r) In the nacelle and engine area, examine the control cables
for corrosion, locking, safety and correct installation.

(s) Do the steps (q) and (r) again on the other engine.

(3) Test

(a) Do the cable tension procedure

(Ref. 76-11-00, P. Block 501).

(b) Do the functional test of the power and fuel-feather

(Ref. 76-11-00, P. Block 501).

(c) Make sure that a qualified person does two last inspections
of all the works done.

(d) Lubricate the power and fuel-feather control system

(Ref. 12-22-76, P. Block 301).

Effectivity: See TOC CONFIG. 1

76-11-00 Pag. 606
Jul. 15/03
 C-295 MAINTENANCE MANUAL

(4) Close-Up

(a) Remove all tools and equipment from the work area. Make sure
that the work area is clean.

(b) Close the left lateral cowling of the engine.

(c) Install the aft upper cowling (Ref. 71-11-14, P. Block 401).

(d) Install the center wing leading edge removed

(Ref. 57-41-11, P. Block 401).

(e) Remove the servicing platform.

(f) Install the ceiling panels removed

(Ref. 25-86-61, P. Block 401 and 25-86-65, P. Block 401).

(g) Install the laterals panels removed from the center console
(Ref. 06-41-53, P. Block 1).

(h) Install the lateral armor plates on the center console, if

necessary (Ref. 25-89-61, P. Block 401).

(j) Install the pilot and copilot seats

(Ref. 25-11-11, P. Block 401).

(k) Remove the safety clips and tags. Close the KA1 circuit
breaker.

(l) Remove the warning notices.

Effectivity: See TOC CONFIG. 1

76-11-00 Pag. 607
Jul. 15/03
 C-295 MAINTENANCE MANUAL

INTENTIONALLY LEFT BLANK

Effectivity: See TOC CONFIG. 1

76-11-00 Pag. 608
Jul. 15/03
 C-295 MAINTENANCE MANUAL
CONTROL QUADRANT ZD133

REMOVAL/INSTALLATION

WARNING: AFTER THE REMOVAL, ADJUSTMENT OR REPLACEMENT OF AN ENGINE

COMPONENT, FULLY EXAMINE THE WORK AREA TO MAKE SURE THAT:
- NO DISTORTION, TOOLS, UNWANTED MATERIALS OR OTHER LOOSE OBJECTS
PREVENT THE CORRECT MOVEMENT OR SAFE OPERATION OF THE SYSTEM
- THE SYSTEMS AND INSTALLATIONS IN THE WORK AREA ARE CLEAN.

WARNING: AFTER THE REMOVAL, ADJUSTMENT, OR REPLACEMENT OF A COMPONENT OF A

PRIMARY OR RELATED SYSTEM, FULLY EXAMINE THE COMPONENTS FOR:
- THE SAFETY OF LOCKING DEVICES
- THE FULL AND FREE MOVEMENT IN THE CORRECT DIRECTION
- THE TENSION.

WARNING: PUT WARNING NOTICES IN THE FLIGHT COMPARTMENT BEFORE YOU START THE
MAINTENANCE WORK ON THE ENGINE CONTROL SYSTEMS. THIS WILL PREVENT
THE ACCIDENTAL CONTROL LEVERS OPERATION.

1. Equipment and Material

ITEM DESIGNATION

A. - Warning Notices
B. - Cotter Pin
C. - Protection Plugs and Caps
D. - Storage Bag
E. ITEM 20-15-01 Circuit Breaker Safety Clips and Tags

Referenced Procedures:

- 21-11-00, P. Block 501 - Compression System

- 25-11-11, P. Block 401 - Pilot and Copilot Seats
- 27-51-00, P. Block 501 - Flaps - Mechanical and Electrical Control
- 27-51-11, P. Block 401 - Command Lever, CE4
- 31-52-00, P. Block 501 - Unsafe Takeoff Warning System
- 61-21-00, P. Block 501 - Propeller Controlling
- 71-00-00, P. Block 501 - Power Plant
- 76-11-00, P. Block 501 - Power and Fuel-Feather Controls System

Effectivity: See TOC CONFIG. 1

76-11-51 Pag. 401
May 31/03
 C-295 MAINTENANCE MANUAL

2. Procedure

A. Job Set-Up

(1) Open, safety and tag these circuit breakers:

PANEL SERVICE FIN

SYSTEMS 1 START KA1

SYSTEMS 1 FTHR KC5
SYSTEMS 1 WARNING 1 QB47
SYSTEMS 1 FLAPS SYS CE1
SYSTEMS 2 CAB PRESS HE1
SYSTEMS 2 FTHR KC4

(2) Remove the command lever, CE4 (Ref. 27-51-11, P. Block 401).

(3) Remove the pilot and copilot seats (Ref. 25-11-11, P. Block 401).

(4) Remove the lateral panels from the center console to get access
to the lever arms. Keep the screws in a storage bag for the
subsequent installation.

(5) Put warning notices in the flight compartment to tell personnel

that you will do a maintenance task. This will prevent the
operation of the related system (See step (1)).

B. Removal (Fig. 401)

(1) Disconnect the electrical connectors (9) and (11) from the
related receptacles (8) and (10). Put protection plugs and caps
to the connectors and receptacles.

(2) Remove the cotter pins (17), nuts (16), washers (15) and bolts
(12) from the rod ends (14) and levers (13). The rod ends (14)
are of the power lever (5) and fuel-feather lever (6). Discard
the cotter pins.

(3) Remove the screws (1) and washers (2) which attach the control
quadrant assembly (3) to the center console (4).

(4) Keep all the attachment items removed in a storage bag.

(5) Lift carefully the control quadrant assembly (3). Remove it from
the center console (4). Make sure that the rods (5) and (6) do
not touch the electrical assemblies and structure.

Effectivity: See TOC CONFIG. 1

76-11-51 Pag. 402
May 31/03
 C-295 MAINTENANCE MANUAL
Control Quadrant

EM1.76.11.51.4AO.00.01-00

Fig. 401 Control Quadrant

Effectivity: See TOC CONFIG. 1

76-11-51 Pag. 403
May 31/03
 C-295 MAINTENANCE MANUAL

C. Preparation for Installation (Fig. 401)

(1) Remove the protection plugs and caps from the electrical
connectors (9) and (11). Examine the connectors fro signs of
damage.

(2) Examine the lever arm assemblies (14) and the gust lock lever for
signs of damage.

D. Installation (Fig. 401)

(1) Put the control quadrant assembly (3) in the correct position on
the center console (4). Make sure that the rods (5) and (6) do
not touch the electrical assemblies and structure.

(2) Attach the control quadrant (3) to the center console (4) with
the screws (1) and washers (2). Torque the screws to the standard
value.

(3) Engage the gust lock lever (7) to the operation rod.

(4) Engage the rod ends (14) of the power and fuel-feather levers to
the lever arms (13).

(5) Put the screws (12) through the rod ends (14) and lever arms
(13).

(6) Put the washers (15) and nuts (16) to the screws (12). Torque the
nuts to the standard value. Safety the nuts (16) with new cotter
pins (17).

(7) Connect the electrical connectors (9) and (11) to the related
receptacles (8) and (10).

(8) Install the command lever in the control quadrant assembly

(Ref. 27-51-11, P. Block 401).

E. Test

(1) Do the adjustment/test procedure of the power and fuel-feather

controls (Ref. 76-11-00, P. Block 501).

(2) Do the adjustment/test procedure of the power plant

(Ref. 71-00-00, P. Block 501).

(3) Do the adjustment/test procedure of the compression system

(Ref. 21-11-00, P. Block 501).

(4) Do the adjustment/test procedure of the flaps mechanical and

electrical system (Ref. 27-51-00, P. Block 501).

Effectivity: See TOC CONFIG. 1

76-11-51 Pag. 404
May 31/03
 C-295 MAINTENANCE MANUAL

(5) Do the adjustment/test procedure of the unsafe takeoff warning

system (Ref. 31-52-00, P. Block 501).

(6) Do the adjustment/test procedure of the propeller controlling

(Ref. 61-21-00, P. Block 501).

F. Close-Up

(1) Remove all tools and equipment from the work area. Make sure that
the work area is clean.

(2) Install the lateral panels of the center console. Tighten the
screws to the standard value.

(3) Install the pilot and copilot seats

(Ref. 25-11-11, P. Block 401).

(4) Remove the warning notices.

Effectivity: See TOC CONFIG. 1

76-11-51 Pag. 405
May 31/03
 C-295 MAINTENANCE MANUAL

INTENTIONALLY LEFT BLANK

Effectivity: See TOC CONFIG. 1

76-11-51 Pag. 406
May 31/03
 C-295 MAINTENANCE MANUAL
FLIGHT COMPARTMENT CONTROL CABLES

REMOVAL/INSTALLATION

1. Reason for the Job

To remove and install the power and fuel-feather control cables when they
are unserviceable or to get access to other components.

2. Equipment and Material

ITEM DESIGNATION

A. - Warning Notices
B. MS24665-86 Cotter Pin
C. - Rigging Pin, 4,55 mm (0,183 in)
D. - Stainless Steel Lockwire 0,8 mm (0,32 in)

Referenced Procedures:

- 06-41-53, P. Block 1 - Access Provisions - Fuselage

- 21-11-18, P. Block 401 - AIR CONDITIONING Control Unit
- 24-34-11, P. Block 401 - SYSTEMS TEST Control Unit
- 24-61-13, P. Block 401 - AVIONICS Circuit Breakers Panel
- 25-86-61, P. Block 401 - Flight Compartment Ceiling Panels
- 30-11-11, P. Block 401 - ICE PROTECTION Control Unit
- 33-21-11, P. Block 401 - INTERNAL LT Control Unit
- 33-40-11, P. Block 401 - EXT LT Control Unit
- 52-31-11, P. Block 401 - HYDR UTILITY Control Unit

3. Procedure

A. Job Set-Up

(1) LH Cable:

(a) Remove the AVIONICS circuit breakers panel

(Ref. 24-61-13, P. Block 401).

(b) Remove the ICE PROTECTION control unit

(Ref. 30-11-11, P. Block 401).

(c) Remove the SYSTEM TEST control unit

(Ref. 24-30-11, P. Block 401).

Effectivity: See TOC CONFIG. 1

76-11-61 Pag. 401
May 31/03
 C-295 MAINTENANCE MANUAL

(d) Remove the EXT LT control unit

(Ref. 33-40-11, P. Block 401).

(e) Remove the left cover from the center windshield.

(2) RH Cable:

(a) Remove the AVIONICS circuit breakers panel

(Ref. 24-61-13, P. Block 401).

(b) Remove the HYDR UTILITY control unit

(Ref. 52-31-11, P. Block 401).

(c) Remove the AIR CONDITIONING control unit

(Ref. 21-11-18, P. Block 401).

(d) Remove the INTERNAL LT control unit

(Ref. 33-21-11, P. Block 401).

(e) Remove the right cover from the center windshield.

(3) Remove the lateral panel from the console

(Ref. 06-41-53, P. Block 1).

(4) Remove the flight compartment ceiling panels

(Ref. 25-86-61, P. Block 401).

(5) Put warning notices in the correct position to prevent the

operation of the power and fuel-feather levers.

B. Removal (Fig. 401)

NOTE: The four power and fuel-feather control cables are the same.
Thus, this procedure gives the removal of one of them.

(1) Move the power/fuel-feather lever, if necessary, to install the

rigging pin (19) through the pulley (20).

NOTE: With the rigging pin (19) installed, do not move the
power/fuel-feather lever until replacement components are
installed and adjusted.

(2) Remove and discard the cotter pin (9).

(3) Remove the nut (10), washer (8) and bolt (5). Disconnect the
fork-end (6) from the control lever (7).

(4) Remove the for-end (6) from the cable (1).

(5) Remove and discard the lockwire from the nuts (2) and (4).

Effectivity: See TOC CONFIG. 1

76-11-61 Pag. 402
May 31/03
 C-295 MAINTENANCE MANUAL

(6) Remove the nut (4) and the lock washer (3).

(7) Pull the cable (1) out of the fitting (23).

(8) Remove the screw (11) and washer (12) from the clamp (13).

(9) Pull the cable (1) out of the clamps (22).

(10) Remove the nuts (14), washers (15) and screws (16).

(11) Remove the nuts (17), washers (18) and screws (24).

(12) Loosen the nut (25).

(13) Remove the quick release clamp (21).

(14) Remove the cable (1) from the aircraft.

C. Preparation for Installation (Fig. 401)

(1) Examine the replacement component for signs of damage or

corrosion. The damages are not permitted.

(2) Move the clamps (13), (26) and (27) to the replacement cable.

D. Installation (Fig. 401)

(1) Put the cable (1) through the fitting (23).

(2) Install the lock washer (3) and nut (4) on the cable (1). Do not
tighten.

(3) Install the fork-end (6) on the cable (1). Make sure that the
fork-end is safetied.

(4) Adjust the nuts (2) and (4) until the fork-end (6) aligns with
the control lever (7). Then, put the bolt (5).

(5) Install the washer (8) and nut (10).

(6) Safety the nut (10) with a new cotter pin (9).

(7) Attach the clamp (13) to the clamp (28) with the screw (11) and
washer (12). The clamp (28) is on the support of the center
console.

(8) Install the clamps (26) with the screws (16), washers (15) and
nuts (14).

(9) Install the cable (1) on the clamps (22).

Effectivity: See TOC CONFIG. 1

76-11-61 Pag. 403
May 31/03
 C-295 MAINTENANCE MANUAL
Power and Fuel-Feather Control Cables - Flight Compartment

EM1.76.11.61.4AO.01.01-00

Fig. 401 Power and Fuel-Feather Control Cables - Flight Compartment

(Sheet 1 of 2)

Effectivity: See TOC CONFIG. 1

76-11-61 Pag. 404
May 31/03
 C-295 MAINTENANCE MANUAL

EM1.76.11.61.4AO.02.01-00

Fig. 401 Power and Fuel-Feather Control Cables - Flight Compartment

(Sheet 2 of 2)

Effectivity: See TOC CONFIG. 1

76-11-61 Pag. 405
May 31/03
 C-295 MAINTENANCE MANUAL

(10) Install the clamps (27) with the screws (24), washers (18) and
nuts (17).

(11) Engage the cable (1) to the pulley (20) with the quick release
clamps (21).

(12) Tighten the nut (25).

(13) Remove the rigging pin (19).

E. Close-Up

(1) LH Cable:

(a) Install the AVIONICS circuit breakers panel

(Ref. 24-61-13, P. Block 401).

(b) Install the ICE PROTECTION control unit

(Ref. 30-11-11, P. Block 401).

(c) Install the SYSTEMS TEST control unit

(Ref. 24-34-11, P. Block 401).

(d) Install the EXT LT control unit

(Ref. 33-40-11, P. Block 401).

(e) Install the left cover on the center windshield.

(2) RH Cable:

(a) Install the AVIONICS circuit breakers panel

(Ref. 24-61-13, P. Block 401).

(b) Install the HYDR UTILITY control unit

(Ref. 52-31-11, P. Block 401).

(c) Install the AIR CONDITIONING control unit

(Ref. 21-11-18, P. Block 401).

(d) Install the INTERNAL LT control unit

(Ref. 33-21-11, P. Block 401).

(e) Install the right cover on the center windshield.

Effectivity: See TOC CONFIG. 1

76-11-61 Pag. 406
May 31/03
 C-295 MAINTENANCE MANUAL

(3) Install the lateral panel of the center console

(Ref. 06-41-53, P. Block 1).

(4) Install the flight compartment ceiling panels

(Ref. 25-86-61, P. Block 401).

(5) Remove the warning notices.

(6) Remove all tools and equipment from the work area. Make sure that
the work area is clean.

Effectivity: See TOC CONFIG. 1

76-11-61 Pag. 407
May 31/03
 C-295 MAINTENANCE MANUAL

INTENTIONALLY LEFT BLANK

Effectivity: See TOC CONFIG. 1

76-11-61 Pag. 408
May 31/03
 C-295 MAINTENANCE MANUAL
FUSELAGE TO CENTER WING CONTROL CABLES

REMOVAL/INSTALLATION

WARNING: PUT ON PROTECTION GLOVES WHEN YOU TOUCH THE CONTROL CABLES. THE
CABLES CAN CAUSE INJURY TO YOUR HANDS.

1. Reason for the Job

To remove and install the power and fuel-feather control cables (in the
center wing or fuselage) when they are unserviceable or to get access to
other components.

2. Equipment and Material

ITEM DESIGNATION

A. - Warning Notices
B. - Servicing Platform
C. - String
D. MS24665-88 Cotter Pin
E. MS21256-2 Locksprings for Turnbuckles
F. Z-21.201 Grease

Referenced Procedures:

- 57-41-11, P. Block 401 - Center Wing Leading Edge

- 71-00-00, P. Block 201 - Power Plant
- 71-11-13, P. Block 401 - Left and Right Door Cowling
- 76-11-00, P. Block 501 - Power and Fuel-Feather Controls System

3. Procedure

A. Job Set-Up

(1) Put warning notices in the correct position to prevent the

operation of the control levers on the control quadrant.

(2) To get access to the routing cable:

(a) Put the servicing platform in the correct position.

(b) Remove the ceiling upholstery or the lateral panels as

necessary.

Effectivity: See TOC CONFIG. 1

76-11-62 Pag. 401
May 31/03
 C-295 MAINTENANCE MANUAL

(c) Remove the necessary panels from center wing leading edge
(Ref. 57-41-11, P. Block 401).

(d) Remove the necessary left and right door cowlings

(Ref. 71-11-13, P. Block 401).

B. Removal (Fig. 401)

(1) Turnbuckle connections:

(a) Remove and discard the lockspring (12).

(b) Disconnect the turnbuckle (13) from the related cable end
(11).

(c) Temporarily attach the cable in its position with a string.

(2) Pulley and Cable connections

(a) Remove and discard the cotter pin (16).

(b) Carefully pull the cable to release the tension. Disconnect

the swaged end (15) from the pulley (14).

(c) Let the cable stay in its position until you install the new
cable.

C. Preparation of the Replacement Cable

(1) Examine the replacement cable for signs of damage and corrosion.

(2) Lubricate lightly the cable with grease Z-21.201.

(3) Temporarily attach the new cable end to the used cable end with a
string, if necessary. This will make the installation easier.

D. Installation (Fig. 401)

(1) Carefully pull the used cable out. Put the new cable around the
applicable pulleys, guides and structures.

(2) With the new cable in the correct position, remove the string and
the used cable.

(3) If the cable end goes through the pressure seals:

(a) Remove the nuts (6), washers (5) and (3) and screws (2).

(b) Remove the circlips (1), adapters (8) and support plate (4).

Effectivity: See TOC CONFIG. 1

76-11-62 Pag. 402
May 31/03
 C-295 MAINTENANCE MANUAL
Power and Fuel-Feather Control Cables

EM1.76.11.62.4AO.00.01-00

Fig. 401 Power and Fuel-Feather Control Cables

Effectivity: See TOC CONFIG. 1

76-11-62 Pag. 403
May 31/03
 C-295 MAINTENANCE MANUAL

(c) Remove the teflon pressure seal (7).

(d) Put the replacement cable through the bulkhead and support
plate (4).

(e) Put the support plate (4) in the correct position. Attach it
to the support of the frame with the screws (2), washers (3)
and (5), and nuts (6).

(f) Put the adapters (8) on the support plate (4). Attach them
with the circlips (1).

(g) Put the replacement cable along its routing.

(4) Pulley and cable connections

(a) Put the replacement cable end through the pulleys. Connect
the swaged end (15) to the pulley (14).

(b) Install a cotter pin (16) through the pulley (14) to keep
the swaged end (15) in the pulley groove.

(5) Turnbuckle connections

(a) Connect the replacement and used cable ends (11) to the
turnbuckle body (13). Adjust the turnbuckle until there is a
light tension.

(b) Do the cable tension and adjustment procedure

(Ref. 76-11-00, P. Block 501).

(c) Make sure that the cable ends stay in safety conditions (not
more than three threads out of the turnbuckle body).

(d) Safety the turnbuckle (13) to the cable ends (11) with new
locksprings (12).

Effectivity: See TOC CONFIG. 1

76-11-62 Pag. 404
May 31/03
 C-295 MAINTENANCE MANUAL

E. Test

ACTION RESULT

(1) Operate the control system for The system operates smoothly
the full travel. during all the travel.

(2) Examine all the components The pulleys operate smoothly.

operated for free movement in
the full travel. The cables move and do not
touch the adjacent structure or
components.

The turnbuckles do not touch

the pulleys at the end of the
travel.

The controls system operates in

the correct directions.

(3) Do the control system test The results are those shown in
(Ref. 76-11-00, P. Block 501). the test.

(4) Do the ground test of the two The results are those shown in
engines. Examine the alignment the test.
of the controls
(Ref. 71-00-00, P. Block 201). The controls operate correctly.

F. Close-Up

(1) Install the panels on the center wing leading edge

(Ref. 57-41-11, P. Block 401).

(2) Install the left and right door cowlings

(Ref. 71-11-13, P. Block 401).

(3) Install the internal upholstery or the lateral panels.

(4) Remove the servicing platform.

(5) Remove the warning notices.

(6) Remove all tools and equipment from the work area. Make sure that
the work area is clean.

Effectivity: See TOC CONFIG. 1

76-11-62 Pag. 405
May 31/03
 C-295 MAINTENANCE MANUAL

INTENTIONALLY LEFT BLANK

Effectivity: See TOC CONFIG. 1

76-11-62 Pag. 406
May 31/03
 C-295 MAINTENANCE MANUAL
CENTER WING TO NACELLE CONTROL CABLES

REMOVAL/INSTALLATION

WARNING: AFTER THE REMOVAL, ADJUSTMENT OR REPLACEMENT OF AN ENGINE

COMPONENT, FULLY EXAMINE THE WORK AREA TO MAKE SURE THAT:
- NO DISTORTION, TOOLS, UNWANTED MATERIALS OR OTHER LOOSE OBJECTS
PREVENT THE CORRECT MOVEMENT OR SAFE OPERATION OF THE SYSTEM
- THE SYSTEMS AND INSTALLATIONS IN THE WORK AREA ARE CLEAN.

WARNING: AFTER THE REMOVAL, ADJUSTMENT, OR REPLACEMENT OF A COMPONENT OF A

PRIMARY OR RELATED SYSTEM, FULLY EXAMINE THE COMPONENTS FOR:
- THE SAFETY OF THE LOCKING DEVICES
- THE FULL AND FREE MOVEMENT IN THE CORRECT DIRECTION
- THE TENSION.

WARNING: PUT WARNING NOTICES IN THE FLIGHT COMPARTMENT BEFORE YOU START THE
MAINTENANCE WORK ON THE ENGINE CONTROL SYSTEMS. THIS WILL PREVENT
THE ACCIDENTAL CONTROL LEVERS OPERATION.

CAUTION: YOU MUST GIVE PROTECTION TO THE CABLES, RODS, LINKAGE AND GEARBOX
FROM DIRT AND MOISTURE. KEEP THESE COMPONENTS IN SEALED AND CLEAN
POLYETHYLENE BAGS IMMEDIATELY AFTER THE REMOVAL.

NOTE: You must do this procedure to remove or install all or a part of the
power or fuel-feather control system (in the engine nacelle area).

1. Equipment and Material

ITEM DESIGNATION

A. CAN36043B30 Fiber Glass Tape Soak in Silicone

B. ITEM 20-15-01 Circuit Breaker Safety Clips and Tags
C. - Warning Notices
D. MS24665-151 Cotter Pin
E. - Clean Polyethylene Bag

Effectivity: See TOC CONFIG. 1

76-11-64 Pag. 401
May 31/03
 C-295 MAINTENANCE MANUAL
ITEM DESIGNATION

F. - Servicing Platform
G. MS20995C32 Stainless Steel Lockwire, 0,8 mm (0,032 in)
H. MS20995C41 Stainless Steel Lockwire, 1,04 mm (0,041 in)
J. MS20995C47 Stainless Steel Lockwire, 1,19 mm (0,047 in)

Referenced Procedures:

- 71-11-12, P. Block 401 - Bridge Cowling

- 71-11-13, P. Block 401 - Left and Right Door Cowling
- 71-00-00, P. Block 501 - Power Plant
- 76-11-00, P. Block 501 - Power and Fuel-Feather Control System

2. Procedure

A. Job Set-Up

(1) Open, safety and tag this circuit breaker:

PANEL SERVICE FIN

SYSTEMS 1 START KA1

(2) Put warning notices in the correct position to prevent:

- The accidental operation of the engines
- The movement of the power and fuel-feather control levers.

(3) Put the servicing platform in the correct position.

(4) Remove the left and right door cowlings (at the zone 414 (424)),
to get access to the pulley and lever assembly of the rear
nacelle (Ref. 71-11-13, P. Block 401).

(5) Remove the rear and forward center cowlings in the right side (at
the zone 413 (423)), to get access to the control assemblies in
the engine area (Ref. 71-11-12, P. Block 401).

Effectivity: See TOC CONFIG. 1

76-11-64 Pag. 402
May 31/03
 C-295 MAINTENANCE MANUAL

B. Removal (Fig. 401)

(1) Control items from the Propeller Valve Module (PVM) to the
Mechanical Fuel Control Unit (MFCU).

(a) Remove and discard the cotter pins (1). Remove the nuts (2),
washers (3), bolts (4) and washers (5). Disconnect the
fork-ends of the rod assembly (6) from the MFCU and PVM
ends.

(2) Control items from the Mechanical Fuel Control Unit (MFCU) to the
front spar.

(a) Remove and discard the cotter pins (7), nuts (8), washers
(9) and bolts (10). Disconnect the power or fuel-feather
cable ends (11).

(b) Cut and remove the lockwire from the rotary ends (12).
Loosen the nuts (13). Disconnect the power and fuel-feather
cables from the engine support (14).

(c) Remove and discard the cotter pins (17). Remove the nuts
(18), washers (19), bolts (20) and washers (21). Remove the
half clamps (24) and the rubber joints (23) from the
joint-swivel (22). Discard the joint.

(d) Remove the screws (25) and washers (26) from the clamps (28)
and support assembly (27).

(e) Remove the power or fuel-feather control cables (11).

(f) At the front spar, remove the cables clamp (15). Disconnect
the power and fuel feather cable ends (11) from the support
(16).

(g) Keep all the removed attachment items in a storage bag.

C. Preparation of the Replacement Component

NOTE: The manufacturer supplies replacement control cables

lubricated. Thus, it is not necessary to lubricate them.

(1) Make sure that all the cables and fittings are clean. Reject the
cable if you think that it has dirt or moisture internally.

Effectivity: See TOC CONFIG. 1

76-11-64 Pag. 403
May 31/03
 C-295 MAINTENANCE MANUAL
Power and Fuel-Feather Controls - Nacelle

EM1.76.11.64.4AO.01.01-00

Fig. 401 Power and Fuel-Feather Controls - Nacelle (Sheet 1 of 2)

Effectivity: See TOC CONFIG. 1

76-11-64 Pag. 404
May 31/03
 C-295 MAINTENANCE MANUAL

EM1.76.11.64.4AO.02.01-00

Fig. 401 Power and Fuel-Feather Controls - Nacelle (Sheet 2 of 2)

Effectivity: See TOC CONFIG. 1

76-11-64 Pag. 405
May 31/03
 C-295 MAINTENANCE MANUAL

D. Installation (Fig. 401)

(1) Control items from the Mechanical Fuel Control Unit (MFCU) to the
front spar.

(a) Install the rotary ends (12) on the engine support (14).
Torque the nuts (13) to the standard value. Safety with
lockwire.

(b) Install the power or fuel-feather cable ends (11) on the

MFCU ends with the bolts (10), washers (9) and nuts (8).
Torque the nut to the standard value. Safety with new cotter
pins (7).

(c) Put the power or fuel-feather cables through the

joint-swivel (22).

(d) Connect the power or fuel-feather cable ends (11) to the

support assembly (16). Install and safety the cable clamp
(15).

(e) Put in the joint-swivel (22), the half clamps (24), with the
rubber joints (23) installed. Attach them with the bolts
(20), washers (21) and (19) and nuts (18). Torque the nuts
to the standard torque value. Safety with new cotter pins
(17).

(f) Install the clamps (28) on the power or fuel-feather cables

(11).

(g) Attach the clamps (28) with the screws (25) and washers (26)
on the support assemblies (27).

(2) Control items from the Mechanical Fuel Control Unit (MFCU) to the
Propeller Valve Module (PVM).

(a) Engage the fork-end of the rod assembly (6) to the MFCU and
PVM ends. Attach them with the bolts (4), washers (5) and
(3) and nuts (2). Torque the nuts to the standard value.
Safety with new cotter pins (1).

E. Test

(1) Do the adjustment/test procedure of the power and fuel-feather

controls system (Ref. 76-11-00, P. Block 501).

(2) Do the close-up procedure.

(3) Do the power plant test (Ref. 71-00-00, P. Block 501).

Effectivity: See TOC CONFIG. 1

76-11-64 Pag. 406
May 31/03
 C-295 MAINTENANCE MANUAL

F. Close-Up

(1) Remove all tools and equipment from the work area. Make sure that
the work area is clean.

(2) Install the left and right door cowlings

(Ref. 71-11-13, P. Block 401).

(3) Install the rear and forward center cowlings in the right side
(Ref. 71-11-12, P. Block 401).

(4) Remove the servicing platform.

(5) Remove the safety clips and tags. Close the KA1 circuit breaker.

(6) Remove the warning notices.

Effectivity: See TOC CONFIG. 1

76-11-64 Pag. 407
May 31/03
 C-295 MAINTENANCE MANUAL

INTENTIONALLY LEFT BLANK

Effectivity: See TOC CONFIG. 1

76-11-64 Pag. 408
May 31/03
 C-295 MAINTENANCE MANUAL
LEVER ASSEMBLY

REMOVAL/INSTALLATION

WARNING: AFTER THE REMOVAL, ADJUSTMENT OR REPLACEMENT OF AN ENGINE

COMPONENT, FULLY EXAMINE THE WORK AREA TO MAKE SURE THAT:
- NO DISTORTION, TOOLS, UNWANTED MATERIALS OR OTHER LOOSE OBJECTS
PREVENT THE CORRECT MOVEMENT OR SAFE OPERATION OF THE SYSTEM
- THE SYSTEMS AND INSTALLATIONS IN THE WORK AREA ARE CLEAN.

WARNING: AFTER THE REMOVAL, ADJUSTMENT, OR REPLACEMENT OF A COMPONENT OF A

PRIMARY OR RELATED SYSTEM, FULLY EXAMINE THE COMPONENTS FOR:
- THE SAFETY OF THE LOCKING DEVICES
- THE FULL AND FREE MOVEMENT IN THE CORRECT DIRECTION
- THE TENSION.

WARNING: PUT WARNING NOTICES IN THE FLIGHT COMPARTMENT BEFORE YOU START THE
MAINTENANCE WORK ON THE ENGINE CONTROL SYSTEMS. THIS WILL PREVENT
THE ACCIDENTAL CONTROL LEVERS OPERATION.

1. Reason for the Job

To remove and install the power and fuel-feather control levers when they
are unserviceable or to get access to other components.

2. Equipment and Material

ITEM DESIGNATION

A. - Warning Notices
B. MS24665-153 Cotter Pin
C. - Storage Bag
D. ITEM 20-15-01 Circuit Breaker Safety Clips and Tags

Referenced Procedures:

- 06-41-53, P. Block 1 - Access Provisions - Fuselage

- 21-11-00, P. Block 501 - Compression System
- 25-11-11, P. Block 401 - Pilot and Copilot Seats
- 31-52-00, P. Block 501 - Unsafe Takeoff Warning System
- 61-21-00, P. Block 501 - Propeller Controlling
- 71-00-00, P. Block 501 - Power Plant

Effectivity: See TOC CONFIG. 1

76-11-65 Pag. 401
May 31/03
 - 76-11-00, P. Block 501 - Power and Fuel-Feather Controls System

C-295 MAINTENANCE MANUAL

3. Procedure

A. Job Set-Up

(1) Open, safety and tag these circuit breakers:

PANEL SERVICE FIN

SYSTEMS 1 START KA1

SYSTEMS 1 FTHR KC5
SYSTEMS 1 WARNING 1 QB47
SYSTEMS 2 CAB PRESS HE1
SYSTEM 2 FTHR KC4

(2) Remove the pilot and copilot seats (Ref. 27-11-11, P. Block 401).

(3) Remove the lateral panels from the center console, to get access
to the lever arms (Ref. 06-41-53, P. Block 1).

(4) Keep the screws in a storage bag for the subsequent installation.

(5) Put warning notices in the correct position to prevent:

- The accidental operation of the engines
- The movement of the power and fuel-feather control levers.

B. Removal (Fig. 401)

(1) Remove and discard the cotter pins (1).

(2) Remove the nuts (2) and washers (3).

(3) Remove the nuts (4), screws (5) and washers (6), which attach the
lever assembly to the aircraft.

(4) Remove the support assemblies (7) from the lever assembly.

(5) Remove the bushings (8), twin lever assemblies (9), spacers (10),
twin lever assemblies (11), spacers (12) and shaft (13).

(6) Remove the support assemblies (14) from the aircraft.

(7) Keep all removed attachment items in a storage bag.

Effectivity: See TOC CONFIG. 1

76-11-65 Pag. 402
May 31/03
 C-295 MAINTENANCE MANUAL
Lever Assembly

EM1.76.11.65.4AO.00.01-00

Fig. 401 Lever Assembly

Effectivity: See TOC CONFIG. 1

76-11-65 Pag. 403
May 31/03
 C-295 MAINTENANCE MANUAL

C. Preparation for Installation (Fig. 401)

(1) Examine the support assemblies (7) and (14) and twin lever
assemblies (9) and (11) for signs of damage or corrosion.

(2) Clean and examine the installation area and the replacement
components.

D. Installation (Fig. 401)

(1) Install the shafts (13) on the support assemblies (14).

(2) Install the spacers (12), twin lever assemblies (11), spacers
(10), twin lever assemblies (9) and bushings (8) on the shafts
(13).

(3) Install the support assemblies (7).

(4) Install the washers (3) and nuts (2). Safety the nuts (2) with
new cotter pins (1).

(5) Put the lever assemblies on the aircraft in the correct position.
Attach them with washers (6), screws (5) and nuts (4).

E. Test

(1) Do the adjustment/test procedure of the power and fuel-feather

controls (Ref. 76-11-00, P. Block 501).

(2) Do the adjustment/test procedure of the power plant

(Ref. 71-00-00, P. Block 501).

(3) Do the adjustment/test procedure of the compression system

(Ref. 21-11-00, P. Block 501).

(4) Do the adjustment/test procedure of the unsafe takeoff warning

system (Ref. 31-52-00, P. Block 501).

(5) Do the adjustment/test procedure of the propeller controlling

(Ref. 61-21-00, P. Block 501).

Effectivity: See TOC CONFIG. 1

76-11-65 Pag. 404
May 31/03
 C-295 MAINTENANCE MANUAL

F. Close-Up

(1) Install the lateral panels on the center console

(Ref. 06-41-53, P. Block 1).

(2) Install the pilot and copilot seats

(Ref. 25-11-11, P. Block 401).

(3) Remove all tools and equipment from the work area. Make sure that
the work area is clean.

(4) Remove the warning notices.

Effectivity: See TOC CONFIG. 1

76-11-65 Pag. 405
May 31/03
 C-295 MAINTENANCE MANUAL

INTENTIONALLY LEFT BLANK

Effectivity: See TOC CONFIG. 1

76-11-65 Pag. 406
May 31/03
 C-295 MAINTENANCE MANUAL
PULLEY ASSEMBLY

REMOVAL/INSTALLATION

WARNING: AFTER THE REMOVAL, ADJUSTMENT OR REPLACEMENT OF AN ENGINE

COMPONENT, FULLY EXAMINE THE WORK AREA TO MAKE SURE THAT:
- NO DISTORTION, TOOLS, UNWANTED MATERIALS OR OTHER LOOSE OBJECTS
PREVENT THE CORRECT MOVEMENT OR SAFE OPERATION OF THE SYSTEM
- THE SYSTEMS AND INSTALLATIONS IN THE WORK AREA ARE CLEAN.

WARNING: AFTER THE REMOVAL, ADJUSTMENT, OR REPLACEMENT OF A COMPONENT OF A

PRIMARY OR RELATED SYSTEM, FULLY EXAMINE THE COMPONENTS FOR:
- THE SAFETY OF THE LOCKING DEVICES
- THE FULL AND FREE MOVEMENT IN THE CORRECT DIRECTION
- THE TENSION.

WARNING: PUT WARNING NOTICES IN THE FLIGHT COMPARTMENT BEFORE YOU START THE
MAINTENANCE WORK ON THE ENGINE CONTROL SYSTEMS. THIS WILL PREVENT
THE ACCIDENTAL CONTROL LEVERS OPERATION.

1. Reason for the Job

To remove and install the pulley assembly when it is unserviceable or to

get access to other components.

2. Equipment and Material

ITEM DESIGNATION

A. - Warning Notices
B. MS24665-151 Cotter Pin
C. - Rigging Pin, 4,65 mm (0,183 in)
D. MS20995C32 Stainless Steel Lockwire, 0,81 mm (0,032 in)

Referenced Procedure:

- 25-86-61, P. Block 401 - Flight Compartment Ceiling Panels

- 76-11-00, P. Block 501 - Power and Fuel-Feather Controls System

Effectivity: See TOC CONFIG. 1

76-11-66 Pag. 401
May 31/03
 C-295 MAINTENANCE MANUAL

3. Procedure

A. Job Set-Up

(1) Remove the flight compartment ceiling panels

(Ref. 25-86-61, P. Block 401).

(2) Put warning notices in the correct position to prevent:

- The accidental operation of the engines
- The movement of the power and fuel-feather control levers.

B. Removal (Fig. 401)

NOTE: The two pulley assemblies are the same. Thus, this procedure
gives the removal of one of them.

(1) Move the power/fuel-feather lever as necessary to install the

rigging pin (1) through the pulley (2).

NOTE: With the rigging pin (1) installed, do not move the
power/fuel-feather lever until the replacement components
are installed and adjusted.

(2) Remove and discard the cotter pin (12).

(3) Remove and discard the lockwire from the screws (3) and (9).

(4) Remove the quick release clamp (8).

(5) Remove the cable (7) from the pulley assembly (2).

(6) Remove the screws (3) and washers (4).

(7) Remove the pulley assembly (2) from the aircraft.

(8) Remove the nut (13) and washer (11). Remove the plate (14) from
the pulley assembly (10). Remove the pulley (10).

(9) Remove the nuts (5), washers (6) and screws (9).

(10) Remove the shaft (15) from the aircraft.

C. Preparation for Installation (Fig. 401)

(1) Clean and examine the installation area and replacement

component.

Effectivity: See TOC CONFIG. 1

76-11-66 Pag. 402
May 31/03
 C-295 MAINTENANCE MANUAL
Pulley Assembly

EM1.76.11.66.4AO.00.01-00

Fig. 401 Pulley Assembly

Effectivity: See TOC CONFIG. 1

76-11-66 Pag. 403
May 31/03
 C-295 MAINTENANCE MANUAL

(2) Examine the pulley assemblies for signs of damage or corrosion.

D. Installation (Fig. 401)

(1) Put the pulley assembly (2) in the correct position on the
support (16). Attach it with the washers (4) and screws (3).
Torque the screws to the standard value. Safety them with new
lockwire.

(2) Connect the cable (7) to the pulley assembly (2) with the quick
release clamp (8).

(3) Put the shaft (15) in the correct position on the support (16).
Attach it with the screws (9), washers (6) and nuts (5). Torque
the nuts to the standard value. Safety the screws (9) with new
lockwire.

(4) Attach the pulley (10) to the shaft (13) with the nut (13).

(5) Safety the nut (13) with a new cotter pin (12).

(6) Remove the rigging pin (1).

E. Test

(1) Do the adjustment/test procedure of the power and fuel-feather

controls system (Ref. 76-11-00, P. Block 501).

F. Close-Up

(1) Install the flight compartment ceiling panels

(Ref. 25-86-61, P. Block 1).

(2) Remove the warning notices.

(3) Remove all tools and equipment from the work area. Make sure that
the work area is clean.

Effectivity: See TOC CONFIG. 1

76-11-66 Pag. 404
May 31/03
 C-295 MAINTENANCE MANUAL
SUPPORT ASSEMBLY

REMOVAL/INSTALLATION

WARNING: AFTER THE REMOVAL, ADJUSTMENT OR REPLACEMENT OF AN ENGINE

COMPONENT, FULLY EXAMINE THE WORK AREA TO MAKE SURE THAT:
- NO DISTORTION, TOOLS, UNWANTED MATERIALS OR OTHER LOOSE OBJECTS
PREVENT THE CORRECT MOVEMENT OR SAFE OPERATION OF THE SYSTEM
- THE SYSTEMS AND INSTALLATIONS IN THE WORK AREA ARE CLEAN.

WARNING: AFTER THE REMOVAL, ADJUSTMENT, OR REPLACEMENT OF A COMPONENT OF A

PRIMARY OR RELATED SYSTEM, FULLY EXAMINE THE COMPONENTS FOR:
- THE SAFETY OF THE LOCKING DEVICES
- THE FULL AND FREE MOVEMENT IN THE CORRECT DIRECTION
- THE TENSION.

WARNING: PUT WARNING NOTICES IN THE FLIGHT COMPARTMENT BEFORE YOU START THE
MAINTENANCE WORK ON THE ENGINE CONTROL SYSTEMS. THIS WILL PREVENT
THE ACCIDENTAL CONTROL LEVERS OPERATION.

1. Reason for the Job

To remove and install the pulleys support assembly (in the center wing)
when it is unserviceable or to get access to other components.

2. Equipment and Material

ITEM DESIGNATION

A. - Warning Notices
B. - Servicing Platform
C. - Rigging Pin, 4,65 mm (0,183 in)
D. MS20995C20 Stainless Steel Lockwire, 0,51 mm (0,020 in)

Referenced Procedures:

- 06-41-57, P. Block 1 - Access Provisions - Wings

- 76-11-00, P. Block 501 - Power and Fuel-Feather Controls System

Effectivity: See TOC CONFIG. 1

76-11-67 Pag. 401
May 31/03
 C-295 MAINTENANCE MANUAL

3. Procedure

A. Job Set-Up

(1) Put the servicing platform in the correct position.

(2) Remove the access panels from the center wing leading edge
(Ref. 06-41-57, P. Block 1).

(3) Put warning notices in the correct position to prevent:

- The accidental operation of the engines
- The movement of the power and fuel-feather control levers.

B. Removal (Fig. 401)

NOTE: The two support assemblies are the same. Thus, this procedure
gives the removal of one of them.

(1) Move the power/fuel-feather levers as necessary, to install the

rigging pin (1) through the pulley (2).

NOTE: With the rigging pin (1) installed, do not move the
power/fuel-feather lever until the replacement components
are installed and adjusted.

(2) Remove the screws (7) and washers (6). Remove the pulley
assemblies (2).

(3) Remove the screws (4) and washers (3). Remove the support (5)
from the aircraft.

C. Preparation for Installation (Fig. 401)

(1) Clean and examine the installation area and the replacement
component.

(2) Examine the support (5) for signs of damage or corrosion.

D. Installation (Fig. 401)

(1) Put the support (5) in the correct position on the front spar.
Attach it with the washers (3) and screws (4). Torque the screws
to the standard value.

Effectivity: See TOC CONFIG. 1

76-11-67 Pag. 402
May 31/03
 C-295 MAINTENANCE MANUAL
Support Assembly

EM1.76.11.67.4AO.00.01-00

Fig. 401 Support Assembly

Effectivity: See TOC CONFIG. 1

76-11-67 Pag. 403
May 31/03
 C-295 MAINTENANCE MANUAL

(2) Put the pulley assemblies (2) in the correct position on the
support (5). Attach them with the washers (6) and screws (7).
Torque the screws (7) to the standard value. Safety the screws
wit new lockwire.

(3) Remove the rigging pin (1).

E. Test

(1) Do the adjustment/test procedure of the power and fuel-feather

controls system (Ref. 76-11-00, P. Block 501).

F. Close-Up

(1) Install the access panels removed on the center wing leading edge
(Ref. 06-41-57, P. Block 1)

(2) Remove the servicing platform.

(3) Remove the warning notices.

(4) Remove all tools and equipment from the work area. Make sure that
the work area is clean.

Effectivity: See TOC CONFIG. 1

76-11-67 Pag. 404
May 31/03
 C-295 MAINTENANCE MANUAL
BETA LOCKOUT SYSTEM

DESCRIPTION/OPERATION

1. General

In the landing, when the aircraft is on ground, power levers can go back
below the flight idle (FI) position, but with the triggers lifted. In this
PL's position, below the FI, the EPC changes the operation from the power
adjustment mode to the beta mode. In this mode, the system lets the
reverse operation.

The control quadrant ZD133 has a solenoid that locks the power levers
(PL's) in the FI position. This prevents the accidental operation of the
PL's positions below the FI when the aircraft is in flight.

The Beta Lockout System (BLS) lets the pilot set the PL´s positions below
the FI position in these conditions:
- When the aircraft is on ground, with the automatic operation of the
related weight-on-wheel microswitch.
- In the landing, immediately after the aircraft touchdown, with the
automatic operation of the reverse control unit. In this condition, the
operation of the related weight-on-wheel microswitch is possibly not
stable.
- When the aircraft is on ground and the related weight-on-wheel
microswitch is defective, with the manual operation of the BETA
LOCKOUT/OVRD lighted switch.

With the BLS de-energized, the status white indicator (UNLOCK) comes on.
These indicators are in the front of each pilot, in the left and right
instruments panels. They can operate independently of the flight phase
(the aircraft in flight or on ground). The indicators operate because of a
BLS position indicator on the control quadrant. The switch is mechanically
connected to the position of the BLS lock rod.

The BLS de-energizes, with the aircraft in flight or on ground, when you
push the BETA LOCKOUT/OVRD pushbutton. With the BLS de-energized, the
system connects again if you push this pushbutton.

When you push the BETA LOCKOUT/OVRD pushbutton to de-energize the BLS, the
IEDS receives a signal and its non-volatile memory keeps it. At the end of
the flight, when the engines stop, the IEDS display shows the NEW
EXCEEDANCE message. This is necessary for the maintenance personnel to
examine the exceedances in the IEDS maintenance section. The IEDS
maintenance section includes a BLS disconnected message. The crew cannot
set it again.

Effectivity: See TOC CONFIG. 1

76-14-00 Pag. 1
May 31/03
 C-295 MAINTENANCE MANUAL

2. Component Location (Fig. 1)

ITEM FIN DESIGNATION ZONE ACCESS REFERENCE

PANEL

1. ZD133 Control Quadrant 213 - 76-11-51

BETA LOCKOUT/OVRD
Lighted Switch
2. KB48 Reverse Control Unit 151 251BF 61-26-31
3. KB60 Relay 151 251BF 76-14-51
4. PC13 SYSTEMS 1 Circuit 217 - 24-61-11
Breaker Panel
KB21 WARN 1 Circuit 217 - 24-61-11
Breaker
5. PC12 SYSTEMS 2 Circuit 217 - 24-61-11
Breaker Panel
FD31 WARN 2 Circuit 217 -
Breaker
6. ZD4 BETA UNLKD Right 217 -
Lighted Switch
7. ZD3 BETA UNLKD Left 217 -
Lighted Switch
8. ZD117 ICE PROTECTION 217 - 30-11-11
Control Unit
HB51 Relay

3. Description

The BLS has these components:

- The PL´s lock solenoid that is a part of the control quadrant, ZD133
- The BETA LOCKOUT/OVRD lighted switch that is a part of the control
quadrant, ZD133
- The reverse control unit, KB48, installed below the main compartment
floor, between the STA 12248 and STA 12756
- The relay, KB60, installed below the main compartment floor, between the
STA 12248 and STA 12756
- The relay, HB51, installed in the ICE PROTECTION control unit, ZD117.

Effectivity: See TOC CONFIG. 1

76-14-00 Pag. 2
May 31/03
 C-295 MAINTENANCE MANUAL
Beta Lockout System - Component Location

EM1.76.14.00.0AO.00.01-00

Fig. 1 Beta Lockout System - Component Location

Effectivity: See TOC CONFIG. 1

76-14-00 Pag. 3
May 31/03
 C-295 MAINTENANCE MANUAL
The 28VDC power supplies to the circuit are from:
- The BAT BUS 1 through the ICE PROTECTION/PROP circuit breaker, HB1,
installed on the SYSTEMS 1 circuit breakers panel, PC13.
- The GEN BUS 2 through the WARN 2 circuit breaker, FD31, installed on the
SYSTEMS 2 circuit breakers panel, PC12.

Also the circuit uses different signals from the antiskid system for the
operation.

4. Component Description

A. Control Quadrant, ZD133

The control quadrant, ZD133, has the PL´s lock solenoid and the BETA
LOCKOUT/OVRD lighted switch.

(1) PL´s Lock Solenoid

The PL´s lock solenoid is on the left lateral of the control

quadrant, ZD133.

The function of the PL´s lock solenoid is to prevent the PL´s

selection below the FI position during the flight aircraft
condition.

When the aircraft is in flight, the PL´s lock solenoid receives a

28VDC supply. This 28VDC supply operates the solenoid, which
prevent the accidental selection of the PL´s to the GI or REV
position.

(2) BETA LOCKOUT/OVRD Lighted Switch

The BETA LOCKOUT OVRD lighted switch is on the front panel of the
control quadrant ZD133. It is a pushbutton switch with two
circuits and two positions, and with the OVRD caption.

The function of the BETA LOCKOUT/OVRD lighted switch is to

override manually the operation of the PL's lock solenoid.

B. Reverse Control Unit, KB48

(1) Description

The reverse control unit, KB48, is a light aluminum alloy casing

with a 19-pin circular electrical connector installed on one
side. For more data about the description of the reverse control
unit (Ref. 61-26-00, P. Block 1).

Effectivity: See TOC CONFIG. 1

76-14-00 Pag. 4
May 31/03
 C-295 MAINTENANCE MANUAL

(2) Operation

The functions of the reverse control unit KB48 are these:

- To override automatically the operation of the PL's lock
solenoid when the wheels turn speed is equal to or more than
540 rpm. This applies immediately after the aircraft touchdown.
- To let, with the relay KB60 energized, the 28VDC supply to the
PL's lock solenoid in all other conditions different to those
given
- To supply the 28VDC to the Stall Warning Circuit in the takeoff
when the wheels turn speed is equal to or more than 540 rpm.
For more data about the operation of the reverse control unit
(Ref. 61-26-00, P. Block 1).

5. Operation (Fig. 2)

The 28VDC electrical power supplies for the circuit are from:
- The GEN BUS 1 through the WARN 1 circuit breaker, KB21
- The GEN BUS 2 through the WARN 2 circuit breaker, FD31.

The filter KB56 gives a filter to the 28VDC from GEN BUS 1 supplied to the
reverse control unit, KB48 (Ref. 61-26-00, P. Block 1).

When the aircraft is in flight, the Weight-On-Wheels microswitch, HB17,

closes its contacts. Then, it connects the 28VDC from the BAT BUS 1 to the
coil of the relay HB51 (Ref. 61-26-00, P. Block 1).Thus, the 28VDC from
GEN BUS 1 goes to the PL's lock solenoid through:
- The closed pins of the operated relay KB60
- The closed pins of the operated relay HB51, and
- The closed pins of the BETA LOCKOUT OVRD lighted switch.

In this condition, the operated PL's lock solenoid prevents the accidental
selection of the PL's positions below FI (GI or REV).

Effectivity: See TOC CONFIG. 1

76-14-00 Pag. 5
May 31/03
 C-295 MAINTENANCE MANUAL
Beta Lockout System - Operation and Interfaces

EM1.76.14.00.0BO.01.01-00

Fig. 2 Beta Lockout System - Operation and Interfaces (Sheet 1 of 2)

Effectivity: See TOC CONFIG. 1

76-14-00 Pag. 6
May 31/03
 C-295 MAINTENANCE MANUAL

EM1.76.14.00.0BO.02.01-00

Fig. 2 Beta Lockout System - Operation and Interfaces (Sheet 2 of 2)

Effectivity: See TOC CONFIG. 1

76-14-00 Pag. 7
May 31/03
 C-295 MAINTENANCE MANUAL
The operation of the PL's lock solenoid can be manually and automatically
overridden.

A. Manually Overridden Operation of the PL's Lock Solenoid

The BETA LOCKOUT OVRD lighted switch manually overrides the operation
of the PL's lock solenoid. With the BETA LOCKOUT OVRD lighted switch
pushed:
- The OVRD caption comes on
- The PL's lock solenoid de-energizes.

When you push the BETA LOCKOUT/OVRD pushbutton to de-energize the

BLS, the IEDS receives a signal and its non-volatile memory keeps it.
At the end of the flight, when the engines stop, the IEDS display
shows the NEW EXCEEDANCE message. This is necessary to examine the
exceedances in the IEDS maintenance section for the maintenance
personnel. The IEDS maintenance section includes a BLS disconnected
message that the crew cannot set again.

B. Automatically Overridden Operation of the PL's Lock Solenoid

The operation of the reverse control unit KB48, or the

Weight-On-Wheels microswitch, HB17, automatically overrides the
operation of the PL's lock solenoid (Ref. 61-26-00, P. Block 1).

Effectivity: See TOC CONFIG. 1

76-14-00 Pag. 8
May 31/03
 C-295 MAINTENANCE MANUAL
BETA LOCKOUT SYSTEM

TROUBLESHOOTING

WARNING: MAKE SURE THAT YOU ISOLATE ALL THE CIRCUITS IN MAINTENANCE BEFORE
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

1. General

The BLS troubleshooting procedures are in the Reverse Control System

(Ref. 61-26-00, P. Block 101). This chapter does the system
troubleshooting in these conditions:
- Aircraft on ground
- Aircraft in flight.

A. Aircraft on ground

The troubleshooting flow charts in this condition give a list of

possible failures of the system components for this fault:
- It is not possible to set the Power Levers (PL´s) below the FI
position.

A logic list gives the possible failures of the system components

with the applicable solution to each.

B. Aircraft in flight

The troubleshooting flow charts in this condition give a list of

possible failures of the system components for this fault:
- It is possible to set the Power Levers (PL´s) below the FI position
(flight idle).

A logic list gives the possible failures of the system components

with the applicable solution to each.

2. Reference Procedures

- 61-26-00, P. Block 101 - Reverse Control System

Effectivity: See TOC CONFIG. 1

76-14-00 Pag. 101
May 31/03
 C-295 MAINTENANCE MANUAL

INTENTIONALLY LEFT BLANK

Effectivity: See TOC CONFIG. 1

76-14-00 Pag. 102
May 31/03
 C-295 MAINTENANCE MANUAL
BETA LOCKOUT SYSTEM

ADJUSTMENT/TEST

WARNING: MAKE SURE THAT YOU ISOLATE ALL THE CIRCUITS IN MAINTENANCE BEFORE
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

WARNING: MAKE SURE THAT WARNING NOTICES ARE IN THE CORRECT POSITION TO TELL
PERSONNEL THAT YOU WILL DO A MAINTENANCE TASK

1. Functional Test of the Beta Lockout System (BLS)

A. Reason for the Job

To make sure that all the components of the BLS operate correctly.

B. Equipment and Material

ITEM DESIGNATION

(1) - Warning Notices

(2) ITEM 32-42-09 Wheel Turn Test Unit
(3) ITEM 10-00-09 Safety Pin for Main Landing Gear
(4) ITEM 20-15-01 Circuit Breaker Safety Clips and Tags

Referenced Procedures:

- 24-40-00, P. Block 201 - External Power

- 31-61-00, P. Block 501 - Multifunction Display System (MFDS)
- 32-31-00, P. Block 1 - Normal Extension and Retraction
- 32-41-11, P. Block 401 - Transducer GB11 (GB10), GB13 (GB12)
- 32-42-00, P. Block 1 - Braking

C. Procedure

(1) Job Set-Up

(a) Put warning notices in the correct position to tell

personnel that you will do a maintenance task.

(b) Make sure that the landing gear selector lever is set to the
DOWN position (Ref. 32-31-00, P. Block 1).

(c) Install the safety pins of the landing gear.

Effectivity: See TOC CONFIG. 1

76-14-00 Pag. 501
May 31/03
 C-295 MAINTENANCE MANUAL

(d) Connect the GPU. Set the aircraft electrical system to ON

(Ref. 24-40-00, P. Block 201).

(e) Connect the GEN and BAT No. 1 and No. 2 bus-bar
distribution.

(f) Close these circuit breakers:

PANEL SERVICE FIN

L MISCELLANEOUS ANTI-SKID GB1

R MISCELLANEOUS ANTI-SKID GB2
R MISCELLANEOUS WARNING SYS WA1
SYSTEMS 1 WARNING 1 QB47
SYSTEMS 2 WARNING 2 XA2
SYSTEMS 2 WARNING SYS WA2
SYSTEMS 2 LDG GR POSN DJ1

(g) Remove the covers from the wheel speed drive transducers
GB13 and GB12 of the left and right main landing gear
(Ref. 32-41-11, P. Block 401).

(h) Connect the wheel turn test unit to the wheel speed drive
transducers GB13 and GB12.

(j) Set the four weight-on-wheels (WOW) microswitches of the

left and right main landing gear (MLG) to the ground
position (disconnected).

(k) On the wheel turn test unit, set the MAINS switch to the OFF
position.

(l) On the wheel turn test unit, set the PORT wheel DRIVE switch
to the OFF position.

(m) On the wheel turn test unit, set the STB'D wheel DRIVE
switch to the OFF position.

(n) On the wheel turn test unit, turn the SPEED controls fully
counterclockwise.

(p) On the wheel turn test unit, set the MAINS switch to the ON
position.

Effectivity: See TOC CONFIG. 1

76-14-00 Pag. 502
May 31/03
 C-295 MAINTENANCE MANUAL

(q) On the wheel turn test unit, set the DISPLAY CHECK switch to
the CHECK position (PORT and STB´D DRIVE switches to the ON
position). Make sure that the RPM indicator shows all the
numbers 8.

(2) Test

ACTION RESULT

(a) Make sure that the The FAIL and DEGRADE

weight-on-wheels (WOW) captions, of the antiskid
microswitch, HB17, on the system, come on.
left MLG is in the ground
position (disconnected).

(b) On the center console, set The FAIL and DEGRADE

the antiskid switch GB4 to captions, of the antiskid
the ON position system, go off.
(Ref. 32-42-00, P. Block 1).

(c) Make sure that the BETA The amber lights of BLS
LOCKOUT/OVRD lighted switch status, on the left and right
is not pushed and is off. instrument panels, are on and
This lighted switch is on the show BETA UNLKD.
control quadrant of the
center console.

(d) Move the Power Levers (PL) The PL´s go to the MAX AUTO
fully forward. Then, fully position, and then to the
rearward. FULL REV position.

(e) Set the PL´s to the FI

(flight idle) position.

(f) Set the WOW microswitch, The amber lights of BLS

HB17, on the left rear MLG to status, on the left and right
the flight position instrument panels, go off.
(connected).

(g) Move the PL´s as far rearward You can not move rearward the
as possible. PL´s below the FI position.

Effectivity: See TOC CONFIG. 1

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May 31/03
 C-295 MAINTENANCE MANUAL
ACTION RESULT

(h) On the control quadrant, push The amber lights of BLS

the BETA LOCKOUT/OVRD lighted status, on the left and right
switch. instrument panels, come on
and show BETA UNLKD. On the
control quadrant, the BETA
LOCKOUT/OVRD lighted switch
comes on.

(j) Move the PL´s as far rearward You can not move rearward the
as possible. PL´s below the FI position to
the FULL REV position.

(k) Set the PL´s to a position

above the FI position.

(l) On the control quadrant, push The amber lights of BLS

the BETA LOCKOUT/OVRD lighted status, on the left and right
switch. instrument panels, go off. On
the control quadrant, the
BETA LOCKOUT/OVRD lighted
switch goes off.

(m) Move the PL´s as far rearward You can not move rearward the
as possible. PL´s below the FI position.

(n) On the wheel turn test unit, The amber lights of BLS
do this task: status, on the left and right
instrument panels, come on
- Set the SPEED control for and show BETA UNLKD. You can
the PORT and STARBOARD not move the PL´s below the
wheels to 540 ±25 RPM. FI position to FULL REV
position.

(p) On the wheel turn test unit, The amber lights of BLS
do this task: status, on the left and right
instrument panels, go off.
- Turn the SPEED control for You can not move the PL´s
the PORT and STARBOARD below the FI position.
wheels fully
counterclockwise to show 0
RPM.

Effectivity: See TOC CONFIG. 1

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 C-295 MAINTENANCE MANUAL
ACTION RESULT

(r) Set the WOW microswitch, The amber lights of BLS

HB17, on the left rear MLG to status, on the left and right
the ground position instrument panels, come on
(disconnected). and show BETA UNLKD. You can
not move the PL´s below the
FI position to FULL REV
position.

(s) On the center console, set The FAIL and DEGRADE

the anti-skid switch, GB4, to captions, of the antiskid
the OFF position system, come on.
(Ref. 32-42-00, P. Block 1).

(t) Do a check that the IEDS of

the indicated engine has
recorded that you pushed the
BETA LOCKOUT/OVRD lighted
switch
(Ref. 31-61-00, P. Block 501)

(u) Start again the IEDS

(Ref. 31-61-00, P. Block 501)

(3) Close-Up

(a) On the wheel turn test unit, set the PORT and STARBOARD
wheel DRIVE switches to the OFF position.

(b) On the wheel turn test unit, set the MAINS switch to the OFF
position.

(c) Disconnect the wheel turn test unit from the wheel speed
drive transducers GB13 and GB12.

(d) Install the covers on the wheel speed drive transducers,

GB13 and GB12, of the left and right MLG
(Ref. 32-41-11, P. Block 401).

(e) Disconnect the GEN and BAT No. 1 and No. 2 bus-bar
distribution.

Effectivity: See TOC CONFIG. 1

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May 31/03
 C-295 MAINTENANCE MANUAL

(f) Set the aircraft electrical system to OFF. Disconnect the

GPU (Ref. 24-40-00, P. Block 201).

(g) Remove the warning notices.

(h) Remove all tools and equipment from the work area. Make sure
that the work area is clean.

Effectivity: See TOC CONFIG. 1

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May 31/03