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Extra 500. Maintenance Manual (2012) - page 10

30-20-00

AIR INTAKES

Description

The EXTRA 500 is equipped with an exhaust heated engine inlet. Pulling the

INTAKE ANTI ICE Bowden cable opens the “ashtray” in the LH exhaust stack

which routes hot exhaust air into the double walled engine air inlet. The air

flows out on the RH side to the RH exhaust stack.

Pulling the Bowden cable will also throw a microswitch on the LH exhaust

stack to illuminate the INTAKE HEAT safe operation light and to activate the

engine compressor inlet anti ice system

(Rolls Royce

250-B17F Series

Operation and Maintenance Manual, LOAP 1).

30-20-01

Bowden Cable

The Engine anti-ice Bowden cable is installed in the middle console in the

cockpit and goes through the front pressure bulkhead/firewall to the LH engine

exhaust stack in the engine compartment.

Removal/Installation

Detail Steps/Work Items

Key Items

1

Remove LH upper cowling.

Refer to Chapter 71-10-01.

2

Disconnect cable of Bowden cable on LH

exhaust stack.

3

Disconnect Jacket of Bowden cable on LH

exhaust stack.

4

Disconnect any tie-raps in engine

compartment that hold the Bowden cable.

5

Remove upper paneling part of middle

Refer to Chapter 25-10-26.

console in which the Bowden cable holding

plate is mounted.

NOTE

Do not pull the cable from the jacket. There is a very small metal ball

that will fall out.

6

Remove Bowden cable from mounting

plate.

7

With a firm pull, break the pressure

cabin/firewall sealing and remove Bowden

cable.

8

Install in reverse sequence of removal.

Page Date:

30 Page 15

Detail Steps/Work Items

Key Items

Refer to Product Label and Material Safety Data Sheet for health and

WARNING

safety information before using PR812.

9

Seal the Bowden cable from the firewall

side with PR812

PR 1750 accelerator contains harmful vapors and is readily absorbed

WARNING

through the skin.

Avoid all contact with the skin and ingestion.

Always wash hands before eating or smoking.

Use adequate ventilation, hand protection and chemical-type goggles

when working with this product.

If accelerator contacts skin, flush area with warm water. Obtain medical

attention in cases of extreme exposure or ingestion.

PR 1750 sealant contains solvents.

WARNING

Use adequate ventilation or air-supplied respirators during application.

Avoid repeated or prolonged breathing of vapors.

In case of extreme vapor exposure, remove affected personnel to fresh

air immediately and obtain medical attention.

For complete health and safety information, a material safety data sheet

is available from the manufacturer.

10

Seal the Bowden cable from the inside with

For mixing and application of

PR 1750.

PR 1750 sealant refer to

manufacturer's instructions.

11

Rig the Bowden cable.

See paragraph Rigging below.

Rigging

Detail Steps/Work Items

Key Items

1

Remove the LH upper cowling to gain

Refer to Chapter 71-10-01.

access to the LH exhaust stack

2

Push the INTAKE ANTI ICE knob fully in.

3

Set the upper set screw that the ‘ashtray’ is

fully closed when the lever is set against it.

4

Clamp the Bowden cable jacket so the

jacket protrudes 4 mm +/- 1 mm from

clamp.

5

Attach cable to lever while lever is at upper

set screw.

6

Pull the INTAKE ANTI ICE knob fully out.

7

Make sure that the ‘ashtray’ is fully out.

20° travel

8

Set the lower set screw accordingly.

9

Perform micro switch rigging.

Refer to Subject 30-20-02.

Page 16 30

Page Date: 9. August 2013

30-20-02

Micro Switch

The engine anti-ice micro switch is located on the LH exhaust stack.

Removal/Installation

Detail Steps/Work Items

Key Items

1

Ensure BATT switch is OFF and no external

power connected.

2

Remove the LH upper cowling

Refer to Chapter 71-10-01.

3

Mark and cut wiring of the micro switch.

Connect later by splicing.

4

Remove micro switch.

2 screws

5

Install in reverse sequence of removal.

6

Perform micro switch rigging.

See paragraph Rigging below.

Rigging

Detail Steps/Work Items

Key Items

1

Remove the LH upper cowling

Refer to Chapter 71-10-01.

2

Pull the INTAKE ANTI ICE knob fully out.

3

Make sure the micro switch is activated,

loosen, adjust and retighten at set and/or

bend micro switch lever if needed.

30-20-03

Helical Metallic Hoses

There are two helical metallic hoses installed in engine compartment for

exhaust air routing from the LH exhaust stack to the inlet and from the inlet to

the RH exhaust stack

Removal/Installation

Detail Steps/Work Items

Key Items

1

Remove exhaust stacks

Refer to Ch. 78-00-01/02

2

Unscrew helical metallic hose from inlet

3

Install in reverse sequence of removal.

IMPORTANT

Make sure while setting the length of the helical metallic hose that the

forces on the engine flange while attaching the exhaust stack must be

minimal. Screw in the helical metallic hose minimum one full turn on

each side. Maximum two full turns each side are possible.

Page Date:

30 Page 17

30-30-00

PITOT, STATIC AND STALL WARNING

Description

The EXTRA 500 is equipped with two heated Pitot tubes, one underneath each

wing. Standard AN-type (AN 5812-1) Pitot tubes are used. The electric Pitot

heat is activated by switching the L-PITOT-R switches to the ON position. As

long as the aircraft is on ground the heating of the Pitot tubes is avoided by

means of a squat switch installed at the nose gear strut. To provide a means for

checking the system on ground the switches can be set to a momentary TEST

position to override the squat switch. Avoid operating the system in this mode

longer than 10 sec. on ground to avoid an overheat condition. The current

consumption of the heating elements is monitored by current sensors during

operation. If an open circuit causes the Pitot tube heaters to fail, the PITOT

HEAT LEFT/RIGHT illuminates in the annunciator panel.

The two dual static ports installed in the aft fuselage sides are equipped with

electric heater elements to prevent icing. They are also activated by the L-

PITOT-R switches. Heating is disabled on ground by means of a squat switch

and current sensors generate the STATIC HEAT LEFT/RIGHT annunciation in

case of malfunction. Temperature rise after activation of the test mode on

ground is much slower than for the Pitot heat. Be aware of this behavior when

checking the system on ground.

The Stall detector installed in the left wing leading edge within the access

panel for the recognition lights features three electric circuits for icing

protection. The movable sensing vane, the mounting plate and the case itself

are heated by electric heating elements. The heatings are activated by the

PITOT-R switch and protected by the squat switch against inadvertent operation

on ground. The TEST position of the switch overrides this protection to allow

system checks on the ground (time limited up to max. 10 sec). The main

heating circuits (vane and mounting plate) are monitored by a current sensor,

generating the STALL HEAT warning indication in the annunciator panel in case

of an open circuit.

NOTE

In case of defective Pitot tube, static port or stall detector heat elements,

the respective components have to be replaced as a whole

(refer to

Chapter 34-10).

30-30-01

Current Sensor (Avionic Bay)

Three current sensors are installed in the avionic bay and are accessible by the

LH avionic bay access panel. The sensors are labeled 3HG, 5HG and 7HG. The

following table shows to which systems they are related.

Label

System

3HG

Stall heat

5HG

Pitot heat RH

7HG

Pitot heat LH

Page 18 30

Page Date: 9. August 2013

Removal/Installation

Detail Steps/Work Items

Key Items

1

Ensure BATT switch is OFF and no external

power connected.

2

Remove LH avionic bay access panel.

Refer to Chapter 51-00-01.

3

Remove the wiring from the respective

current sensor.

4

Remove the mounting plate.

4 bolts

To get access to the underside

of the current sensor. Notice

ground bonding.

5

Remove current sensor.

2 bolts

6

Install in reverse sequence of removal.

Ensure mounting plate is

correctly grounded and cable

loom cable clamp is installed.

30-30-02

Current Sensor (Tail Cone)

Two current sensors are installed in the aircraft tailcone on the underside of the

air condition soft start module. The sensors are labeled 1HS and 4HS. The

following table shows to which systems they are related.

Label

System

1HS

Static heat RH

4HS

Static heat LH

Removal/Installation

Detail Steps/Work Items

Key Items

1

Ensure BATT switch is OFF and no external

power connected.

2

Remove tailcone access panel.

Refer to Chapter 51-00-01.

3

Remove the air condition soft start module.

Refer to Chapter 21-50-03

Disconnecting the electrical

wiring is not necessary.

4

Disconnect the electrical connector.

5

Remove the mounting plate.

4 bolts

5

Remove current sensor.

2 Allen screws

6

Install in reverse sequence of removal.

Ensure mounting plate is

correctly grounded.

Page Date:

30 Page 19

30-40-00

WINDSHIELD

An electric windshield heat for the pilot’s side of the windshield is part of the

standard icing protection system. Also refer to Chapter 56-10.

The system consists of three wire circuits bonded between the inner and outer

windshield layer, one for the heating itself and two for the redundant

temperature sensing. The heating current is switched by a special heat

controller regulating the windshield temperature between 20°C and 40°C in

case the system is active. The system may be activated by means of the

WINDSH switch located in the DEICE group within the left side panel. In case of

malfunction of the system, this condition is indicated by a red WINDSHIELD

HEAT FAIL annunciator light. The following failure conditions cause a warning

indication:

•

One or both temperature sensing circuits open or shorted

•

Overheat signal from at least one of the sensing circuits (more than 50°C)

An additional means for monitoring the function of the windshield is provided

by a green WINDSHIELD HEAT ON annunciator light (controlled by a current

sensor in the heating circuit) illuminating when the heating current flows. This

light is cycling during normal windshield heat operation.

The system remains operative (green light cycling) as long as one of the two

sensing circuits is functioning although the red WINDSHIELD HEAT FAIL

warning annunciates one defective temperature sensing circuit. If both sensing

circuits are defective the windshield controller inhibits any further windshield

heating.

30-40-01

Windshield Heat Controller

The windshield heat controller is installed beside the pilot seat, behind the

pilot’s legroom LH paneling.

Removal/Installation

Detail Steps/Work Items

Key Items

1

Ensure BATT switch is OFF and no external

power connected.

2

Remove pilot seat.

Refer to Chapter 25-10-11.

3

Remove all LH forward lower paneling

Refer to Chapter 25-00-01.

screws.

4

Carefully swivel the paneling forward to

gain access from behind.

5

Remove electrical connector.

6

Remove windshield heat controller.

2 nuts

7

Install in reverse sequence of removal.

Page 20 30

Page Date: 9. August 2013

30-40-02

Windshield Heat Current Sensor

The windshield heat current sensor is installed beside the pilot seat, behind the

pilot’s legroom LH paneling.

Removal/Installation

Detail Steps/Work Items

Key Items

1

Ensure BATT switch is OFF and no external

power connected.

2

Remove pilot seat.

Refer to Chapter 25-10-11.

3

Remove all LH forward lower paneling

Refer to Chapter 25-00-01.

screws.

4

Carefully swivel the paneling forward to

gain access from behind.

5

Remove electrical connections.

4 screws

6

Remove windshield heat current sensor

2 nuts

including mounting plate.

7

Remove current sensor from mounting plate.

2 bolts

8

Install in reverse sequence of removal.

Page Date:9. August 2013

30 Page 21

30-60-00

PROPELLER

Description

The propeller of the EXTRA 500 is equipped with electrically heated boots at

the blades for icing protection. All blades are heated continuously when

switched on. All necessary information for repair and maintenance of the

system is contained in BF Goodrich Aerospace publications as listed in the

LOAP 14-17.

30-60-01

Propeller Ammeter

The propeller ammeter is installed in the upper left corner of the instrument

panel.

Removal/Installation

Detail Steps/Work Items

Key Items

1

Remove RH and LH IFD.

Refer to Chapter 31-60-01.

2

Disconnect electrical connector ammeter.

3

Remove propeller ammeter.

4 screws

4

Install in reverse sequence of removal.

Page 22 30

Page Date: 9. August 2013

30-80-00

DETECTION

30-80-01

Ice Light

An ice light is installed on the forward left side of the fuselage. It is accessible

from inside the engine compartment when the LH upper cowling is removed.

Removal/Installation

Detail Steps/Work Items

Key Items

1

Ensure BATT switch is OFF and no external

power connected.

2

Remove upper LH cowling.

Refer to Chapter 71-10-01

3

Disconnect electrical connection.

4

Remove ice light cover and window.

3 bolts

5

Disassemble ice light.

4 bolts

6

Install in reverse sequence of removal

Page 24 30

Page Date: 9. August 2013

31-10-00

INSTRUMENT & CONTROL PANELS

31-10-01

Left Side Panel

Description

On the LH of the pilot, most of the switches and circuit breakers are installed in

a switch board assembly, the left side panel. This assembly contains all

electrical busses excluding the hot bus. This assembly can be taken out of the

aircraft as a whole.

Removal/Installation

Detail Steps/Work Items

Key Items

1

Ensure BATT switch is OFF and no external

power connected.

2

Remove pilot’s seat.

Refer to Chapter 25-10-11.

2

Remove left legroom side paneling.

Refer to Chapter 25-00-01.

3

Remove 6 screws of the upper part of the

2 screws on the top

left side panel.

4 screws on the side

4

Remove 3 screws of the lower part of the

left side panel.

5

Disconnect the 3 electrical connectors and

the power connector.

Take care not to damage luminescent foil connections

CAUTION

6

Remove the two parts of the left side panel.

7

Install in reverse sequence of removal.

31-10-02

Left Main Panel

Removal/Installation

Detail Steps/Work Items

Key Items

1

Remove IFDs.

Refer to Subject 31-60-01

2

Disconnect wiring/piping from back-up

flight instruments and propeller ammeter.

3

Remove left main panel.

8 Phillips screws

Page 4 31

Detail Steps/Work Items

Key Items

4

Install in reverse sequence of removal.

31-10-03

Right Main Panel

Removal/Installation

Detail Steps/Work Items

Key Items

1

Remove RH IFD.

Refer to Subject 31-60-01

2

Remove 10 Phillips screws around right

main panel.

2

Slightly swivel down right main panel

Take care not to damage

electrical wiring

3

Disconnect electrical wiring from

annunciator panel

4

Disconnect wiring from fuel gauges.

5

Disconnect wiring from fuel flow indicator.

6

Disconnect wiring from turn coordinator.

7

Install in reverse sequence of removal.

31-10-04

Lower Main Panel

Removal/Installation

Detail Steps/Work Items

Key Items

1

Remove LH and RH main panel

Refer to Subject 31-10-02/03

2

Remove engine indicators.

Refer to Chapter 77-40

3

Disconnect electrical wiring from ELT

switch.

4

Disconnect electrical wiring from LANDING

GEAR switch.

5

Disconnect electrical wiring from FLAP

switch.

6

Remove attachment nuts from the other

switches.

7

Disconnect electrical wiring from dimming

potentiometers.

31 Page 5

Detail Steps/Work Items

Key Items

8

Remove lower main panel.

14 bolts

9

Install in reverse sequence of removal.

31-10-05

Glare Shield

Removal/Installation

Detail Steps/Work Items

Key Items

1

Remove main panels.

Refer to Subjects 31-60-02

thru 04

2

Disconnect wiring from autopilot.

3

Remove glare shield.

4 screws

4

Install in reverse sequence of removal.

31-10-06

Control Display Unit

Removal/Installation

Follow the ACD215 Removal and Installation procedure presented in the

Entegra Integrated Flight Display System Product Maintenance Manual (LOAP

24).

Tests and Checks

Perform the applicable Return to Service Tests and Checks presented in the

Entegra Integrated Flight Display System Product Maintenance Manual (LOAP

24). whenever the unit has been reinstalled.

Page 6 31

31-50-00

CENTRAL WARNING SYSTEMS

Description

The central warning system in the EXTRA 500 consists of an annunciator

panel. The annunciator panel is located on the top RH instrument panel. (Refer

to the Emergency Procedures (Amplified) part of Section 3 in the EXTRA 500

Pilot's Operating Handbook for further information to the particular caution

and warning lights.)

31-50-01

Annunciator Panel (Westcoast Specialties)

The annunciator panel is located on the top RH instrument panel.

r

r

r

r

y

y

r

r

r

r

y

y

r

r

r

y

y

y

y

y

g

g

g

y

y

y

g

g

y

y

y

g

g

r = red, y = yellow, g = green

Figure 31-1

Annunciator Panel (Westcoast Specialties)

Removal/Installation

Detail Steps/Work Items

Key Items

1

Remove RH IFD.

Refer to Subject 31-60-01

2

Disconnect electrical wiring from

annunciator panel.

3

Remove panel.

4 screws

4

Install in reverse sequence of removal.

5

Check if all lamps work by placing the

NIGHT/DAY switch located on the left side

panel in the TEST position.

Page Date:

11. July 2012

31 Page 7

Lamp Replacement

Each annunciator light (lamp module) is illuminated by two lamps. Relamp by

pushing in lamp module approximately 1/16^th of an inch and release. The lamp

module will partially eject. Pull to disengage, then rotate downward to expose

the lamps. When reinserting lamp modules ensure both latching springs engage

cap assy by slowly pushing cap with equal force on both sides.

31-50-02

Annunciator Panel (EXTRA)

The annunciator panel is located on the top RH instrument panel.

r = red, y = yellow, g = green

Figure 31-2

Annunciator Panel (EXTRA)

Removal/Installation

Detail Steps/Work Items

Key Items

1

Unscrew the four inner bolts.

2

Pull the panel out.

3

Disconnect electrical connectors.

4

Install in reverse sequence of removal.

5

Check if all lamps work by placing the

NIGHT/DAY switch located on the left side

panel in the TEST position.

Page 8 31

Page Date:

11. July 2012

31-60-00

CENTRAL DISPLAY SYSTEMS

Description

The central display system of the EXTRA 500 contains 2 Avidyne Integrated

Flight Displays (IFDs).

31-60-01

Integrated Flight Display (IFD)

Removal/Installation

Follow the IFD5000i Removal and Installation procedure presented in the

Entegra Integrated Flight Display System Product Maintenance Manual (LOAP

24) observing the following aircraft specific hints:

Ensure BATT switch is OFF and no external power connected.

The wiring and piping for the RH IFD is dimensioned in the way that it can be

disconnected/connected when the IFD is removed from and held next to the

instrument panel. The wiring and piping for the LH IFD is shorter so that

connecting/disconnecting has to be done with IFD installed. For that reason the

RH IFD must be removed to get access to the wiring/piping connectors.

The wiring is marked conforming to the designations on the IFD backsides.

However the piping (Pitot/static) is colored as shown in the following:

IMPORTANT

The colors of pitot/static lines do not match with the port markings on the

backside of the IFDs.

Piping Colors

LH IFD

RH IFD

PITOT

white

blue

STATIC

red

green

Tests and Checks

Perform the applicable Return to Service Tests and Checks presented in the

Entegra Integrated Flight Display System Product Maintenance Manual (LOAP

24) whenever the unit has been reinstalled.

Pitot/Static Check

Perform applicable Return to Service Pitot/static Check according to FAR 43,

Appendix E and AC 43.13-1B CHG1 (or later) Ch. 12-59 whenever the unit

has been reinstalled.

Magnetometer Calibration

It is advisable to integrate the Compass Swing procedure outlined in Chapter

34-20-02 in this calibration procedure.

Page Date:

31 Page 9

It is recommended to perform the calibration with a mobile external power

unit.

Detail Steps/Work Items

Key Items

1

Place the aircraft in a magnetically clean area

2

Attach external power

3

Switch on BATT, EXT PWR, and AVIONICS

4

Wait, until both IFD-s have aligned

5

Wait additional 10 minutes.

6

Press ‘SYS’ and select ‘setup’ on both IFD-s

7

Press ‘Update Databases’ L(ine) S(elect) K(ey)

8

Press ‘Confirm’ LSK

9

Simultaneously hold the LH upper and third

LSK for 5 seconds

10

Press ‘Proceed’ LSK

11

Check ‘Technician maintenance mode’

indication

12

Press ‘SYS’ and select ‘cal’

13

Press ‘Cal select - select Magnetometer

calibration’

14

Check ‘Calibrate Heading’ indication

IMPORTANT

Place the ailerons to neutral and do not move them during calibration

and verification.

Calibration

15

Place the aircraft to the magnetic north

360°+/−1°

16

Switch on STROBE

17

Follow the procedure as displayed on IFD-s

18

After the heading point (330°):

19

Check ‘Magnetometer Calibration Complete’

indication.

20

Wait 10 seconds

21

Press ‘Done’

22

Wait until IFD-s to reboot.

23

Switch off EXT PWR

24

Switch off BATT

25

Wait one minute

26

Verify neither “Mag CAL 1 required” or

“Mag CAL 2 required” appears.

Page 10 31

Page Date: 9. August 2013

Magnetometer Check

Detail Steps/Work Items

Key Items

1

Place the aircraft in a magnetically clean area

2

Attach external power

3

Switch on BATT

4

Switch on EXT PWR

5

Wait until IFD-s to reboot and are aligned

6

Check ‘Mag Cal 1 (or 2) Required’ Caution

does NOT appear.

7

Place the aircraft to the given directions.

If values are out of limit

Check if reading in limits and note values.

perform Magnetometer

Calibration Procedure

8

Heading accuracy each IFD at 0°true within or

True:

LH:

RH:

at 356 to 004°

9

LH and RH IFD-s at 0°true within or at 2° of

each other

10

Heading accuracy each IFD at 90°true within

True:

LH:

RH:

or at 86 to 94 °

11

LH and RH IFD-s at 90°true within or at 2° of

each other

12

Heading accuracy each IFD at 180°true within

True:

LH:

RH:

or at 176 to 184°

13

LH and RH IFD-s at 180°true within or at 2° of

each other

14

Heading accuracy each IFD at 270°true within

True:

LH:

RH:

or at 266 to 274°

15

LH and RH IFD-s at 270°true within or at 2° of

each other

16

Switch off EXT PWR

17

Switch off BATT

Page Date:

31 Page 11

Nose gear and main gear extends and retracts under high pressure.

DANGER

Operation of the landing gear can cause death or injuries in its

working area!

Before beginning any work in the landing gear working area, pull the

electric circuit breaker located on the left side panel and marked

GEAR-CTRL.

In case of intentional gear operation by switch or circuit breaker

handling make sure, that neither a person nor any object is located in

the upper landing gear doors travel area.

NOTE

With the aircraft being airborne or jacked and BATT and EXT PWR

switch OFF, the hot bus feeds an AUX circuit, which supplies the

directional valves with electrical power to keep the landing gear in the

up-position. The AUX circuit is protected by the GEAR AUX 1 (left side

panel) and GEAR AUX 2 (E-box) circuit breakers. Push these circuit

breakers in.

However, the nose gear and main gear will slowly extend due to valve

oil leakage, if the hydraulic pump is not being activated temporarily to

maintain hydraulic pressure. If retracted landing gear position is

intended, turn BATT switch ON (left side panel, toggle switch) and push

circuit breakers GEAR-CTRL and HYDR (left side panel) in, while the

landing gear switch (left main panel) is in the UP position.

If the aircraft is jacked with landing gear retracted and external power

not connected, the battery will be discharged within approx. 2 days.

Troubleshooting

The following paragraph tabulates the troubleshooting procedures relevant to

the landing gear system. The complaints are classified in order to the landing

gear sub-systems.

Complaint

Possible Cause

Remedy

Main Gear and Doors

Refer to Section 32-10

Wings are not level

Main gear struts bent or

Inspect the main gear struts for

damaged

cracks and bending

Drag brace is not locked in

Inspect the drag brace, the

overcenter position

torque link rod and the main

gear-attachment frame for

cracks and bending. Check the

length of the torque link rod.

Gas-leakage by worn O-ring

Check the nitrogen gas

sealing of the shock absorber.

pressure and inflate if required

Main gear rattles while taxiing

Worn collar bushings

Replace

Oil stains beneath the shock

Leakage by worn ore damaged

Replace

absorber

O-ring and scraper rings

Nose Gear and Doors

Refer to Section 32-20

Oil stains beneath the nose

Leakage by worn ore damaged

Replace O-ring, refill

32 Page 7

Complaint

Possible Cause

Remedy

gear oleo-strut

O-ring and scraper rings

Aeroshell Fluid 4 as needed

Nose wheel wobbles while

Shimmy damper mechanical

Replace damaged parts

taxiing

damage

Leakage by worn ore damaged

Replace O-ring, refill

O-ring and scraper rings

Aeroshell Fluid 4 as needed

Extension and Retraction

refer to Section 32-30

Oil stains beneath the nose

Leakage by worn ore damaged

Replace damaged parts

gear actuator and hydraulic

O-rings, fittings, hoses or

lines

tubes

Oil stains beneath the main

Leakage by worn ore damaged

Replace damaged parts

gear actuator and hydraulic

O-rings, fittings, hoses or

lines

tubes

Continued hydraulic pump

Abnormal hydraulic internal

Detect leak and seal

operation exceeds 3 seconds

system leakage.

and/or periods of rest shorter

Pressure switch

Adjust or replace

than 2 minutes.

Pump bypass valve

Adjust or replace

Wheels and Breaks

refer to Section 32-40

Wings are not level

Incorrect wheel tube pressure

Check the tube pressure and

inflate to max. pressure if

required

Too much tire wear

Incorrect toe-in

Check and adjust the toe-in

Wheel track out of tolerance

Correct the wheel track

Too much axial play in wheel

Defective wheel bearing

Replace the wheel bearings

Brake disk deformed

Excessive hard braking

Replace brake disk

Dragging brakes

Worn or broken piston return

Repair or replace master

spring in master cylinder

cylinder

Brake does not operate

Brake fluid level low

Inspect master cylinder,

fittings and linings for

leakage. Refill brake fluid

Air in the brake system

Bleed the brake system

Defective master cylinder

Replace the master cylinder.

Then bleed the brake system

Defective fittings or lines

Replace the fitting or line.

Then bleed the brake system

Worn brake lining

Replace the brake lining

Operational Test Procedures

For ground testing the landing gear functions the aircraft must be lifted at the

three jack points (see Ch. 07-10-00). When aircraft is on jacks and landing gear

Page 8 32

Page Date:

shall be driven to another status as it is, follow the Gear Up Procedure or Gear

Down Procedure given in the following.

Nose gear and main gear extends and retracts under high pressure.

DANGER

Operation of the landing gear can cause death or injuries in its working

area !

Before beginning any work in the landing gear working area, pull the

electric circuit breaker located on the left side panel and marked

GEAR-CTRL.

In case of intentional gear operation by switch or circuit breaker

handling make sure, that neither a person nor any object is located in

the upper landing gear doors travel area.

NOTE

With the aircraft being airborne or jacked and BATT and EXT PWR

switch OFF OFF, the hot bus feeds an AUX circuit, which supplies the

directional valves with electrical power to keep the landing gear in the

up-position. The AUX circuit is protected by the GEAR AUX 1 (left side

panel) and GEAR AUX 2 (E-box) circuit breakers. Push these circuit

breakers in.

However, the nose gear and main gear will slowly extend due to valve oil

leakage, if the hydraulic pump is not being activated temporarily to

maintain hydraulic pressure. If retracted landing gear position is

intended, turn BATT switch ON (left side panel, toggle switch) and push

circuit breaker GEAR-CTRL (left side panel) in, while the landing gear

switch (left main panel) is in the UP position.

If the aircraft is jacked with landing gear retracted and external power

not connected, the battery will be discharged within approx. 2 days.

Gear Up Procedure

1

Lift the aircraft on jacks (refer to Chapter 07-10-00).

Upper landing gear doors will close immediately, when BATT or EXT PWR

DANGER

switch is turned to ON and GEAR-CTRL circuit breaker is in. Make sure,

that neither a person nor any object is located in the upper landing gear

doors travel area.

2

Turn BATT and EXT PWR switch ON (left side panel, toggle switch).

3

Push circuit breaker GEAR-CTRL in (left side panel).

Make sure, that neither a person nor any object is located in the landing

DANGER

gear travel area.

4

Pull and move LANDING GEAR switch UP (left main panel, below RH side of

control yoke).

5

Wait until HYDRAULIC PUMP light is off indicating that the gear up procedure

is completed. However GEAR WARN remains illuminated and aural warning is

still active. This is normal as engine power is below approach setting (35%

torque).

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