Extra 500. Maintenance Manual (2012)

24-00-00

GENERAL

Description

Refer to Figure 24-1. The electrical system is a 28 VDC system with negative

ground. The primary DC power source is an engine driven 28 V/200 A starter-

generator. It is backed up by an engine driven 26 V/20 A standby alternator. In

addition a lead acid battery

(24 V/28 Ah) is installed in the engine

compartment. Normal battery power is sufficient to start engine or for ground

check operation.

An external 28 VDC power receptacle and its circuit breaker are installed in a

hatch right hand at fixed portion of the cowling.

24 Page 3

Troubleshooting

The following paragraph tabulates the trouble shooting procedures relevant to

the battery system.

Complaint

Possible Cause

Remedy

System not energized when

Depleted or dead battery

Recharge or replace.

battery switch is turned on

Defective wiring

With BATT switch OFF, check

entire DC power system,

accessible from plane fire wall

resp. lower tail cone access

panel, for an open circuit with

a continuity tester

Defective battery relay

With BATT switch ON,

connect a voltmeter to the

main battery bus and check

voltage. If no voltage is

indicated, check and/or replace

relay

Defective BATT switch

Remove switch and check

with continuity tester. Replace

switch if defective.

Battery discharged

Charging rate too low

Check generator

Battery has been left standing

Recharge or replace

too long without recharging

Equipment has been left on

Replace battery

accidentally

Short circuit in wiring

Check wiring, replace battery.

Short battery life

Low charging rate

Check generator voltage

Corroded or loose battery

Clean and tighten, recharge

connections

battery.

Reduced battery capacity

Replace battery.

Battery polarity reversed

Connected backwards on

Battery should be slowly

airplane or charger

discharged completely, then

charged correctly and tested

Battery freezes

Undercharged or overcharged

Replace battery

battery

24 Page 7

Complaint

Possible Cause

Remedy

Starter-generator does not

Starter-generator defective

Replace starter-generator.

produce current when

Generator control unit

Replace generator control unit.

switched on.

defective

GEN switch defective

Replace GEN switch.

Generator relay defective

Replace generator relay (E-

box).

Current indication defective

Replace shunt.

Replace indicator.

Repair wiring.

Standby alternator does not

Bus voltage above 26.5 V

Normal, no action required.

produce power when switched

Alternator defective

Replace alternator.

Alternator controller defective

Replace alternator controller.

Wiring defective

Repair wiring.

STDBY ALT switch defective

Replace STDBY ALT switch.

Alternator relay defective

Replace alternator relay (E-

box).

Alternator fuse defective

Examine reason and replace

alternator fuse (E-box).

Current indication defective

Replace shunt.

Replace indicator.

Repair wiring.

Load bus without power

Starter-generator or external

Normal, no action required.

power not on.

Load bus fuse defective

Replace fuse (E-box).

Battery bus without power

Battery bus fuse defective

Replace fuse (E-box).

Avionic bus without power

Battery bus without power

See above.

AVIONICS switch defective

Replace AVIONICS switch (left

side panel).

Avionic bus relay defective

Replace avionic bus relay (left

side panel).

AV BUS circuit breaker

Replace AV BUS circuit

defective

breaker (left side panel).

Page 8 24

24-30-00

DC GENERATION

Refer to Figure 24-1.

DC generation is done by the following devices:

• Starter-generator

• Standby Alternator

• Battery

24-30-10

Starter-Generator

A starter-generator is mounted on the accessory gearbox of the engine. It is a

direct driven starter during engine start and a DC generator driven by the

engine during engine operation. Its rated capacity is

200 A maximum for

continuous operation.

Removal/Installation

Remove the LH upper engine cowling to get access to the starter-generator.

Refer to AIRCRAFT PARTS CORP. Installation Instructions 200SGL Series

Starter-Generators (LOAP 39) for further information.

24-30-11

Generator Control Unit (GCU)

The starter-generator is regulated by the GCU (Generator Control Unit) to

provide an output voltage of 28.5 V DC. The GCU is installed to the fuselage

structure behind the left legroom side paneling. The GCU is controlled by the

GEN and GEN TEST switches located on the MAIN section of the left side panel.

Following engine start, the generator delivers electrical power when the GEN

switch is switched to ON position.

In case the generator is not switched on or has failed the red GENERATOR FAIL

warning light on the annunciator panel illuminates. With the generator test

switch (GEN TEST, left side panel) the overvoltage protection function of the

GCU can be tested (switch position: OV-TEST). The TRIP position of this

switch gives the possibility to “trip” the generator by momentarily interrupting

its excitation. Both test functions lead to disengagement of the generator from

the aircraft bus system. The momentary RESET position of the GEN switch

serves to energize the generator field in case problems have occurred trying to

connect the generator to the aircraft bus system (switching the generator ON).

Resetting the generator is recommended in that case before trying to switch the

generator on again.

24 Page 9

Removal/Installation

Detail Steps/Work Items

Key Items

Ensure BATT switch is OFF and no external

power connected.

Remove left legroom side paneling.

Refer to Chapter 25-00-01.

Remove electrical connector.

Remove GCU.

4 bolts

Install in reverse order of removal.

24-30-20

Standby Alternator

In case of a starter-generator failure a gear driven standby alternator provides

an additional power source in excess to the aircraft battery. The standby

alternator is controlled by the STDBY ALT switch in the MAIN section of the

left side panel. Switching it to the ON position will command the alternator

regulating unit to regulate an alternator output voltage of 26 VDC. Therefore as

long as bus voltage is higher caused by an active generator the alternator load

will be zero. As soon as bus voltage drops below the regulation voltage of the

standby alternator the alternator feeds to the bus system. Max. rated current is

20 A which is available with N1 being at approx 92 %. At 78 % N1 about 10 A

are available. Below 70 % N1 the standby alternator isn’t able to provide a

relevant current.

Operation of the standby alternator is indicated by a yellow STANDBY ALTERN

ON caution light on the annunciator panel. Continuous illumination of this light

signals operation below the 20 A output limitation.

If the STANDBY ALTERN ON caution light starts blinking, the load on the

CAUTION

alternator exceeds its rated capacity. Reduce consumption of electrical

consumers within 5 minutes to 20 A or less.

Removal/Installation

Remove the upper engine cowlings to get access to the stand-by alternator.

Refer to B & C SPECIALTY PRODUCTS Installation Instructions for BC410

Alternators (LOAP 40) for further information.

24-30-21

Alternator Regulator

The alternator regulator is mounted to the cabin side of the firewall.

Refer to B & C SPECIALTY PRODUCTS B & C SPECIALTY PRODUCTS

Troubleshooting Guide (LOAP 28) for further information.

Page 10 24

Removal/Installation

Detail Steps/Work Items

Key Items

Ensure BATT switch is OFF and no external

power connected.

Remove RH and LH IFD.

Refer to Chapter 31-60-01.

Remove electrical connection.

Remove 2 nuts.

Remove regulator.

Install in reverse order of removal.

24-30-30

Battery

The 24 VDC/28 Ah valve regulated lead acid battery is located in the engine

compartment, mounted to the pressure bulkhead and protected by a vented

aluminum case. The battery is directly connected to the hot bus. The battery

supplies power to the electrical system when BATT switch is switched to ON

position.

Recharging the battery may be done with battery installed. There are two

procedures:

Charging with external power

Detail Steps/Work Items

Key Items

Always keep sparks or any form of ignition away from the battery being

WARNING

charged. Explosive gases are being generated during the charging

process.

Set external power unit to 28 VDC.

Connect external power.

Switch on BATT.

Switch on EXT PWR.

24 Page 11

Charging over charger plug

Detail Steps/Work Items

Key Items

Always keep sparks or any form of ignition away from the battery being

WARNING

charged. Explosive gases are being generated during the charging

process.

Do not charge with more than 5 A.

Use only supplied unit or equivalent.

Connect the charger to the charger plug.

Connect the charger to the wall socket.

Removal/Installation

Detail Steps/Work Items

Key Items

Ensure BATT switch is OFF and no external

power connected.

Remove upper engine cowlings.

Refer to Ch. 71-10-01/02.

Disconnect the quick connect plug.

Disconnect the 2 retainers.

Remove battery from aircraft.

Install in reverse order of removal

24-30-40

Indication

Electric system relevant indication is made by the digital indicator cluster

installed in the left side of the main panel and the following lights in the

annunciator panel:

GENERATOR FAIL (red), see Subject 24-30-10.

LO VOLTAGE (yellow), illuminates as soon as bus voltage drops below 25.5 V.

STANDBY ALTERN ON (yellow), see Subject 24-30-20.

EXTERNAL POWER (green), see Subject 24-40-00.

24-30-41

Indicator Cluster

The digital indicator cluster installed in the left side of the main panel indicates

three electric system parameters among other engine parameters (also refer to

Chapter 77-40-02):

Page 12 24

VDC (bus voltage)

During normal operation (generator active) a voltage of approx 28 V should be

indicated. With standby alternator the indication should be about 26 V. Battery

nominal voltage is 24 V.

GEN AMPS (Generator Load)

Generator load is indicated on this indicator as long as the generator is active

(GENERATOR FAIL warning light off). Generator Load should be kept below

200 A. In case the generator is offline this indicator automatically displays the

standby alternator load. The standby alternator load has to stay below 20 A (see

also Subject 24-30-20).

BAT AMPS

The battery amp indicator shows load or charging current on the battery. A

negative indication means battery is being charged, a positive indication means

battery is discharged (load on battery).

Removal/Installation

For removal/installation procedures refer to Chapter 77-40-02.

24 Page 13

24-40-00

EXTERNAL POWER

Description

An external power receptacle is installed under an access door on the right side

of the engine compartment. The use of external power is recommended for

engine starting in case aircraft battery is weak, for ground operation of the

vapor cycle air condition system or for any prolonged ground operation of

aircraft systems. An external power source being connected with the external

power receptacle and switched on will be indicated by a green EXTERNAL

POWER annunciation light in the annunciator panel. To enable the external

power source to supply power to the aircraft the EXT PWR switch on the MAIN

section of the left side panel has to be switched on.

Do not connect ground power units with a capacity greater than 1200 A

CAUTION for engine start.

NOTE

It is not possible to connect the starter-generator and an external power

source simultaneously to the aircraft bus system. This is to avoid any

uncontrolled currents between these units.

Additionally a battery charger plug is installed at the external power receptacle.

The battery may be charged with 29.0 V and 5 A.

Page 14 24

24-60-00

DISTRIBUTION

Description

Electrical power from the various power sources is supplied to the E-box. The

E-box incorporates the main devices of the distribution system such as fuses,

circuit breakers, relays, and shunts and is installed on the engine side of the

firewall. From there power is distributed partly through individual fuses to the

following buses:

•

Hot Bus,

•

Emergency Bus,

•

Battery Bus and Avionic Bus

•

Load Bus,

The battery directly feeds the hot bus supplying power for equipment, which

has to be independent from the battery switch position (e.g. ELT; see Figure

24-2 for location of battery switch).

Turning the battery switch to the ON-position will activate a relay connecting

the battery to the battery bus and further to the emergency bus. This allows

starting the engine and feeding the other equipment and, if engine is running,

recharging the battery with the starter/generator.

The generator is activated by turning GEN switch to the ON-position (see

Figure 24-2). So the generator is activated and the generator relay connects the

generator to the load, battery and emergency bus.

From the main bus electrical power is distributed to the various busses as

outlined on Figure 24-1. The avionic bus can be disconnected by the AVIONICS

switch.

The main control switches of the electrical power system are located on the

MAIN section of the left side panel (see Figure 24-2) and are marked EXT PWR,

BATT, STBY ALT, GEN and GEN TEST.

Push-pull circuit breakers automatically break the current if an overload occurs

to prevent damage to the electrical wiring and equipment. The most circuit

breakers are installed to the left side panel (see Figure 24-3). A single circuit

breaker is installed on the upper LH engine mount (GCU) and under the

external power hatch (EXT PWR) respectively. All other circuit breakers are

installed to the E-box located on the engine side of the firewall and are labeled

GEAR AUX 2, BATT CHARGE, SPARE, ALT FIELD 2, COURTESY LT, and ELT.

Generally where exclusively wiring shall be protected poly switches are used.

They are installed on different locations of the electrical system.

24 Page 15

24-60-01

E-box

Removal/Installation

Detail Steps/Work Items

Key Items

Ensure BATT switch is OFF and no external

power connected.

Remove upper engine cowlings.

Refer to Ch. 71-10-01/02.

Disconnect the SCEET hoses from the oil

cooler inlet.

Remove 10 attachment screws of the oil

cooler inlet.

Remove oil cooler inlet.

Remove 8 oil cooler outlet attachment

screws.

Move oil cooler and outlet some centimeters

To get access to the E-box.

forward.

Disconnect electrical connector

Disconnect power lines

Remove upper E-box cover.

1 screw

Disconnect 3 main power bulkhead feed-

Hold threaded rod in place by

throughs.

means of an Allen wrench.

Remove 3 attachment screws.

Remove E-box.

Remove cover plate and shell plate.

Plates are screwed on.

Install in reverse sequence of removal.

24-60-02

Switches

Removal/Installation

The switches on the instrument panel are accessible from the backside after

removal of the RH IFD. The LANDING GEAR, FLAP, and ELT switch

backsides are directly accessible from the legroom.

The backsides of the left side panel switches are accessible when the upper and

lower part of the left side panel has been removed.

Generally conventional switches are used, so that removal is done by

disconnecting the electrical wiring and removing attachment screws or nuts.

Installation is vice versa.

Page 16 24

24-60-03

Circuit Breakers

Removal/Installation

The circuit breakers on the left side panel are accessible from the backside

when the upper and lower part of the left side panel has been removed.

To get access to the E-box circuit breakers the E-box must be removed (refer to

Subject 24-60-01).

Generally conventional circuit breakers are used, so that removal is done by

disconnecting the electrical wiring (busses) and removing attachment screws or

nuts. Installation is vice versa.

24-60-04

Relays

Relays are installed in the left side panel, in the E-box and behind the RH IFD.

To get access to the relays either the E-box (see Subject 24-60-01), the left side

panel (see Chapter 31-10-01) or the RH IFD (see Chapter 31-60-01) must be

removed

Electrical wiring is generally connected to the relays by means of relay sockets.

The relays are mounted to the sockets with bolts.

24-60-05

Shunts

Shunts are installed in the E-box.

To get access to the shunts the E-box must be removed (refer to Subject 24-60-

01).

Electrical wiring is generally connected to the shunts by means of screws. The

shunts are mounted to the supports with bolts.

24-60-06

Fuses

The main fuses are installed in the E-box with bolts. They are accessible after

removal of the upper E-box cover.

24 Page 17

TABLE OF CONTENTS

25-00-00

GENERAL

25-10-01

Paneling

Description

Removal/Installation

25-10-00

FLIGHT COMPARTMENT

25-10-10

Seats, Seat Belts, and Shoulder Harnesses

Description

25-10-11

Pilot's Seat

Removal/Installation

25-10-12

Copilot's Seat

Removal/Installation

25-10-21

LH Side Armrest Paneling

Removal/Installation

25-10-22

RH Side Armrest Paneling

Removal/Installation

25-10-23

Front Ceiling Paneling

Removal/Installation

25-10-24

Upper Side Paneling LH/RH Side

Removal/Installation

25-10-25

Windshield Middle Strut Paneling

Removal/Installation

25-10-26

Middle Console Paneling Upper Part

Description

Removal/Installation

25-10-27

Middle Console Paneling Lower Part

Description

Removal/Installation

25-20-00

PASSENGER COMPARTMENT

25-20-10

Seats

25-20-11

Front Passenger Seats

Removal/Installation

25-20-12

Aft Passenger Seats

Removal

Installation

25-20-21

LH Side Armrest Paneling

Removal/Installation

Page 2 25

25-00-00

GENERAL

25-10-01

Paneling

Description

If not described in another way paneling is generally mounted to the aircraft

structure with Phillips screws.

Removal/Installation

Take care of the paneling installations such as switches, sockets, lights etc.

when removing. Ensure BATT switch is OFF and no external power connected,

when electrical devices are involved. Sometimes the paneling overlaps. Then it

is necessary to remove also the adjacent paneling. Move paneling some

centimeters inboard after removal of Philips screws to get access to the

paneling backsides. Then disconnect electrical wiring. Installing is vice versa.

25 Page 5

25-10-00

FLIGHT COMPARTMENT

25-10-10

Seats, Seat Belts, and Shoulder Harnesses

Description

The pilot's and copilot's seats are one piece, four-way adjustable seats

incorporating energy absorbers which reduce forces working on the occupants

in case of crash. The seats may be moved forward, aft, up, and down. The

adjustment is made by pulling a handle located at the right respective left

forward underside of the seat to release the fixing mechanism. The horizontal

adjustment range is 152 mm, 5 fixed positions are provided. The vertical

adjustment range is

80 mm, 5 fixed positions are provided. Telescopic

cylinders support the pilot during the vertical adjustment.

The seat belts and the shoulder harnesses with inertia reels used for the pilot

and copilot are attached to the seats. The seat belts provide a conventional

adjustment. Shoulder harness adjustment is not necessary due to the inertia

reels, which allow straps to extend and retract as required under normal

movement. However the reels will lock in place in the event of a sudden

deceleration.

25-10-11

Pilot's Seat

Removal/Installation

Detail Steps/Work Items

Key Items

Remove front roll from RH seat track.

2 screws

Remove mounting bracket and roll as

2 screws

a unit from back RH seat track.

Pull off bracket from back LH seat

2 screws

track.

Pull adjusting handle to release bolt at

longitudinal adjusting device.

Slide seat out of mounting console in

forward direction.

Install in reverse order of removal.

Page 6 25

25-10-12

Copilot's Seat

Removal/Installation

Detail Steps/Work Items

Key Items

Remove front roll from LH seat track.

2 screws

Remove mounting bracket and roll as

2 screws

a unit from back LH seat track.

Pull off bracket from back RH seat

2 screws

track.

Pull adjusting handle to release bolt at

longitudinal adjusting device.

Slide seat out of mounting console in

forward direction.

Install in reverse order of removal.

25-10-21

LH Side Armrest Paneling

Removal/Installation

Detail Steps/Work Items

Key Items

Remove left side panel.

Refer to Chapter 31-10-01.

Remove screw fastening microphone twin

socket on rear top of panel.

Remove screw at lower front panel side.

Remove screw at lower rear panel side.

Slightly lift panel and remove it against

flight direction.

Install in reverse sequence of removal.

25 Page 7

25-10-22

RH Side Armrest Paneling

Removal/Installation

Detail Steps/Work Items

Key Items

Ensure BATT switch is OFF and no external

power connected.

Remove microphone socket cover on rear

top of panel.

Remove screw at lower front panel side.

Remove screw at lower rear panel side.

Slightly lift panel and remove it against

flight direction.

Install in reverse sequence of removal.

25-10-23

Front Ceiling Paneling

Removal/Installation

Detail Steps/Work Items

Key Items

Ensure BATT switch is OFF and no external

power connected.

Take care not to damage sunblinds. Swivel sunblinds up before

CAUTION

removing ceiling panel

Remove 4 screws around upper windshield

frame.

Remove 4 screws near panel edges.

Disconnect plug for dome light/speaker

wiring.

Carefully remove adhesive tape at panel

back side.

Remove front ceiling paneling.

Install in reverse sequence of removal.

Page 8 25

25-10-24

Upper Side Paneling LH/RH Side

Removal/Installation

Detail Steps/Work Items

Key Items

Remove 2 screws in windshield frame area.

Remove 2 screws in front cabin window

contour area.

Remove upper side paneling.

Install in reverse sequence of removal.

25-10-25

Windshield Middle Strut Paneling

Removal/Installation

Detail Steps/Work Items

Key Items

Ensure BATT switch is OFF and no external

power connected.

Remove 2 screws at compass.

Disconnect wiring for compass lighting.

Remove compass.

Remove 4 screws at paneling.

Remove windshield middle strut paneling.

Install in reverse sequence of removal.

25-10-26

Middle Console Paneling Upper Part

Description

The middle console paneling consists of an upper and lower part. The upper

part is screwed on the lower part and on the middle console structure.

Removal/Installation

Detail Steps/Work Items

Key Items

Remove trim wheel.

1 Phillips screw

Remove the back-up microphone from the

middle console.

25 Page 9

Detail Steps/Work Items

Key Items

Remove the upper part of middle console

24 Phillips screws

paneling.

Install in reverse sequence of removal.

Check the function of the back-up

microphone.

25-10-27

Middle Console Paneling Lower Part

Description

The lower part of the middle console paneling is aligned by 4 guiding pins in

the fuselage frame and fixed by the upper part of the paneling.

Removal/Installation

Detail Steps/Work Items

Key Items

Remove upper part of the middle console

Refer to Subject 25-12-06

paneling.

Disconnect air hoses from the legroom

1 worm drive hose clamp

dispensers.

each side

Move lower part paneling some centimeter

aft and remove.

Install in reverse sequence of removal.

Insert guide pins to the

related holes in the forward

paneling edges.

Page 10 25

25-20-00

PASSENGER COMPARTMENT

25-20-10

Seats

The passenger seats are one piece seats as well but are placed on a fix position.

However the backrest of both aft seats can be swiveled forward allowing easy

access to the baggage compartment. For this purpose a release handle located

on the inner side of the backrest has to be pulled up.

Ensure backrest is locked by checking the down position of the release

WARNING handle before using the seat.

The seat belts provide a conventional adjustment however the locking

mechanism is placed on the inner side of the seat providing a lock for the

shoulder strap, which is equipped with inertia reels. The attachments of the seat

belts and shoulder harnesses are integrated in the seat.

25-20-11

Front Passenger Seats

Removal/Installation

Detail Steps/Work Items

Key Items

Remove screws at mounting console.

4 Allen screws LN 29952-0615M

Remove seat.

Install in reverse order of removal.

If necessary, use mounting template

at landing gear attachment for front

side screws.

25-20-12

Aft Passenger Seats

Removal

Detail Steps/Work Items

Key Items

Remove front paneling of baggage

To get access to the mounting

compartment from seat assembly.

consoles.

Remove back side screws at inner and

4 Allen screws LN 9037 - 06018

outer seat mounting console.

Remove front side screws at inner and

1 Allen screw LN 9037 - 06016 and

outer seat mounting console.

2 Allen screws LN 9037 - 06018

25 Page 11

Remove screws at higher angle

6 Allen screws AN 5260 - 1032

bracket.

Installation

Insert front side screws at inner and

1 Allen screw LN 9037 - 06016 and

outer seat mounting console.

2 Allen screws LN 9037 - 06018

Before tightening front side screws

4 Allen screws LN 9037 - 06018

completely, adjust seat from rear side

and install back side screws at inner

and outer seat mounting console.

Tighten front side screws at inner and

outer seat mounting console.

Install screws at higher angle bracket.

6 Allen screws AN 5260 - 1032

Reinstall front paneling of baggage

compartment..

25-20-21

LH Side Armrest Paneling

Removal/Installation

Detail Steps/Work Items

Key Items

Ensure BATT switch is OFF and no external

power connected.

Remove microphone socket cover on front

top of panel.

Remove microphone socket cover on rear

top of panel.

Remove 5 screws at entrance bottom panel

sheet.

Loosen screws at door sealing frame in

armrest area.

NOTE

On some aircraft, the armrest is fixed with additional latches to the door

frame. In this case remove the screws and the latches completely.

Remove screw at lower front panel side.

Remove screw at lower rear panel side.

Pull armrest together with frame floor

finishing inboard and remove it against

flight direction.

Install in reverse sequence of removal.

Page 12 25

25-20-22

RH Side Armrest Paneling

Removal/Installation

Detail Steps/Work Items

Key Items

Ensure BATT switch is OFF and no external

power connected.

Remove microphone socket cover on front

top of panel.

Remove microphone socket cover on rear

top of panel.

Remove table.

Refer to Subject 0.

Remove screw at lower front panel side.

Pull back frame floor finishing.

Slightly lift panel and remove it against

flight direction.

Install in reverse sequence of removal.

25-20-31

Storage Boxes LH/RH

Description

Storage boxes are located between LH and RH side pilot’s/copilot’s and front

passenger seats. They provide a place for depositing especially the emergency

torch, first aid kit and the aircraft documentation material.

Removal/Installation

Detail Steps/Work Items

Key Items

Ensure BATT switch is OFF and no external

power connected.

Slide pilot’s and co-pilot’s seat into most

forward position.

Remove 2 screws at front and back bottom

side.

4 LH box

Remove screws at floor and back wall of

upper and lower storage compartments.

4 RH box

Take out fire extinguisher, remove bolts

holding extinguisher support bracket.

Install in reverse sequence of removal.

25 Page 13

25-50-00

BAGGAGE COMPARTMENT

Description

The baggage compartment is located behind the aft passenger seats. To get

access the backrest of both aft seats can be swiveled forward. The release

handle is placed on the left side of the backrest.

The baggage can be secured by tie down belts, which are to be fastened on eyes

located on two compartment sides.

25-50-01

Tie Down Belts

Removal/Installation

Detail Steps/Work Items

Key Items

Release the handles at aft passenger seat

backrests and swivel backrests forward.

Remove 2 Phillips screws AN 526 C .1032

R8 securing front belt brackets to LH and

RH side console.

Remove front belt.

Remove 2 Phillips screws AN 526 C .1032

R8 securing aft belt brackets to LH and RH

side console.

Remove aft belt.

Install in reverse sequence of removal.

Install screws just so tight,

that belt brackets can be

rotated freely, but without

play.

25 Page 15

TABLE OF CONTENTS

27-00-00

GENERAL

Description

27-00-01

Control Cable

Tensions

Figure 27-01

Control System Surview

27-00-10

CONTROL SPRINGS

Location

27-00-11

Down-Spring

Description

27-00-12

Interconnection Aileron/Rudder

Description

27-00-13

Centering Rudder

Description

27-00-14

Nose Gear Steering

Description

27-00-15

Nose Gear Control Cable

Description

27-10-00

AILERONS

Description

Troubleshooting

Removal/Installation

27-10-01

Aileron Cables

Removal/Installation

27-20-00

RUDDER

Description

Troubleshooting

Removal/Installation

27-20-01

Rudder Cables

Removal/Installation

27-30-00

ELEVATOR AND TAB

Description

Troubleshooting

Removal/Installation

27-30-01

Elevator Cables

Removal/Installation

Page 2 27

27-50-00

FLAP SYSTEM

Description

Rigging and Adjustment

Track Adjustment

Guidance Checks and Adjustment

Actuation Adjustment

27-50-01

Flap Drive Motor

Description

27-50-02

Inboard Power Transmission Flexible Shaft

Description

27-50-03

Outboard Power Transmission Flexible Shaft

Description

27-50-04

Power Transmission Screw Jacks

Description

27-50-05

Flap Control Box

Description

27-50-06

Flap Limit Switches

Description

Adjustment

27-50-07

Flap Asymmetry Senders

Adjustment

27 Page 3

Extra 500. Maintenance Manual (2012) - page 7