P500 006 000 Rev.9 IV

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

32-20-00Page 01

NOSE GEAR - DESCRIPTION

1. Introduction

A. The S6 features a steerable and retractable nose landing gear, which is equipped with an elastomer shock absorber. In retracted position the landing gear leg and the wheel well is fully covered by a landing gear door. The nose-gear is made of a steel tube which is stiff to torque.

2. Description and Operation

A. The nose gear consists of a welded tubular steel strut attached to the forward fuselage-section at an attachment-plate by bolts. The shock-strut is dampened by the use of elastomers and has a maximum spring-travel of approx. 100 mm (4 in). The nose-wheel is steered by rotating the nose-wheel-fork, which is attached to the lower end of the shock-strut. This kinematic is performed with several levers. When the nose gear is loaded on ground, it connects automatically to the rudder-controls.Then it is operated via a connecting fork and push rod by rudder pedals. In the un-loaded position, it is automatically disconnected from the rudder-controls and locks in the direction of the longitudinal-axis.The actuation for retraction is driven by a hydaulic cylinder mounted to the drag strut of the landing gear leg. The door is connected kinematically to the nose gear leg.

Nov 18/11

EFFECTIVITY

Model S6-RT

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

NOSE GEAR - MAINTENANCE

1. Nose Gear Leg Removal/Installation (Refer to Figure 201)

A. Remove Nose Gear Leg(1) Jack aircraft or weight tail of aircraft to raise nose wheel (refer to 07-00-00).(2) Remove nose gear door (refer to 32-31-00).(4) Remove bolt securing nose gear leg to drag strut.(5) Remove front panels and coverings of cabin interior (refer to 25-21-00) to get access to main

bolt of nose landing gear leg.(6) Support nose gear leg or get assistance by another person (7) Remove main bolt securing nose gear leg to front fuselage structure. Access to the nose gear

main bolt is provided from the cockpit (bottom of front fuselage tunnel).(8) Remove nose gear leg from the front fuselage downwards.

B. Install Nose Gear Leg(1) Place nose gear leg in position. Support nose gear leg or get assistance by another person.(2) Install main bolt of nose gear bracket in the front fuselage from the cockpit (bottom of front

fuselage tunnel).(3) Install washer and self-securing nut to bolt.(4) Connect nose gear leg to strut and install bolt securing nose gear leg to drag strut. Install

washer and self-securing nut.(5) Tighten the two bolts securing nose gear leg and secure all nuts with locking varnish. (6) Install panels and coverings of cabin interior (refer to 25-21-00).(7) Re-install nose gear door (refer to 32-31-00).(9) Ensure the steering system is operating properly.

2. Elastomer Parts Removal/Installation

The removal removal of elastomer parts must be performed by an authorized maintenance organisation. For detailled information contact the manufacturer.

3. Ultra-Bushing Removal/Installation (Refer to Figure 201)

A. Remove Ultra-Bushing(1) Remove nose gear leg (refer to pt. 1).(2) Remove locking screws for ultra-bushing bolts from above.(3) Remove bolts for ultra-bushing attachment on both sides.(4) Remove ultra-bushings from nose gear leg.

B. Install Ultra-Bushing(1) Place ultra-bushings into position and install bolts for attachment to nose gear leg.(2) Install locking screws for ultra-bushing bolts from above.(3) Re-install nose gear leg (refer to pt. 1).(4) Perform functional test of nose-wheel steering and locking of nose-wheel steering if

unloaded.

32-20-00Page 201

EFFECTIVITY

Model S6-RT

Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

NOSE GEAR - MAINTENANCE

1. Nose Gear Leg Removal/Installation (Refer to Figure 201)

A. Remove Nose Gear Leg(1) Jack aircraft or weight tail of aircraft to raise nose wheel (refer to 07-00-00).(2) Remove nose gear door (refer to 32-31-00).(4) Remove bolt securing nose gear leg to drag strut.(5) Remove front panels and coverings of cabin interior (refer to 25-21-00) to get access to main

bolt of nose landing gear leg.(6) Support nose gear leg or get assistance by another person (7) Remove main bolt securing nose gear leg to front fuselage structure. Access to the nose gear

main bolt is provided from the cockpit (bottom of front fuselage tunnel).(8) Remove nose gear leg from the front fuselage downwards.

B. Install Nose Gear Leg(1) Place nose gear leg in position. Support nose gear leg or get assistance by another person.(2) Install main bolt of nose gear bracket in the front fuselage from the cockpit (bottom of front

fuselage tunnel).(3) Install washer and self-securing nut to bolt.(4) Connect nose gear leg to strut and install bolt securing nose gear leg to drag strut. Install

washer and self-securing nut.(5) Tighten the two bolts securing nose gear leg and secure all nuts with locking varnish. (6) Install panels and coverings of cabin interior (refer to 25-21-00).(7) Re-install nose gear door (refer to 32-31-00).(9) Ensure the steering system is operating properly.

2. Elastomer Parts Removal/Installation

The removal removal of elastomer parts must be performed by an authorized maintenance organisation. For detailled information contact the manufacturer.

3. Ultra-Bushing Removal/Installation (Refer to Figure 201)

A. Remove Ultra-Bushing(1) Remove nose gear leg (refer to pt. 1).(2) Remove locking screws for ultra-bushing bolts from above.(3) Remove bolts for ultra-bushing attachment on both sides.(4) Remove ultra-bushings from nose gear leg.

B. Install Ultra-Bushing(1) Place ultra-bushings into position and install bolts for attachment to nose gear leg.(2) Install locking screws for ultra-bushing bolts from above.(3) Re-install nose gear leg (refer to pt. 1).(4) Perform functional test of nose-wheel steering and locking of nose-wheel steering if

unloaded.

32-20-00Page 201

EFFECTIVITY

Model S6-RT

Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

Installation of Nose WheelFigure 202

A

ADetail-

32-20-00Page 203

32-20-00Page 202

Nose Gear Leg InstallationFigure 201

A

ADetail-

EFFECTIVITY

Model S6-RT

EFFECTIVITY

Model S6-RT

Front FuselageTunnel Structure

Strut

Nose Gear Leg

Nov 18/11 Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

Installation of Nose WheelFigure 202

A

ADetail-

32-20-00Page 203

32-20-00Page 202

Nose Gear Leg InstallationFigure 201

A

ADetail-

EFFECTIVITY

Model S6-RT

EFFECTIVITY

Model S6-RT

Front FuselageTunnel Structure

Strut

Nose Gear Leg

Nov 18/11 Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

EXTENSION AND RETRACTION - DESCRIPTION

1. Introduction

A. The S6 features a retractable tricycle landing gear with a nose wheel steering. The retracting mechanism for main landing gear and nose landing gear is driven hydraulically.


A. The extension and retraction of the main and nose landing gear is realized for all landing gear legs separate hydraulic actuators. The extension of the landing gear is supported by the tare weight of the landing gear legs.The hydraulic sytem for actuation is pressurized by an hydraulic drive unit, installed in the rear section of the center fuselage steel-frame. The unit consists of the electrically powered hydraulic pump including controller for the pressurization of the complete hydraulic system and a pressure reservoir (or pressure accumulator) for emergency extension of the main and nose landing gear. The pressure reservoir is filled to and is equipped with a pressure gauge (near hydr. drive unit) to check storage pressure. After switching off the hydraulic pump the system pressure is maintained by check valves. With master-switch (Batt) ON the hydraulic drive unit automatically pumps up the system pressure to min. 90 bar / 1305 psi (pressure automatic) if necessary.In the extended end position, the supporting struts of nose and main landing gear legs are secured by a deadlock blocking and additional springs independent from hydraulic pressure.

The extension and retraction is operated by one combined lever switch for nose and main landing gear. The switch is located in the area of the control elements of the instrument panel on the left side of the propeller pitch control unit.

The lever switch provides two settings:- Position UP: RETRACT landing gear- Position DOWN: EXTEND landing gear

The electrical system for actuation and control of the landing gear is protected by three separate circuit breakers (CB):

- 1 CB (25A) for main landing gear- 1 CB (2A) for landing gear control including lever switch and indication lights

The emergency extension of the landing gear (nose and main landing gear legs as well as the gear doors) is operated by a handle located next to the Fuel Shut Off Valve. Pulling the handle bar for the emergency extension of the landing gear releases the valve for emergency extend (VEE) by a bowden cable. The valve opens the pressure reservoir to the hydraulic system, which extends all hydraulic actuators for one time to the final stop and locks in the dead locking position of the particular landing gear drag strut. The tare weight of the landing gear legs has a supporting function.At the same time with operation of emergency extend the lever of the VEE actuation locks and deactivates the hydraulic drive unit, which also turns off the red warning light for drop of pressure.

90 bar / 1305 psi ± 8%

32-30-00Page 01

Nov 18/11

EFFECTIVITY

Model S6-RT

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

EXTENSION AND RETRACTION - DESCRIPTION

1. Introduction

A. The S6 features a retractable tricycle landing gear with a nose wheel steering. The retracting mechanism for main landing gear and nose landing gear is driven hydraulically.


A. The extension and retraction of the main and nose landing gear is realized for all landing gear legs separate hydraulic actuators. The extension of the landing gear is supported by the tare weight of the landing gear legs.The hydraulic sytem for actuation is pressurized by an hydraulic drive unit, installed in the rear section of the center fuselage steel-frame. The unit consists of the electrically powered hydraulic pump including controller for the pressurization of the complete hydraulic system and a pressure reservoir (or pressure accumulator) for emergency extension of the main and nose landing gear. The pressure reservoir is filled to and is equipped with a pressure gauge (near hydr. drive unit) to check storage pressure. After switching off the hydraulic pump the system pressure is maintained by check valves. With master-switch (Batt) ON the hydraulic drive unit automatically pumps up the system pressure to min. 90 bar / 1305 psi (pressure automatic) if necessary.In the extended end position, the supporting struts of nose and main landing gear legs are secured by a deadlock blocking and additional springs independent from hydraulic pressure.

The extension and retraction is operated by one combined lever switch for nose and main landing gear. The switch is located in the area of the control elements of the instrument panel on the left side of the propeller pitch control unit.

The lever switch provides two settings:- Position UP: RETRACT landing gear- Position DOWN: EXTEND landing gear

The electrical system for actuation and control of the landing gear is protected by three separate circuit breakers (CB):

- 1 CB (25A) for main landing gear- 1 CB (2A) for landing gear control including lever switch and indication lights

The emergency extension of the landing gear (nose and main landing gear legs as well as the gear doors) is operated by a handle located next to the Fuel Shut Off Valve. Pulling the handle bar for the emergency extension of the landing gear releases the valve for emergency extend (VEE) by a bowden cable. The valve opens the pressure reservoir to the hydraulic system, which extends all hydraulic actuators for one time to the final stop and locks in the dead locking position of the particular landing gear drag strut. The tare weight of the landing gear legs has a supporting function.At the same time with operation of emergency extend the lever of the VEE actuation locks and deactivates the hydraulic drive unit, which also turns off the red warning light for drop of pressure.

90 bar / 1305 psi ± 8%

32-30-00Page 01

Nov 18/11

EFFECTIVITY

Model S6-RT

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

32-30-00Page 201

EXTENSION AND RETRACTION

1. General

A. The following section describes maintenance procedures on the extension and retraction mechanism of the landing gear.

NOTE: For reinstallation of landing gear legs at least one technical versed person to assist is necessary.

- MAINTENANCE

2. Fill Hydraulic System and Oil Change

A. Replenish Oil (1) Turn landing gear switch in extend-position. Turn master switch ON.(2) Screw out the plug of the hydraulic drive (refer to figure 201). (3) Clean dipstick of the plug.(4) Fill in oil until filling level is between the markings of the plug.(5) Screw the plug completely in and subsequently out to check filling level.(6) Fasten the plug.

B. Change Oil (1) Turn landing gear switch in extend-position. Turn master switch OFF.(2) Perform an emergency-extension.(3) Open the vent screws at the extract side of the hydraulic cylinder and discharge oil.(4) Remove oil tank of the hydraulic drive by loosen the fastening screw at the bottom side.

Empty and clean it.(5) Fasten the vent screws.(6) Re-install the oil tank of the hydraulic drive.(7) Turn lever of the emergency-extension-valve back in vertical position (starting position).(8) Screw out the plug of hydraulic drive and fill in oil.(9) Distribute oil in hydraulic system by turning the master switch ON. Take breaks on time

while replenishing oil due to prevent sucking air into system.(10) Bleed the hydraulic system (refer to pt. 3).

Hydraulic System SchematicFigure 01

Main Gear, right

Nose Gear

Main Gear, left

Pre

ssure

Lin

e R

etr

actio

n

Pre

ssure

Lin

e E

xte

nsio

n

Hyd

raulic D

rive

Emergency-Extension-Valve

Hydraulic System

32-30-00Page 02

Nov 18/11 Nov 18/11

90 bar /1305 psi ± 8%

90 bar /1305 psi ± 8%

EFFECTIVITY

Model S6-RT

EFFECTIVITY

Model S6-RT

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

32-30-00Page 201

EXTENSION AND RETRACTION

1. General

A. The following section describes maintenance procedures on the extension and retraction mechanism of the landing gear.

NOTE: For reinstallation of landing gear legs at least one technical versed person to assist is necessary.

- MAINTENANCE

2. Fill Hydraulic System and Oil Change

A. Replenish Oil (1) Turn landing gear switch in extend-position. Turn master switch ON.(2) Screw out the plug of the hydraulic drive (refer to figure 201). (3) Clean dipstick of the plug.(4) Fill in oil until filling level is between the markings of the plug.(5) Screw the plug completely in and subsequently out to check filling level.(6) Fasten the plug.

B. Change Oil (1) Turn landing gear switch in extend-position. Turn master switch OFF.(2) Perform an emergency-extension.(3) Open the vent screws at the extract side of the hydraulic cylinder and discharge oil.(4) Remove oil tank of the hydraulic drive by loosen the fastening screw at the bottom side.

Empty and clean it.(5) Fasten the vent screws.(6) Re-install the oil tank of the hydraulic drive.(7) Turn lever of the emergency-extension-valve back in vertical position (starting position).(8) Screw out the plug of hydraulic drive and fill in oil.(9) Distribute oil in hydraulic system by turning the master switch ON. Take breaks on time

while replenishing oil due to prevent sucking air into system.(10) Bleed the hydraulic system (refer to pt. 3).

Hydraulic System SchematicFigure 01

Main Gear, right

Nose Gear

Main Gear, left

Pre

ssure

Lin

e R

etr

actio

n

Pre

ssure

Lin

e E

xte

nsio

n

Hyd

raulic D

rive

Emergency-Extension-Valve

Hydraulic System

32-30-00Page 02

Nov 18/11 Nov 18/11

90 bar /1305 psi ± 8%

90 bar /1305 psi ± 8%

EFFECTIVITY

Model S6-RT

EFFECTIVITY

Model S6-RT

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

32-30-00Page 203

32-30-00Page 202

3. Bleed Hydraulic System

(1) Landing Gear legs are extended, drag braces are locked.(2) Loosen rod heads of the hydraulic cylinders off of the drag braces (refer to pt. 5).(3) Open vent screws of the hydraulic cylinders due to bleed the hydraulic system by actuating

the landing gear switch in the cockpit to retract and extend the hydraulic cylinder rods. Pay attention, that sufficient space is available for extention and retraction of the hydraulic cylinder rods.

(4) Turn main switch ON.(5) Retract the hydraulic cylinders.(6) Turn main switch OFF.(7) Perform an emergency-extension.(8) Turn lever of the emergency-extension-valve back in vertical position (starting position).(9) Wait for at least 10 minutes for the oil to settle..(10) Repeat steps (5) to (9).(12) Fasten the vent screws.(13) Reconnect the rod heads with the drag braces (refer to pt. 5).

4. Oil Hoses Removal/Installation (Refer to Figure 201, 202 & 204)

A. Remove an Oil Hose(1) Discharge the pressure from the hydraulic cylinders by the vent screws.(2) Loosen oil hoses off of the hydraulical cylinders, the pressure accumulator and the hydraulic

distribution system.

NOTE: Insert a plug immediately to the oil hoses or provide a collecting vessel to prevent losing oil.

B. Install an Oil Hose(1) Connect oil hoses to the hydraulic cylinders, the pressure accumulator and the hydraulic

distribution system.(2) Screw out the plug of hydraulic drive and fill in oil.(3) Distribute oil in hydraulic system by turning the master switch ON. Take breaks on time

while replenishing oil due to prevent sucking air into system.(4) Bleed the system (refer to pt. 3).

B

A

ADetail-

Hydraulic System InstallationFigure 201

Plug

Hydraulic Drive

BDetail-

May 04/12 Nov 18/11

EFFECTIVITY

Model S6-RT

EFFECTIVITY

Model S6-RT

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

32-30-00Page 203

32-30-00Page 202

3. Bleed Hydraulic System

(1) Landing Gear legs are extended, drag braces are locked.(2) Loosen rod heads of the hydraulic cylinders off of the drag braces (refer to pt. 5).(3) Open vent screws of the hydraulic cylinders due to bleed the hydraulic system by actuating

the landing gear switch in the cockpit to retract and extend the hydraulic cylinder rods. Pay attention, that sufficient space is available for extention and retraction of the hydraulic cylinder rods.

(4) Turn main switch ON.(5) Retract the hydraulic cylinders.(6) Turn main switch OFF.(7) Perform an emergency-extension.(8) Turn lever of the emergency-extension-valve back in vertical position (starting position).(9) Wait for at least 10 minutes for the oil to settle..(10) Repeat steps (5) to (9).(12) Fasten the vent screws.(13) Reconnect the rod heads with the drag braces (refer to pt. 5).

4. Oil Hoses Removal/Installation (Refer to Figure 201, 202 & 204)

A. Remove an Oil Hose(1) Discharge the pressure from the hydraulic cylinders by the vent screws.(2) Loosen oil hoses off of the hydraulical cylinders, the pressure accumulator and the hydraulic

distribution system.


B. Install an Oil Hose(1) Connect oil hoses to the hydraulic cylinders, the pressure accumulator and the hydraulic

distribution system.(2) Screw out the plug of hydraulic drive and fill in oil.(3) Distribute oil in hydraulic system by turning the master switch ON. Take breaks on time

while replenishing oil due to prevent sucking air into system.(4) Bleed the system (refer to pt. 3).

B

A

ADetail-

Hydraulic System InstallationFigure 201

Plug

Hydraulic Drive

BDetail-

May 04/12 Nov 18/11

EFFECTIVITY

Model S6-RT

EFFECTIVITY

Model S6-RT

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

5. Hydraulic Cylinders Removal/Installation (refer to Figure 203 & 204)

A. Remove Hydraulic Cylinder(1) Discharge the pressure from the hydraulic cylinder by the vent screw.(2) Loosen oil hoses off of the hydraulical cylinder.


(3) Loosen bolts of the hydraulic cylinder.

B. Install Hydraulic Cylinder(1) Install bolts of the hydraulic cylinder. (2) Connect the oil hoses to the hydraulic cylinder.(3) Refill oil and bleed hydraulic system (refer to pt. 2 and 3).(4) Ensure the hydraulic cylinder is working properly.

6. Pressure Accumulator Removal/Installation (Refer to Figure 202)

A. Remove Pressure Accumulator(1) Landing Gear legs are extended, drag braces are locked.(2) Turn main switch OFF.(3) Perform an emergency-extension.(4) Turn lever of the emergency-extension-valve back in vertical position (starting position).(5) Open the vent screws of the hydraulic cylinders at the

housing side - main landing gearextract side - nose landing gear

and discharge oil.(6) Remove the oil hose. (7) Remove the pressure accumulator.

B. Install a Pressure Accumulator(1) Install the pressure accumulator.(2) Connect the oil hose.(3) Refill oil and bleed the system (refer to pt. 2 and 3).(4) Check system pressure 90 bar / 1305 psi ± 8% on pressure gauge.

32-30-00Page 205

32-30-00Page 204

A

Extension System Oil Hose InstallationFigure 202

ADetail-

BDetail-

CDetail-DDetail-

Pressure Accumulator

Nov 18/11

EFFECTIVITY

Model S6-RT

EFFECTIVITY

Model S6-RT

May 04/12

CB

D

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

5. Hydraulic Cylinders Removal/Installation (refer to Figure 203 & 204)

A. Remove Hydraulic Cylinder(1) Discharge the pressure from the hydraulic cylinder by the vent screw.(2) Loosen oil hoses off of the hydraulical cylinder.


(3) Loosen bolts of the hydraulic cylinder.

B. Install Hydraulic Cylinder(1) Install bolts of the hydraulic cylinder. (2) Connect the oil hoses to the hydraulic cylinder.(3) Refill oil and bleed hydraulic system (refer to pt. 2 and 3).(4) Ensure the hydraulic cylinder is working properly.

6. Pressure Accumulator Removal/Installation (Refer to Figure 202)

A. Remove Pressure Accumulator(1) Landing Gear legs are extended, drag braces are locked.(2) Turn main switch OFF.(3) Perform an emergency-extension.(4) Turn lever of the emergency-extension-valve back in vertical position (starting position).(5) Open the vent screws of the hydraulic cylinders at the

housing side - main landing gearextract side - nose landing gear

and discharge oil.(6) Remove the oil hose. (7) Remove the pressure accumulator.

B. Install a Pressure Accumulator(1) Install the pressure accumulator.(2) Connect the oil hose.(3) Refill oil and bleed the system (refer to pt. 2 and 3).(4) Check system pressure 90 bar / 1305 psi ± 8% on pressure gauge.

32-30-00Page 205

32-30-00Page 204

A

Extension System Oil Hose InstallationFigure 202

ADetail-

BDetail-

CDetail-DDetail-

Pressure Accumulator

Nov 18/11

EFFECTIVITY

Model S6-RT

EFFECTIVITY

Model S6-RT

May 04/12

CB

D

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

Main Landing Gear Extension System InstallationFigure 203

BDetail-

A

A

ADetail-

Nose Landing Gear Extension System InstallationFigure 204

32-30-00Page 207

Nov 18/11

BDetail-

ADetail-

32-30-00Page 206

EFFECTIVITY

Model S6-RT

EFFECTIVITY

Model S6-RT

May 04/12

B

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

Main Landing Gear Extension System InstallationFigure 203

BDetail-

A

A

ADetail-

Nose Landing Gear Extension System InstallationFigure 204

32-30-00Page 207

Nov 18/11

BDetail-

ADetail-

32-30-00Page 206

EFFECTIVITY

Model S6-RT

EFFECTIVITY

Model S6-RT

May 04/12

B

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

32-31-00Page 01

LANDING GEAR DOORS - DESCRIPTION

1. Introduction

A. The S6 features a retractable tricycle landing gear with landing gear doors for all three landing gear legs and landing gear bays. The landing gear doors are actuated by mechanical linkage to the particular landing gear leg.


A. All three landing gear legs are equipped with separate gear doors to cover each of the landing gear leg and the landing gear bays completely and aerodynamically. The gear doors are open in the extended landing gear configuration and are closed simultaneously with retraction of the landing gear legs.

The doors of the main landing gear are arranged along direction of flow. They are mounted above the landing gears on the side of the center fuselage cowling. The gear doors are mechanical dependent on the landing gear legs and closes with the retraction of the gear legs by drivers of composite material (GRP). In retracted position of the landing gear legs, each door is kept in open position by a pneumatic spring.The nose landing gear has a gear door also arranged along direction of flow. It is mounted sideways to the nose landing gear. The actuation of the door is linked kinematically to the nose landing gear leg.

Nov 18/11

EFFECTIVITY

Model S6-RT

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

32-31-00Page 01

LANDING GEAR DOORS - DESCRIPTION

1. Introduction

A. The S6 features a retractable tricycle landing gear with landing gear doors for all three landing gear legs and landing gear bays. The landing gear doors are actuated by mechanical linkage to the particular landing gear leg.


A. All three landing gear legs are equipped with separate gear doors to cover each of the landing gear leg and the landing gear bays completely and aerodynamically. The gear doors are open in the extended landing gear configuration and are closed simultaneously with retraction of the landing gear legs.

The doors of the main landing gear are arranged along direction of flow. They are mounted above the landing gears on the side of the center fuselage cowling. The gear doors are mechanical dependent on the landing gear legs and closes with the retraction of the gear legs by drivers of composite material (GRP). In retracted position of the landing gear legs, each door is kept in open position by a pneumatic spring.The nose landing gear has a gear door also arranged along direction of flow. It is mounted sideways to the nose landing gear. The actuation of the door is linked kinematically to the nose landing gear leg.

Nov 18/11

EFFECTIVITY

Model S6-RT

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

LANDING GEAR DOORS

1. General

A. The following section describes maintenance procedures on the extension and retraction section of the landing gear doors.

B. For provided instructions necessarry for removal/installation of the main landing gear doors, refer to 71-10-00.

2. Main Landing Gear Doors Removal/Installation

A. Remove Main Landing Gear Door(1) Remove bolt of the rod head of the pneumatic spring.

(2) Loosen bolts of the hinge.(3) Unhinge main landing gear door

B. Install Main Landing Gear Door (1) Install bolts to the hinges.(2) Re-install bolt to the rod head of the pneumatic spring.

3. Nose Landing Gear Door Removal/Installation (Refer to Figure 202)

A. Remove Nose Landing Gear Door(1) Remove bolt of the rod head belonging to the tension spring.

B. Install Nose Landing Gear Door (1)

- MAINTENANCE

(Refer to Figure 201)

CAUTION: The door retracting mechanism is under tension. Loosen bolt without fixing the rod of the tension spring can cause injuries.


(2) Loosen bolts of the hinge.(3) Unhinge nose landing gear door

Install bolts to the hinges.(2) Re-install bolt to the rod head of the tension spring.

32-31-00Page 201

Nov 18/11

EFFECTIVITY

Model S6-RT

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

LANDING GEAR DOORS

1. General

A. The following section describes maintenance procedures on the extension and retraction section of the landing gear doors.

B. For provided instructions necessarry for removal/installation of the main landing gear doors, refer to 71-10-00.

2. Main Landing Gear Doors Removal/Installation

A. Remove Main Landing Gear Door(1) Remove bolt of the rod head of the pneumatic spring.

(2) Loosen bolts of the hinge.(3) Unhinge main landing gear door

B. Install Main Landing Gear Door (1) Install bolts to the hinges.(2) Re-install bolt to the rod head of the pneumatic spring.

3. Nose Landing Gear Door Removal/Installation (Refer to Figure 202)

A. Remove Nose Landing Gear Door(1) Remove bolt of the rod head belonging to the tension spring.

B. Install Nose Landing Gear Door (1)

- MAINTENANCE

(Refer to Figure 201)



(2) Loosen bolts of the hinge.(3) Unhinge nose landing gear door

Install bolts to the hinges.(2) Re-install bolt to the rod head of the tension spring.

32-31-00Page 201

Nov 18/11

EFFECTIVITY

Model S6-RT

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

AB

ADetail-

BDetail-

Nose Landing Gear Door InstallationFigure 202

Main Landing Gear Door InstallationFigure 201

32-31-00Page 202

Nov 18/1132-31-00

Page 203

Nov 18/11

A

ADetail-

ADetail-

EFFECTIVITY

Model S6-RT

EFFECTIVITY

Model S6-RT

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

AB

ADetail-

BDetail-

Nose Landing Gear Door InstallationFigure 202

Main Landing Gear Door InstallationFigure 201

32-31-00Page 202

Nov 18/1132-31-00

Page 203

Nov 18/11

A

ADetail-

ADetail-

EFFECTIVITY

Model S6-RT

EFFECTIVITY

Model S6-RT

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

32-40-00Page 01

WHEELS AND BRAKES - DESCRIPTION

1. Introduction

A. Nose and main landing gear wheels are of conventional design.The wheels of the main landing gear are each equipped with a dual-piston disc brake assembly. The brakes can be locked for parking.


A. The main-wheel brakes are hydraulically actuated and designed as dual-piston disk brakes. The brakes are activated by operating the brake lever at the control stick. The main brake cylinder is located at the brake lever. The expansion reservoir is located at the left hand brake lever (on right brake lever with optional dual brake levers installed). To prevent the brakes from locking, the brake circuit is equipped with an anti lock regulator which is mounted in the mid section of the fuselage.To lock the wheels for parking (hydraulic parking brake), push in the locking pin at the side of the left hand brake lever.

Nov 18/11

EFFECTIVITY

Model S6-RT

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

32-40-00Page 01

WHEELS AND BRAKES - DESCRIPTION

1. Introduction

A. Nose and main landing gear wheels are of conventional design.The wheels of the main landing gear are each equipped with a dual-piston disc brake assembly. The brakes can be locked for parking.


A. The main-wheel brakes are hydraulically actuated and designed as dual-piston disk brakes. The brakes are activated by operating the brake lever at the control stick. The main brake cylinder is located at the brake lever. The expansion reservoir is located at the left hand brake lever (on right brake lever with optional dual brake levers installed). To prevent the brakes from locking, the brake circuit is equipped with an anti lock regulator which is mounted in the mid section of the fuselage.To lock the wheels for parking (hydraulic parking brake), push in the locking pin at the side of the left hand brake lever.

Nov 18/11

EFFECTIVITY

Model S6-RT

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

WHEELS AND BRAKES - MAINTENANCE

1. Main Gear Wheels Removal/Installation (Refer to Figure 201)

A. Remove a Main Gear Wheel(1) Jack aircraft or appropriate to hang up main gear wheel free (Refer to 7-00-00).(2) Remove screws securing wheel fairings and remove wheel fairings.(3) Remove wheel axle nut.(4) Pull wheel from axle.(5) If necessary disconnect brake line at brake caliper and immediately plug or cap hydraulic

fitting and brake line.

WARNING: CONTACT WITH HYDRAULIC FLUID CAN CAUSE SKIN IRRITATIONS.

CAUTION: EXCESSIVE HYDRAULIC FLUID WILL ATTACK THE SURFACE OF VARIOUS MATERIALS. READ AND ADHERE TO ALL MANUFACTURERS INSTRUCTIONS.PROVIDE A SUITABLE COLLECTING VESSEL FOR HYDRAULIC FLUID.

(6) Remove brake caliper if necessary (refer to pt. 6)

B. Install a Main Gear Wheel(1) Install brake caliper if removed (refer to pt. 6).(2) Slide the wheel assembly including brake caliper and back plate onto the axle, with the brake

disc onboard and the valve shaft outboard.Pay attention to put brake caliper back plate into right position onto attaching bolt of rocker arm.

(3) Install self-securing axle nut and finger-tighten. Then, while slowly continuing to tighten with a wrench, simultaneously rotate the wheel assembly by hand. Tighten until a slight resistance in the wheel bearings is obvious.

NOTE: When the axle nut is set in its final position, there should be no resistance to rotation and no side-to-side play in the wheel bearings.

(4) Reconnect brake line to brake caliper if disconnected during removal of main gear wheel.(5) Refill if necessary, and bleed brake system, refer to “Brake System Bleeding” below.(6) Install wheel fairing and secure with screws.

2. Main Gear Wheel Disassembly/Assembly (Refer to Figure 202-1

A. The following procedure describes the main steps for disassembling/assembling of the BERINGER main gear wheel.For further information refer to manual MONT_R5_1, Procedure to change tyre on the BERINGER wheel, latest revision of the BERINGER company.

32-40-00Page 201

32-40-00Page 02

ADetail-

Brake SystemFigure 01

Brake Levers on theControl Sticks

Brake Reservoir

(optional)

Brake Disk LH

Brake Assembly LHBrake Disk RH

Brake Assembly RHBrake PressureRegulator

Note: Sample view, shown with both control sticks equipped with a brake lever (optional)

A

Nov 18/11 Nov 18/11

EFFECTIVITY

Model S6-RT

EFFECTIVITY

Model S6-RT

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

WHEELS AND BRAKES - MAINTENANCE

1. Main Gear Wheels Removal/Installation (Refer to Figure 201)

A. Remove a Main Gear Wheel(1) Jack aircraft or appropriate to hang up main gear wheel free (Refer to 7-00-00).(2) Remove screws securing wheel fairings and remove wheel fairings.(3) Remove wheel axle nut.(4) Pull wheel from axle.(5) If necessary disconnect brake line at brake caliper and immediately plug or cap hydraulic

fitting and brake line.



(6) Remove brake caliper if necessary (refer to pt. 6)

B. Install a Main Gear Wheel(1) Install brake caliper if removed (refer to pt. 6).(2) Slide the wheel assembly including brake caliper and back plate onto the axle, with the brake

disc onboard and the valve shaft outboard.Pay attention to put brake caliper back plate into right position onto attaching bolt of rocker arm.

(3) Install self-securing axle nut and finger-tighten. Then, while slowly continuing to tighten with a wrench, simultaneously rotate the wheel assembly by hand. Tighten until a slight resistance in the wheel bearings is obvious.

NOTE: When the axle nut is set in its final position, there should be no resistance to rotation and no side-to-side play in the wheel bearings.

(4) Reconnect brake line to brake caliper if disconnected during removal of main gear wheel.(5) Refill if necessary, and bleed brake system, refer to “Brake System Bleeding” below.(6) Install wheel fairing and secure with screws.

2. Main Gear Wheel Disassembly/Assembly (Refer to Figure 202-1

A. The following procedure describes the main steps for disassembling/assembling of the BERINGER main gear wheel.For further information refer to manual MONT_R5_1, Procedure to change tyre on the BERINGER wheel, latest revision of the BERINGER company.

32-40-00Page 201

32-40-00Page 02

ADetail-

Brake SystemFigure 01

Brake Levers on theControl Sticks

Brake Reservoir

(optional)

Brake Disk LH

Brake Assembly LHBrake Disk RH

Brake Assembly RHBrake PressureRegulator

Note: Sample view, shown with both control sticks equipped with a brake lever (optional)

A

Nov 18/11 Nov 18/11

EFFECTIVITY

Model S6-RT

EFFECTIVITY

Model S6-RT

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

Main Gear Wheel Installation (Illustration of leg shows fix Landing Gear)Figure 201

B. Tools, Equipment and Material

Required Quantity Equipment Parts No. Supplierin

9.D 1 OUT-AV-SUP-INT OPA 01 BERINGER6.D 1 OUT-AV-SUP-EXT OPA 01 BERINGER

The tools OUT-AV-SUP-INT and OUT-AV-SUP-EXT can be manufactured from drawings attached to manual MONT_R5_1, latest revision from BERINGER company. Alternatively the tools (incl. screws and conical spacer) can be ordered as kit for 5” wheels from BERINGER company under P/N OPA01. Without this tools a proper mounting could not be guaranteed.

C. Disassemble a Main Gear Wheel

WARNING: DO NOT ATTEMPT SEPARATE WHEEL HALVES BEFORE TIRES COMPLETELY ARE DEFLATED.

(1) Completely deflate tire to zero pressure.(2) Unscrew the needle valve.(3) Remove brake disc (pt. 7).(4) Separate the tire from the two sides of the wheel:

Press with a vice till the tire is separated, turn 90° wise and press again until the tire iscompletely separated. Use tire mounting lubricant to facilitate separation of the tire.

(5) Check the tire is completely free from the wheel (tire can rotate on the wheel by handturning). Tire mounting lubricant makes separation easier.

(6) Remove eight M6 screws connecting connecting left and right wheel half.(7) Extract the side of the wheel which has the disc brackets. Pull up delicately by hand.

Be carefull to the O-ring used for sealing.(8) Remove tire from the other two parts of the wheel carefully. Use tire mounting lubricant to

facilitate removal.There must not be used any tools for this operation.

(9) Remove O-rings of second wheel half and small O-ring for valve.(10) Clean all parts of the tire carefully if removed completely.

D. Assemble a Main Gear Wheel(1) For assembly all parts must be clean and dry. New O-rings have to be used for each new

assembling.(2) Remove needle valve insert with appropriate tool from valve.(3) Insert an axle diameter 3 mm without sharp edges in the valve hole of the wheel flange. The

axle has to stick out of the valve end slightly. Slide the small O-ring (clean and dry) onto the axle on the inboard flange.

(4) Check the ring groove is free from dirt. Insert the large O-ring (clean and dry) to the ring groove.

(5) Place the wheel flange spacer to the wheel flange. Pay attention to correct positioning of valve insert.Press wheel flange and spacer with hand and check the two parts are in contact.

(6) Place wheel flange and spacer on the assembling tool with the smaller diameter.

32-40-00Page 203

ADetail-

32-40-00Page 202

Brake Caliper Assemblywith Back Plate

Brake Disc

Wheel Axle

Nov 18/11 Nov 18/11

A

EFFECTIVITY

Model S6-RT

EFFECTIVITY

Model S6-RT

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

Main Gear Wheel Installation (Illustration of leg shows fix Landing Gear)Figure 201



9.D 1 OUT-AV-SUP-INT OPA 01 BERINGER6.D 1 OUT-AV-SUP-EXT OPA 01 BERINGER

The tools OUT-AV-SUP-INT and OUT-AV-SUP-EXT can be manufactured from drawings attached to manual MONT_R5_1, latest revision from BERINGER company. Alternatively the tools (incl. screws and conical spacer) can be ordered as kit for 5” wheels from BERINGER company under P/N OPA01. Without this tools a proper mounting could not be guaranteed.

C. Disassemble a Main Gear Wheel

WARNING: DO NOT ATTEMPT SEPARATE WHEEL HALVES BEFORE TIRES COMPLETELY ARE DEFLATED.

(1) Completely deflate tire to zero pressure.(2) Unscrew the needle valve.(3) Remove brake disc (pt. 7).(4) Separate the tire from the two sides of the wheel:

Press with a vice till the tire is separated, turn 90° wise and press again until the tire iscompletely separated. Use tire mounting lubricant to facilitate separation of the tire.

(5) Check the tire is completely free from the wheel (tire can rotate on the wheel by handturning). Tire mounting lubricant makes separation easier.

(6) Remove eight M6 screws connecting connecting left and right wheel half.(7) Extract the side of the wheel which has the disc brackets. Pull up delicately by hand.

Be carefull to the O-ring used for sealing.(8) Remove tire from the other two parts of the wheel carefully. Use tire mounting lubricant to

facilitate removal.There must not be used any tools for this operation.

(9) Remove O-rings of second wheel half and small O-ring for valve.(10) Clean all parts of the tire carefully if removed completely.

D. Assemble a Main Gear Wheel(1) For assembly all parts must be clean and dry. New O-rings have to be used for each new

assembling.(2) Remove needle valve insert with appropriate tool from valve.(3) Insert an axle diameter 3 mm without sharp edges in the valve hole of the wheel flange. The

axle has to stick out of the valve end slightly. Slide the small O-ring (clean and dry) onto the axle on the inboard flange.

(4) Check the ring groove is free from dirt. Insert the large O-ring (clean and dry) to the ring groove.

(5) Place the wheel flange spacer to the wheel flange. Pay attention to correct positioning of valve insert.Press wheel flange and spacer with hand and check the two parts are in contact.

(6) Place wheel flange and spacer on the assembling tool with the smaller diameter.

32-40-00Page 203

ADetail-

32-40-00Page 202

Brake Caliper Assemblywith Back Plate

Brake Disc

Wheel Axle

Nov 18/11 Nov 18/11

A

EFFECTIVITY

Model S6-RT

EFFECTIVITY

Model S6-RT

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

Wheel Assembly (general gross view, without Brake Disc)Figure 202 - 1 Tightening Sequence Wheel Assembly

Figure 202 - 2

(7) Clean tire flanges with thinner and spray the flanges with tire mounting lubricant.(8) Slide new tire onto wheel flange spacer. Use tire mounting lubricant and conical tool if

necessary.

NOTE: Pay attention to correct rotational position of the tire: The colored triangle/marking on tire must be in front of the valve!

(9) Place the second part of the assembling tool (bigger diameter) to the tire. Insert the three bolts.

(10) Press the tire by tightening the bolts until the tire flange is completely below the level of the horizontal surface of the wheel flange spacer.

(11) Clean horizontal surface of the wheel flange spacer.(12) Clean second wheel flange and ensure there is no dirt in the ring groove. Insert O-ring to the

ring groove.(13) Place the wheel assembly incl. assembling tool on the second wheel flange. Pay attention to

keep the O-ring in correct position in the ring groove during placement.(14) Put Loctite (blue) to the end of each wheel screw and insert screws to the wheel flange side of

the valve. Torque 8 screws M6 to contact (2 to 4 Nm [20 to 40 lb.in]).(15) Torque screws to 10 Nm [90 lb.in]. Follow the prescribed tightening sequence (refer to Figure

202 - 2). After completion torque each screw a second time.(16) Remove axle for small O-ring positioning from the valve and screw needle valve.(17) Inflate tire to appropriate pressure (refer to 12-16-00). After 24 hours check the leakage/drop

in pressure is not more than 10%. Reinflate if necessary and screw cap.(18) Install brake disc (pt. 7).

3

5

7

2

4

6

8

1

O-Ring Seal

32-40-00Page 205

ADetail-

32-40-00Page 204

Wheel Flange

Wheel FlangeWheel FlangeSpacer

Position Valve

in.lbs

90+/-2

A

A

Nov 18/11 Nov 18/11

EFFECTIVITY

Model S6-RT

EFFECTIVITY

Model S6-RT

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

Wheel Assembly (general gross view, without Brake Disc)Figure 202 - 1 Tightening Sequence Wheel Assembly

Figure 202 - 2

(7) Clean tire flanges with thinner and spray the flanges with tire mounting lubricant.(8) Slide new tire onto wheel flange spacer. Use tire mounting lubricant and conical tool if

necessary.

NOTE: Pay attention to correct rotational position of the tire: The colored triangle/marking on tire must be in front of the valve!

(9) Place the second part of the assembling tool (bigger diameter) to the tire. Insert the three bolts.

(10) Press the tire by tightening the bolts until the tire flange is completely below the level of the horizontal surface of the wheel flange spacer.

(11) Clean horizontal surface of the wheel flange spacer.(12) Clean second wheel flange and ensure there is no dirt in the ring groove. Insert O-ring to the

ring groove.(13) Place the wheel assembly incl. assembling tool on the second wheel flange. Pay attention to

keep the O-ring in correct position in the ring groove during placement.(14) Put Loctite (blue) to the end of each wheel screw and insert screws to the wheel flange side of

the valve. Torque 8 screws M6 to contact (2 to 4 Nm [20 to 40 lb.in]).(15) Torque screws to 10 Nm [90 lb.in]. Follow the prescribed tightening sequence (refer to Figure

202 - 2). After completion torque each screw a second time.(16) Remove axle for small O-ring positioning from the valve and screw needle valve.(17) Inflate tire to appropriate pressure (refer to 12-16-00). After 24 hours check the leakage/drop

in pressure is not more than 10%. Reinflate if necessary and screw cap.(18) Install brake disc (pt. 7).

3

5

7

2

4

6

8

1

O-Ring Seal

32-40-00Page 205

ADetail-

32-40-00Page 204

Wheel Flange

Wheel FlangeWheel FlangeSpacer

Position Valve

in.lbs

90+/-2

A

A

Nov 18/11 Nov 18/11

EFFECTIVITY

Model S6-RT

EFFECTIVITY

Model S6-RT

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

Brake Caliper AssemblyFigure 203

3. Nose Gear Wheel Removal/Installation

A. Remove Nose Gear Wheel(1) Jack aircraft or weight tail of aircraft to raise nose wheel, refer to Chapter 7, “Lifting and

Shoring”.(2) Remove screws securing wheel fairing and remove wheel fairing.(3) Remove axle bolt from wheel fork.(4) Remove cap bushings from wheel fork arms.(5) Remove nose wheel assembly backwards from wheel fork.

B. Install Nose Gear Wheel(1) Slide the whole wheel assembly (with axle, spacers, and washers in position) between wheel

fork arms.(2) Insert cap bushings into wheel fork arms.(3) Insert axle bolt and torque self-securing nut until slight bearing drag, when the wheel is

rotated. Then, back off nut to nearest castellation and install pin.

NOTE: When the axle bolt nut is set in its final position, there should be no resistance to rotation and no side-to-side play in the wheel bearings.

(4) Install wheel fairing.

4. Nose Gear Wheel Disassembly/Assembly

A. The procedure for disassembly/assembly and change of tire for the nose gear wheel is identical to the procedures described for the main gear wheels (except of inapplicable brake discs).Refer to pt. 2 for further information and description of procedures.

5. Brake Lever / Brake Master Cylinder Removal/Installation

A. The pilot’s control stick (optional also control stick for the co-pilot) is equipped with a brake lever and integrated brake master cylinder.



B. Remove a Brake Master Cylinder(1) Remove bleeder fitting at wheel brake caliper and drain hydraulic fluid from master brake

cylinders.(2) Disconnect brake lever including brake master cylinder from pilot control stick (optional also

from co-pilot control stick in combination with brake fluid reservoir).(3) Disconnect hydraulic brake line hoses from master cylinder and remove brake lever and

brake master cylinder from the aircraft.(4) Plug or cap hydraulic fittings, hoses and lines to prevent the entry of contaminants.

32-40-00Page 207

32-40-00Page 206

Brake CaliperAssembly

Brake Disc

Back Plate

A

Nov 18/11 Nov 18/11

EFFECTIVITY

Model S6-RT

EFFECTIVITY

Model S6-RT

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

Brake Caliper AssemblyFigure 203

3. Nose Gear Wheel Removal/Installation

A. Remove Nose Gear Wheel(1) Jack aircraft or weight tail of aircraft to raise nose wheel, refer to Chapter 7, “Lifting and

Shoring”.(2) Remove screws securing wheel fairing and remove wheel fairing.(3) Remove axle bolt from wheel fork.(4) Remove cap bushings from wheel fork arms.(5) Remove nose wheel assembly backwards from wheel fork.

B. Install Nose Gear Wheel(1) Slide the whole wheel assembly (with axle, spacers, and washers in position) between wheel

fork arms.(2) Insert cap bushings into wheel fork arms.(3) Insert axle bolt and torque self-securing nut until slight bearing drag, when the wheel is

rotated. Then, back off nut to nearest castellation and install pin.

NOTE: When the axle bolt nut is set in its final position, there should be no resistance to rotation and no side-to-side play in the wheel bearings.

(4) Install wheel fairing.

4. Nose Gear Wheel Disassembly/Assembly

A. The procedure for disassembly/assembly and change of tire for the nose gear wheel is identical to the procedures described for the main gear wheels (except of inapplicable brake discs).Refer to pt. 2 for further information and description of procedures.

5. Brake Lever / Brake Master Cylinder Removal/Installation

A. The pilot’s control stick (optional also control stick for the co-pilot) is equipped with a brake lever and integrated brake master cylinder.



B. Remove a Brake Master Cylinder(1) Remove bleeder fitting at wheel brake caliper and drain hydraulic fluid from master brake

cylinders.(2) Disconnect brake lever including brake master cylinder from pilot control stick (optional also

from co-pilot control stick in combination with brake fluid reservoir).(3) Disconnect hydraulic brake line hoses from master cylinder and remove brake lever and

brake master cylinder from the aircraft.(4) Plug or cap hydraulic fittings, hoses and lines to prevent the entry of contaminants.

32-40-00Page 207

32-40-00Page 206

Brake CaliperAssembly

Brake Disc

Back Plate

A

Nov 18/11 Nov 18/11

EFFECTIVITY

Model S6-RT

EFFECTIVITY

Model S6-RT

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

NOTE: Brake master cylinder repair should be accomplished according to manufacturer's specifications.

B. Install a Brake Master Cylinder(1) Connect hydraulic hoses to brake master cylinder.(2) Place brake lever with brake master cylinder into position and connect brake master cylinder

to control stick.(3) Install bleeder fitting at wheel brake caliper.(4) Refill and bleed brake system, refer to “Brake System Bleeding” below.(5) Test brake system and ensure brakes are operating properly, refer to “Adjustment/Test”.

6. Brake Caliper Removal/Installation



A. Remove a Caliper(1) Disconnect brake line at brake caliper and immediately plug or cap hydraulic fitting and

brake line.(2) Remove main gear wheels to get access to brake caliper back plate (refer to pt. 1).(3) Slide caliper housing with counter pressure plate and back plate inward away from the wheel

brake disc and remove caliper from the wheel.(4) Remove the three bolts that secure the brake caliper assembly to back plate and remove back

plate.

B. Install a Caliper(1) Install back plate to brake caliper assembly with three bolts. Pay attention to correct mounting

direction of back plate. Secure bolts with locking varnish. (2) Push back brake cylinder pistons with brake lining. Only use finger force. (3) Slide the caliper housing with brake cylinders, brake linings, counter pressure plate and back

plate onto the brake disc from wheel inward direction.(4) Install main gear wheels with brake caliper assembly and back plate to wheel axle and rocker

arm (refer to pt. 1).(5) Reconnect brake line to brake caliper.(6) Refill if necessary, and bleed brake system (refer to pt. 9).(7) Test brake system and ensure brakes are operating properly, refer to “Adjustment/Test”.

7. Brake Disc Removal/Installation

Minimum allowable brake disc thickness is 2.6 mm [1/10 in.].

A. Remove Brake Disc(1) Remove main gear wheel from main gear leg, refer to “Main Gear Wheels

Removal/Installation” (refer pt. 1) above.(2) Slide away brake caliper and remove from wheel to get full access to brake disc (refer to pt. 6).(3) Remove securing wire fixing the brake disc to wheel flange in axial direction.(4) Remove brake disc.

B. Install Brake Disc

NOTE: Before reinstalling the brake disc, inspect brake disc for camber and excessive scoring. Scoring should not be deeper than 0.5 mm [2/100 in.].

(1) Install brake disc to tooth system of main wheel flange.(2) Install securing wire around wheel flange brim to fix the brake disc to wheel flange in axial

direction.

32-40-00Page 209

32-40-00Page 208

Brake Caliper and Brake Disc AssemblyFigure 204

Brake Disc

Brake Caliper Housing

Counter Pressure Platewith Brake Lining

Brake Lining

Brake Caliper Back Plate

Nov 18/11 Nov 18/11

EFFECTIVITY

Model S6-RT

EFFECTIVITY

Model S6-RT

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

NOTE: Brake master cylinder repair should be accomplished according to manufacturer's specifications.

B. Install a Brake Master Cylinder(1) Connect hydraulic hoses to brake master cylinder.(2) Place brake lever with brake master cylinder into position and connect brake master cylinder

to control stick.(3) Install bleeder fitting at wheel brake caliper.(4) Refill and bleed brake system, refer to “Brake System Bleeding” below.(5) Test brake system and ensure brakes are operating properly, refer to “Adjustment/Test”.

6. Brake Caliper Removal/Installation



A. Remove a Caliper(1) Disconnect brake line at brake caliper and immediately plug or cap hydraulic fitting and

brake line.(2) Remove main gear wheels to get access to brake caliper back plate (refer to pt. 1).(3) Slide caliper housing with counter pressure plate and back plate inward away from the wheel

brake disc and remove caliper from the wheel.(4) Remove the three bolts that secure the brake caliper assembly to back plate and remove back

plate.

B. Install a Caliper(1) Install back plate to brake caliper assembly with three bolts. Pay attention to correct mounting

direction of back plate. Secure bolts with locking varnish. (2) Push back brake cylinder pistons with brake lining. Only use finger force. (3) Slide the caliper housing with brake cylinders, brake linings, counter pressure plate and back

plate onto the brake disc from wheel inward direction.(4) Install main gear wheels with brake caliper assembly and back plate to wheel axle and rocker

arm (refer to pt. 1).(5) Reconnect brake line to brake caliper.(6) Refill if necessary, and bleed brake system (refer to pt. 9).(7) Test brake system and ensure brakes are operating properly, refer to “Adjustment/Test”.

7. Brake Disc Removal/Installation

Minimum allowable brake disc thickness is 2.6 mm [1/10 in.].

A. Remove Brake Disc(1) Remove main gear wheel from main gear leg, refer to “Main Gear Wheels

Removal/Installation” (refer pt. 1) above.(2) Slide away brake caliper and remove from wheel to get full access to brake disc (refer to pt. 6).(3) Remove securing wire fixing the brake disc to wheel flange in axial direction.(4) Remove brake disc.

B. Install Brake Disc

NOTE: Before reinstalling the brake disc, inspect brake disc for camber and excessive scoring. Scoring should not be deeper than 0.5 mm [2/100 in.].

(1) Install brake disc to tooth system of main wheel flange.(2) Install securing wire around wheel flange brim to fix the brake disc to wheel flange in axial

direction.

32-40-00Page 209

32-40-00Page 208

Brake Caliper and Brake Disc AssemblyFigure 204

Brake Disc

Brake Caliper Housing

Counter Pressure Platewith Brake Lining

Brake Lining

Brake Caliper Back Plate

Nov 18/11 Nov 18/11

EFFECTIVITY

Model S6-RT

EFFECTIVITY

Model S6-RT

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

(3) Install brake caliper assembly including back plate to brake disc (refer to pt. 6).(4) Install main gear wheel (refer to pt. 1).

8. Brake Lining / Brake Pads Replacement

Minimum allowable brake pads thickness (brake lining without base plate) is 1.0 mm [4/100 in.].

A. The following procedure describes the main steps for replacement of the BERINGER brake pads.For further information refer to manual MONT_PADS_1, Procedure to change brake pads on 2 piston caliper, latest revision of the BERINGER company.

B. Remove Brake Linings(1) Remove caliper from main gear wheel, as described in pt. 6.(2) Remove three bolts M8 fixing counter pressure plate to brake caliper housing assembly. If

necessary heat the caliper to 60-80°C [140-176°F] to loose the bolts.(3) Remove brake pads from pistons and counter pressure plate.(4) Clean around the pistons with a dry cloth.(5) Push back the two pistons with one finger (no force needed). If you cannot push back the

piston with one finger, the caliper must be checked and rebuilt.

C. Install Brake Lining(1) Position the new pads against pistons of caliper and second one against counter pressure

plate. Assemble caliper and counter pressure plate with brake pads in between.(2) Insert three bolts for assembling caliper, counter pressure plate and brake pads. Put blue

Loctite 243 on the end of each bolt.(3) Torque bolts to 25 Nm [220 lb.in]. Secure with locking varnish.(3) Reinstall brake caliper assembly to main gear wheel (refer to pt. 6).

9. Brake Hoses Replacement



A. Remove Brake Hoses(1) Remove left and right center fuselage cowlings and lower cowling (refer to 06-30-00 and

71-10-00).(2) Remove seats, lower seat coverings and front fuselage tunnel cover (refer to 25-10-00 and

25-21-00).(3) Place some cloth below the particular brake hoses area to absorb potentially dripping brake

fluid.(4) Empty the hydraulic fluid reservoir using a pipette to minimize the potentially dripping

brake fluid volume.

NOTE: The hydraulic fluid reservoir is located at the pilot's brake lever or if installed (optionally) at the co-pilot's brake lever.

32-40-00Page 210

(5) Remove/loosen clamp holders attaching brake hoses to main landing gear legs, control stick and to aircraft structure.

(6) Disconnect brake hoses on both ends from brake system components.(7) Remove/replace brake hoses one after another.(8) Pull out brake hoses from front fusealge structure (below seat bulkhead) carefully.(9) Remove brake hoses from aircraft.

B. Install Brake Hoses(1) Fit new cable protection to particular brake hoses with contact to structure.(2) Install brake hoses to airframe. Lead front fuselage brake hoses through seat bulkhead. Pay

attention to correct routing.(3) Install clamp holders attaching brake hoses to main landing gear legs, control stick and to

aircraft structure.(4) Connect brake hoses on both ends to brake system components.(5) Install front fuselage tunnel cover, lower seat coverings and seats (refer to 25-10-00 and

25-21-00).(6) Install center fuselage cowlings (refer to 06-30-00 and 71-10-00).(7) Replenish brake system (refer to 12-15-00).(8) Bleed brake system (refer to pt. 10).(9) Perform functional test.

10. Brake System Bleeding

A. After any maintenance at the brake system (component replacement etc.), or in case of non-correct function of the system because of trapped air, the system must be bled.



3.A 1 Transparent PVC Hose, 3 m (9.8 ft.) HZ-KSL 041 Stemme3.A 1 Transparent PVC Hose, 10 cm (4 in.) HZ-KSL 041 Stemme3.A AR Hydraulic Fluid DOT 4 - any

3.A 1 Syringe 150 – 250 ml - any

3.A 1 Spanner, Width 11 mm - any3.A 1 Torx Driver T15 - any3.A AR Cleaning Rags -3.A AR Cable Ties - any

C. Bleed the brake system as follows:

CAUTION: LAY CLEANING RAGS AROUND THE PILOT STICK BASE (IF THE CO-PILOT

STICK IS EQUIPPED WITH A BRAKE LEVER – AROUND THE CO-PILOT STICK

BASE) TO PROTECT CABIN INTERIOR AGAINST SOILING.

(1) Open the reservoir at the pilot stick (optional at the co-pilot stick) with a torx driver T15.(2) Connect the HZ-KSL041 hose (approx. 10 cm [4 in.]) to the syringe.

32-40-00Page 211

Nov 18/11 Nov 18/11

EFFECTIVITY

Model S6-RT

EFFECTIVITY

Model S6-RT

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

(3) Install brake caliper assembly including back plate to brake disc (refer to pt. 6).(4) Install main gear wheel (refer to pt. 1).

8. Brake Lining / Brake Pads Replacement

Minimum allowable brake pads thickness (brake lining without base plate) is 1.0 mm [4/100 in.].

A. The following procedure describes the main steps for replacement of the BERINGER brake pads.For further information refer to manual MONT_PADS_1, Procedure to change brake pads on 2 piston caliper, latest revision of the BERINGER company.

B. Remove Brake Linings(1) Remove caliper from main gear wheel, as described in pt. 6.(2) Remove three bolts M8 fixing counter pressure plate to brake caliper housing assembly. If

necessary heat the caliper to 60-80°C [140-176°F] to loose the bolts.(3) Remove brake pads from pistons and counter pressure plate.(4) Clean around the pistons with a dry cloth.(5) Push back the two pistons with one finger (no force needed). If you cannot push back the

piston with one finger, the caliper must be checked and rebuilt.

C. Install Brake Lining(1) Position the new pads against pistons of caliper and second one against counter pressure

plate. Assemble caliper and counter pressure plate with brake pads in between.(2) Insert three bolts for assembling caliper, counter pressure plate and brake pads. Put blue

Loctite 243 on the end of each bolt.(3) Torque bolts to 25 Nm [220 lb.in]. Secure with locking varnish.(3) Reinstall brake caliper assembly to main gear wheel (refer to pt. 6).

9. Brake Hoses Replacement



A. Remove Brake Hoses(1) Remove left and right center fuselage cowlings and lower cowling (refer to 06-30-00 and

71-10-00).(2) Remove seats, lower seat coverings and front fuselage tunnel cover (refer to 25-10-00 and

25-21-00).(3) Place some cloth below the particular brake hoses area to absorb potentially dripping brake

fluid.(4) Empty the hydraulic fluid reservoir using a pipette to minimize the potentially dripping

brake fluid volume.

NOTE: The hydraulic fluid reservoir is located at the pilot's brake lever or if installed (optionally) at the co-pilot's brake lever.

32-40-00Page 210

(5) Remove/loosen clamp holders attaching brake hoses to main landing gear legs, control stick and to aircraft structure.

(6) Disconnect brake hoses on both ends from brake system components.(7) Remove/replace brake hoses one after another.(8) Pull out brake hoses from front fusealge structure (below seat bulkhead) carefully.(9) Remove brake hoses from aircraft.

B. Install Brake Hoses(1) Fit new cable protection to particular brake hoses with contact to structure.(2) Install brake hoses to airframe. Lead front fuselage brake hoses through seat bulkhead. Pay

attention to correct routing.(3) Install clamp holders attaching brake hoses to main landing gear legs, control stick and to

aircraft structure.(4) Connect brake hoses on both ends to brake system components.(5) Install front fuselage tunnel cover, lower seat coverings and seats (refer to 25-10-00 and

25-21-00).(6) Install center fuselage cowlings (refer to 06-30-00 and 71-10-00).(7) Replenish brake system (refer to 12-15-00).(8) Bleed brake system (refer to pt. 10).(9) Perform functional test.

10. Brake System Bleeding

A. After any maintenance at the brake system (component replacement etc.), or in case of non-correct function of the system because of trapped air, the system must be bled.



3.A 1 Transparent PVC Hose, 3 m (9.8 ft.) HZ-KSL 041 Stemme3.A 1 Transparent PVC Hose, 10 cm (4 in.) HZ-KSL 041 Stemme3.A AR Hydraulic Fluid DOT 4 - any

3.A 1 Syringe 150 – 250 ml - any

3.A 1 Spanner, Width 11 mm - any3.A 1 Torx Driver T15 - any3.A AR Cleaning Rags -3.A AR Cable Ties - any

C. Bleed the brake system as follows:

CAUTION: LAY CLEANING RAGS AROUND THE PILOT STICK BASE (IF THE CO-PILOT

STICK IS EQUIPPED WITH A BRAKE LEVER – AROUND THE CO-PILOT STICK

BASE) TO PROTECT CABIN INTERIOR AGAINST SOILING.

(1) Open the reservoir at the pilot stick (optional at the co-pilot stick) with a torx driver T15.(2) Connect the HZ-KSL041 hose (approx. 10 cm [4 in.]) to the syringe.

32-40-00Page 211

Nov 18/11 Nov 18/11

EFFECTIVITY

Model S6-RT

EFFECTIVITY

Model S6-RT

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

(3) Fill the syringe with DOT4.(5) Check all fittings for firm fit.(6) Connect the syringe to the right main wheel bleeder valve (the most far point in relation to the

reservoir).(7) Open bleeder valve with spanner (11 mm ) and pump hydraulic fluid into system until the fluid

level in the reservoir rises.(8) Close bleeder valve at the right main wheel.(9) Fill the long hose (approx. 3m [9.8 ft.]) completely with hydraulic fluid.(10) Connect the hose to the bleeder valve at the right main wheel.(11) Lay the other hose end into the reservoir and fix it by suitable means to prevent it from falling

(e.g. tape or cable tie).(12) Observing the fluid in the brake system reservoir, press the brake lever several times until air

bubbles cease to appear. Make sure the reservoir doesn't become empty. Refill hydraulic fluid on time.

CAUTION: AVOID OVERFILLING OF THE RESERVOIR! THIS CAN CAUSE SOILING OR DAMAGE TO THE COCKPIT EQUIPMENT.

(13) Close bleeder valve at the right main wheel.(14) Connect the filled with hydraulic fluid hose to the bleeder valve at the left main wheel.(15) Repeat steps 11 thru 13.(16) If required repeat bleeding procedure at the right main wheel.

NOTE: If both sticks are equipped with a brake lever (option), remove the brake lever from the pilot stick and lay it down horizontally in the cockpit. Do not disconnect the fluid lines!Then, during bleeding procedure move this brake lever some times slightly to remove trapped air from the lever system itself.Install brake lever after bleeding procedure is completed.

11. Adjustment/Test

A. There is no need to adjust the brakes since the brake pistons move to compensate for brake and wear.

B. After component replacement or repair:(1) Check the brakes for firm brake lever pressure and bleed the system if either brake feels spongy.(2) Perform a minimum of six stops from a speed of between 45 and 75 km/h [25 and 40 kts], using

light brake lever effort and letting the brakes cool partially (about one minute) between stops. Check the aircraft is not turning from centerline while apply brake lever.

(3) Check all fittings and hoses for any leakage.

32-40-00Page 212

Nov 18/11

CHAPTER 33

LIGHTS

EFFECTIVITY

Model S6-RT

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

(3) Fill the syringe with DOT4.(5) Check all fittings for firm fit.(6) Connect the syringe to the right main wheel bleeder valve (the most far point in relation to the

reservoir).(7) Open bleeder valve with spanner (11 mm ) and pump hydraulic fluid into system until the fluid

level in the reservoir rises.(8) Close bleeder valve at the right main wheel.(9) Fill the long hose (approx. 3m [9.8 ft.]) completely with hydraulic fluid.(10) Connect the hose to the bleeder valve at the right main wheel.(11) Lay the other hose end into the reservoir and fix it by suitable means to prevent it from falling

(e.g. tape or cable tie).(12) Observing the fluid in the brake system reservoir, press the brake lever several times until air

bubbles cease to appear. Make sure the reservoir doesn't become empty. Refill hydraulic fluid on time.

CAUTION: AVOID OVERFILLING OF THE RESERVOIR! THIS CAN CAUSE SOILING OR DAMAGE TO THE COCKPIT EQUIPMENT.

(13) Close bleeder valve at the right main wheel.(14) Connect the filled with hydraulic fluid hose to the bleeder valve at the left main wheel.(15) Repeat steps 11 thru 13.(16) If required repeat bleeding procedure at the right main wheel.

NOTE: If both sticks are equipped with a brake lever (option), remove the brake lever from the pilot stick and lay it down horizontally in the cockpit. Do not disconnect the fluid lines!Then, during bleeding procedure move this brake lever some times slightly to remove trapped air from the lever system itself.Install brake lever after bleeding procedure is completed.

11. Adjustment/Test

A. There is no need to adjust the brakes since the brake pistons move to compensate for brake and wear.

B. After component replacement or repair:(1) Check the brakes for firm brake lever pressure and bleed the system if either brake feels spongy.(2) Perform a minimum of six stops from a speed of between 45 and 75 km/h [25 and 40 kts], using

light brake lever effort and letting the brakes cool partially (about one minute) between stops. Check the aircraft is not turning from centerline while apply brake lever.

(3) Check all fittings and hoses for any leakage.

32-40-00Page 212

Nov 18/11

CHAPTER 33

LIGHTS

EFFECTIVITY

Model S6-RT

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

Page 0133 - TOC

TABLE OF CONTENTS

ChapterSection

Title Subject Page Effectivity

EQUIPMENT / FURNISHINGS - GENERAL................................................33-00-00 1Introduction 33-00-00 1General Description 33-00-00 1

INTERIOR LIGHTS - MAINTENANCE PRACTICES..................................33-10-00 201 Int. LightsGeneral 33-10-00 201 Int. LightsTools, Equipment and Material 33-10-00 201 Int. LightsFlood Light Assembly Removal/Installation 33-10-00 203 Int. LightsFlood Light Assembly Replacement 33-10-00 203 Int. Lights

EXTERIOR LIGHTS - MAINTENANCE PRACTICES .................................33-40-00 201 Ext. LightsGeneral 33-40-00 201 Ext. LightsTools, Equipment and Material 33-40-00 201 Ext. LightsLanding Light Removal/Installation 33-40-00 201 Ext. LightsNavigation / Position Light Replacement 33-40-00 201 Ext. LightsAnti-Collision Strobe Light Assembly Removal/Installation 33-40-00 202 Ext. Lights

Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

Page 0133 - TOC

TABLE OF CONTENTS

ChapterSection


EQUIPMENT / FURNISHINGS - GENERAL................................................33-00-00 1Introduction 33-00-00 1General Description 33-00-00 1

INTERIOR LIGHTS - MAINTENANCE PRACTICES..................................33-10-00 201 Int. LightsGeneral 33-10-00 201 Int. LightsTools, Equipment and Material 33-10-00 201 Int. LightsFlood Light Assembly Removal/Installation 33-10-00 203 Int. LightsFlood Light Assembly Replacement 33-10-00 203 Int. Lights

EXTERIOR LIGHTS - MAINTENANCE PRACTICES .................................33-40-00 201 Ext. LightsGeneral 33-40-00 201 Ext. LightsTools, Equipment and Material 33-40-00 201 Ext. LightsLanding Light Removal/Installation 33-40-00 201 Ext. LightsNavigation / Position Light Replacement 33-40-00 201 Ext. LightsAnti-Collision Strobe Light Assembly Removal/Installation 33-40-00 202 Ext. Lights

Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

33-00-00Page 01

LIGHTS - GENERAL

1. Introduction

A. This chapter describes interior and exterior lighting systems used on the STEMME S6, including removal and installation procedures of components and light bulb replacement instructions.

2. General Description

A. Interior lighting (optional) is provided by a soft red flood light installed in the cockpit aft under the fuel shut off valve console. The floodlight illuminates the instrumentation and slightly the cabin interior without glaring the pilots or reflecting on the canopy.Additionally most of the avionics equipment (optional) is internal lighted. Refer to appropriate manufacturer's publications for maintenance instruction.

B. Exterior lighting (optional) consists of navigation lights and a single landing light.The navigation lights, located in the wing tip position of the winglets, provide integral anti-collision strobe lights and position lights.The landing light is a flood light mounted to the nose gear strut.

Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

33-00-00Page 01

LIGHTS - GENERAL

1. Introduction

A. This chapter describes interior and exterior lighting systems used on the STEMME S6, including removal and installation procedures of components and light bulb replacement instructions.


A. Interior lighting (optional) is provided by a soft red flood light installed in the cockpit aft under the fuel shut off valve console. The floodlight illuminates the instrumentation and slightly the cabin interior without glaring the pilots or reflecting on the canopy.Additionally most of the avionics equipment (optional) is internal lighted. Refer to appropriate manufacturer's publications for maintenance instruction.

B. Exterior lighting (optional) consists of navigation lights and a single landing light.The navigation lights, located in the wing tip position of the winglets, provide integral anti-collision strobe lights and position lights.The landing light is a flood light mounted to the nose gear strut.

Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

INTERIOR LIGHTS - MAINTENANCE PRACTICE

1. General

A. The maintenance of the interior light is limited to removal and installation of the flood light and LED array replacement.

2. Tools, Equipment and Material

Required in Quantity Equipment Parts No. Manufacturer4.A. 1 Flood Light LED - -

Array

3. Flood Light Assembly Removal/Installation

A. Remove Flood Light Assembly(1) Disconnect flood light electrical wires.(3) Remove flood light mounting from fuel shut off valve console.

B. Install Flood Light Assembly(1) Install flood light mounting from fuel shut off valve console.(2) Connect flood light electrical wires.(3) Perform functional check, adjust flood light if necessary.

4. Flood Light LED Replacement

A. Flood Light LED Array Replacement(1) Ensure BAT and Instrument light switches are in OFF position.(2) Remove flood light assembly (refer pt. 3).(3) Replace flood light LED array by new one.(4) Install flood light assembly (refer pt. 3).

33-10-00Page 201

EFFECTIVITY

Aircraft equipped with Interior Lights

Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

INTERIOR LIGHTS - MAINTENANCE PRACTICE

1. General

A. The maintenance of the interior light is limited to removal and installation of the flood light and LED array replacement.


Required in Quantity Equipment Parts No. Manufacturer4.A. 1 Flood Light LED - -

Array

3. Flood Light Assembly Removal/Installation

A. Remove Flood Light Assembly(1) Disconnect flood light electrical wires.(3) Remove flood light mounting from fuel shut off valve console.

B. Install Flood Light Assembly(1) Install flood light mounting from fuel shut off valve console.(2) Connect flood light electrical wires.(3) Perform functional check, adjust flood light if necessary.

4. Flood Light LED Replacement

A. Flood Light LED Array Replacement(1) Ensure BAT and Instrument light switches are in OFF position.(2) Remove flood light assembly (refer pt. 3).(3) Replace flood light LED array by new one.(4) Install flood light assembly (refer pt. 3).

33-10-00Page 201

EFFECTIVITY

Aircraft equipped with Interior Lights

Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

EXTERIOR LIGHTS - MAINTENANCE PRACTICE

1. General

A. The maintenance of exterior lights is limited to removal and installation of components, and light LED array replacement. NAV lights and landing lights consist of LED arrays. In case of failure the complete light array has to be replaced.


Required in Quantity Equipment Parts No. Manufacturer3.A. 1 Ldg. Light LED - -4.A. 1 Nav. Light LED - -4.A. 1 Pos. Light LED - -4.B. 1 Flash Tube Assy - -

3. Landing Light LED Replacement

A. Replace Landing Light LED array holder(1) Remove landing light diffuser lens by removing screws.(2) Pull LED array holder carefully out of landing light housing. Disconnect electrical wires.(3) Replace LED array holder by new one and connect to electrical wires.(4) Install LED array holder carefully to landing light housing. Pay attention not to break or

clamp the wiring.(5) Install landing light diffuser lens using screws.(6) Perform functional check, adjust landing light if necessary.

C. Landing Light Inspection/Check(1) Turn BAT switch ON.(2) Turn LDG light ON.(3) Verify the landing light works properly.(4) Turn OFF all switches.

4. Navigation / Position Light LED Replacement

A. Navigation / Position Light LED Replacement(1) Ensure BAT, POS and ACL switches are in OFF position.(2) Remove screws securing NAV/POS light LED assembly to winglet. Carefully remove

assembly from winglet.(3) Disconnect electrical wires.(4) Replace LED light assembly by new one and connect to electrical wires.(5) Insert assembly to socket of winglet and fix with two srews.

33-40-00Page 201

EFFECTIVITY

Aircraft equipped with Exterior Lights

Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

EXTERIOR LIGHTS - MAINTENANCE PRACTICE

1. General

A. The maintenance of exterior lights is limited to removal and installation of components, and light LED array replacement. NAV lights and landing lights consist of LED arrays. In case of failure the complete light array has to be replaced.


Required in Quantity Equipment Parts No. Manufacturer3.A. 1 Ldg. Light LED - -4.A. 1 Nav. Light LED - -4.A. 1 Pos. Light LED - -4.B. 1 Flash Tube Assy - -

3. Landing Light LED Replacement

A. Replace Landing Light LED array holder(1) Remove landing light diffuser lens by removing screws.(2) Pull LED array holder carefully out of landing light housing. Disconnect electrical wires.(3) Replace LED array holder by new one and connect to electrical wires.(4) Install LED array holder carefully to landing light housing. Pay attention not to break or

clamp the wiring.(5) Install landing light diffuser lens using screws.(6) Perform functional check, adjust landing light if necessary.

C. Landing Light Inspection/Check(1) Turn BAT switch ON.(2) Turn LDG light ON.(3) Verify the landing light works properly.(4) Turn OFF all switches.

4. Navigation / Position Light LED Replacement

A. Navigation / Position Light LED Replacement(1) Ensure BAT, POS and ACL switches are in OFF position.(2) Remove screws securing NAV/POS light LED assembly to winglet. Carefully remove

assembly from winglet.(3) Disconnect electrical wires.(4) Replace LED light assembly by new one and connect to electrical wires.(5) Insert assembly to socket of winglet and fix with two srews.

33-40-00Page 201

EFFECTIVITY


Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

B. Navigation / Position Lights Inspection/Check(1) Turn BAT switch ON.(2) Turn POS and ACL switch ON.(3) Verify the navigation / position lights works properly.(4) Turn OFF all switches.

5. Anti-Collision Strobe Light Assembly Replacement

WARNING: HIGH VOLTAGE! ENSURE ELECTRICAL POWER TO STROBE LIGHT SYSTEM IS OFF.

NOTE: Removal and installation is typical for both the left wing anti-collision strobe light assembly and the right wing anti-collision strobe light assembly.

A. Replace Anti-Collision Strobe Light Assembly(1) Ensure BAT, POS and ACL switches are in OFF position.(2) Remove screws securing strobe light module to winglet. Carefully remove light assembly.(3) Disconnect electrical wire at connector.(4) Replace strobe light module and connect to electrical wires at connector.(5) Carefully install light assembly to winglet and fix with screws.

B. Anti-Collision Strobe Light Inspection/Check(1) Turn BAT switch ON.(2) Turn ACL switch ON.(3) Verify the anti-collision strobe light works properly.(4) Turn OFF all switches.

33-40-00Page 202

33-40-00Page 203

EFFECTIVITY


EFFECTIVITY


Exterior Lights InstallationFigure 201

A

A

ADetail-

Nov 18/11Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

B. Navigation / Position Lights Inspection/Check(1) Turn BAT switch ON.(2) Turn POS and ACL switch ON.(3) Verify the navigation / position lights works properly.(4) Turn OFF all switches.

5. Anti-Collision Strobe Light Assembly Replacement

WARNING: HIGH VOLTAGE! ENSURE ELECTRICAL POWER TO STROBE LIGHT SYSTEM IS OFF.

NOTE: Removal and installation is typical for both the left wing anti-collision strobe light assembly and the right wing anti-collision strobe light assembly.

A. Replace Anti-Collision Strobe Light Assembly(1) Ensure BAT, POS and ACL switches are in OFF position.(2) Remove screws securing strobe light module to winglet. Carefully remove light assembly.(3) Disconnect electrical wire at connector.(4) Replace strobe light module and connect to electrical wires at connector.(5) Carefully install light assembly to winglet and fix with screws.

B. Anti-Collision Strobe Light Inspection/Check(1) Turn BAT switch ON.(2) Turn ACL switch ON.(3) Verify the anti-collision strobe light works properly.(4) Turn OFF all switches.

33-40-00Page 202

33-40-00Page 203

EFFECTIVITY


EFFECTIVITY


Exterior Lights InstallationFigure 201

A

A

ADetail-

Nov 18/11Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

CHAPTER 34

NAVIGATION

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

CHAPTER 34

NAVIGATION

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

Page 0134 - TOC

TABLE OF CONTENTS

ChapterSection


NAVIGATION - GENERAL..............................................................................34-00-00 1Introduction 34-00-00 1General Description 34-00-00 1

PITOT/STATIC SYSTEM - DESCRIPTION ....................................................34-10-00 1 ProfessionalIntroduction 34-10-00 1 ProfessionalDescription and Operation 34-10-00 1 Professional

PITOT/STATIC SYSTEM - MAINTENANCE PRACTICES..........................34-10-00 201General 34-10-00 201Pitot Tube Removal/Installation 34-10-00 201Instruments Removal/Installation 34-10-00 201Inspection/Check 34-10-00 201

STALL WARNING SYSTEM - DESCRIPTION .............................................34-11-00 1Introduction 34-11-00 1Description and Operation 34-11-00 1

STALL WARNING SYSTEM - MAINTENANCE PRACTICES ...................34-11-00 201General 34-11-00 201Transmitter Removal/Installation 34-11-00 201Adjustment 34-11-00 201

ATTITUDE AND DIRECTION - TROUBLESHOOTING ...........................34-20-00 101 ProfessionalGeneral 34-20-00 101 ProfessionalTroubleshooting EFIS D-10A 34-20-00 101 Professional

ATTITUDE AND DIRECTION - MAINTENANCE PRACTICES...............34-20-00 201 ProfessionalGeneral 34-20-00 201 ProfessionalMagnetic Compass Removal/Installation 34-20-00 201 ProfessionalEFIS D-10A Removal/Installation 34-20-00 201 ProfessionalAdjustment/Test 34-20-00 202 Professional

ATTITUDE AND DIRECTION - MAINTENANCE PRACTICES...............34-20-00 201 ClassicGeneral 34-20-00 201 ClassicMagnetic Compass Removal/Installation 34-20-00 201 ClassicAdjustment/Test 34-20-00 201 Classic

ATTITUDE AND DIRECTION - TROUBLESHOOTING ...........................34-20-00 101 AdvancedGeneral 34-20-00 101 AdvancedTroubleshooting EFIS D-10A 34-20-00 101 Advanced

Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

Page 0134 - TOC

TABLE OF CONTENTS

ChapterSection


NAVIGATION - GENERAL..............................................................................34-00-00 1Introduction 34-00-00 1General Description 34-00-00 1

PITOT/STATIC SYSTEM - DESCRIPTION ....................................................34-10-00 1 ProfessionalIntroduction 34-10-00 1 ProfessionalDescription and Operation 34-10-00 1 Professional

PITOT/STATIC SYSTEM - MAINTENANCE PRACTICES..........................34-10-00 201General 34-10-00 201Pitot Tube Removal/Installation 34-10-00 201Instruments Removal/Installation 34-10-00 201Inspection/Check 34-10-00 201

STALL WARNING SYSTEM - DESCRIPTION .............................................34-11-00 1Introduction 34-11-00 1Description and Operation 34-11-00 1

STALL WARNING SYSTEM - MAINTENANCE PRACTICES ...................34-11-00 201General 34-11-00 201Transmitter Removal/Installation 34-11-00 201Adjustment 34-11-00 201

ATTITUDE AND DIRECTION - TROUBLESHOOTING ...........................34-20-00 101 ProfessionalGeneral 34-20-00 101 ProfessionalTroubleshooting EFIS D-10A 34-20-00 101 Professional

ATTITUDE AND DIRECTION - MAINTENANCE PRACTICES...............34-20-00 201 ProfessionalGeneral 34-20-00 201 ProfessionalMagnetic Compass Removal/Installation 34-20-00 201 ProfessionalEFIS D-10A Removal/Installation 34-20-00 201 ProfessionalAdjustment/Test 34-20-00 202 Professional

ATTITUDE AND DIRECTION - MAINTENANCE PRACTICES...............34-20-00 201 ClassicGeneral 34-20-00 201 ClassicMagnetic Compass Removal/Installation 34-20-00 201 ClassicAdjustment/Test 34-20-00 201 Classic

ATTITUDE AND DIRECTION - TROUBLESHOOTING ...........................34-20-00 101 AdvancedGeneral 34-20-00 101 AdvancedTroubleshooting EFIS D-10A 34-20-00 101 Advanced

Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

34-00-00Page 01

NAVIGATION - GENERAL

1. Introduction

A. This chapter describes units and components that provide aircraft navigational information.


A. Different instruments and devices offer a means of determining the flight conditions, aircraft attitude and the position of the aircraft over the groundThe following groups can be separated according to way data is sourced:

(1) The Flight Environmental Data / Pitot Static Section (Refer to 34-10-00) describes systems which sense environmental conditions and use the data to influence navigation. Includes items that depend on the pitot/static system such as vertical speed indicator, airspeed indicator, and altimeter.

(2) The Stall Warning Section (Refer to 34-11-00) describes the Stall Warning System which uses aerodynamic forces.

(3) The Attitude and Direction Section (Refer to 34-20-00) describes systems which use magnetic, gyroscopic and inertia forces. Includes the magnetic compass.

(4) The Independent Position Determining Section (Refer to 34-40-00) describes systems which provide information to determine position and is mainly independent of ground installations. Includes the global position system (GPS).

(5) The Dependent Position Determining Section (Refer to 34-50-00) describes systems which provide information to determine position and is mainly dependent on ground installations. This includes items such as the transponder.

ATTITUDE AND DIRECTION - MAINTENANCE PRACTICES...............34-20-00 201 AdvancedGeneral 34-20-00 201 AdvancedMagnetic Compass Removal/Installation 34-20-00 201 AdvancedEFIS D-10A Removal/Installation 34-20-00 201 AdvancedAdjustment/Test 34-20-00 202 Advanced

INDEPENDENT POSITION DETERMINING –

TROUBLESHOOTING.....................................................................................34-40-00 101 ProfessionalGeneral 34-40-00 101 ProfessionalTroubleshooting 34-40-00 101 Professional

NDEPENDENT POSITION DETERMINING –

MAINTENANCE PRACTICES ........................................................................34-40-00 201 ProfessionalGeneral 34-40-00 201 ProfessionalGarmin GNS 430 Unit Removal/Installation 34-40-00 201 ProfessionalGPS Antenna Removal/Installation 34-40-00 202 ProfessionalInspection/Check 34-40-00 202 Professional


MAINTENANCE PRACTICES ........................................................................34-40-00 201 AdvancedGeneral 34-40-00 201 AdvancedGarmin GPSMAP 695 Unit Removal/Installation 34-40-00 201 AdvancedGPS Antenna Removal/Installation 34-40-00 202 AdvancedInspection/Check 34-40-00 202 Advanced

DEPENDENT POSITIONING DETERMINING –

MAINTENANCE PRACTICES .......................................................................34-50-00 201 ProfessionalGeneral 34-50-00 201 ProfessionalGarmin GTX 330 Transponder Removal/Installation 34-50-00 202 ProfessionalTransponder Antenna Removal/Installation 34-50-00 202 Professional

34 - TOCPage 02

TABLE OF CONTENTS (Continued)

ChapterSection


Nov 18/11Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

34-00-00Page 01

NAVIGATION - GENERAL

1. Introduction

A. This chapter describes units and components that provide aircraft navigational information.


A. Different instruments and devices offer a means of determining the flight conditions, aircraft attitude and the position of the aircraft over the groundThe following groups can be separated according to way data is sourced:

(1) The Flight Environmental Data / Pitot Static Section (Refer to 34-10-00) describes systems which sense environmental conditions and use the data to influence navigation. Includes items that depend on the pitot/static system such as vertical speed indicator, airspeed indicator, and altimeter.

(2) The Stall Warning Section (Refer to 34-11-00) describes the Stall Warning System which uses aerodynamic forces.

(3) The Attitude and Direction Section (Refer to 34-20-00) describes systems which use magnetic, gyroscopic and inertia forces. Includes the magnetic compass.

(4) The Independent Position Determining Section (Refer to 34-40-00) describes systems which provide information to determine position and is mainly independent of ground installations. Includes the global position system (GPS).

(5) The Dependent Position Determining Section (Refer to 34-50-00) describes systems which provide information to determine position and is mainly dependent on ground installations. This includes items such as the transponder.

ATTITUDE AND DIRECTION - MAINTENANCE PRACTICES...............34-20-00 201 AdvancedGeneral 34-20-00 201 AdvancedMagnetic Compass Removal/Installation 34-20-00 201 AdvancedEFIS D-10A Removal/Installation 34-20-00 201 AdvancedAdjustment/Test 34-20-00 202 Advanced

INDEPENDENT POSITION DETERMINING –

TROUBLESHOOTING.....................................................................................34-40-00 101 ProfessionalGeneral 34-40-00 101 ProfessionalTroubleshooting 34-40-00 101 Professional


MAINTENANCE PRACTICES ........................................................................34-40-00 201 ProfessionalGeneral 34-40-00 201 ProfessionalGarmin GNS 430 Unit Removal/Installation 34-40-00 201 ProfessionalGPS Antenna Removal/Installation 34-40-00 202 ProfessionalInspection/Check 34-40-00 202 Professional


MAINTENANCE PRACTICES ........................................................................34-40-00 201 AdvancedGeneral 34-40-00 201 AdvancedGarmin GPSMAP 695 Unit Removal/Installation 34-40-00 201 AdvancedGPS Antenna Removal/Installation 34-40-00 202 AdvancedInspection/Check 34-40-00 202 Advanced

DEPENDENT POSITIONING DETERMINING –

MAINTENANCE PRACTICES .......................................................................34-50-00 201 ProfessionalGeneral 34-50-00 201 ProfessionalGarmin GTX 330 Transponder Removal/Installation 34-50-00 202 ProfessionalTransponder Antenna Removal/Installation 34-50-00 202 Professional

34 - TOCPage 02

TABLE OF CONTENTS (Continued)

ChapterSection


Nov 18/11Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

PITOT / STATIC SYSTEM - DESCRIPTION

1. Introduction

A. The static and Pitot pressure system supplies Pitot and static pressure for the airspeed indicator, the altimeter and the vertical speed indicator


A. Pitot-Static Tube and LinesThe Pitot and static pressures are picked up by the Pitot-static tube, installed on the leading edge of the left inner wing tip, and carried through lines inside the wing and fuselage to the gauges on the instrument panel.Both the pitot- and the static pressure lines have filter elements to prevent foreign matters such as dust or water from entering the flight instruments. The filter elements located in the line front Instrument Panel area may be easily replaced.

B. Fig. 01 shows the Pitot/Static System schematically.

34-10-00Page 01

EFFECTIVITY

Aircraft equipped with Professional Line Avionics

Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

PITOT / STATIC SYSTEM - DESCRIPTION

1. Introduction

A. The static and Pitot pressure system supplies Pitot and static pressure for the airspeed indicator, the altimeter and the vertical speed indicator


A. Pitot-Static Tube and LinesThe Pitot and static pressures are picked up by the Pitot-static tube, installed on the leading edge of the left inner wing tip, and carried through lines inside the wing and fuselage to the gauges on the instrument panel.Both the pitot- and the static pressure lines have filter elements to prevent foreign matters such as dust or water from entering the flight instruments. The filter elements located in the line front Instrument Panel area may be easily replaced.

B. Fig. 01 shows the Pitot/Static System schematically.

34-10-00Page 01

EFFECTIVITY


Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

Pitot-Static System SchematicFigure 1

PITOT/STATIC SYSTEM - MAINTENANCE PRACTICES

1. General

A. Proper maintenance of Pitot/static system is essential for proper indicating of altimeter, air speed indicator, and vertical speed indicator. Moisture, obstructions, and leaks in the system will result erroneous, erratic, or zero readings on the associated instruments.Filters should be regularly inspected and replaced if required.

B. The Pitot-static tube should be removed and a cover should be placed over the Pitot head while the aircraft is parked, to prevent insects and water from entering the pitot orifice at the wing port. For further information refer to 10-10-00 and to the aircraft Flight Manual.

CAUTION: NEVER BLOW COMPRESSED AIR THROUGH PITOT OR STATIC LINES TOWARD INSTRUMENTS THIS CAN CAUSE DAMAGE TO INSTRUMENTS.


Required in Quantity Equipment Parts No. Manufacturer

5.B. 1 Sphygmo- - commerciallymanometer Pres- availablesure Bulb withCheck Valve

5.B. 1 Surgical Hose commerciallyavailable

3. Instruments Removal/Installation

A. Removal of an Instrument

CAUTION! PLUG OR CAP INSTRUMENT PORTS IMMEDIATELY AFTER DISCONNECTING PITOT OR STATIC LINES TO PREVENT ENTRY OF DIRT OR FOREIGN MATERIAL.

(1) Gain access to the back of instrument and disconnect static or/and Pitot tube from instrument.

(2) Remove screws securing instrument to instrument panel.(3) Remove instrument.

B. Installation of an instrument(1) Place instrument onto the instrument panel and secure with screws.(2) Reconnect static or/and Pitot tube to instrument.

34-10-00Page 201

34-10-00Page 02

Filters

redblue

EncoderAirspeed Indicator

Altimeter

Mech. Variometer

Pitot -Static T ube

AS P

EFIS D-10A

Left Wing

Flask

Soaring Computer

Quick Connector

Total Pressure

Static Pressure

EFFECTIVITY


Nov 18/11Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

Pitot-Static System SchematicFigure 1

PITOT/STATIC SYSTEM - MAINTENANCE PRACTICES

1. General

A. Proper maintenance of Pitot/static system is essential for proper indicating of altimeter, air speed indicator, and vertical speed indicator. Moisture, obstructions, and leaks in the system will result erroneous, erratic, or zero readings on the associated instruments.Filters should be regularly inspected and replaced if required.

B. The Pitot-static tube should be removed and a cover should be placed over the Pitot head while the aircraft is parked, to prevent insects and water from entering the pitot orifice at the wing port. For further information refer to 10-10-00 and to the aircraft Flight Manual.

CAUTION: NEVER BLOW COMPRESSED AIR THROUGH PITOT OR STATIC LINES TOWARD INSTRUMENTS THIS CAN CAUSE DAMAGE TO INSTRUMENTS.


Required in Quantity Equipment Parts No. Manufacturer

5.B. 1 Sphygmo- - commerciallymanometer Pres- availablesure Bulb withCheck Valve

5.B. 1 Surgical Hose commerciallyavailable

3. Instruments Removal/Installation

A. Removal of an Instrument

CAUTION! PLUG OR CAP INSTRUMENT PORTS IMMEDIATELY AFTER DISCONNECTING PITOT OR STATIC LINES TO PREVENT ENTRY OF DIRT OR FOREIGN MATERIAL.

(1) Gain access to the back of instrument and disconnect static or/and Pitot tube from instrument.

(2) Remove screws securing instrument to instrument panel.(3) Remove instrument.

B. Installation of an instrument(1) Place instrument onto the instrument panel and secure with screws.(2) Reconnect static or/and Pitot tube to instrument.

34-10-00Page 201

34-10-00Page 02

Filters

redblue

EncoderAirspeed Indicator

Altimeter

Mech. Variometer

Pitot -Static T ube

AS P

EFIS D-10A

Left Wing

Flask

Soaring Computer

Quick Connector

Total Pressure

Static Pressure

EFFECTIVITY


Nov 18/11Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

4. Inspection/Check

A. After any component replacement or repair, the system should be checked for proper function and a leakage test should be performed.

B. Pitot System Leak Test(1) Fasten surgical hose and sphygmomanometer bulb over Pitot head.(2) Pump bulb until airspeed indicator registers 270 km/h IAS [145 KIAS].(3) Close check valve.(4) Wait 15 seconds for airspeed indicator to stabilize.(5) Observe airspeed indicator for one minute.(6) The airspeed drop should no more than 20 km/h IAS [10 KIAS].(7) Slowly release check valve so pressure is reduced gradually to prevent instrument damage.(8) If test reveals a leak in system, check all connections for tightness and repair faulty

components.

C. Static System Leak Test(1) At pitot-static tube tape over static ports..(2) Insert a “T” in a static pressure line.(3) Squeeze sphygmomanometer bulb and close check valve to establish a vacuum inside bulb.(4) Connect sphygmomanometer to the static pressure line.(5) Slowly open air bulb check valve until altimeter indicates a-1000-foot increase in altitude then

close check valve to trap suction in system.(6) While increasing suction and altimeter indicating 1000 feet, ensure that the airspeed indicator

shows an increase and the vertical speed indicator shows a climb indication.(7) Leakage shall not exceed 100 feet of altitude loss as indicated on the altimeter.(8) If leakage rate exceeds the maximum allowable, check all fittings and hoses for condition and

tightness and repeat leak test.(9) If leakage rate still exceeds the maximum allowable, perform the following procedure:(10) Disconnect static pressure lines from airspeed indicator, vertical speed indicator and altitude

encoder.(11) Connect lines together using suitable fittings so altimeter is the only instrument still

connected into static pressure system.(12) Repeat leak test to ascertain whether the static pressure system or the bypassed instruments

are causing the leakage. If instruments are fault, they must be repaired by an approved repair station or replaced. If static pressure system is faulty, proceed as follows:

CAUTION: DO NOT APPLY POSITIVE PRESSURE WITH AIRSPEED INDICATOR OR VERTICAL SPEED INDICATOR CONNECTED TO STATIC PRESSURE SYSTEM.

(13) Remove sphygmomanometer assembly.(14) Insert a “T” in a static pressure line.(15) Attach hose to “T” and slowly apply positive pressure until altimeter indicates a 500-foot

decrease in altitude. Maintain this altimeter indication while checking for leaks.(16) Coat line with a solution of mild soap and water, watching for bubbles to locate leaks.(17) Tighten leaking connections. Repair or replace defective components.(18) Reconnect airspeed, vertical speed indicator and altitude encoder. Repeat static system leak

test

34-10-00Page 202

STALL WARNING SYSTEM - DESCRIPTION

1. Introduction

A. The aircraft is equipped in with a stall warning system. It signals an approaching stall to the pilot by an audible alarm in the cockpit.


A. The stall warning system consists of a mechanical transmitter, located in the leading edge of the left outer section of the inner wing and a warning buzzer behind the instrument panel. Both are connected by electrical wires.

B. As the aircraft approaches a stall, the low pressure on the upper surface of the wings moves forward around the leading edge of the wings. As a result, a micro plate at the transmitter is deflected upwards. A mechanical contact is made thereby sending an electrical signal to the warning buzzer in the cockpit.

34-11-00Page 01

Nov 18/11Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

4. Inspection/Check

A. After any component replacement or repair, the system should be checked for proper function and a leakage test should be performed.

B. Pitot System Leak Test(1) Fasten surgical hose and sphygmomanometer bulb over Pitot head.(2) Pump bulb until airspeed indicator registers 270 km/h IAS [145 KIAS].(3) Close check valve.(4) Wait 15 seconds for airspeed indicator to stabilize.(5) Observe airspeed indicator for one minute.(6) The airspeed drop should no more than 20 km/h IAS [10 KIAS].(7) Slowly release check valve so pressure is reduced gradually to prevent instrument damage.(8) If test reveals a leak in system, check all connections for tightness and repair faulty

components.

C. Static System Leak Test(1) At pitot-static tube tape over static ports..(2) Insert a “T” in a static pressure line.(3) Squeeze sphygmomanometer bulb and close check valve to establish a vacuum inside bulb.(4) Connect sphygmomanometer to the static pressure line.(5) Slowly open air bulb check valve until altimeter indicates a-1000-foot increase in altitude then

close check valve to trap suction in system.(6) While increasing suction and altimeter indicating 1000 feet, ensure that the airspeed indicator

shows an increase and the vertical speed indicator shows a climb indication.(7) Leakage shall not exceed 100 feet of altitude loss as indicated on the altimeter.(8) If leakage rate exceeds the maximum allowable, check all fittings and hoses for condition and

tightness and repeat leak test.(9) If leakage rate still exceeds the maximum allowable, perform the following procedure:(10) Disconnect static pressure lines from airspeed indicator, vertical speed indicator and altitude

encoder.(11) Connect lines together using suitable fittings so altimeter is the only instrument still

connected into static pressure system.(12) Repeat leak test to ascertain whether the static pressure system or the bypassed instruments

are causing the leakage. If instruments are fault, they must be repaired by an approved repair station or replaced. If static pressure system is faulty, proceed as follows:

CAUTION: DO NOT APPLY POSITIVE PRESSURE WITH AIRSPEED INDICATOR OR VERTICAL SPEED INDICATOR CONNECTED TO STATIC PRESSURE SYSTEM.

(13) Remove sphygmomanometer assembly.(14) Insert a “T” in a static pressure line.(15) Attach hose to “T” and slowly apply positive pressure until altimeter indicates a 500-foot

decrease in altitude. Maintain this altimeter indication while checking for leaks.(16) Coat line with a solution of mild soap and water, watching for bubbles to locate leaks.(17) Tighten leaking connections. Repair or replace defective components.(18) Reconnect airspeed, vertical speed indicator and altitude encoder. Repeat static system leak

test

34-10-00Page 202

STALL WARNING SYSTEM - DESCRIPTION

1. Introduction

A. The aircraft is equipped in with a stall warning system. It signals an approaching stall to the pilot by an audible alarm in the cockpit.


A. The stall warning system consists of a mechanical transmitter, located in the leading edge of the left outer section of the inner wing and a warning buzzer behind the instrument panel. Both are connected by electrical wires.

B. As the aircraft approaches a stall, the low pressure on the upper surface of the wings moves forward around the leading edge of the wings. As a result, a micro plate at the transmitter is deflected upwards. A mechanical contact is made thereby sending an electrical signal to the warning buzzer in the cockpit.

34-11-00Page 01

Nov 18/11Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

STALL WARNING SYSTEM - MAINTENANCE PRACTICES

1. General

A. The system is maintenance-free.Under winter conditions, make sure that the system transmitter micro plate is always clear from ice and snow.

2. Transmitter Removal/Installation

A. Remove Transmitter(1) Remove screws securing transmitter to wing structure. Carefully remove transmitter trough

opening from wing.(4) Label and disconnect electrical connectors.

B. Install Transmitter(1) Connect electrical connectors.(2) Place transmitter into position and secure with four screws to wing leading edge structure.

3. Adjustment

A. The stall warning system is adjusted that way the system will come into actionapprox. 6 - 12 km/h (3.5 - 6.5 kts) before aircraft stalls.If the values are not achieved, bend the transmitter metal sheet 1 to 2 mm up or down carefully by using an appropriate caliper. A test for proper system operation is only possible in flight. Repeat procedure until transmitter sheet is in the correct place.

34-11-00Page 201

Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

STALL WARNING SYSTEM - MAINTENANCE PRACTICES

1. General

A. The system is maintenance-free.Under winter conditions, make sure that the system transmitter micro plate is always clear from ice and snow.

2. Transmitter Removal/Installation

A. Remove Transmitter(1) Remove screws securing transmitter to wing structure. Carefully remove transmitter trough

opening from wing.(4) Label and disconnect electrical connectors.

B. Install Transmitter(1) Connect electrical connectors.(2) Place transmitter into position and secure with four screws to wing leading edge structure.

3. Adjustment

A. The stall warning system is adjusted that way the system will come into actionapprox. 6 - 12 km/h (3.5 - 6.5 kts) before aircraft stalls.If the values are not achieved, bend the transmitter metal sheet 1 to 2 mm up or down carefully by using an appropriate caliper. A test for proper system operation is only possible in flight. Repeat procedure until transmitter sheet is in the correct place.

34-11-00Page 201

Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

ATTITUDE AND DIRECTION - TROUBLESHOOTING

1. General

A. This section lists some of the more common troubles, which may be encountered in maintaining the Dynon Avionics EFIS D-10A, their probable causes and remedies.

B. If a problem on the EFIS D-10A occurs, at first check all electrical connections and wiring for proper conditions..

2. Troubleshooting EFIS D-10A

A. Refer to wiring diagrams P308-150.013 and P312-250.011.

B. The EFIS includes a lot of setup possibilities. Please refer to owners manual of the EFIS and check the actual settings at the EFIS first.

34-20-00Page 101

Trouble Probable Cause Remedy

No display on EFIS when Avionics Master is switched on (dark screen)

No power supply at EFIS Check related CB and the connector at the unit

No magnetic heading displayed Remote magnetic sensor not connected

Check electrical connection and actual setup

Deviation between EFIS magnetic heading and magnetic compass >10°

Remote magnetic sensor and/or magnetic compass not compensated

Perform magnetic compensation for both the remote sensor and the magnetic compass

No OAT displayed OAT sensor not installed/connected Check electrical connections (NOTE: connected remote magnetic sensor is necessary for OAT display)

OAT sensor not activated

Check accrual setup of EFIS

Display does not show all possible data Displayed data depends of setup Check actual setup

EFFECTIVITY


Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M


1. General






34-20-00Page 101













EFFECTIVITY


Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

ATTITUDE AND DIRECTION - MAINTENANCE PRACTICES

1. General

A. The construction and function of the STEMME S6 magnetic compass is of conventional design and has no special features.

B. The STEMME S6 is equipped with an electronic flight information system (EFIS), Dynon Avionics EFIS D-10A, replacing the analog gyro instruments. For further information concerning the installed EFIS refer to the Installation Manual for the installed Dynon Avionics EFIS D10-A, P/N 100341-000, latest revision.

C. The maintenance is limited to component removal and re-installation.

2. Magnetic Compass Removal/Installation

A. Remove Magnetic Compass(1) Ensure BAT switch is in off position.(2) Remove screws securing compass to instrument panel cover and lift up compass carefully.(3) Remove compass from aircraft.

B. Install Magnetic Compass(1) Place compass on instrument panel cover.(2) Install compass to panel cover and secure using screws.

3. Dynon Avionics EFIS D-10A Removal/Installation

A. Remove EFIS D-10A(1) Ensure BAT switch is in off position.(2) Remove instrument panel cover, refer to Chapter 31, Section “Instrument Panel

Maintenance”.(3) Disconnect electrical connector from EFIS.(4) Remove pitot and static tube from EFIS.(5) Remove nuts and washers from back side of the panel sheet securing EFIS to instrument

panel.(6) Remove EFIS from instrument panel tray.

B. Install EFIS D-10A(1) Place EFIS into position and slide into panel tray.(2) Fix EFIS to panel by installing nuts and washers to bolts at panel back side.(3) Reconnect pitot and static tube to EFIS(4) Reconnect electrical connector to EFIS.(5) Install instrument panel cover, refer to Chapter 31, Section “Instrument Panel Maintenance”.

4. Adjustment / Test

A. Magnetic Compass Calibration(1) Prior to calibrating compass place the aircraft in as realistic flight environment as possible.

34-20-00Page 201

EFFECTIVITY


Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M


1. General














34-20-00Page 201

EFFECTIVITY


Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

(a) Place aircraft in level flight attitude(b) Check the canopy is closed.(c) Check flaps are retracted.(d) Start engine and turn ON all electrical equipment that usually is used at cruise (Refer to

STEMME S6 Flight Manual).

CAUTION: SINCE INSUFFICIENT ENGINE COOLING ON GROUND, DO IT OPERATE NOT MORE AS 3 MIN AT CRUISE RPM.

(e) Run engine and set throttle at cruise position.

NOTE: When performing maintenance practices on the magnetic compass, use a non-magnetic or plastic screwdriver.

(2) Remove screws securing access plate to compass housing to reveal adjustment screws.(3) Set adjustment screws of compensator on zero. Zero position is indicated when dot of screw

is aligned with dot on compass frame.(4) Taxi airplane to compass rose.(5) Align centerline of aircraft on magnetic North heading. Adjust N - S set screw until compass

reads North.(6) Align centerline of aircraft on magnetic East heading. Adjust E - W set screw until compass

reads East.(7) Align centerline of aircraft on magnetic South heading and note resulting South error.(8) Adjust N - S set screw until one-half of error is removed.(9) Align centerline of aircraft on magnetic West heading and note resulting West error.(10) Adjust E - W set screw until one-half of error is removed.(11) Align centerline of aircraft in successive magnetic 30-degree headings and record compass

readings on appropriate compass correction (deviation) card. Deviations must not exceed 10 degrees on any heading.

34-20-00Page 202

EFFECTIVITY



1. General

A. The construction and function of the STEMME S6 magnetic compass; the turn coordinator; the attitude indicator (horizon), and of the directional gyro is of conventional design and has no special features.

B. For further information concerning the installed gyro instrument components refer to the manufacturers manuals.





3. Turn Coordinator Removal/Installation

A. Remove Turn Coordinator(1) Ensure BAT switch is in off position.(2) Remove instrument panel cover, refer to Chapter 31, Section “Instrument Panel

Maintenance”.(3) Disconnect electrical connector from turn coordinator.(4) Remove screws securing turn coordinator to instrument panel.(5) Remove turn coordinator from aircraft.

B. Install Turn Coordinator(1) Place turn coordinatorr to instrument panel and secure using screws.(2) Reconnect electrical connector to turn coordinator.(3) Install instrument panel cover, refer to Chapter 31, Section “Instrument Panel Maintenance”.

4. Attitude Indicator Removal/Installation

A. Remove Attitude Indicator(1) Ensure BAT switch is in off position.(2) Remove instrument panel cover, refer to Chapter 31, Section “Instrument Panel

Maintenance”.(3) Disconnect electrical connector from attitude indicator.(4) Remove screws securing attitude indicator to instrument panel.

34-20-00Page 201

EFFECTIVITY

Aircraft equipped with Classic Line Avionics

Nov 18/11Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M











34-20-00Page 202

EFFECTIVITY



1. General

A. The construction and function of the STEMME S6 magnetic compass; the turn coordinator; the attitude indicator (horizon), and of the directional gyro is of conventional design and has no special features.

B. For further information concerning the installed gyro instrument components refer to the manufacturers manuals.





3. Turn Coordinator Removal/Installation

A. Remove Turn Coordinator(1) Ensure BAT switch is in off position.(2) Remove instrument panel cover, refer to Chapter 31, Section “Instrument Panel

Maintenance”.(3) Disconnect electrical connector from turn coordinator.(4) Remove screws securing turn coordinator to instrument panel.(5) Remove turn coordinator from aircraft.

B. Install Turn Coordinator(1) Place turn coordinatorr to instrument panel and secure using screws.(2) Reconnect electrical connector to turn coordinator.(3) Install instrument panel cover, refer to Chapter 31, Section “Instrument Panel Maintenance”.

4. Attitude Indicator Removal/Installation

A. Remove Attitude Indicator(1) Ensure BAT switch is in off position.(2) Remove instrument panel cover, refer to Chapter 31, Section “Instrument Panel

Maintenance”.(3) Disconnect electrical connector from attitude indicator.(4) Remove screws securing attitude indicator to instrument panel.

34-20-00Page 201

EFFECTIVITY


Nov 18/11Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

(5) Remove attitude indicator from aircraft.

B. Installation of the attitude indicator(1) Position attitude indicator onto instrument panel and secure with screws.(2) Connect electrical connector to the instrument.(3) Install instrument panel cover, refer to Chapter 31, Section “Instrument Panel Maintenance”.

5. Directional Gyro Removal/Installation

A. Remove Directional Gyro(1) Remove instrument panel cover, refer to Chapter 31, Section “Instrument Panel

Maintenance”.(2) Disconnect electrical connector from back of the instrument.(3) Remove screws securing directional gyro to instrument panel.(4) Remove directional gyro from aircraft.

B. Install Directional Gyro(1) Position directional gyro onto instrument panel and secure with screws.(2) Connect electrical connector to the instrument.(3) Install instrument panel cover, refer to Chapter 31, Section “Instrument Panel Maintenance”.


A. Magnetic Compass Calibration(1) Prior to calibrating compass place the aircraft in as realistic flight environment as possible.(a) Place aircraft in level flight attitude(b) Check the canopy is closed.(c) Check flaps are retracted.(d) Start engine and turn ON all electrical equipment that usually is used at cruise (Refer to








34-20-00Page 202



34-20-00Page 203

EFFECTIVITY


EFFECTIVITY


Nov 18/11Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

(5) Remove attitude indicator from aircraft.

B. Installation of the attitude indicator(1) Position attitude indicator onto instrument panel and secure with screws.(2) Connect electrical connector to the instrument.(3) Install instrument panel cover, refer to Chapter 31, Section “Instrument Panel Maintenance”.

5. Directional Gyro Removal/Installation

A. Remove Directional Gyro(1) Remove instrument panel cover, refer to Chapter 31, Section “Instrument Panel

Maintenance”.(2) Disconnect electrical connector from back of the instrument.(3) Remove screws securing directional gyro to instrument panel.(4) Remove directional gyro from aircraft.

B. Install Directional Gyro(1) Position directional gyro onto instrument panel and secure with screws.(2) Connect electrical connector to the instrument.(3) Install instrument panel cover, refer to Chapter 31, Section “Instrument Panel Maintenance”.


A. Magnetic Compass Calibration(1) Prior to calibrating compass place the aircraft in as realistic flight environment as possible.(a) Place aircraft in level flight attitude(b) Check the canopy is closed.(c) Check flaps are retracted.(d) Start engine and turn ON all electrical equipment that usually is used at cruise (Refer to








34-20-00Page 202



34-20-00Page 203

EFFECTIVITY


EFFECTIVITY


Nov 18/11Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

EFFECTIVITY

Aircraft equipped with Advanced Line Avionics


1. General






34-20-00Page 101













Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

EFFECTIVITY



1. General






34-20-00Page 101













Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

EFFECTIVITY



1. General














34-20-00Page 201

Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

EFFECTIVITY



1. General














34-20-00Page 201

Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

EFFECTIVITY












34-20-00Page 202

INDEPENDENT POSITION DETERMINING

1. Genera

A. This section lists some of the more common troubles, which may be encountered in maintaining the Garmin GNS 430W system, their probable causes and remedies.

B. If a problem on the GNS 430W system occurs, at first check all electrical connections and wiring for proper conditions.

2. Troubleshooting


B. For more details and interpreting possible error messages of the GNS 430W please refer to the manuals of the manufacturer.

C. When switching GNS 430W ON, a self test routine will take place. At the end of that routine, the CDI will stay with deflected pointers and flags. If the units pass this self test, the wiring between GN S430W and CDI is OK. In addition, the GNS 430W includes various setup and self-diagnosting menus. Refer installation manual for setup and diagnostic instructions

- TROUBLESHOOTING

l

Page 10134-40-00

EFFECTIVITY



No display on GN430W (dark screen) when switched on

No power supply at GNS 430W Switch on battery switch and Avionics Master

GNS430W not fully inserted into the rack

Make sure that GNS430W is proper inserted and locked

CDI does show the correct pointer deflections and flags after self test

Connection between GNS430W and CDI interrupted

Check wiring for loosen plugs or damaged wires

GNS430W does not receive satellite signals

GPS antenna covered or disconnected Make sure that the GPS antenna has free view to the sky Check antenna connectors

GNS430W does not receive VOR/LOC/GS signals

Wrong frequency tuned Verify the correct frequency setting

VOR antenna or antenna splitter disconnected or reversed or antenna wires damaged

Check VOR antenna for proper wiring and connection

Ground station too far away and/or flight level too low

Doublecheck GNS430W on ground

Nov 18/11Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

EFFECTIVITY












34-20-00Page 202

INDEPENDENT POSITION DETERMINING

1. Genera

A. This section lists some of the more common troubles, which may be encountered in maintaining the Garmin GNS 430W system, their probable causes and remedies.

B. If a problem on the GNS 430W system occurs, at first check all electrical connections and wiring for proper conditions.

2. Troubleshooting


B. For more details and interpreting possible error messages of the GNS 430W please refer to the manuals of the manufacturer.

C. When switching GNS 430W ON, a self test routine will take place. At the end of that routine, the CDI will stay with deflected pointers and flags. If the units pass this self test, the wiring between GN S430W and CDI is OK. In addition, the GNS 430W includes various setup and self-diagnosting menus. Refer installation manual for setup and diagnostic instructions

- TROUBLESHOOTING

l

Page 10134-40-00

EFFECTIVITY



No display on GN430W (dark screen) when switched on

No power supply at GNS 430W Switch on battery switch and Avionics Master

GNS430W not fully inserted into the rack

Make sure that GNS430W is proper inserted and locked

CDI does show the correct pointer deflections and flags after self test

Connection between GNS430W and CDI interrupted

Check wiring for loosen plugs or damaged wires

GNS430W does not receive satellite signals

GPS antenna covered or disconnected Make sure that the GPS antenna has free view to the sky Check antenna connectors

GNS430W does not receive VOR/LOC/GS signals

Wrong frequency tuned Verify the correct frequency setting

VOR antenna or antenna splitter disconnected or reversed or antenna wires damaged

Check VOR antenna for proper wiring and connection

Ground station too far away and/or flight level too low

Doublecheck GNS430W on ground

Nov 18/11Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

INDEPENDENT POSITION DETERMINING – MAINTENANCE PRACTICES

1. General

A. This section covers that portion of the system which provides information to determine position and is mainly independent of ground installations. Includes the global position system (GPS).

B. Garmin GNS 430 SystemThe GNS 430 system is a fully integrated, panel mounted instrument, which contains a VHF Communications Transceiver, a VOR/ILS receiver, and a Global Positioning System (GPS) Navigation computer. The primary function of the GPS portion of the system is to acquire signals from the GPS system satellites, recover orbital data, make range and Doppler measurements, and process this information in real-time to obtain the user's position, velocity, and time.GPS Signals are received by an antenna mounted on top of fuselage near the top deck hatches.

C. Refer to 23-10-00 for the description of the communication portion of the GNS 430.

D. Refer to Garmin 400 Series Installation Manual, P/N 190-00140-02, latest revision for additional maintenance information on the GNS 430 System.

2. Garmin GNS 430 Unit Removal/Installation

A. Remove GNS 430 Unit(1) Ensure BAT switch is in off position.(2) Pull COMM and NAV circuit breakers.(3) Insert a 3/32 hex wrench into the access hole at the bottom of the unit face and engage hex

bolt.(4) Turn wrench counterclockwise until the unit is forced out about 3/8” and can be freely pulled

from the rack.(5) Pull unit from rack.

B. Install GNS 430 Unit

CAUTION: WHEN MOUNTING THE UNIT, DO NOT PRESS ON DISPLAY WINDOW AS DAMAGE MAY RESULT.BE SURE NOT TO OVER TIGHTEN THE UNIT INTO THE RACK. THE APPLICATION OF HEX WRENCH TORQUE EXCEEDING 15 IN.LBS CAN DAMAGE THE LOCKING MECHANISM.

NOTE: It may be necessary to insert the hex wrench into the access hole at the bottom of the unit face and rotate the mechanism 90° counterclockwise to insure correct position prior to placing the unit in the rack.

(1) Slide unit carefully straight in the rack until it stops, about 1 inch short of the final position.(2) Insert a 3/32 hex wrench into the access hole at the bottom of the unit face and engage hex

bolt.(3) Turn wrench clockwise while pressing on the left side of the bezel until the unit is firmly

seated in the rack.(4) Reset COMM and NAV circuit breakers.

34-40-00Page 201

EFFECTIVITY


Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M


1. General


B. Garmin GNS 430 SystemThe GNS 430 system is a fully integrated, panel mounted instrument, which contains a VHF Communications Transceiver, a VOR/ILS receiver, and a Global Positioning System (GPS) Navigation computer. The primary function of the GPS portion of the system is to acquire signals from the GPS system satellites, recover orbital data, make range and Doppler measurements, and process this information in real-time to obtain the user's position, velocity, and time.GPS Signals are received by an antenna mounted on top of fuselage near the top deck hatches.

C. Refer to 23-10-00 for the description of the communication portion of the GNS 430.

D. Refer to Garmin 400 Series Installation Manual, P/N 190-00140-02, latest revision for additional maintenance information on the GNS 430 System.

2. Garmin GNS 430 Unit Removal/Installation

A. Remove GNS 430 Unit(1) Ensure BAT switch is in off position.(2) Pull COMM and NAV circuit breakers.(3) Insert a 3/32 hex wrench into the access hole at the bottom of the unit face and engage hex



B. Install GNS 430 Unit





seated in the rack.(4) Reset COMM and NAV circuit breakers.

34-40-00Page 201

EFFECTIVITY


Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

3. GPS Antenna Removal/Installation

A. Remove GPS Antenna(1) Remove the top instrument panel cover.(2) Disconnect the antenna cable from antenna.(3) Remove nuts and washers securing antenna to instrument panel frame.(4) Remove antenna from aircraft.

B. Install GPS Antenna(1) Position antenna onto the instrument panel frame.(2) Install washers and nuts securing antenna to instrument panel frame. Simultaneously

connect ground cable to backing plate.(3) Reconnect antenna cable.(4) Install the top instrument panel cover.

4. Inspection/Check

A. A flight test is recommended after the GNS 430 unit installation to ensure proper function. Check the communications transceiver for satisfactory operating range in several altitudes. Verify that the unit is communicating properly with in-panel instruments. Compare on-screen indications with the information depicted on the CDI.

34-40-00Page 202

EFFECTIVITY



1. General


B. Garmin GPSMAP 695 SystemThe GPSMAP 695 system is a GPS derived analog flight instrumentation, position, navigation, and hazard avoidance information to the pilot using a large 7” wide display. The primary function of the Global Positioning System (GPS) Navigation computer is to acquire signals from the GPS system satellites, recover orbital data, make range and Doppler measurements, and process this information in real-time to obtain the user's position, velocity, and time.GPS Signals are received by an antenna mounted on top of fuselage near the top deck hatches.

C. Refer to Garmin GPSMAP 695 Installation Manual, latest revision for additional maintenance information on the GPSMAP 695 System.

2. Garmin GPSMAP 695 Unit Removal/Installation

A. Remove GPSMAP 695 Unit(1) Ensure BAT switch is in off position.(2) Pull NAV circuit breaker.(3) Insert a 3/32 hex wrench into the access hole at the bottom of the unit face and engage hex



B. Install GPSMAP 695 Unit





seated in the rack.(4) Reset NAV circuit breaker.

34-40-00Page 201

EFFECTIVITY


Nov 18/11Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M





4. Inspection/Check

A. A flight test is recommended after the GNS 430 unit installation to ensure proper function. Check the communications transceiver for satisfactory operating range in several altitudes. Verify that the unit is communicating properly with in-panel instruments. Compare on-screen indications with the information depicted on the CDI.

34-40-00Page 202

EFFECTIVITY



1. General


B. Garmin GPSMAP 695 SystemThe GPSMAP 695 system is a GPS derived analog flight instrumentation, position, navigation, and hazard avoidance information to the pilot using a large 7” wide display. The primary function of the Global Positioning System (GPS) Navigation computer is to acquire signals from the GPS system satellites, recover orbital data, make range and Doppler measurements, and process this information in real-time to obtain the user's position, velocity, and time.GPS Signals are received by an antenna mounted on top of fuselage near the top deck hatches.

C. Refer to Garmin GPSMAP 695 Installation Manual, latest revision for additional maintenance information on the GPSMAP 695 System.

2. Garmin GPSMAP 695 Unit Removal/Installation

A. Remove GPSMAP 695 Unit(1) Ensure BAT switch is in off position.(2) Pull NAV circuit breaker.(3) Insert a 3/32 hex wrench into the access hole at the bottom of the unit face and engage hex



B. Install GPSMAP 695 Unit





seated in the rack.(4) Reset NAV circuit breaker.

34-40-00Page 201

EFFECTIVITY


Nov 18/11Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M





4. Inspection/Check

A. A flight test is recommended after the GPSMAP 695 unit installation to ensure proper function.

34-40-00Page 202

EFFECTIVITY


DEPENDENT POSITIONING DETERMINING - MAINTENANCE PRACTICES

1. General

A. This section covers that portion of the system which provides information to determine position and is mainly dependent on ground installations. Includes items such as the Garmin GNS 430 GPS system and the Garmin GTX 330 Transponder system.The scope of maintenance is limited to the removal and installation of system components.

B. Garmin GNS 430 SystemThe GNS 430 system is a fully integrated, panel mounted instrument, which contains a VHF Communications Transceiver, a VOR/ILS receiver, and a Global Positioning System (GPS) Navigation computer. The primary function of the VOR/ILS Receiver portion of the equipment is to receive and demodulate VOR, Localizer, and Glide Slope signals. NAV/LOC/GS signals are received by the VOR/LOC antenna mounted on top of the vertical stabilizer.For removal/installation of the GNS 430 unit, refer to 34-40-00.

For a complete description of the GNS 430, refer to the GARMIN GNS 430 Pilot's Guide and Reference, P/N 190-00140-00, latest revision.Refer to Garmin 400 Series Installation Manual, P/N 190-00140-02, latest revision for additional maintenance information on the GNS 430 System.

C. Garmin GTX 330 Mode S TransponderThe Garmin GTX 330 is a panel mounted Non-Diversity Mode S Transponder working like a radio transmitter and receiver that operates on radar frequencies, receiving ground radar or TCAS interrogations at 1030 MHz and transmitting a coded response of pulses to ground based radar on a frequency of 1090 MHz. The GTX 330 is equipped with IDENT capability that activates the Special Position Identification (SPI) pulse for 18 seconds. The GTX 330 replies to Mode A, Mode C and Mode S All-Call interrogation. As a Level 2 transponder, the GTX 330 provides downlink of aircraft information. Ground stations can interrogate Mode S Transponders individually using a 24-bit ICAO Mode S address, which is unique to the particular aircraft. In addition, ground stations may interrogate a GTX 330 for its Transponder data capability and the aircraft's Flight ID, which may be the registration number or other call sign. For a complete description of the GTX 330, refer to the Pilot's Guide of the GTX 330, P/N 190-00207-00, latest revision.The electrical circuit of the GTX 330 Mode S Transponder is protected by a circuit breaker labelled as “Transponder”. The transponder antenna is installed on the bottom of the cabin, below the co-pilot's seat.

For additional maintenance information on the GTX 330 Mode S Transponder, refer to GTX 330 Installation Manual, P/N 190-00207-02, latest revision..

2. Garmin GTX 330 Transponder Removal/Installation

A. Remove Garmin GTX 330 Transponder(1) Ensure the BAT switch is in off position.(2) Pull XPDR circuit breaker.(3) Insert a 3/32 hex wrench into the access hole at the unit face and engage hex bolt.(4) Turn wrench counterclockwise until the unit is forced out about 3/8” and can be freely pulled

34-50-00Page 201

EFFECTIVITY


Nov 18/11Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M





4. Inspection/Check

A. A flight test is recommended after the GPSMAP 695 unit installation to ensure proper function.

34-40-00Page 202

EFFECTIVITY



1. General

A. This section covers that portion of the system which provides information to determine position and is mainly dependent on ground installations. Includes items such as the Garmin GNS 430 GPS system and the Garmin GTX 330 Transponder system.The scope of maintenance is limited to the removal and installation of system components.

B. Garmin GNS 430 SystemThe GNS 430 system is a fully integrated, panel mounted instrument, which contains a VHF Communications Transceiver, a VOR/ILS receiver, and a Global Positioning System (GPS) Navigation computer. The primary function of the VOR/ILS Receiver portion of the equipment is to receive and demodulate VOR, Localizer, and Glide Slope signals. NAV/LOC/GS signals are received by the VOR/LOC antenna mounted on top of the vertical stabilizer.For removal/installation of the GNS 430 unit, refer to 34-40-00.

For a complete description of the GNS 430, refer to the GARMIN GNS 430 Pilot's Guide and Reference, P/N 190-00140-00, latest revision.Refer to Garmin 400 Series Installation Manual, P/N 190-00140-02, latest revision for additional maintenance information on the GNS 430 System.

C. Garmin GTX 330 Mode S TransponderThe Garmin GTX 330 is a panel mounted Non-Diversity Mode S Transponder working like a radio transmitter and receiver that operates on radar frequencies, receiving ground radar or TCAS interrogations at 1030 MHz and transmitting a coded response of pulses to ground based radar on a frequency of 1090 MHz. The GTX 330 is equipped with IDENT capability that activates the Special Position Identification (SPI) pulse for 18 seconds. The GTX 330 replies to Mode A, Mode C and Mode S All-Call interrogation. As a Level 2 transponder, the GTX 330 provides downlink of aircraft information. Ground stations can interrogate Mode S Transponders individually using a 24-bit ICAO Mode S address, which is unique to the particular aircraft. In addition, ground stations may interrogate a GTX 330 for its Transponder data capability and the aircraft's Flight ID, which may be the registration number or other call sign. For a complete description of the GTX 330, refer to the Pilot's Guide of the GTX 330, P/N 190-00207-00, latest revision.The electrical circuit of the GTX 330 Mode S Transponder is protected by a circuit breaker labelled as “Transponder”. The transponder antenna is installed on the bottom of the cabin, below the co-pilot's seat.

For additional maintenance information on the GTX 330 Mode S Transponder, refer to GTX 330 Installation Manual, P/N 190-00207-02, latest revision..

2. Garmin GTX 330 Transponder Removal/Installation

A. Remove Garmin GTX 330 Transponder(1) Ensure the BAT switch is in off position.(2) Pull XPDR circuit breaker.(3) Insert a 3/32 hex wrench into the access hole at the unit face and engage hex bolt.(4) Turn wrench counterclockwise until the unit is forced out about 3/8” and can be freely pulled

34-50-00Page 201

EFFECTIVITY


Nov 18/11Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M


B. Install Garmin GTX 330 Transponder

CAUTION: BE SURE NOT TO OVER TIGHTEN THE UNIT INTO THE RACK. THE APPLICATION OF HEX WRENCH TORQUE EXCEEDING 15 IN.LBS CAN DAMAGE THE LOCKING MECHANISM.

NOTE: It may be necessary to insert the hex wrench into the access hole at the unit face and rotate the mechanism 90° counterclockwise to insure correct position prior to placing the unit in the rack.


bolt.(3) Turn wrench clockwise until the unit is secured in the rack.(4) Reset XPDR circuit breaker.

3. Transponder Antenna Removal/Installation

A. Remove Transponder Antenna(1) Disconnect antenna cable from antenna.(2) Remove nuts and washers securing antenna to lower engine cowling 200CL (Ref. 06-30-00).(3) Remove antenna from aircraft.

B. Install Transponder Antenna(1) Insert antenna studs through mounting holes and position from inside of lower engine

cowling 200CL the aluminum sheet and the backing plate.(2) Install washers and nuts securing transponder antenna to lower engine cowling 200CL.(3) Reconnect antenna cable to antenna.

4. VOR/LOC Antenna Removal/Installation

A. Remove VOR/LOC Antenna(1) Remove upper front gear fairing 100AT (Ref. 06-30-00) and cover plate on the lower cockpit.(2) Disconnect antenna cable from antenna.(3) Remove tape-glued VOR/LOC antenna from the lower cockpit.

B. Install VOR/LOC Antenna(1) Position VOR/LOC antenna to lower cockpit and glue with double side glue tape in

appropriate position.(2) Reconnect antenna cable to antenna.(3) Reinstall cover plate on the lower cockpit and upper front gear fairing.

34-50-00Page 202


1. General

A. This section covers that portion of the system which provides information to determine position and is mainly dependent on ground installations. Includes items such as the VOR-CDI and the Becker BXP6401 - 2 Transponder system.The scope of maintenance is limited to the removal and installation of system components.

B. The installed VOR-CDI is a panel mounted instrument, which contains a VHF Communications Transceiver and a VOR/ILS receiver.

C. Refer to manufacturers Installation Manual, latest revision for additional maintenance information on the installed VOR-CDI System.

D. The Becker BXP6401 - 2 Mode S Transponder forms the airborne component of the air traffic control. It functions in accordance with the secondary radar principle and allows air traffic control to locate, identify and track the aircraft.For a complete description of the Becker BXP6401 - 2, refer to the Pilot's Guide of the Becker BXP6401 - 2, P/N 0591.823 - 071, latest revision.The electrical circuit of the Becker BXP6401 - 2 Mode S Transponder is protected by a circuit breaker labelled as “Transponder”. The transponder antenna is installed on the bottom of the cabin, below the co-pilot's seat.

For additional maintenance information on the Becker BXP6401 - 2 Mode S Transponder, refer to Becker BXP6401 - 2 Installation and Operation Manual, P/N 0584.071 - 071, latest revision.

2. VOR-CDI Instrument Removal/Installation

A. Remove VOR-CDI Instrument(1) Ensure BAT switch is in off position.(2) Pull COMM and NAV circuit breakers.(3) Remove instrument panel cover, refer to Chapter 31, Section “Instrument Panel

Maintenance”.(4) Disconnect electrical connector and antenna from VOR-CDI.(5) Remove screws securing VOR-CDI to instrument panel.(6) Remove VOR-CDI from aircraft.

B. Install VOR-CDI Instrument(1) Place VOR-CDI to instrument panel and secure using screws.(2) Reconnect electrical connector and antenna to VOR-CDI.(3) Install instrument panel cover, refer to Chapter 31, Section “Instrument Panel Maintenance”.(4) Reset COMM and NAV circuit breakers.

34-50-00Page 201

EFFECTIVITY


EFFECTIVITY


Nov 18/11Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M


B. Install Garmin GTX 330 Transponder

CAUTION: BE SURE NOT TO OVER TIGHTEN THE UNIT INTO THE RACK. THE APPLICATION OF HEX WRENCH TORQUE EXCEEDING 15 IN.LBS CAN DAMAGE THE LOCKING MECHANISM.

NOTE: It may be necessary to insert the hex wrench into the access hole at the unit face and rotate the mechanism 90° counterclockwise to insure correct position prior to placing the unit in the rack.


bolt.(3) Turn wrench clockwise until the unit is secured in the rack.(4) Reset XPDR circuit breaker.









34-50-00Page 202


1. General

A. This section covers that portion of the system which provides information to determine position and is mainly dependent on ground installations. Includes items such as the VOR-CDI and the Becker BXP6401 - 2 Transponder system.The scope of maintenance is limited to the removal and installation of system components.

B. The installed VOR-CDI is a panel mounted instrument, which contains a VHF Communications Transceiver and a VOR/ILS receiver.

C. Refer to manufacturers Installation Manual, latest revision for additional maintenance information on the installed VOR-CDI System.

D. The Becker BXP6401 - 2 Mode S Transponder forms the airborne component of the air traffic control. It functions in accordance with the secondary radar principle and allows air traffic control to locate, identify and track the aircraft.For a complete description of the Becker BXP6401 - 2, refer to the Pilot's Guide of the Becker BXP6401 - 2, P/N 0591.823 - 071, latest revision.The electrical circuit of the Becker BXP6401 - 2 Mode S Transponder is protected by a circuit breaker labelled as “Transponder”. The transponder antenna is installed on the bottom of the cabin, below the co-pilot's seat.


2. VOR-CDI Instrument Removal/Installation

A. Remove VOR-CDI Instrument(1) Ensure BAT switch is in off position.(2) Pull COMM and NAV circuit breakers.(3) Remove instrument panel cover, refer to Chapter 31, Section “Instrument Panel

Maintenance”.(4) Disconnect electrical connector and antenna from VOR-CDI.(5) Remove screws securing VOR-CDI to instrument panel.(6) Remove VOR-CDI from aircraft.

B. Install VOR-CDI Instrument(1) Place VOR-CDI to instrument panel and secure using screws.(2) Reconnect electrical connector and antenna to VOR-CDI.(3) Install instrument panel cover, refer to Chapter 31, Section “Instrument Panel Maintenance”.(4) Reset COMM and NAV circuit breakers.

34-50-00Page 201

EFFECTIVITY


EFFECTIVITY


Nov 18/11Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

3. Transponder Removal/Installation

A. Remove Becker BXP6401 - 2 Transponder(1) Ensure the BAT switch is in off position.(2) Pull XPDR circuit breaker.(3) Remove instrument panel cover, refer to Chapter 31, Section “Instrument Panel

Maintenance”.(4) Disconnect electrical connectors and pressure tube from Transponder.(5) Remove screws and washers securing Becker BXP6401 - 2 Transponder to instrument panel.(6) Remove Transponder from instrument panel.

B. Install Becker BXP6401 - 2 Transponder

(1) Slide Transponder carefully straight in the panel rack and secure using screws and washers.(2) Reconnect electrical connectors and pressure tube to Becker BXP6401 - 2 Transponder.(3) Install instrument panel cover, refer to Chapter 31, Section “Instrument Panel Maintenance”.(4) Reset XPDR circuit breaker.









Becker BXP6401 - 2

34-50-00Page 202

EFFECTIVITY


6. Inspection/Check

A. A flight test is recommended after the VOR-CDI installation to ensure proper function. Check the communications transceiver for satisfactory operating range in several altitudes. Verify that the unit is communicating properly with in-panel instruments.

34-50-00Page 203

EFFECTIVITY


Nov 18/11Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M

3. Transponder Removal/Installation













Becker BXP6401 - 2

34-50-00Page 202

EFFECTIVITY


6. Inspection/Check

A. A flight test is recommended after the VOR-CDI installation to ensure proper function. Check the communications transceiver for satisfactory operating range in several altitudes. Verify that the unit is communicating properly with in-panel instruments.

34-50-00Page 203

EFFECTIVITY


Nov 18/11Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M


1. General

A. This section covers that portion of the system which provides information to determine position and is mainly dependent on ground installations. This function is realized by the Becker BXP6401 - 2 Transponder system.The scope of maintenance is limited to the removal and installation of system components.

B. The Becker BXP6401 - 2 Mode S Transponder forms the airborne component of the air traffic control. It functions in accordance with the secondary radar principle and allows air traffic control to locate, identify and track the aircraft.For a complete description of the Becker BXP6401 - 2, refer to the Pilot's Guide of the Becker BXP6401 - 2, P/N 0591.823 - 071, latest revision.The electrical circuit of the Becker BXP6401 - 2 Mode S Transponder is protected by a circuit breaker labelled as “Transponder”. The transponder antenna is installed on the bottom of the cabin, below the co-pilot's seat.


2. Becker BXP6401 - 2 Transponder Removal/Installation







34-50-00Page 201

EFFECTIVITY


Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M


1. General

A. This section covers that portion of the system which provides information to determine position and is mainly dependent on ground installations. This function is realized by the Becker BXP6401 - 2 Transponder system.The scope of maintenance is limited to the removal and installation of system components.

B. The Becker BXP6401 - 2 Mode S Transponder forms the airborne component of the air traffic control. It functions in accordance with the secondary radar principle and allows air traffic control to locate, identify and track the aircraft.For a complete description of the Becker BXP6401 - 2, refer to the Pilot's Guide of the Becker BXP6401 - 2, P/N 0591.823 - 071, latest revision.The electrical circuit of the Becker BXP6401 - 2 Mode S Transponder is protected by a circuit breaker labelled as “Transponder”. The transponder antenna is installed on the bottom of the cabin, below the co-pilot's seat.


2. Becker BXP6401 - 2 Transponder Removal/Installation







34-50-00Page 201

EFFECTIVITY


Nov 18/11

MAINTENANCE MANUAL

STEMME TSA-M

MAINTENANCE MANUAL

STEMME TSA-M



34-50-00Page 202

EFFECTIVITY


Nov 18/11

Documents

P500 006 000 Rev.9 IV