Dash 8 Series 100 Technical Training Manual

CHAPTER
6−12
Aircraft General
and Servicing
 Dash 8 Series 100 Technical Training Manual

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CHAPTER 6 − 12
Aircraft General and Servicing

Dash 8 Series 100

General. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 Aircraft Parking & Mooring
Aircraft Specifications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6 Parking Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24
Parking Brake . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24
Time Limitations and Maintenance Checks Gust Lock . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24
General. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 Landing Gear Ground Locks. . . . . . . . . . . . . . . . . . . . . . 24
Covers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26
Aircraft Coordinate System Propeller Restraints . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26
General. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 Static Ground Points . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26
Aircraft Mooring . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26
Aircraft Zones
General. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 Aircraft Servicing
General. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28
Access Panels Identification Servicing Points . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28
General. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16
Fueling
Aircraft Jacking Procedures General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36
General. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 Precautions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 36
Jacking the Aircraft at the Axles . . . . . . . . . . . . . . . . . . 18 Fuelling with APU Running . . . . . . . . . . . . . . . . . . . . . . . 40
Jacking the Complete Aircraft . . . . . . . . . . . . . . . . . . . . 20

Aircraft Towing
General. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22
Towing Sequence . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

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CHAPTER 6 − 12
Aircraft General and Servicing

Hydraulic Systems Wash Water System

General. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42 General. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 68
Hydraulic Servicing Procedures . . . . . . . . . . . . . . . . . . . 44 Replenishing Water Systems . . . . . . . . . . . . . . . . . . . . . 68
Bleeding the System . . . . . . . . . . . . . . . . . . . . . . . . . . . . 44 Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 70
Overspill Container . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46
Emergency System Reservoir . . . . . . . . . . . . . . . . . . . . 48 Lavatory
General. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 72
Landing Gear System Servicing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 72
General. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52
Precautions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52 Ground Air Connection
Charging of the Nose Gear Shock Strut . . . . . . . . . . . . 54 General. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 74
Charging of the Main Gear Shock Strut . . . . . . . . . . . . . 58 Application and Removal of Ground Conditioned Air . 74
Connection Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . 74
Tire Pressure Servicing Disconnection Procedures . . . . . . . . . . . . . . . . . . . . . . . 74
General. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 62
Fuselage Drains
Parking Brake Accumulator General. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 76
General. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 64
Engine Oil
Oxygen System General. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 78
General. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 66 Checking the Oil System Level . . . . . . . . . . . . . . . . . . . 78

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CHAPTER 6 − 12
Aircraft General and Servicing

APU Oil
General. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 80
Check Oil Level . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 80

Window Cleaning
General. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 82
Cleaning Aircraft Windows and Windshields . . . . . . . . 82

Electrical System
General. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 84
Application of External DC Power . . . . . . . . . . . . . . . . . 86
Removal of External DC Power . . . . . . . . . . . . . . . . . . . 86
Application of External AC (Variable Frequency) Power88
Removal of External AC (Variable Frequency) Power. 88

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Dash 8 Series 100

General Aircraft Specifications

The Dehavilland Dash−8 100 series aircraft is manufactured by The Dash−8 100 series has several variants, as detailed in the fol−
Bombardier aerospace, deHavilland division in Downsview, Ontario, lowing chart:
Canada.

The Dash−8 100 series aircraft is of the high wing configuration,

powered by 2 Pratt and Whitney PW120A/121 engines, which
drives a four bladed constant speed variable pitch Hamilton
Standard 14SF7 Propeller.

Certified all weather short to medium range transport category two

pilot aircraft. It can be used in cargo or passenger capacity.

The Dash−8 100 has a maximum take−off weight of 34500 pounds

(15650 kg) and a cruise speed of 258 knots at a maximum altitude
of 25000Ft, while maintaining a cabin altitude of 8000Ft

With optional, long range fuel tanks, the aircraft has a maximum
range of 1,098 nm (2,034 km).

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   

   

   

   

   

   

   

   

   



   

   

   



   



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

   


  



  




  

  




 


 


 











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85ft 0in.

26ft 0in.

Ø13ft 0in

11ft 11in.*

3ft 1in.*
(CLEARANCE 4ft 3in.
STATIC) 25ft 10.4in.

8ft 4in.

24ft 5in.*
4ft 11in. 6ft 8in.
FTSD30600a_001

26ft 1in

NOTE: * Dimensions to ground line are

73ft 0.1in approximate only and vary depending
on airplane configuration and loading
conditions.
Structural Weight Limits Series 100A

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Time Limitations and Maintenance Checks

(AMM Chapter 5−0−00)

General

Chapter 5 of the Aircraft Maintenance Manual provides the following Rough towing 5−50−81
unscheduled Maintenance inspections that must be carried out if
Volcanic ash condition 5−50−86
the aircraft has encountered one of the described events.
Tire failure 5−50−91
Hard Landing 5−50−11 Excessive braking 5−50−96
Severe turbulence 5−50−21
Bird strike 5−50−26 Scheduled maintenance can be found in the Maintenance Program
Manual PSM 1−8−7.
Lightning strike 5−50−31
The scheduled maintenance tasks will be discussed at the end of
Inspect EDP after loss of hydraulic fluid 5−50−33 each chapter, in the Maintenance Practices section of the training
manual.
AC generator after overheat condition 5−50−36
Excessive air manoeuvres 5−50−41
Exceeded gear maximum operation speed
5−50−46
Exceeded maxi flap extended operation speed
5−50−51
Exposure to high or gusty winds 5−50−61
Excessive de−icing 5−50−71
Inspection after autofeather at high power or after power loss with
autofeather armed 5−50−76
Inspection after loss of engine oil pressure due to a cracked PCU
pump housing 5−50−77

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Course Notes: Instructor Questions\Comments:

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Aircraft Coordinate System

(AMM Chapter 6−20−00)

General

The three main reference axes are designated X, Y and Z and ordi−
nates are located along these axes from a point of origin.

The point of origin for the longitudinal axis X, lateral axis Y and verti−
cal axis Z is in front of the aircraft and below the static ground line on
the aircraft centerline.

Identification of the ordinates is by the dimension in inches from the

point of origin prefixed by a letter denoting the axis, X 176.00 repre−
sents a position 176 inches along the X axis from the point of origin.

The point of origin for the 100 series aircraft is located 43.00 inches
forward of aircraft nose.

Each of the Major assemblies ie. Nacelles, Horizontal Stabilizer etc

has its own reference axis. The coordinates in these areas are identi−
fied by the letter for the major axis with a suffix letter indicating the
assembly, followed by the dimension in inches from the assembly
point of origin, example: XN 55.00 represents a position 55.00 inches
aft of the point of origin for the engine nacelle.

This point of origin coincides with the basic aircraft ordinate X

257.00.

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 Dash 8 Series 100 Technical Training Manual

ZH
HORIZONTAL
STABILIZER XH
ORIGIN

VERTICAL
STABILIZER*

ZW YH

WING XW
YW
ORIGIN

ZN

XN

YN
NACELLE
Z ORIGIN

Y
FTSD10600a_034

Y *INCLUDED IN FUSELAGE
COORDINATE SYSTEM X,
BASIC AIRCRAFT
Y, AND Z
AND FUSELAGE ORIGIN

Aircraft Co−ordinate System

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 Dash 8 Series 100 Technical Training Manual

Aircraft Zones
(AMM Chapter 6−30−00)

General

The aircraft zoning system provides positive identification of areas

in the aircraft by major zones, major sub−zones and zones.

The aircraft is divided into eight major zones identified as follows:

Major Zone

100 Lower Fuselage

200 Upper Fuselage

300 Empennage

400 Power Plants and Nacelles

500 Left Wing

600 Right Wing

700 Landing Gear and Landing Gear Doors

800 Doors

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 Dash 8 Series 100 Technical Training Manual

100 − Lower Fuselage 200 − Upper Fuselage 300 − Empennage

400 − Power Plants and Nacelles 500 − Left Wing 600 − Right Wing
FTSD30600a_055

700 − Landing Gear and 800 − Doors

Landing Gear Doors Aircraft Zones

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06−30−00 Page 15
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 Dash 8 Series 100 Technical Training Manual

Access Panels Identification

(AMM Chapter 6−40−00)

General

To facilitate maintenance of system and system components, and

the inspection of the aircraft structure, adequate access panels and
doors are provided in the aircraft exterior surfaces.

Each access panel is identified in relation to the aircraft zone in

which the panel or door is located. The identification consists of a
three digit zone number followed by two letters.

Within each zone, the panels and doors are identified by the first
letter (allocated in a logical sequence), and the second letter indi−
cates the location of the access, as follows:

T−Top B − Bottom L − Left R − Right Z−internal

AMM Chapter 6−40−10 provides an outline of the exterior panels and

which components can be located when the panel is removed.

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 Dash 8 Series 100 Technical Training Manual

111AT 212AL 212B R 212AL 212B R 111AT

113AL 121AL 121B L 112AR 111AT 113AL 122B R 122AR

112B R 112AR
112 AT
FTSD30600a_007

ZONE 112 : A: T:
1- Maj o r Zo n e Fi r s t Pan e l In Th e P h y s i c al Lo c at i o n L- Le f t
1- Maj o r Su b z o n e 112 Zo n e R- Ri g h t
2 - Zo n e T - To p
B - Bo t t o m
Z- In t e r n al
Access Panels And Doors - Front

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 Dash 8 Series 100 Technical Training Manual

Aircraft Jacking Procedures

(AMM Chapter 7−00−00)

General Jacking the Aircraft at the Axles

Three jacking points are provided for jacking the complete aircraft, Apply parking brake.
located one on each wing rear spar and one in the nose. Individual
jacking at each of the landing gear units, for wheel changing, is pos− Install ground locks on main landing gear and apply nose
sible using jacking pads at the base of the main gear shock struts gear ground lock.
and on the nose gear suspension lever.
If the nose landing gear unit is to be jacked, proceed as
follows:
CAUTION:
THE MAXIMUM AIRCRAFT WEIGHT FOR JACKING THE COM−
Center the nose wheels.
PLETE AIRCRAFT IS MAXIMUM RAMP/TAXI WEIGHT: MODEL
100 34,700 Lbs 15,740 kg Engage castor lock and secure with ball lock pin.

CAUTION: Position jack under main or nose jacking pad as required.

ON ANVS EQUIPPED AIRCRAFT PULL AND CLIP ANVS CIR−
CUIT BREAKERS BEFORE JACKING. Chock wheels at other two landing gear units.

NOTE: Raise jack until wheels are 1 to 2 inches (2.5 to 5.1 cm)
Three men are required, one for each lifting jack. One man is also clear of ground.
required at each wing jack to hold jacking adapter in position until
On completion of maintenance operations, lower jack and
jack makes contact.
remove from vicinity of aircraft.

EFFECTIVITY: ALL
07−00−00 Page 18
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 Dash 8 Series 100 Technical Training Manual

A B

NOSE GEAR JACKING

A FUSELAGE NOSE B AT LANDING GEAR AXLES

C D D C
FTSD10600a_033

WING JACKING C MAIN GEAR JACKING

D
COMPLETE AIRPLANE AT LANDING GEAR AXLES

Aircraft Jacking

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 Dash 8 Series 100 Technical Training Manual

Aircraft Jacking Procedures cont’d

Jacking the Complete Aircraft

Install the plumb bob. Lock lifting jack extensions.

Adjust the jacks until the plumb bob point aligns with lateral
Remove the forward right emergency exit door from the aircraft.
mark on the target plate at station Y42.500.
CAUTION: Position the tail stand.
DOOR WILL FALL FREELY INWARD WHEN OUTSIDE OPER−
ATING HANDLE IS ACTUATED. ENSURE ADEQUATE SUP− On completion of maintenance operations, remove tail stand, unlock
PORT IS AVAILABLE INSIDE THE AIRCRAFT TO PREVENT lifting jack extension and lower all three lifting jacks simultaneously
DAMAGE TO DOOR STRUCTURE. until the shock struts support the aircraft.

Lower each jack in turn, with one man to remove jacking adapter.
Suspend plumb bob from hanger at forward emergency exit.
Remove lifting jacks from vicinity of aircraft.
Make sure that the panel located at the upper emergency exit door
opening does not make contact with the plumb bob line at station Remove the plumb bob.
X255.00. Re−install the Emergency exit.
Permit the point of the plumb bob to hang above the target plate not With dc power applied (refer to Chapter 12), and hydraulic power off,
more than 0.5 inches (1.27 cm). press MEMORY RESET then SYSTEM TEST buttons located on
Install ground locks on main landing gear and apply nose gear PSEU front panel, to ensure that PSEU memory is cleared of faults.
ground lock.

Carry out post flight BITE procedure on the PSEU.

Position jack at each jacking point, insert jacking adapter and raise
jack height until jack contacts adapter.

Raise all three lifting jacks simultaneously until aircraft wheels are 1
to 2 inches (2.5 to 5.1 cm) clear of ground.

EFFECTIVITY: ALL
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 Dash 8 Series 100 Technical Training Manual

Callout Key
1
1. Hangar
2 . P lumb Bob

SERIES 100

Y42.500

X225.000
2

A T ARGET PLAT E
FTSD10600a_012

Aircraft Leveling

EFFECTIVITY: ALL
08−00−00 Page 21
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 Dash 8 Series 100 Technical Training Manual

Aircraft Towing
(AMM Chapter 9−00−00)

General
WARNING:
Towing is accomplished by attaching a tow bar to the towing spools IF THE NOSE GEAR GROUND LOCK CANNOT BE ENGAGED
located on the nose gear inner cylinder at the suspension lever PROPERLY, IT COULD BE AN INDICATION OF MALFUNCTION
pivot point and observing the following precautions: OF NOSE GEAR LOCKING MECHANISM. IN SUCH A CASE,
IMMEDIATELY SUPPORT AIRCRAFT AT NOSE BEFORE CAR−
CAUTION: RYING OUT ANY INVESTIGATION.
MAXIMUM NORMAL TOWING TURNING LIMITS ARE INDICATED
BY PAINTED ARROWS ON NOSE LANDING GEAR DOORS (120
Towing Sequence
DEGREES EACH WAY FROM CENTER). CARE SHOULD BE
EXERCISED NOT TO EXCEED THE TURNING LIMITS IN ORDER
Nosewheel steering switch "OFF".
TO AVOID DAMAGING THE NOSE GEAR.
Ensure that nose gear ground lock is engaged and that main gear
WARNING: ground lock pins are installed.
BEFORE TOWING AIRCRAFT ENSURE NOSEWHEEL STEER−
ING SWITCH IS "OFF" BEFORE ATTACHING TOW BAR AND Check brake system accumulator pressure gage located in the right
REMAINS "OFF" DURING TOWING, ON COMPLETION OF TOW− hand wing root to ensure sufficient pressure (2500 psi minimum).
ING OR PARKING, NOSEWHEEL MUST BE CENTERED BEFORE Pump up accumulator pressure with hand pump as required.
DISCONNECTING TOW BAR OR INJURY COULD RESULT TO
PERSONNEL FROM MOVING TOW BAR IF THE NOSEWHEEL Station a crewmember in the flight compartment to operate the
SWITCH IS INADVERTENTLY SWITCHED TO "ON" AND NOSE− emergency/ parking brake as necessary.
WHEEL RETURNS TO CENTER.
Limit aircraft towing speed to 5 MPH maximum

CAUTION:
DURING TOWING, ONLY APPLY BRAKE IN AN EMERGENCY.

EFFECTIVITY: ALL
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 Dash 8 Series 100 Technical Training Manual

Callout Key
1 . To w i n g S p o o l
2
2. Inner Cylinder
3. Suspension Lever
3

1 1
FTSD30600a_009

NOSEWHEEL

To w i n g A t t a c h m e n t P o i n t s

EFFECTIVITY: ALL
09−00−05 Page 23
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 Dash 8 Series 100 Technical Training Manual

Aircraft Parking & Mooring

(AMM Chapter 10−00−00)

Parking Procedures Parking Brake

Park aircraft heading into wind with flaps up, apply the parking Engage the parking brake by pulling the striped parking brake lever
brake, engage gust lock, engage nose gear ground lock, install on the left hand side of the center console, to the PARK position.
main gear ground lock pins, install protective covers and propeller Check the brake system accumulator pressure gage located in the
restraints, as required, close all doors and statically ground the air− right hand wing root to ensure sufficient pressure (2500 psi mini−
craft. Before leaving the aircraft ensure that battery switches are set mum). Pump up accumulator pressure with handpump located in
to OFF the right hand nacelle as required.

Place suitable wheel chocks in front and behind the main and nose− Gust Lock
wheels. The front and rear chocks at each wheel position should be
tied together for greater security. Lock the control surfaces by setting the CONT LOCK lever located
on the center console to the LOCK position. Set the ailerons to the
NOTE: neutral position and ensure that the aileron locks engage. Push
Park aircraft with nose wheel centered. either control column fully forward to engage the elevator locks.

WARNING: Landing Gear Ground Locks

IF THE NOSE GEAR GROUND LOCK CANNOT BE ENGAGED
PROPERLY, IT COULD BE AN INDICATION OF MALFUNCTION Engage nose gear ground lock located on the left hand side of the
OF NOSE GEAR LOCKING MECHANISM. IN SUCH A CASE, nose section, by pressing button on door and pulling the striped
IMMEDIATELY SUPPORT AIRCRAFT AT NOSE BEFORE CAR− nose gear ground lock door out and turning 90 degrees clockwise.
RYING OUT ANY INVESTIGATION. Install main gear ground lock pins.

EFFECTIVITY: ALL
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 Dash 8 Series 100 Technical Training Manual

2 3 Callout Key
1. P arking Brake ON
2. B a tte r y S w i tc h e s O F F
3. Gus t Loc k ON
4. S ta ti c C o v e r s I n s ta l l e d
5. P i to t C o v e r s I n s ta l l e d
6. P as s e nge r Door Clos e d
7. Baggage Door Clos e d
8. E x h a u s t C o v e r s ( O p ti o n a l )
9. Flaps Up
10. M a i n G e a r P i n s I n s ta l l e d
11. C h o c k s I n s ta l l e d M a i n & N o s e
12 . P r o p e l l e r T e a th e r I n s ta l l e d
13. I n ta k e P l u g s
14. N o s e W h e e l S tr a i g h t
15. Nos e Ground Loc k

4 5 6 7
FTSD10600a_045

15 14 13 12 10 11 9 8

Aircraft Outdoor Parking External

EFFECTIVITY: ALL
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 Dash 8 Series 100 Technical Training Manual

Aircraft Parking & Mooring cont’d

(AMM Chapter 10−00−00)

Covers

The following covers should be installed if the aircraft is to be parked

outside :
· Engine air intake
· Pitot head
· Static covers
· Engine exhaust duct (optional)

Propeller Restraints

Two propeller restraints are provided to prevent windmilling of the

propellers during parking. Each restraint is secured to a fitting on the
associated engine nacelle.

Static Ground Points

Attach a static ground line to the GROUND (EARTH) HERE point on

either of the main landing gear cross beams. Ground points must be
clean to ensure continuity. Attach other end of static line to ground
rod or other suitable grounding location.

Aircraft Mooring

If the aircraft is to be parked outside during very high wind condi−

tions(above 60 MPH) it is advisable to carry out mooring procedures.

EFFECTIVITY: ALL
10−00−00 Page 26
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 Dash 8 Series 100 Technical Training Manual

Course Notes: Instructor Questions\Comments:

EFFECTIVITY: ALL
00−00−00 Page 27
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 Dash 8 Series 100 Technical Training Manual

Aircraft Servicing
(AMM Chapter 12−00−00)

General

This chapter contains details of aircraft servicing points, the application

of ground hydraulic and electrical power, scheduled and unscheduled
servicing, and fluid replenishment procedures applicable to the whole
aircraft.
NOTE:
To prevent damage to surface finishes it is recommended that person−
nel wear soft soled shoes if their work requires walking on wing sur−
faces or fuselage areas of the aircraft.

Servicing Points

The following are the servicing points on the Dash−8100 series aircraft;

Brake system hand pump − Right hand nacelle

Parking brake accumulator − Right hand wing root

Hydraulic reservoirs − Left and right nacelles

Ground air connection − Left or right hand side of tail section

Engine oil filler − Left hand side of each nacelle

Hydraulic ground service panel − Right hand side of each nacelle

Over wing refueling points − Middle of each wing upper surface

EFFECTIVITY: ALL
12−00−00 Page 28
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 Dash 8 Series 100 Technical Training Manual

A C

B HYDRAULIC RESERVOIR
(No. 1 & No. 2 NACELLES)
A BRAKE SYSTEM HANDPUMP

G F D
E PARKING BRAKE
C
ENGINE OIL FILLER SYSTEM ACCUMULATOR
G
(2 PLACES)

INLET
E OVERWING FUEL FILLERS (DOOR OPEN) DOOR
CLOSED
FTSD10600a_028

D GROUND CONDITIONED
AIR CONNECTION

NOTE: The Ground conditioned air

HYDRAULIC GROUND connection is located on left hand
F SERVICING PANEL side with APU installed, or right
(No. 1 & No. 2 NACELLES) hand side when APU is not installed.
Aircraft Servicing Points (1 of 3)

EFFECTIVITY: ALL
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 Dash 8 Series 100 Technical Training Manual

Aircraft Servicing
(AMM Chapter 12−00−00) cont’d

Servicing Points cont’d

Hydraulic fill port − On the return manifold in each nacelle

Emergency hydraulic reservoir − Right hand side nose compartment

Crew oxygen bottle − Right hand side nose compartment

Magnetic dipsticks − 2 outboard of each nacelle on the

underside of each wing

Refuel/Defuel panel & adapter − Rear of the right hand nacelle

Warm water servicing panel (optional)

− Right hand side of forward fuselage

Lavatory servicing panel − Right hand side of forward fuselage

EFFECTIVITY: ALL
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 Dash 8 Series 100 Technical Training Manual

QUICK RELEASE
FILL CONNECTION

A RETURN MANIFOLD
(No. 1 & No. 2 NACELLES)
B TOILET SERVICING PANEL C CREW OXYGEN BOTTLE

A B C

D
E

H G F D MAGNETIC DIPSTICK
H PRESSURE REFUEL/ (2 EACH WING)
DEFUEL PANEL
FTSD10600a_029

F WARM WATER WASH SYSTEM

SERVICING PANEL
E HYDRAULIC RESERVOIR
G PRESSURE REFUEL/ (MAIN GEAR ALTERNATE
DEFUEL ADAPTER Aircraft Servicing Points (2 of 3) EXTENSION)

EFFECTIVITY: ALL
12−00−00 Page 31
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 Dash 8 Series 100 Technical Training Manual

Aircraft Servicing
(AMM Chapter 12−00−00) cont’d

Servicing Points cont’d

External AC Adapter − inboard side of the right hand nacelle

External DC Adapter − Left hand side of the forward nose section

Batteries − Forward left hand nose compartment

EFFECTIVITY: ALL
12−00−00 Page 32
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 Dash 8 Series 100 Technical Training Manual

A GROU
ND PO
WER
28 V D
C

A EXTERNAL POWER B EXTERNAL POWER

CONNECTOR (AC) CONNECTOR (DC)
FTSD10600a_030

C B
C BATTERIES
Aircraft Servicing Points (3 of 3)

EFFECTIVITY: ALL
12−00−00 Page 33
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 Dash 8 Series 100 Technical Training Manual

Course Notes: Instructor Questions\Comments:

EFFECTIVITY: ALL
00−00−00 Page 34
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 Dash 8 Series 100 Technical Training Manual

1
Callout Key
1. Fue l Truc k
2 . G r o u n d A i r C o n d i ti o n i n g
U n i t ( A p u N o t I n s ta l l e d )
6 7 8 3 . T r a c to r ( W i th B a g g a g e C a r ts )
4 . D C E l e c tr i c P o w e r U n i t
5. Tow Bar
6 . T o w i n g T r a c to r
7 . Toile t Se rvic e Ve hic le
8 . A C E l e c tr i c P o w e r U n i t

4
CLEAR − ZONE
FTSD10600a_039

AROUND FUEL VENTS

DURING REFUELING

Aircraft Servicing Arrangement

EFFECTIVITY: ALL
12−00−00 Page 35
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 Dash 8 Series 100 Technical Training Manual

Fueling

General

Fuel tank capacities are:

Left wing 423 USG 1601 Liters 2882lbs 1307Kgs
CAUTION:
Right wing 423 USG 1601 Liters 2882lbs 1307Kgs
MAXIMUM REFUELING PRESSURE IS 50 PSI.
Total 846 USG 3202 Litres 5764lbs 2614Kgs
MINIMUM REFUELING PRESSURE IS 20 PSI

Total Useable fuel is 5678Lbs

Precautions
Pressure refueling facilities are provided by a single point adapter
and control panel located in the rear of right hand engine nacelle.
No smoking or any other kind of open flame is allowed in the vicinity
Provision is also made for gravity refueling through overwing filler
of the aircraft.
caps on each wing. Only fuel conforming to P and W (Canada)
Specification CPW 204 must be used. Position a suitable type fire extinguisher in the immediate area of
WARNING: the aircraft and ensure that personnel involved in refueling are
FUEL VAPORS ARE EXTREMELY EXPLOSIVE AND EVERY familiar with its use.
PRECAUTION MUST BE TAKEN TO PREVENT IGNITION. SAFE− Ground aircraft and fuel tender.
TY PRECAUTIONS ARE PROVIDED TO PREVENT INJURY TO
PERSONNEL AND/OR DAMAGE TO EQUIPMENT, AND TO Ensure that aircraft electrical power is off except when pressure
ALERT PERSONNEL TO THE HARMFUL EFFECTS OF FUEL refueling method is used. During pressure refueling, all electrical
COMING IN CONTACT WITH EYES AND SKIN AND INHALATION services must be off, except those required for monitoring the oper−
OF FUEL VAPORS. ation.

Avoid fuel spillage as this will greatly increase the fire hazard.
PERSONNEL MUST TAKE EVERY PRECAUTION TO AVOID
FUEL CONTACTING EYES AND SKIN, INHALATION OF FUEL Before refueling the auxiliary fuel tanks (if required) make sure the
VAPORS, AND ACCIDENTAL SWALLOWING OF FUEL. ANYONE main fuel tanks are full.
EXPOSED TO THESE CONDITIONS MUST WASH CONTACTED Prior to carrying out the Pre−Check test operation of the back−up
AREAS THOROUGHLY WITH WATER AND SEEK PROMPT MED− refuel shut−off feature, reduce the refueling pressure to minimum.
ICAL ATTENTION.

EFFECTIVITY: ALL
12−10−28 Page 36
Jan/07
 A B

No 1 TANK No 2 TANK

FUEL 2 FUEL 2
1 QTY 1 QTY

POWER ON
LBS X 1000 3 LBS X 1000 3
0 0
T OFF T
SE REFUEL DEFUEL SE

C
DUMP VALVE REFUEL REFUEL DUMP VALVE
OPEN SHUTOFF SHUTOFF OPEN
TANK 1 TANK 1 TANK 1 TANK 1
PRE CHECK BATT
TEST REFUEL
MASTER
GROUND
VALVE TANK TANK CREW
CLOSED 1 2
JACK

PRESSURE REFUEL/
A DEFUEL PANEL

C OVERWING FUEL FILLERS

FTSD10600a_046

PRESSURE REFUEL/
B DEFUEL ADAPTER Fuelling Points

12−10−28 Page 37
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 Dash 8 Series 100 Technical Training Manual

Fueling cont’d

Precautions cont’d

In case of fuel spillage, either at the aircraft refueling adapter or at

the wing tank vents, refueling operations should be stopped imme−
diately.

Before inserting fueling nozzle in tank at overwing filling point, or

connecting fuel tender hose to refuel/defuel adapter, ground nozzle
or hose to grounding socket adjacent to filling point and momentari−
ly bare hand contact fuel nozzle before commencing operation to
allow static electrical potential equalization.

Avoid carrying out other work on the aircraft during a refueling oper−
ation.

Inform the fuel truck operator in advance that APU will be running.
Fuel truck must be parked at least 30 feet (9.2 meters) from the
exhaust .

EFFECTIVITY: ALL
12−10−28 Page 38
Jan/07
 FUEL TRUCK
CLEAR ZONES
DURING REFUELING
FUEL VENTS
ft
20
7m

6.2 m
30ft
N O T E : P a r k th e f u e l tr u c k a t AP U EXHAUST
l e a s t 9 . 2 m ( 3 0 f t) a w a y OP ENING
FTSD10600a_02 2

f r o m th e e x h a u s t i f A P U
i s o p e r a ti n g .

APU − Fuel T ruck Zones During Pressure Refueling

12−10−28 Page 39
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 Dash 8 Series 100 Technical Training Manual

Fueling cont’d

Fuelling with APU Running

Aircraft with APU. If unit is to be run during pressure refueling oper−

ations, the following additional safety precautions apply:

Do not operate APU unattended during pressure refueling.

Do not operate APU during gravity refueling.

The aircraft left main fuel tank must contain sufficient fuel to allow
continuous operation of the APU.

Keep clear of exhaust when working in the vicinity.

EFFECTIVITY: ALL
12−10−28 Page 40
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 AP U ACCESS P ANEL HOT ZONE

5 DEGREES
AP P ROXIMATELY

2.5 METERS
8 FEET AP P ROXIMATELY

20° AP P ROXIMATELY
AP U INTAKE OP ENING
HOT ZONE
FTSD10600a_02 4

AP U EXHAUST
OP ENING
APU Exhaust Gasses − Plan And Elevation Views

EFFECTIVITY: ALL
12−10−28 Page 41
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 Dash 8 Series 100 Technical Training Manual

Hydraulic Systems

General

Hydraulic power is provided by two independent main systems to WARNING:

operate various flight controls and landing gear services. In addi− CHECK THAT MAIN GEAR GROUND LOCK AND MAIN GEAR
tion there is a separate system for main landing gear emergency DOORS LOCK PINS ARE INSTALLED BEFORE REPLENISHING
extension. HYDRAULIC SYSTEM.

The following approved hydraulic fluids may be freely mixed and

used for replenishment purposes:
· Hyjet IV

· Hyjet IV−A

· Hyjet IV−A Plus

· Skydrol LD4

· Skydrol 500B4

WARNING:
HYDRAULIC FLUID MAY CAUSE SKIN IRRITATION. AVOID PRO−
LONGED OR REPEATED CONTACT WITH SKIN. IN CASE OF
EYE CONTACT, FLUSH EYES THOROUGHLY WITH WATER
AND SEEK PROMPT MEDICAL ATTENTION. IN CASE OF
INGESTION, SEEK PROMPT MEDICAL ATTENTION.

EFFECTIVITY: ALL
12−10−29 Page 42
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 Dash 8 Series 100 Technical Training Manual

RESER. FILL

SUCTION
AIN
DR

SAFE

B B BRAKE SYSTEM HANDPUMP

A EMERGENCY A
RESERVOIR

QUICK RELEASE
FILL CONNECTION
FTSD10600a_049

RETURN MANIFOLD
C
(No. 1 & No. 2 NACELLES)

Hydraulic Systems

EFFECTIVITY: ALL
12−10−29 Page 43
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 Dash 8 Series 100 Technical Training Manual

Hydraulic Systems cont’d

Hydraulic Servicing Procedures Bleeding the System

The following is an outline to servicing the Main hydraulic systems On related engine, hand swing propeller smartly in a counterclock−
on the Dash−8 100 aircraft as per AMM 12−10−29. wise direction (while looking aft) until resistance to rotation is felt.
· Landing gear − Extended.
NOTE:
· Roll spoilers − Retracted. With D.C. ground power on aircraft a pressure reading of between
500−1000 psi should be seen by observer on related pressure
· Wing flaps − Up. gauge in cockpit.

· Parking brake system − Pressurized (2700 to 3000 psi). NOTE:

If Pressure build−up does not occur on propeller rotation refer to the
· Main landing gear doors open and door lock pins installed. AMM 12−10−29.

Remove dust caps from FILL port on return manifold and BLEED/ Press the bleeder button while the propeller is hand swung, and
SAMPLE port on rear of ground service panel. bring fluid level to value given on Temp/Quantity graph adjacent to
indicator.
Connect fluid dispenser feed line coupling to FILL port on return
manifold. Release bleeder button.
NOTE:
Ensure hose and supply source are free of air and contamination. Disconnect filling rig and bleed/sample port drain hose and reinstall
dust caps.
Connect drain hose with container to BLEED/SAMPLE port to col−
lect fluid. Repeat on other system.

Introduce fluid until correct fluid level is attained, as defined by

graph of TEMP/ QUANTITY adjacent to indicator.

EFFECTIVITY: ALL
12−10−29 Page 44
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 Dash 8 Series 100 Technical Training Manual

1 2
Callout Key
1. Bleeder Button
2. Reservoir
3. Handpump
4. Quantity Indicator
5. Overspill Container Jar
6. Bleed Port
7. Ground Service Panel
8. Return Manifold
9. Fill Port
10. Dipstick

10
9

8
FTSD30600a_014

7 6 5 4 3

Replenishing Main Hydraulic Systems Reservoirs

EFFECTIVITY: ALL
12−10−29 Page 45
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 Dash 8 Series 100 Technical Training Manual

Hydraulic Systems cont’d

Overspill Container

An overspill container assembly is installed in each nacelle. The

assembly consists of an aluminum container, a lid and a contents
dipstick, and has a capacity of 1.2 liters.

Accumulation of fluid from the standby power unit pump seal drain
and the reservoir pressure relief valve is collected in the overspill
container.

The dipstick with an engraved SAFE level, is provided to facilitate

checking of the fluid level and so determine the need for emptying.

Contents Check

Remove dipstick from overspill container.

If fluid level is below SAFE mark, replace dipstick.

If fluid level is above SAFE mark, unscrew and remove container jar
from container lid and dump fluid into suitable receptacle.

Install jar in container lid.

Install dipstick.

EFFECTIVITY: ALL
12−10−29 Page 46
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 Dash 8 Series 100 Technical Training Manual

B
FTSD10600a_047

A B

Hydraulic Overspill Container

EFFECTIVITY: ALL
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 Dash 8 Series 100 Technical Training Manual

Hydraulic Systems cont’d

Emergency System Reservoir

An emergency system provides hydraulic power for extension of the

main landing gear by an auxiliary actuator when the main system
hydraulic power is not available.

The reservoir is mounted in the RH side of the nose equipment

compartment. Secured to the reservoir cap are suction, fill and drain
line connections and dipstick assembly. A level mark on the dip−
stick is stamped ’SAFE’ and a label on the outside of the reservoir
is marked EMER LANDING GEAR RESERVOIR.

Replenishing the Emergency System

Open right hand, bottom, nose equipment compartment door.

Ensure that exterior of reservoir is clean, especially in area of dip−

stick.

Remove dust cap from fill connection.

Referring to dipstick, replenish reservoir as necessary to SAFE

level. Install dipstick.

Install cap on fill connection.

EFFECTIVITY: ALL
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 Dash 8 Series 100 Technical Training Manual

Callout Key
1. Fill Connection
RESER. FILL
2. Dust Cap
3. Clamp
SUCTION 4. Reservoir
AIN
DR 5. Dispstick

SAFE
4

3
FTSD30600a_017

1 2
A A
Replenishing Emergency System Reservoir

EFFECTIVITY: ALL
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 Dash 8 Series 100 Technical Training Manual

Course Notes: Instructor Questions\Comments:

EFFECTIVITY: ALL
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 Dash 8 Series 100 Technical Training Manual

HYDRAULIC SYSTEM RESERVOIR FILLING INSTRUCTIONS

BLEEDING NO. 1
3.0
A. 1. Ensure that the following conditions exist: B. 1. Check supply of Hydraulic System for air
entrapment as follows:

(QTS)
WA R N I N G CHECK THAT MAIN GEAR GROUND LOCK
AND MAIN GEAR DOORS LOCK PINS ARE NOTE: It is recommended that an observer
is in cockpit to check gages. 2.0
INSTALLED BEFORE REPLENISHING
HYDRAULIC SYSTEM.

QUANTITY
(a) On related engine, hand swing propeller smartly
in a counterclockwise direction (while looking aft)
(a) Landing gear - Extended.
until resistance to rotation is felt.
(b) Roll spoilers - Retracted. 1.0
(c) Wing flaps - Up. -50 0 50 100 150 200
(b) With D.C. ground power on aircraft a pressure reading
(d) Parking brake system - Pressurized (2700 to 3000 psi) FLUID TEMP
of between 500-1000 psi should be seen by observer
(e) Main landing gear doors open and door lock pins installed. (°F)
on related pressure gauges in cockpit.
No. 1 MAIN HYDRAULIC SYSTEM
2. Remove dust caps from FILL port on return manifold and (c) Press the bleeder button while the propeller is hand RESERVOIR
BLEED/SAMPLE port on rear of ground service panel. swung and bring fluid level to value given on Temp/
Quantity graph adjacent to indicator.
3. Connect fluid dispenser feed line coupling to FILL port
on return manifold. Connect drain hose with container (d) Release bleeder button. NO. 2
to BLEED/SAMPLE port to collect fluid.

(QTS)
(e) Disconnect filling rig and bleed/sample port drain
NOTE: Ensure hose and supply are hose and reinstall dust caps. 5.0
free or air and contamination.

QUANTITY
4.0
4. Introduce fluid until correct fluid level is attained,
as defined by graph of TEMP / QUANTITY adjacent
to indicator. 3.0
FTSD30600a_015

2.0
N O T E : R e s e r v o i r L a b e l - A p p l i c a b l e To B o t h N o . 1
a n d N o . 2 M a i n S y s t e m R e s e r v o i r. s -50 0 50 100 150 200
FLUID TEMP
(°F)
No. 2 MAIN HYDRAULIC SYSTEM
RESERVOIR
Hydraulic System Servicing

EFFECTIVITY: ALL
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 Dash 8 Series 100 Technical Training Manual

Landing Gear

General

The shock struts can be charged with nitrogen and hydraulic fluid CAUTION:
without jacking the aircraft. BEFORE RELEASING PRESSURE FROM SHOCK STRUTS,
ENSURE THAT AIRCRAFT IS WELL CLEAR OF HANGAR
When a shock strut has been replaced, or fully recharged, check STRUCTURE AND GROUND EQUIPMENT.
that nitrogen pressure/strut extension is correct as soon as possible
after five landings; refer to servicing curve on applicable instruction ISOLATE ELECTRICAL POWER FROM LANDING GEAR AND
and identification plate. If incorrect, rectify in accordance with appro− DEPRESSURIZE HYDRAULIC SYSTEMS.
priate charging procedure for nose or main gear shock strut.

Precautions
WARNING:
FAILURE TO OBSERVE SAFETY PRECAUTIONS DETAILED IN
THE FOLLOWING PROCEDURES COULD RESULT IN INJURY
TO PERSONNEL AND/OR DAMAGE TO EQUIPMENT.

CAUTION:
ENSURE THAT CORRECT HYDRAULIC FLUID, SPECIFICATION
MIL− H−5606, IS USED TO FILL SHOCK STRUTS.

USE OF PHOSPHATE ESTER BASE FLUIDS IS STRICTLY PRO−

HIBITED, AS IT WOULD RESULT IN SEVERE DETERIORATION
OF SHOCK STRUT SEALS.

USE ONLY NITROGEN WHEN CHARGING SHOCK STRUTS. DO

NOT USE COMPRESSED AIR.

EFFECTIVITY: ALL
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 Dash 8 Series 100 Technical Training Manual

A B

Charging Port

Bleed Port
FTSD10600a_056

A NOSE GEAR B MAIN GEAR

Landing Gear

EFFECTIVITY: ALL
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 Dash 8 Series 100 Technical Training Manual

Landing Gear cont’d

Charging of the Nose Gear Shock Strut

The Nose gear shock strut can be serviced with or without the use Connect nitrogen servicing hose kit to charging valve, check that
of a Hydraulic Fluid Dispenser with Adapter. In this section we will swivel nut is loosened and inflate shock strut until Dimension ’X’ is
cover the procedure without the Hydraulic Fluid Dispenser. 1.0 to 3.0 inches (2.54 to 7.62 cm).

Tighten swivel nut but do not torque

WARNING:
CHECK THAT NOSE GEAR GROUND LOCK IS FULLY Remove nitrogen servicing hose kit and connect pressure gage to
ENGAGED AND NOSE GEAR DOORS LOCK PIN IS INSTALLED charging valve.
BEFORE SERVICING SHOCK STRUT. IF GROUND LOCK WILL
Loosen swivel nut, observe pressure reading on gage and retighten
NOT MOVE TO FULLY ENGAGED POSITION, INSTALL NOSE
swivel nut. Remove pressure gage.
FUSELAGE JACK IMMEDIATELY BEFORE INVESTIGATING
CAUSE OF PROBLEM. Determine correct Dimension ’X’ for observed pressure reading from
servicing curve. If incorrect, increase or decrease nitrogen pressure
through charging valve to obtain correct Dimension ’X’.

Remove valve cap and loosen swivel nut on charging valve and Torque swivel nut and install valve cap.
slowly release all nitrogen pressure until shock strut is fully com−
pressed with aircraft weight on nose gear.

Remove lockwire from valve body and remove charging valve from
shock strut.

Fill shock strut, through charging valve port, with hydraulic fluid.
Continue filling until overflow is free of air bubbles.

Install new preformed packing on valve body and reinstall charging

valve on shock strut. Torque valve body and safety with lockwire.

EFFECTIVITY: ALL
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 Dash 8 Series 100 Technical Training Manual

Callout Key
B
1. Va l v e C a p
2. Swivel Nut
3. Va l v e B o d y
4. Preformed Packing

1 2 3 X

S E RV I C E I N S T R U C T I O N S
A N D I D E N T I F I C AT I O N P L AT E
FTSD30600a_008

4
B
C H A R G I N G VA LV E
Nose Gear Shock Strut Servicing

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 Dash 8 Series 100 Technical Training Manual

Landing Gear cont’d

Charging of the Nose Gear Shock Strut cont’d

As soon as possible after five landings, carry out the following pro−
cedures.

Remove valve cap and connect pressure gage to charging valve.

Loosen swivel nut, note nitrogen pressure and measure shock strut
extension Dimension ’X’.

From servicing curve, check Dimension ’X’ which corresponds with

nitrogen pressure noted in step (b).

If nitrogen pressure/shock strut extension does not correspond with

readings from servicing curve, rectify as follows:

Tighten swivel nut and remove pressure gage from charging valve.

Connect nitrogen servicing hose kit to charging valve, loosen swivel

nut and increase or decrease nitrogen pressure to obtain correct
pressure/shock strut extension (Dimension ’X’) shown on servicing
curve.

Tighten swivel nut, and disconnect nitrogen servicing hose kit from
charging valve.

Install valve cap.

EFFECTIVITY: ALL
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 Dash 8 Series 100 Technical Training Manual

SERVICE INSTRUCTIONS
SHOCK STRUT ASSEMBLY
DHC-8 NOSE GEAR

1. OPEN CHARGING VALVE TO FULLY COMPRESS STRUT.

2. WITH AIRCRAFT WEIGHT ON GEAR CONNECT HYDRAULIC LINE
TO CHARGING VALVE. FILL STRUT TO OVERFLOW WITH
MIL-H-5606 HYDRAULIC FLUID
3. DISCONNECT HYDRAULIC SUPPLY.
4. INFLATE STRUT WITH NITROGEN UNTIL DIMENSION 'X' IS
1.0 TO 3.0 INCHES.
1500 1500
5. MEASURE NITROGEN PRESSURE IN STRUT.
6. DETERMINE CORRECT DIMENSION 'X' FOR THIS PRESSURE FROM
SERVICING CURVE.
1300 1300
7. EITHER ADD OR RELEASE NITROGEN TO OBTAIN CORRECT
DIMENSION 'X'
1100 1100

PRESSURE

PRESSURE
(PSI)

(PSI)
INFORMATION: GAS CHARGE PRESSURE WITH STRUT FULLY
EXTENDED IS 290 PSI. (WHEN DIM. 'X' = 5.17in.) 900 900

700 700
NOTE: As soon as possible after 5 landings,
carry out a nitrogen pressure/shock strut
F T S D 3 0 6 0 0 a _ 0 11

extension check.
500 500

WA R N I N G RELEASE INFLATION PRESSURE IN 300 300

4.0 3.0 2.0 1.0 0.5
STRUT BEFORE DISASSEMBLY
'X' DIMENSION
(IN.)
Nose Gear Service Instruction Decals

12−10−33 Page 57
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 Dash 8 Series 100 Technical Training Manual

Landing Gear cont’d

Charging of the Main Gear Shock Strut

WARNING: When shock strut is fully compressed, tighten swivel nut (3) and
CHECK THAT MAIN GEAR GROUND LOCK AND MAIN GEAR close valve on hydraulic fluid return line. If necessary, repeat steps
DOORS LOCK PINS ARE INSTALLED BEFORE SERVICING until discharging fluid is completely free of air bubbles.
SHOCK STRUT. Remove hydraulic fluid return line and charging rig and install dust
cap on lower charging valve.
Remove upper charging valve cover plate from shock strut fairing.
Connect nitrogen servicing hose kit to upper charging valve and
Remove valve cap, loosen swivel nut on upper charging valve and ensure that swivel nut is loosened. Inflate shock strut until strut
slowly release all nitrogen pressure until shock strut is fully com− starts to extend and note pressure at which this occurs.
pressed with aircraft weight on main gear.
From servicing curve, establish shock strut extension Dimension ’X’
Tighten swivel nut (3) and connect hydraulic fluid return line to which corresponds to nitrogen pressure noted in step.
upper charging valve.
Gradually increase nitrogen pressure through upper charging valve
NOTE: until shock strut extension is equal to Dimension ’X’ established in
Return line should be clear plastic tubing to allow observation of air step.
bubbles in discharged hydraulic fluid Tighten swivel nut, and disconnect nitrogen servicing hose kit from
Connect hydraulic fluid charging rig to lower charging valve and upper charging valve. Install valve cap.
pump fluid into shock strut until strut extends 2.0 to 3.0 inches (5.08 Install upper charging valve cover plate on shock strut fairing,
to 7.62 cm).

At upper charging valve, loosen swivel nut (3) and open valve on
hydraulic fluid return line. Allow aircraft weight to fully compress
shock strut and discharge excess fluid and air back to reservoir on
hydraulic fluid charging rig.

EFFECTIVITY: ALL
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 Dash 8 Series 100 Technical Training Manual

Callout Key
1 NIT ROGEN SERVICING HOSE
1. P re forme d P ac king KIT AND PRESSURE GAUGE
UPPER CHARGING
2. Valve Cap VALVE (NIT ROGEN)
3. Swive l Nut
4. Valve Body
5. Lowe r Charging Valve
(Hy draulic Fluid)
6 . S e r v i c e I n s tr u c ti o n s 4 3 2
A n d I d e n ti f i c a ti o n
A

6
A

0−500 P SI
FTSD10600a_02 5

RETURN

P RSSURE

HYDRAULIC FLUID
Replenishing Main Gear Shock Strut CHARGING RIG

EFFECTIVITY: ALL
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 Dash 8 Series 100 Technical Training Manual

Landing Gear cont’d

Charging of the Main Gear Shock Strut cont’d

As soon as possible after five landings, carry out the following pro− Tighten swivel nut , and disconnect nitrogen servicing hose kit from
cedures. upper charging valve.
WARNING:
CHECK THAT MAIN GEAR GROUND LOCK AND MAIN GEAR Install valve cap.
DOORS LOCK PINS ARE INSTALLED BEFORE SERVICING
SHOCK STRUT. Install upper charging valve cover plate on shock strut fairing.

Remove upper charging valve cover plate from shock strut fairing.

Remove valve cap and connect pressure gage to upper charging

valve.

Loosen swivel nut , note nitrogen pressure and measure shock strut
extension Dimension ‘X’.

From servicing curve, check Dimension ‘X’ which corresponds with

nitrogen pressure from the previous steps.

If nitrogen pressure/shock strut extension does not correspond with

readings from servicing curve, rectify as follows:

Tighten swivel nut and remove pressure gage from upper charging
valve.

Connect nitrogen servicing hose kit to upper charging valve, loosen

swivel nut and increase or decrease nitrogen pressure to obtain cor−
rect pressure/shock strut extension (Dimension ’X’) shown on serv−
icing curve.

EFFECTIVITY: ALL
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 Dash 8 Series 100 Technical Training Manual

Callout Key
SERVICE INSTRUCTIONS
SHOCK STRUT ASSEMBLY 1. Nitrogen Charging
DHC-8 MAIN GEAR 1 Va l v e
2 . O i l C h a r g i n g Va l v e
THIS SEQUENCE OF ACTIONS WILL ACHIEVE THE CORRECT
STATE OF THE UNIT REGARDLESS OF ITS PRIOR STATE 2
X
1. REMOVE NITROGEN CHARGING VALVE FAIRING COVER
2. WITH WEIGHT ON WHEELS SLOWLY OPEN NITROGEN CHARGING
VALVE AND ALLOW STRUT TO FULLY COMPRESS
3. REMOVE NITROGEN CHARGING VALVE
4. CONNECT SOURCE OF MIL-H-5606 FLUID TO OIL CHARGING VALVE
3000 3000
5. FILL STRUT UNTIL OVERFLOW FROM UPPER VALVE PORT IS GAS FREE
6. REMOVE OIL SOURCE
7. REPLACE NITROGEN CHARGING VALVE
8. APPLY NITROGEN PRESSURE UNTIL SHOCK STRUT COMMENCES TO
EXTEND AND NOTE PRESSURE REQUIRED TO INITIATE THE 2500 2500
EXTENSION
9. IDENTIFY FROM THE CHART THE DIMENSION 'X' THAT
CORRESPONDS TO THE NOTED PRESSURE
10. ADD FURTHER NITROGEN UNTIL THE MEASURED EXTENSION IS 2000 2000

PRESSURE

PRESSURE
EQUAL TO THE IDENTIFIED VALUE OF 'X'

(PSI)

(PSI)
11. CLOSE NITROGEN CHARGING VALVE DISCONNECT GAS SOURCE
AND REPLACE FAIRING COVER
1500 1500

INFORMATION: GAS CHARGE WITH SHOCK STRUT FULLY

EXTENDED - 300PSI. (WHEN DIM. 'X' = 12.5in.)
FTSD30600a_010

1000 1000
NOTE: As soon as possible after 5 landings,
carry out a nitrogen pressure/shock strut
extension check.
500 500
WA R N I N G RELEASE INFLATION PRESSURE IN 7 6 5 4 3 2 1 0
STRUT BEFORE DISASSEMBLY 'X' DIMENSION
(IN.)
Main Gear Service Instruction Decals

EFFECTIVITY: ALL
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 Dash 8 Series 100 Technical Training Manual

Tire Pressure Servicing

General

NOTE:
Inflate tire to correct pressures with dry nitrogen using a nitrogen
servicing hose kit incorporating a low pressure regulator.

Main Wheels: 31.0 x 9.75−13 Refer to AMM For Pressures

26.5 x 8−13

Nose Wheels: 22.0 x 6.5−10 − Refer to AMM For Pressures

18.0 x 5.5−8

EFFECTIVITY: ALL
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 Dash 8 Series 100 Technical Training Manual

A B
Example Only Example Only
NOSE LANDING GEAR MAIN LANDING GEAR
T IRE INFLAT ION PRESSURES T IRE INFLAT ION PRESSURES
DSC 2 61 (2 2 .0 * 6.50 − 10) DSC 394 AND DSC 42 8
60 P SI UNLOADED (31.0 *9.7 5 14)
62 P SI LOADED 97 P SI UNLOADED
101 P SI LOADED

B
A
10600a_053

NOSE GEAR MAIN GEAR

EFFECTIVITY: ALL
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 Dash 8 Series 100 Technical Training Manual

Parking Brake Accumulator

General

An accumulator in the parking brake system maintains pressure for

brake application after engine shutdown.

A handpump is provided for use on the ground only, to restore

accumulator hydraulic pressure when necessary.

The air pressure indicator and the air charging valve are
located at the bottom of the parking brake accumulator in right hand
wing to fuselage fairing.

WARNING:
CHECK THAT MAIN GEAR GROUND LOCK AND MAIN GEAR
DOORS LOCK PINS ARE INSTALLED BEFORE SERVICING
PARKING BRAKE ACCUMULATOR.

Exhaust brake pressure by operating parking brake lever repeatedly

until PARK BRAKE indicator in flight compartment reads zero.

Check accumulator nitrogen pressure on indicator in the right hand

wing root (900 psi minimum).

If accumulator pressure is below 900 psi, remove panel and charge

to 1000 psi with nitrogen at charging valve adjacent to indicator
using servicing hose kit.

Re−install panel.

EFFECTIVITY: ALL
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 Dash 8 Series 100 Technical Training Manual

2 3

4
0

5
PSI
X 1000
FTSD10600a_054

Parking Brake Accumulator

EFFECTIVITY: ALL
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 Dash 8 Series 100 Technical Training Manual

Oxygen System

General

The Dash−8 100 oxygen system consists of high−pressure cylinders, Smoking, or any kind of open flame is prohibited.
portable and stationary, the configuration is dependent on customer
Charge or discharge oxygen cylinders removed from aircraft in well
order optional equipment. General review of the safety precautions
ventilated areas.
will be reviewed in this section.
An oxygen system must be purged if the system has been opened
The following are the standard configuration; or if system pressure is reduced to less than 25 psi for a period
greater than 2 hours
Nose compartment: Fixed cylinder for the crew stationary oxygen
system. An oxygen cylinder must be purged if pressure is reduced to less
than 25 psig for a period greater than 2 hours (refer to Chapter 12).
Flight compartment: Portable crew cylinder.
Ensure cylinder orifice is pointed away from personnel during dis−
Cabin compartment: Portable passenger, flight attendant and first
charge procedures as high pressure oxygen can penetrate the
aid cylinders.
blood stream if directed against the skin.
WARNING: Ensure rate of charging does not exceed 500 psi pressure rise per
THE FOLLOWING RULES MUST BE STRICTLY ADHERED TO minute
WHEN SERVICING OXYGEN CYLINDERS. Maximum cylinder charge pressure is to be as indicated on the indi−
Ensure that personnel trained in the safety precautions are permit− vidual cylinder.
ted to carry out servicing on oxygen equipment.

Ensure all clothing, hands, tools, fittings, oxygen components and

the work area are free from oil and grease. Oil or grease exposed
to oxygen could result in an explosion. Remove all traces of oil or
grease on or around oxygen equipment by washing with a castile
soap and water solution.

EFFECTIVITY: ALL
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 Dash 8 Series 100 Technical Training Manual

A 10 15
5 20

0 25
OXYGEN PRESS
PSI X 100

A FIXED CREW B OXYGEN

OXYGEN BOTTLE PRESSURE GAUGE

B
FTSD30600a_038

C P O R TA B L E
OXYGEN BOTTLE
C
Crew Oxygen System

EFFECTIVITY: ALL
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 Dash 8 Series 100 Technical Training Manual

Wash Water System

General

The wash water system provides warm water to the sink unit in the
lavatory compartment. The system incorporates a 22 litres (5.8
U.S. gallons) tank for cold water, a filter, a micropump, a 400 watt
heater and a manually operated drain valve for draining the system.

The water is electrically heated when the LAVATORY LIGHT switch

on the flight attendants panel is switched to the on position.

Replenishing Water Systems

NOTE:
Potable water only must be used to replenish the water systems.

On lower left underside of door, push up on latch and allow door to

open.

Check drain valve on lower side of tank is closed.

Remove tank filler cap and fill tank to base of filler neck with potable
water.

Install filler cap.

EFFECTIVITY: ALL
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 Dash 8 Series 100 Technical Training Manual

2
Callout Key
3 4 1. Sink Unit
2 7 2. Button Switch
1 WATER TANK
3. Sink Drain
Control
4. Heater
5 . D r a i n Va l v e
6. Filter
5
7. Filler Port
8. Door
9. Latch
MICRO
PUMP 6 1 0 . D r a i n Va l v e
8
FTSD30600a_021

10

S t a n d a r d Wa s h Wa t e r S y s t e m

EFFECTIVITY: ALL
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 Dash 8 Series 100 Technical Training Manual

Wash Water System cont’d

Operation

Warm water is supplied under pressure to the sink unit by the elec−
trically operated micropump.

When faucet lever is pressed and released, 28 volt dc power ener−

gizes the delay relay K1, and through potentiometer (R1) operates
the pump. After approximately 4 seconds, relay K1 de−energizes
and cuts power to the pump.

Selection of the lavatory lights to on the flight attendant’s control

panel connects 28 volt dc power, through thermoswitch (S2), to
energize relay (K2) to operate the water heater, and to maintain the
temperature of the water supplied to the sink unit.

The system drain valve and waste from the sink unit are connected
to the overboard drainage system. A flow sensor in the pump auto−
matically switches off the pump if all the water is used.

EFFECTIVITY: ALL
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 Dash 8 Series 100 Technical Training Manual

MICROPUMP
M WATER
HEATER
28 V DC (D2) R1
5
R SEC
WATER CCW CW K2
PUMP BUTTON TD
SWITCH
S1
K1
DELAY THERMOSWITCH S2
RELAY
LAVATORY
LIGHTING
28 V DC (R3)
5 TO TOILET
L MAIN COMPARTMENT
LAVATORY LIGHTING
LIGHTS

(3321-S3)
FLIGHT
ATTENDANT
SWITCHING
PANEL
FTSD30600a_026

WATER (E2)
15
HTR
28 V DC
R SEC NOTE: In de nt co de is 38 2 1 un less
o the rwise indica te d.

Wa s h Wa t e r S y s t e m E l e c t r i c a l S c h e m a t i c

EFFECTIVITY: ALL
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 Dash 8 Series 100 Technical Training Manual

Lavatory

General

The Toilet unit located in the forward right hand side of the cabin is Charge tank with 2.5 US gallons (9.5 liters) of anti−freeze solution
externally serviced and electrically operated. (mixed 75% to 25%) through either flush/fill line or manually via toi−
let bowl.

System Servicing Disconnect connector (5) and flush/fill hose (4).

Close sewage drain cover (1) and replace cap (2).

WARNING:
CHEMICAL CONCENTRATE USED IN TOILET, MAY CAUSE
IRRITATION IF IT CONTACTS EYES OR SKIN. IF CONCEN− NOTE:
TRATE CONTACTS EYES OR SKIN, FLUSH WITH CLEAN Sewage drain cover will not close if drain plug is not fitted.
WATER. IF IRRITATION PERSISTS, SEEK MEDICAL AID.
Cycle flush system at least once to charge complete system with
Open toilet servicing panel 132AR. anti−freeze

Open sewage drain cover and remove cap.

Couple connector and flush/fill hose to appropriate connections at

service panel.

Extract sewage drain plug by operating plug extractor handle.

When toilet tank has drained, flush with 10 US gallons (37.85 liters)
of water at 30 to 125 psi.

Install sewage drain plug (3).

EFFECTIVITY: ALL
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 Dash 8 Series 100 Technical Training Manual

1
Callout Key
1. Sewage Drain Plug
2. Flush-Fill Hose
3. Connector
4. Plug Extractor Handle

MAIN SEWAGE DRAIN

COVER OPEN AND
FLUSH-FILL CAP
REMOVED
2 3 4
EXTERNAL SERVICING
PANEL DOOR OPEN

CONNECTOR COUPLED FOR

DRAINING AND FLUSHING
OPERATIONS
FTSD30600a_023

1
TO EXTRACT PLUG, PUSH
FROM WATER
DISCHARGE TO T-HANDLE FULLY IN TO
SUPPLY
SERVICE RIG OR ENGAGE PLUG, ROTATE
(30 TO 125 PSI)
WASTE CONTAINER HANDLE 1/4 TURN CLOCK-
WISE TO LOCK, AND PULL
FULLY OUT.
To i l e t S e r v i c i n g

EFFECTIVITY: ALL
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 Dash 8 Series 100 Technical Training Manual

Ground Air Connection

General Connection Procedures

Turn FWD OUTFLOW VALVE selector, located on copilot’s side

Ground conditioned air is supplied to the cabin and flight compart−
console, to OPEN position.
ment through an eight− inch universal ground service air inlet locat−
ed on the left−hand side (with APU installed) or right−hand side (with Apply electrical power.
APU not installed) of the rear fuselage.
Select OFF − RECIRC. switch, located on the AIR CONDITIONING
panel in the flight compartment to RECIRC.
Application and Removal of Ground Conditioned Air
On appropriate side of aircraft, unlatch and open door to gain
WARNING: access to ground service air inlet.
THE USE OF GROUND CONDITIONED AIR, ESPECIALLY WARM
Connect ground air connector to ground service air inlet, ensuring
AIR, WILL CAUSE A POSITIVE CABIN PRESSURE DIFFEREN−
lugs on ground air connector engage slots in ground air inlet.
TIAL. AN UNCONTROLLED RATE OF DOOR OPENING CAUSED
BY A POSITIVE CABIN PRESSURE DIFFERENTIAL MAY CAUSE Rotate ground air connector clockwise until locked into position.
BODILY HARM.

CAUTION: Disconnection Procedures

BEFORE CONNECTING GROUND AIR CONNECTOR ENSURE
Rotate ground air connector counter−clockwise until lugs are
THE SAFETY OUTFLOW VALVE ON THE FRONT PRESSURE
released from slots in ground air inlet.
BULKHEAD IS FULLY OPEN TO ALLOW CABIN PRESSURE TO
RELIEVE WITH AIRSTAIR DOOR CLOSED. Close and latch access door.

Disconnect electrical power,

Select OFF − RECIRC. switch to OFF.

Turn FWD OUTFLOW VALVE selector back to the NORMAL

(closed) position.

EFFECTIVITY: ALL
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 Dash 8 Series 100 Technical Training Manual

INLET
(DOOR OPEN) DOOR
CLOSED 1 2

A GROUND CONDIT IONED

AIR CONNECT ION
Callout Key
N O T E : T h e G r o u n d c o n d i ti o n e d a i r
FTSD10600a_052

c o n n e c ti o n i s l o c a te d o n l e f t h a n d 1 . G r o u n d A i r C o n d i ti o n i n g
s i d e w i th A P U i n s ta l l e d , o r r i g h t U n i t ( A p u I n s ta l l e d )
h a n d s i d e w h e n A P U i s n o t i n s ta l l e d . 2 . G r o u n d A i r C o n d i ti o n i n g
U n i t ( A p u N o t I n s ta l l e d )

Ground Air Servicing

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Fuselage Drains

General

Waste disposal is achieved by means of overboard drainage

through a drain mast located underside of the forward fuselage.

The forward drain lines are from the lavatory compartment and the
passenger door threshold and connect to a common drain pipe.

The common drain pipe connects to the forward drain mast and is
installed at a slight slope to allow drainage when the aircraft is on
the ground.

When the aircraft is in flight, the differential pressure between the

cabin air and outside air induces drainage and prevents ice forma−
tion on mast.

A vent pipe from the toilet is also incorporated into the forward drain
system.

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Callout Key
1. Sink Drain
2 . Toile t Ve nt
3 . L a v a to r y C o m p a r tm e n t
Floor Drain
4 . D r a i n M a s ts
5. P as s e nge r Door Drains

1 4
2
3
FTSD10600a_035

Waste Drains

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 Dash 8 Series 100 Technical Training Manual

CAUTION:
Engine Oil ALLOW 10 TO 15 MINUTES COOL DOWN BEFORE REMOVING
TANK FILLER CAP. REMOVAL OF FILLER CAP WITH OIL AT
MAXIMUM OPERATING TEMPERATURE COULD CAUSE
General
SPILLAGE BY OIL GUSHING FROM FILLER NECK.
Each engine is equipped with an oil tank, which is an integral part of
Open access panel in engine left side panel to gain access to filler
the compressor inlet case. A filler cap, one for each tank, is acces−
cap and sight glass.
sible through an access panel in the engine cowl center panel.
NOTE:
THE SIGHTGLASS IS GRADUATED TO SHOW OIL, ADD 1, 2, 3,
The oil system has a capacity of approximately 25 liters, tank level
AND MIN. EACH ADD GRADUATION REPRESENTS A CHANGE
can be checked by means of a graduated sight glass window on the
IN TANK LEVEL OF ONE LITRE (ONE QUART U.S.).
right hand side of the engine.

Read sight glass. The normal level with cool oil (approx. 21 degrees
Engine oil levels must be checked within 30 minutes of normal
C) is the OIL mark on the sight glass.
engine shutdown. An established delay is necessary to ensure oil
NOTE:
levels not affected by varying oil temperatures and back−to−tank
When assessing oil loss, consumption for a serviceable engine is
drainage.
considered to be negligible. For maximum permissible oil consump−
NOTE:
tion refer to Engine Maintenance Manual.
Engines left for a period (i.e. overnight) may have misleading oil
level indications. If the engine did not have the level checked within
If oil level is below OIL by less than 1/4 graduation, following engine
30 minutes of the last flight, an engine run must be carried out to
operation of approximately one hour, top up tank to OIL mark on
circulate the oil and bring to normal operating temperatures before
sight glass.
an oil level check can be carried out.
Record quantity of oil added.
Checking the Oil System Level
If oil level is below that described above and there are no fault indi−
cations including external leakage, fault flags on condition panel
CAUTION:
(refer to Chapter 71), or reports of low or fluctuating oil pressure, or
DO NOT INTERMIX DIFFERENT TYPES OF OIL. REFER TO THE
indications of excessive blue smoke at engine exhaust, troubleshoot
P&W MAINTENANCE MANUAL.
engine oil system (refer to Engine Maintenance Manual).

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1
Callout Key
1. Cowl Center Panel
2. O i l Ta n k A c c e s s D o o r
3. Filler Cap
4. Sight Glass Window
5. E n g i n e O i l Ta n k

A
4

MAX OIL
LITRES 1 ADD
OR U.S.
QUARTS 2
MIN 3
FTSD30600a_027

Checking Engine Oil

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APU Oil

General

CAUTION:
The Auxiliary Power Unit (APU) is located in the rear fuselage on
DO NOT INTERMIX DIFFERENT TYPES OF OIL. IF TYPE OF
the right hand side, aft of the rear pressure dome. It is mounted
OIL IN USE IS NOT AVAILABLE, DRAIN OIL SUMP, CHANGE FIL−
fore and aft on a rectangular frame and is supported from beneath
TER AND REPLENISH SUMP WITH ANOTHER APPROVED OIL.
by four struts.

Replenish sump slowly with oil until floating ball is in the center of
the sight gage. Install oil fill plug.
Check Oil Level
Close access panel
Open access panel 311AB.

Check level of oil in sump through sight gage. Oil is at correct level
when metal floating ball is in the center of the sight gage.

CAUTION:
DO NOT OVERFILL OIL SUMP. AN OVERFILLED SUMP WILL
RESULT IN OIL FOAMING, LOW OIL PRESSURE AND HIGH OIL
TEMPERATURE.

If oil level is low, replenish:

Remove oil fill plug.

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Callout Key
1. O i l Te m p e r a t u r e S e n s o r S w i t c h
2. Oil Pressure Switch
3. Magnetic Drain Plug
4. Oil Level Sight Gage
5. Oil Filler Cap
6. Oil Filter
APU 7. Floating Ball

SIDE VIEW
4
3 2 1

5
FTSD30600a_048

4
7 6

APU Oil Check

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Window Cleaning

General Cleaning Aircraft Windows and Windshields

Remove excessive amounts of dirt and other substances from the

CAUTION glass surfaces with clean water applied with a sponge or soft cloth
DO NOT USE ANY ABRASIVE MATERIALS, STRONG ACIDS, Wash gently with mild soap and water, or a 50/50 solution of iso−
METHANOL, METHYL−ETHYL−KETONE, NOVAS 1 OR NOVAS 2. propanol and water or aliphatic naphtha TT−N−95, Type II.

DO NOT EXPOSE THE GLASS WINDSCREENS TO ALUMINUM Rinse thoroughly using clean water and dry using clean, soft cloth
CLEANERS OR METAL BRIGHTENERS. THEY CONTAIN SMALL or sponge; use a straight rubbing motion.
AMOUNTS HYDROFLUORIC ACID WHICH DISSOLVES THE
GLASS SURFACE AND SERIOUSLY AFFECTS THE OPTICAL
AND WATER SHEDDING CHARACTERISTICS OF THE WIN−
DOWS

EXTREME CAUTION MUST BE EXERCISED TO ENSURE THE

WINDOWS ARE NOT EXPOSED TO SOLVENTS WHICH ARE
TYPICALLY REQUIRED IN REFINISHING OPERATIONS.
ENSURE THAT THE SOLVENTS OR SOLVENT VAPORS, AS
THEY BLEED OFF THE DRYING PAINTS, DO NOT CONTACT
THE WINDOWS. EVEN AIRCRAFT NOT BEING PAINTED CAN
BE EXPOSED TO SOLVENTS AND VAPORS WHEN HANGARED
IN THE SAME AREA AS AN AIRCRAFT BEING WORKED ON.

A PROTECTIVE FILM OF POLYPROPYLENE OR POLYETHYL−

ENE MUST BE USED AND BE COMPLETELY SEALED ALL
AROUND THE WINDOW FRAME DURING REFINISHING OPERA−
TIONS.

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FTSD30600a_050

Windshield Cleaning

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 Dash 8 Series 100 Technical Training Manual

Electrical System

General

The electrical system on the Dash−8 consists of a DC and AC sys−

tem. The aircraft is primarily DC.

2 nickel−cadmium or sealed lead acid batteries, 2 starter generators

and 2 Transformer rectifier units(TRU) provide the DC power.

The aircraft can be supplied with an external DC source, which is

connected on the left hand side of the nose compartment.

AC power is provided by 2 generators providing 3 phase 115VAC.

External AC can be connected at the right hand nacelle.

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GROU
ND PO
WER
28 V D
C

EXTERNAL POWER
B
CONNECTOR (DC)
A EXTERNAL POWER
CONNECTOR (AC)
C B

C BATTERIES
FTSD10600a_051

Callout Key 2

1. AC Electric Power Unit

2. DC Electric Power Unit

Electrical Power

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Electrical System cont’d

Application of External DC Power Removal of External DC Power

To apply power to the aircraft DC buses from an external DC power Set EXT PWR switch on DC CONTROL panel to OFF; check that
source, proceed as follows: the green advisory light goes off.

Disconnect external DC power source from external DC power

CAUTION:
receptacle and secure cover.
ENSURE BATTERY MASTER SWITCH IS SELECTED TO "BAT−
TERY MASTER". Switch BATTERY MASTER switch to OFF.

Ensure that all circuit breakers are closed.

Ensure that the external power source can maintain 1000 AMPS at
a minimum voltage of 28 Volts and maximum of 28.5 Volts.

Connect external 28 volt DC power source to the external DC

power on the left side of the aircraft nose.

At the DC CONTROL panel on the overhead console in the flight

compartment,select EXT PWR switch to EXT POWER. Check that
the green advisory light comes on. Reset master caution light if acti−
vated.

At the DC SYSTEM power monitor panel, select the voltage selec−

tor switch (left) to all six positions. Check that the BUS VOLTS dis−
play indicates 28 volts at all positions.

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DC SYSTEM
BUS VOLTS MAIN BATT LOAD

LOAD

L ESS R ESS GEN 1 GEN 2

L MAIN R MAIN L TRU R TRU
L SEC R SEC AUX BATT

TEST

DC CONTROL

OFF OFF

AUX MAIN BATTERY

BATT BATT MASTER

OFF OFF OFF OFF

FTSD30600a_057

GEN 1 GEN 2 MAIN BUS BUS FAULT EXT PWR

TIE RESET
+

DC Electrical System

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Electrical System cont’d

Application of External AC (Variable Frequency) Power Connect a 115−volt Variable Frequency ac power source to the
external AC power receptacle on the aircraft, located on the right
engine nacelle inboardside, to the rear of the main strut hinge point.
WARNING:
HYDRAULIC SERVICES MAY OPERATE. CLEAR PERSONNEL
At DC CONTROL panel, select BATTERY MASTER switch to BAT−
FROM RUDDER, FLAPS, SPOILERS AND LANDING GEAR
TERY MASTER.
BEFORE APPLICATION OF EXTERNAL AC (VARIABLE FRE−
QUENCY) POWER.
On AC CONTROL panel on the overhead console, set EXT
POWER switch to EXT POWER; check that green advisory light
NOTE:
comes on.
If the external does not incorporate a 28−volt DC control power
source, control power is provided from the right essential bus
Reset master caution light if activated.
through the EXT PWR LOGIC circuit breaker (F8).

At AC SYSTEM power monitor panel, select VARIABLE FREQUEN−

CY selector knob to all six positions; check that VOLTS indicator
To apply power to the variable frequency AC buses from an exter−
reads 115V nominal on all phases.
nal power source, proceed as follows:

Removal of External AC (Variable Frequency) Power

Ensure that all circuit breakers are closed, and all switches on the
DC CONTROL and AC CONTROL panels are OFF.
At DC CONTROL panel, select BATTERY MASTER switch to OFF.

Pull and clip SPU circuit breakers on the ac circuit breaker panel.
At AC CONTROL panel, select EXT POWER switch to OFF; check
that the green advisory light goes off.
Select SBY HYD PRESS switches − NORM.

Disconnect external ac power source from external ac power recep−

Insert NLG and NLG bay door lock pins if these doors are open.
tacle and secure cover.

Close SPU circuit breakers at ac circuit breaker panel.

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AC SYSTEM
VOLTS LOAD VOLTS LOAD

INVERTERS VARIABLE FREQUENCY

AUX A A
PRI SEC LEFT RIGHT
B B
C C

TEST

AC CONTROL

OFF

GEN 1 GEN 2

INVERTERS

OFF L R OFF
FTSD30600a_058

EXT PRIMARY OFF SECONDARY

POWER AUXILIARY

AC Electrical System

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