RGA/YAK50 Flight Issue 3 - September 2003 1 1 FLIGHT MANUAL Document No. RGA/YAK50/Flight Issue 3 THIS MANUAL SUPERSEDES ALL PREVIOUS ISSUES, DATED 15 September, 2003 AIRCRAFT REGISTRSATION NO: G- ______________ AIRCRAFT SERIAL NO: _________________ THIS HANDBOOK INCLUDES ALL MATERIAL FOR THE OPERATION AND PERIODIC MAINTENANCE OF THIS AIRCRAFT TYPE Richard Goode Aerobatics White Waltham Airfield Maidenhead, Berks SL6 3NJ Tel: 01628 828974 Prepared for Richard Goode Aerobatics using material supplied by the manufacturers. Whilst every effort has been made to ensure the accuracy of transcription & content, no responsibility can be accepted for any error howsoever caused, nor for any subsequent loss or injury arising from such errors. Reliance placed upon the contents of this publication is at the users own risk. Acknowledgement: Jez Hopkinson – The Yakovlevs Display Team
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RGA/YAK50 Flight Issue 3 - September 2003
1
1
FLIGHT MANUAL
Document No. RGA/YAK50/Flight Issue 3
THIS MANUAL SUPERSEDES ALL PREVIOUS ISSUES, DATED 15 September, 2003
AIRCRAFT REGISTRSATION NO: G- ______________
AIRCRAFT SERIAL NO: _________________
THIS HANDBOOK INCLUDES ALL MATERIAL FOR THE OPERATION AND PERIODIC
MAINTENANCE OF THIS AIRCRAFT TYPE
Richard Goode Aerobatics
White Waltham Airfield
Maidenhead, Berks SL6 3NJ
Tel: 01628 828974
Prepared for Richard Goode Aerobatics using material supplied by the manufacturers. Whilst
every effort has been made to ensure the accuracy of transcription & content, no responsibility
can be accepted for any error howsoever caused, nor for any subsequent loss or injury arising
from such errors. Reliance placed upon the contents of this publication is at the users own risk.
Acknowledgement: Jez Hopkinson – The Yakovlevs Display Team
RGA/YAK50 Flight Issue 3 - September 2003
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LOG OF REVISIONS
Revision
Number
and
Date
Revised
Pages
Description
Of Revision
Approval
and
Date
R1 – 13/2/04 Page 22 Insert additional
pre-flight
inspection in
respect of
security of
control linkages
RGA/YAK50 Flight Issue 3 - September 2003
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TABLE OF CONTENTS
Section Page
1 GENERAL 4
2 LIMITATIONS 7
3 EMERGENCY PROCEDURES 14
4 NORMAL PROCEDURES 20
5 PERFORMANCE 29
6 AEROBATICS 32
7 WEIGHT & BALANCE/
EQUIPMENT LIST 37
8 MAINTENANCE 39
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SECTION 1
GENERAL
TABLE OF CONTENTS
Section Page
1.1 AIRFRAME 5
1.2 ENGINE 5
1.3 PROPELLER 5
1.4 FUEL 6
1.5 OIL 6
1.6 COOLING 6
1.7 WEIGHTS 6
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1. GENERAL DESCRIPTION
1.1 Airframe
Class Landplane-Low wing Monoplane
Number of Seats: 1
Airframe Manufacturer AS YAKOVLEV
Airframe Model Number YAK50
Airframe Type: All metal construction conventional design consisting
of spars, stringers, ribs and skin, fabric covered
moveable control surfaces, retractable main gear and
non retractable tail wheel
Dimensions: Wingspan – 9.5m
Overall length – 7.46m
Tip Chord – 1.082m
Root Chord – 1.997m
Wing area – 15.0m2
Weight empty equipped – 740kg
Max take-off weight – 965kg
Tail Unit
Gross Tail plane area 1.325m²
Gross Elevator Area 1.535ms²
Gross Fin Area 0.609m²
Gross Rudder Area 0.871m²
Landing Gear
Track 2.715m
Wheelbase 1.86m
1.2 Engine
Manufacturer: Vedeneev (Ivchenko) M 14 P
Engine Type: Supercharged, gear driven, air cooled radial 9
cylinders, pressure carburettor
Horsepower Rating: Take off: 360 HP-2% for 5 minutes maximum at 2900
propeller RPM (99%) and at a (manifold pressure
equal to ambient plus 125 millimetres of mercury)
Continuous: 295 HP at 2400 propeller RPM (82%)
(manifold pressure equals ambient plus 125
millimetres of mercury).
1.3 Propeller
Propeller Model Number: V530TA-D35
Number of blades: 2
Propeller Diameter: 2.4 m
Propeller Type: Constant speed and hydraulically actuated.
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Propeller blade angles - at 1 metre radius
Low pitch 14.5
High pitch 34.5
Operating Limits 2900RPM (99%) max speed
1.4 Fuel
There is no fuel tank selector, but the aircraft is fitted with a fuel cut off valve that is left
in the ON position at all times except in the case of an engine fire or forced landing.
Fuel Grade: Aviation Fuel 100LL or 91/96 octane
Fuel Capacity: Main Tank Capacity 55 litres
Main Tank Usable 52 litres
Main and Cruise Tank Capacity: 120 litres
Main and Cruise Tank Usable: 117 litres
Carburetor type No float chamber, automatic mixture control
1.5 Oil
The oil tank is provided with a flop tube to enable oil pick up in all flight attitudes. An oil
cooler is located under the forward fuselage and has a cockpit adjustable air outlet door to
control the oil temperature. To facilitate starting in extremely cold conditions, an oil
dilution system is fitted.
Note: The oil dilution system is not usually required in the UK climate. However in cold
conditions, oil pressure will drop to 1kb/cm shortly after starting until oil is warmed.
Oil Grade: MIL-L-6082 Aviation Grade Straight
Mineral Oil for the first 35 hours and at the first 25-hour
oil change
MIL-L-22851 Ashless Dispersant Oil after
the first 50 hours
Viscosity: Grade 100 (SAE 50)
Oil Capacity: Maximum oil capacity: 18 litres
Minimum oil capacity: 8 litres
Recommended for aerobatic
flying: 10 litres
1.6 Cooling system Air. Cowl gills, operated by a cockpit lever are used to control
the CHT of the engine
1.7 Weights
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Maximum gross weight Normal / Ferry Category: 995 kilograms
Maximum gross weight Aerobatic Category: 935 kilograms
SECTION 2
LIMITATIONS
TABLE OF CONTENTS
Section Page
1 AIRSPEED LIMITATIONS 8
2 AIRSPEED LIMITATIONS 9
3 POWERPLANT LIMITATIONS 10
4 PNEUMATIC PRESSURE LIMITS 11
5 WEIGHT LIMITS 11
6 CENTRE OF GRAVITY LIMITS 11
7 MANOEUVRE LIMITS 12
8 FLIGHT LOAD FACTOR LIMITS 12
9 OPERATING LIMITS 12
10 FUEL LIMITATIONS 12
11 PLACARDS 12-13
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1. AIRSPEED LIMITATIONS
Airspeed limitations and their operational significance are shown in figure 2-1.
IAS
Speed km/h Remarks
VNE Never Exceed Speed 430 Do not exceed this
speed in any operation
VMA Maneuvering Speed 300 Do not make abrupt
control movements above
this speed
VLO Maximum Gear Operating Speed 200 Do not extend landing
gear above this speed
VLE Maximum Gear Extended Speed 200 Do not exceed this speed
with landing gear
extended
VMCA Minimum Control Speed This is the minimum
flight speed at which the
aeroplane is directionally
and laterally controllable
Erect 110 km/h
Inverted 140 km/h
Figure 2-1 Airspeed Limitations
CAUTION!
This aeroplane has sensitive elevator and rudder controls at high speed.
Care is needed to avoid overstressing the aeroplane.
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Airspeed Indicator Markings:
Airspeed indicator markings and their colour code significance are shown in figure
2-2.
Markings
IAS
KM/H
Significance
Green
Arc
110 - 300
Normal operating
Yellow
Arc
300 - 430
Operations must be conducted with
caution and only in smooth air
Red Line
430
Maximum speed for all operations
Figure 2-2 Airspeed Indicator Markings
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3. POWER PLANT LIMITATIONS
Engine Model Number: M-14 P
Engine Operating Limits: see Figure 2-3
Power Setting Manifold
Pressure mm
of Merc
Engine
RPM %
Brake
Horsepower
Max Time Max Cyl
Head
Temp oC
Max Oil
Temp oC
TO
Ambient
P + 125
2900 99
360
5 min
220
75
Nominal 1
Ambient
P + 95
2400 82
295
Continuous
220
75
Nominal 2
Ambient
P + 75
2050 70
240
Continuous
220
75
Cruise
1
735
1860 64
180
Continuous
220
75
Cruise 2
670
1730 59
144
Continuous
220
75
At all power
settings
5 mins
240
85
Figure 2-3 Engine Operating Limits
Oil Pressure
Minimum: 2,0 kgs/cm2 (idle power)
Maximum: 6,0 kgs/cm2
Oil grade: 100 Ashless Dispersant Oil MIL-L-22851
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Powerplant Instrument Markings:
Powerplant instrument markings and their colour code significance are shown in figure
2-4
Figure 2-4 Powerplant Instrument Markings
4. PNEUMATIC PRESSURE LIMITS
Main System: Normal range 40-50 kgs/cm2 (Green Arc)
Emergency System: Normal range 40-50 kgs/cm2 (Green Arc)
5. WEIGHT LIMITS
Maximum Take-off and Landing Weight for Normal Category: 995 kgs
Maximum Take-off and Landing Weight for Acrobatic Category: 935 kgs
6. CENTRE OF GRAVITY LIMITS
Instrument
Red Line
Minimum
Limit
Yellow
Arc
Caution
Range
Green Arc
Normal
Operating
Yellow
Arc
Caution
Range
Red Line
Maximum
Limit
Tachometer
24
-
24-82
82-98
99
Oil Temp
40
-
40-75
75-85
85
Cyl Head Temp
-
-
120-220
220-240
240
Fuel Pressure
0,15
0,15–0,2
0,2 – 0,5
-
0,5
Oil Pressure
2
2 - 4
4 - 6
-
6
Carburetor Air
Temp
-
-
10 - 45
-
-
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Centre of Gravity Range:
Gear DOWN = 17.4% to 20.9% MAC (76.5cm to 82.3cm)
The C of G Position will move rearward by +2.5% with the gear retracted. The absolute
Rearward C of G Limit with gear retracted is 23.5% MAC (86.5cm)
7. MANOEUVRE LIMITS
The operation of this aeroplane is permissible in normal and acrobatic categories.
G-Limits are reduced, in the “normal” Cat (with fuel in the cruise tank – MTOW
995 Kgs) to +7 and -4
Max time inverted and with negative load factors: 1,5 min
Max crosswind velocity: 10 kms/h
8. FLIGHT LOAD FACTOR LIMITS
The limit loads in g units for the clean (gear retracted) configuration in the
Aerobatic Category (935 Kgs MTOW) are: +9 / -6G
9. OPERATING LIMITS
This aircraft must be operated by Day VFR only, and not in known icing