StormAircraft Rally Owner's manual

Rally Pilot Operating Handbook
Copyright 2008, Rally Aircraft Revision 4.1 1
STORMAIRCRAFT
RALLY LSA
PILOT OPERATING HANDBOOK
Revision .1
Manufacturer: Stor Aircraft
Model: Rally
Aircraft Registration Nu ber:
N
Airfra e Serial Nu ber:
Date Purchased:

Rally Pilot Operating Handbook
Copyright 2008, Rally Aircraft Revision 4.1 2

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Copyright 2008, Rally Aircraft Revision 4.1 3
TABLE OF CONTENTS
SECTION TITLE PAGE
1.0 GENERAL 5
2.0 SYSTEM DESCRIPTIONS 11
3.0 LIMITATIONS 13
4.0 WEIGHT AND BALANCE 17
5.0 PERFORMANCE 23
6.0 EMERGENCY PROCEDURES 31
7.0 NORMAL PROCEDURES 41
8.0 HANDLING SERVICE AND MAINTENANCE 55
9.0 REQUIRED PLACARDS AND MARKINGS 59
10.0 SUPPLEMENTS 63
11.0 QUICK REFERENCE 65
NOTICE: This Pilot Operating Handbook has be designed to co ply with AC 23-
8B, Appendix 5, Effective 14 August 2003.

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SECTION 1.0
GENERAL
1.1 INTRODUCTION ............................................................................... 6
1.2 DESCRIPTIVE DATA .......................................................................... 6

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5.5 TAKE-OFF DISTANCE CHART
Take off Speed 32°F 32°F 50°F 50°F 70°F 70°F 85°F 85°F 100°F 100°F
Weight Lift off at 50 ft
Press.
Alt—ft.
A B A B A B A B A B
GW:
1320 lbs . 5 Kts.
S.L. 300 558 348 626 404 797 488 1,011 601 1,346
1,000 342 622 400 792 480 1,004 586 1 328 709 1,701
2,000 393 779 468 997 581 1,308 703 1,671 876 2.058
3,000 464 986 571 1.302 686 1,656 851 2,025 1,401 2.,62
,000 557 1,295 680 1,642 837 2,008 1,098 2,431 1,129 2,899
5,000 668 1,627 824 1,988 1,075 2,405 1,361 2,862 1,619 3,343
6,000 815 1,973 1,046 2,380 1,333 2,827 1,586 3,315 1,943 3,921
7,000 1,027 2,358 1,303 2,807 1,565 3,281 1,911 3,859 — —
8,000 1,284 2,787 1,544 3,257 1,888 3,813 — — — —
55 KtS.
B = 50 ft Obstacle
Figure 5— 3, Take-off distance chart

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5.6 TIME, FUEL, AND DISTANCE TO CLIMB CHART (Maximum Rate of Climb)
Conditions: flaps up; full throttle (5500 RPM); standard te perature; zero wind.
Notes:
1) add 1 gal of fuel for engine start, taxi and takeoff
2) increase ti e, fuel and distance by 10% for each 46°F above standard
te p.
From sea level
Weight
(lbs.)
Pressure
Altitude
(feet)
Temp.
(°F)
Climb-
Speed
(knots)
Rate of
Climb
(fp )
Time
( in.)
Fuel
Used
(gal.)
Distance
(s )
SL 60 72 720 0 0 0
1,000 55 72 700 2 0.2 2.5
2,000 52 71 660 3 0.5 4.2
3,000 48 71 620 5 0.7 6.7
,000 44 70 580 7 1.0 9.0
GW: 5,000 41 70 530 9 1.3 11.5
1,320 6,000 37 69 480 11 1.6 15.0
7,000 34 69 425 14 1.9 18.0
8,000 30 68 375 17 2.3 21.0
9,000 26 68 315 20 2.7 26.0
10,000 23 67 275 23 3. 0 30.0
11,000 20 67 220 27 3.7 36.0
12,000 16 66 180 33 4.2 42.5
Time, Fuel and Distance to Climb Chart
Figure 5—4 Ti e, Fuel and Distance to Cli b Chart

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1.1 INTRODUCTION
Section 1 provides basic data and infor ation of general interest.
1.2 DESCRIPTIVE DATA
Engine:
• Nu ber of engines .................... 1
• Engine anufacturer ................. ROTAX
• Engine odel .........................… 912 UL S2
• Engine type .................………... nor ally aspirated, 4-cyl, 4-stroke, liquid/air
cooled engine with opposed cylinders, dry su p forced lubrication with separate
0,8 gal oil tank,
• 2 carburetors, echanical and electric fuel pu ps, Ducati electronic dual igni-
tion, electric starter, integrated reduction gear 1:2.43.
• Horsepower rating and engine speed ........... 100 BHP at 5800 RPM ( ax. 5 in.)
• 95 BHP at 5500 (continuous).
Detailed information on the ROTAX 912 ULS engine shall be found on the engine
Manufacturer’s operating manual.
Propeller:
• Nu ber of blades ........... 3
• Propeller type ................ Ground adjustable
• Propeller dia eter ......... 70 in.
Fuel:
• Nu ber of tanks ......................……………… 2 Wing leading-edge tanks
Oil:
• Oil tank capacity ............................................ 0.8 U. S. gallons
Maximum Aircraft Weights:
• Standard E pty Weight, Basic.......... 760 lbs
• Maxi u useful load …………………… 560 lbs (Ed: Does this change with s aller
tanks?)
Cabin and Entry Dimensions:
• Cabin Height: Top of seats to roof = 40 inches
• Doors: 34 inches wide X 39 inches high
• Length: Instru ent panel to rear bulkhead (baggage area) = 70 inches
Fuel Capacity U.S. Gallons
Total—Standard Tanks 24
Usable—Standard Tanks 23
Total—Long Range Tanks 35
Usable—Long Range Tanks 34

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Baggage Space Dimensions:
• Cabin width: (Door to Door) = 43.7 inches @ door handles
• Baggage Area:
Length = 26 inches.
Width = 28—42 inches at front edge.
Height = 27—32 inches.
Volu e = approx. 16 cu. ft.

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SECTION 2.0
PERFORMANCE SPECIFICATIONS
FOR LSA ACTIVITY
2.1 SPEEDS .......................................................................................... 12
2.2 TAKEOFF PERFORMANCE ............................................................. 12
2.3 LANDING PERFORMANCE ............................................................. 12
2.3 WEIGHTS ....................................................................................... 12
2. LOADING ....................................................................................... 12

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2.1 SPEEDS
Maxi u at sea level ................................................................ 120 kts/138 ph
Cruise (75% power at 2000 ft, ISA conditions ............................ 107 kts/123 ph
STALL SPEED:
Flaps up, power ............................................................................. 44 kts/51 ph
Flaps down, power off ................................................................... 35 kts/40 ph
CRUISE :
75% (4200 rp @ 2000 ft (ISA Conditions) ...................................... range 638 n
34 gal usable fuel .............................................................................. ti e 6.86 hrs
RATE OF CLIMB AT SEA LEVEL: ................................................................ 660 fp
SERVICE CEILING ...................................................................................... 12,000 ft
2.2 TAKEOFF PERFORMANCE (ISA Conditions, Sea Level):
Ground roll .................................................................................................. 360 ft
Total distance over 50 ft obstacle ............................................................... 600 ft
2.3 LANDING PERFORMANCE (ISA Conditions, Sea Level):
Ground roll .................................................................................................. 450 ft
Total distance over 50 ft obstacle . ............................................................ 1000 ft
2.3 WEIGHTS
MAXIMUM WEIGHT:
Sport Light aircrafts Rules ........................................................................ 1,320 lbs
STANDARD EMPTY WEIGHT:
Sport Light Aircraft .................................................................................... 760 lbs
MAXIMUM USEFUL LOAD:
Sport Light Aircraft ................................................................................... . 560 lbs
BAGGAGE ALLOWANCE .......................................................................... 100 lbs
2. LOADING
WING LOADING:
Sport Light Aircraft ............................................................................. .34 lbs/sq ft
POWER LOADING: ................................................................................ 13.2 bs/hp

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SECTION 3.0
LIMITATIONS FOR LSA ACTIVITY
3.1 INTRODUCTION ................................................................................ 1
3.2 AIRSPEED LIMITATIONS .................................................................... 1
3.3 AIRSPEED INDICATOR MARKINGS..................................................... 1
3. MARKING (Knots) VALUE SIGNIFIANCE or RANGE ............................ 15
3.5 POWER PLANT LIMITATIONS ............................................................ 15
3.6 POWER PLANT INSTRUMENT MARKINGS ......................................... 15
3.7 WEIGHT LIMITS FOR SPORT PILOT AIRCRAFT FLYING ACTIVITY ........ 15
3.8 DESIGN CENTER OF GRAVITY LIMITS AND RANGE ............................ 15
3.9 MANEUVER LIMITS ........................................................................... 16
3.10 FLIGHT LOAD FACTOR LIMITS (Normal Category ) .......................... 16
3.11 FUEL LIMITS .................................................................................... 16

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3.1 INTRODUCTION
Section 3 includes operating li itations and instru ent arkings necessary for the
safe operation of the airplane, its engine, standard syste s and standard equip-
ent. The Rally LSA ay be operated VFR at night , and/or, in day/night IFR condi-
tions, provided the aircraft's equip ent eets FAA require ents and restrictions
for such operations, and the pilot holds the required air an's ratings for these op-
erations.
3.2 AIRSPEED LIMITATIONS
Airspeed li itation and their operational significance are shown in figure 3-1.
Figure 3-1, Airspeed Limitations
3.3 AIRSPEED INDICATOR MARKINGS
Airspeed indicator arkings and their color code significance are shown in figure 3-
2.
3. MARKING (Knots) VALUE SIGNIFIANCE or RANGE
SPEED Knots/MPH REMARKS
VNE
Do not exceed this speed
Limited by L.S.A Rule
138/158 Never exceed speed in any operation.
VNO
Do not exceed this speed
120/138 Maxi u structural cruising speed
except in s ooth air, and
then only with caution.
VA
Maneuvering speed
88/101 Do not ake full or abrupt
control ove ents above
this speed.
VFE Max. flap 70/81 Do not exceed this speed
VLE Extended speed 70/81 with flaps down
Color Range Range
White arc 45 – 65 Kts
52—75 ph
Full-flap operating range.
Green arc 50 - 110 Kts
58—127 ph
Nor al operating range.
Yellow arc 110 - 120 Kts
127—138 ph
Operation ust be con-
ducted with caution.
Red line 120 Kts
138 ph
Max. speed—all opera-
tions.
Figure 3-2 Airspeed Indicator Markings

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3.5 POWER PLANT LIMITATIONS
Engine operation li its for takeoff and continuous operation:
• Maxi u power ..................... 95 hp
• Maxi u engine speed .............. 5500 rp
• Maxi u oil te perature ........... 130°C/266°F
• Mini u oil te perature ……… 50°C/120°F
• Maxi u oil pressure .............. 6 bar/87 psi
• Mini u oil pressure .............. 0.8 bar/12 psi (below 3500 rp )
• Nor al operating pressure …. 2.0 + 5.0 bar (29 + 73 psi ) (above 3500 rp )
Detailed operating infor ation shall be found in the Engine Manufacturer’s Manual.
3.6 POWER PLANT INSTRUMENT MARKINGS
Power plant instru ent arkings and their color code significance are shown in Fig-
ure 3-3.
Figure 3-3 Power Plant Instru ent Markings
3.7 WEIGHT LIMITS FOR SPORT PILOT AIRCRAFT FLYING ACTIVITY
• Maxi u takeoff weight (MTOW) ....... 1320 lbs
• Maxi u landing weight ...............…. 1320 lbs
• Maxi u weight in baggage area .......... 100 lbs
3.8 DESIGN CENTER OF GRAVITY LIMITS AND RANGE
Forward: 11.8 inches fro the Wing Leading edge at 900 lbs or less, with straight
line variation to 18.5 inches aft of Datu at all weights. Afterward: 20 in aft of da-
tu at all weights.
The reference datum is the Leading edge of the wing.
INSTRUMENT RED LINE
Min. li it
GREEN ARC
Nor al operating
RED LINE
Max. li it
Tacho eter Not Indicated 1500—5500 rp 5800 rp
Oil te p. Not Indicated 122°F—248°F 266°F- 284°F
Oil pressure 2 bar/29 psi 2—5 bar /29—73 psi 7 bar/100 psi
Cylinder Head te p. 50° C /120° F 75°—125°C/167°—257°F 135°F—284°F
Fuel pressure 0.15 bar/2.2 psi 0.2 – 0.4 bar/3 – 5.8 psi 0.5 bar/7.2 psi

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3.9 MANEUVER LIMITS
This airplane is designed for li ited aerobatic flight (Utility Category)
No aerobatic maneuvers are approved except those listed below: (LSA RULES)
• Chandelle— axi u entry speed ........... 105 knots
• Lazy eights— axi u entry speed ........... 105 knots
• Steep turns— axi u entry speed ............ 105 knots
• Stalls—use slow deceleration
Higher speed can be used if abrupt use of controls is avoided.
Aerobatics that may impose high loads should not be attempted.
The i portant thing to bear in ind in flight aneuvers is that the airplane is
clean in aerodyna ic design and will build up speed quickly with nose-down atti-
tude. Proper speed control is an essential require ent for execution of any aneu-
ver, and care should always be exercised to avoid excessive speed, which in turn can
i pose excessive loads. In the execution of all aneuvers, avoid abrupt use of con-
trols.
3.10 FLIGHT LOAD FACTOR LIMITS (Normal Category ) Gross Weight : 1320 lbs (LSA
RULES)
• Flaps up .........................…. + 4.4 g/-1.76 g
• Flaps down ......................... + 4 g/-1 g
The design load factors are at least 150% of the above, calculated for the LSA
version of the aircraft (i.e. MTOW of 1,320 lbs), and in all cases, the structure eets
or exceeds the design loads.
However, it is highly recommended not to reach the above mentioned Load Factor
Limits.
3.11 FUEL LIMITS
The aircraft is equipped with 2 fuel tanks, located in the leading edge of the
wings, with a standard 24 gal total capacity.
However, the total usable fuel (all flight conditions) is 23 gal.
The unusable fuel which re ains in the botto of the fuel tanks is approxi-
ately 1 gal.
Approved fuel grades and colors:
• Pre iu Leaded or Unleaded auto otive, fuel 92 octane ini u
• 100LL grade aviation fuel (blue) If 100LL is used, Rotax reco ends that 2 fl.
oz. of TCP added to each full fuel load.

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SECTION .0
WEIGHT AND BALANCE
.1 INTRODUCTION ............................................................................ 18
.2 AIRPLANE WEIGHING PROCEDURE ............................................... 18
.3 WEIGHT AND BALANCE ................................................................ 18

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.1 INTRODUCTION
This section describes the procedure for establishing the basic e pty weight
and o ent of the airplane. Sa ple for s are provided for reference. Procedures
for calculating the weight and o ent for various operations are also provided.
.2 AIRPLANE WEIGHING PROCEDURE
a) Preparation:
1) Inflate tires to reco ended operating pressure
2) Drain all fuel
3) Drain all oil
4) Raise flap to the fully retracted position
5) Place the aircraft level
b) Leveling:
1) Place scales under each wheel (440 lbs ini u capacity for scales)
2) Release brakes
3) Check aircraft level
c) Weighing:
1) Record the weight shown on each scale deducting the tare, if any.
d) Measuring (ref. figure 4-1):
1) Obtain easure ent “A” by easuring horizontally (along the airplane
center line) fro a line stretched between the ain wheel centers to a
plu b bob dropped fro the firewall
2) Obtain easure ent “B” by easuring horizontally and parallel to the
airplane center line, fro center of nose wheel axle, left side, to a
plu b bob dropped fro the line between the ain wheel centers.
Repeat on right side and average the easure ents.
Using weights fro (L – R - N) and easure ents fro (B) the airplane weight
and C.G. can be deter ined by co pleting Figure 4-5. The basic e pty weight ay
be deter ined co pleting Figure 4-6.
.3 WEIGHT AND BALANCE
The following procedure will enable you to operate your aircraft within the pre-
scribed weight and C.G. li itations.
To figure weight and balance, use the sa ple proble for , loading graph and
C.G. o ent envelope as follows:
1. Take the basic e pty weight and o ent fro appropriate weight and
balance records carried in your airplane and enter the in the colu n titled
“YOUR AIRPLANE” on the sa ple loading proble .

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2. Use the loading graph to deter ine the o ent/1000 for each addi-
tional ite to be carried on the aircraft, then list these on the loading
proble .
3. Total the weights and o ents/1000 and plot these values on the C.G.
o ent envelope to deter ine whether the point falls within the enve-
lope, and if the loading is acceptable.
X = ARM = (A) - (N) * (B)
W
(A) = 48 in
(B) = 76 in
Figure 4-5 Sa ple Aircraft Weighing and deter ination of CG station
SCALE POSITION
SCALE READING
(lbs) TARE SYMBOL
NET WEIGHT
(lbs)
LEFT WHEEL 310.6 0L 310.6
RIGHT WHEEL 309.2 0 R 309.2
NOSE WHEEL 132.0 0 N 132.0
W751.8SUM OF NET WEIGHTS

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Figure 4-6 Sa ple Aircraft Basic E pty Weight and Mo ent
ITEM WEIGHT (lbs) X CG ARM (in) = MOMENT (lbs/in)
AIRCRAFT BASIC
EMPTY WEIGHT 751.8 13.6 10,227
SAMPLE LOADING PROBLEM SAMPLE AIRPLANE
WEIGHT (lbs) MOMENT
BASIC EMPTY WEIGHT 751.8 10,200
FUEL 26 Gal. 158 4,400
PILOT & PASSENGER 352 14,100
BAGGAGE AREA 40 1,800
TOTAL WEIGHT &MOMENT 1,301.8 21,700
Locate this point (1301.8 at 21,700 on the CG Moment Envelope graph)
YOUR AIRPLANE
WEIGHT (lbs) MOMENT