Pilot Operating Handbook - mavericklsa.com · CONDITIONS OF FLIGHT.....6! 2.5.! ENGINE LIMITATIONS ... The Maverick Pilot Operating Handbook is provided with this aircraft at initial

Date: 10-23-2012 1 of 24 Document #:500401

Pilot Operating Handbook This Pilot Operating Handbook belongs to aircraft serial numbers:

SP = MS9001 - MS9999 FT = MF8001 - MF8999

October 23, 2012

Pilot Operating Handbook

Date: 10-23-2012 2 of 24 Document #:500401

TABLE OF CONTENTS

I REVISION TABLE.................................................................................................... 4 II TABLE OF FIGURES ................................................................................................ 4

1 – GENERAL INFORMATION....................................................................................... 5 2 – LIMITATIONS............................................................................................................. 6

2.1. AIRSPEED LIMITATIONS ............................................................................ 6 2.2. CROSSWIND LIMITATIONS........................................................................ 6 2.3. LOAD FACTORS ............................................................................................ 6 2.4. CONDITIONS OF FLIGHT ............................................................................ 6 2.5. ENGINE LIMITATIONS................................................................................. 7

3 – EMERGENCY PROCEDURES................................................................................... 8 3.1. POWER LOSS ................................................................................................. 8 3.2. LINE TANGLES.............................................................................................. 8 3.3. FIRE ON-BOARD ........................................................................................... 8 3.4. HOLE IN WING (PARACHUTE)................................................................... 8 3.5. FLAT TIRE ...................................................................................................... 8

4 – NORMAL PROCEDURES .......................................................................................... 9 4.1. PREFLIGHT..................................................................................................... 9 4.2. STARTING ENGINE....................................................................................... 9 4.3. TAXI............................................................................................................... 10 4.4. BEFORE TAKEOFF...................................................................................... 10 4.5. NORMAL TAKEOFF.................................................................................... 10 4.6. CRUISE.......................................................................................................... 10 4.7. APPROACH................................................................................................... 10 4.8. NORMAL LANDING.................................................................................... 10

5 – PERFORMANCE....................................................................................................... 11 5.1. NORMAL SPEEDS ....................................................................................... 11 5.2. CLIMB SPEEDS ............................................................................................ 11 5.3. TAKE-OFF DISTANCE ................................................................................ 11 5.4. LANDING DISTANCE ................................................................................. 11 5.5. RANGE .......................................................................................................... 11


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6 – WEIGHT AND BALANCE ....................................................................................... 12 6.1. EMPTY WEIGHT.......................................................................................... 12 6.2. GROSS WEIGHT........................................................................................... 12 6.3. USEFUL LOAD............................................................................................. 12 6.4. WING ATTACHMENT................................................................................. 12 6.5. MAXIMUM FLIGHT WEIGHT.................................................................... 12 6.6. MINIMUM FLIGHT WEIGHT ..................................................................... 12

7 – DESCRIPTION OF THE AIRCRAFT AND ITS SYSTEMS ................................... 13 7.1. ENGINE ......................................................................................................... 13 7.2. PROPELLER.................................................................................................. 13 7.3. FUEL / FUEL CAPACITY ............................................................................ 13 7.4. OIL.................................................................................................................. 13 7.5. GENERAL...................................................................................................... 13

8 – HANDLING, SERVICING, AND MAINTENANCE ............................................... 15 8.1. AIRCRAFT MAINTENANCE MANUAL.................................................... 15

9 – ENVIRONMENTAL RESTRICTIONS.................................................................... 16 9.1. WIND AND TURBULENCE ........................................................................ 16 9.2. RAIN .............................................................................................................. 16 9.3. SNOW ............................................................................................................ 16

A – DATA LOCATION AND CONTACT INFO ........................................................... 17 B – MAINTENANCE MANUAL.................................................................................... 18 C – MANUFACTURER’S STATEMENT OF COMPLIANCE ..................................... 19 D – OPERATOR RESPONSIBILITY STATEMENT AND PLACARD ....................... 20


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I REVISION TABLE Rev Level Reason for change Date Released Approved NC Initial Release 6/28/10 TT 1 Production Release Update 7/8/11 TT 2 Production Release Update 2/8/12 TT 3 Production Release Update 10/23/2012 TT


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1 – GENERAL INFORMATION IMPORTANT: REVIEW ALL MATERIAL IN THIS HANDBOOK PRIOR TO OPERATING THE Maverick This handbook is provided by Beyond Roads LLC to communicate various operating procedures and limitations that apply to the Maverick. It is extremely important that the information provided in this handbook be both understood and applied to operate the Maverick in an enjoyable and safe manner. It is important to apply this information when operating the Maverick. It is also important to maintain the Maverick per the stipulations of the Maintenance Manual that accompanies this handbook. Properly maintaining the Maverick will increase safety, and will better ensure the longevity of this powered parachute aircraft. This handbook is also intended to meet all applicable FAA consensus standards for “aircraft operating instructions” (AOI) for any Maverick aircraft. The terms here are used interchangeably. The Maverick Pilot Operating Handbook is provided with this aircraft at initial sale. To obtain updated information, new additions, and to view the latest available version, please see www.Mavericklsa.com. To complete condition inspection, the latest version should be downloaded from the Beyond Roads website at www.MaverickLSA.com. About Beyond Roads LLC Beyond Roads LLC has been granted the manufacturing rights to the Maverick by the original design and development entity, Itec (Indigenous People’s Technology and Education Center). Contact information for Beyond Roads is as follows: 10575 147th Circle Dunnellon, FL 34432 352-489-4456 [email protected] Terms and Definitions Beyond Roads: Beyond Roads, LLC. LSA: Light Sport Aircraft SLSA: Special Light Sport Aircraft ELSA: Experimental Light Sport Aircraft PPC: Powered Parachute FAA: Federal Aviation Administration CG: Center of Gravity About the Aircraft The Maverick is a PPC LSA. It is constructed of 4130 steel tubing covered with an optional fabric ‘tuxedo’. It has an elliptical ram air wing. More systems information for the Maverick may be found in the Section 7: “Aircraft Systems/Description”.


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See Section 7 for approved engine(s), propeller(s), fuel and oil.

2 – LIMITATIONS

2.1. AIRSPEED LIMITATIONS Powered parachutes are inherently stall resistant. The angle of attack is maintained by the wing rigging and pendulum effect caused by the large separation distance between the center of lift and the center of gravity of the vehicle. However in extreme conditions of pilot induced oscillation and/or combinations of excessive thrust and drag the wing can stall at approx. 25 mph. Maximum airspeed is affected by total flight weight. It should not exceed 50 mph, and will not generally in normal flight operations. Minimum airspeed should never be below 28 mph airspeed. (In the standard configuration, airspeed is primarily determined by the aircraft’s flying weight.- the heavier the aircraft, the higher the airspeed).

2.2. CROSSWIND LIMITATIONS In general, the Maverick should land and takeoff into the wind. The Maverick wing deployment system, does, however, allow for moderate crosswind landings and takeoffs within the following general guidelines: Crosswinds for normal takeoffs should not exceed 45° deviation to either side of runway heading, and the crosswind component should not exceed 5 miles per hour. Crosswind landings can be made, but the wind direction should not exceed 60° from runway heading. The aircraft can land in such short distances that most landings can be achieved by crabbing in the necessary direction on the downwind side of the runway then turning into the wind for the touchdown.

2.3. LOAD FACTORS The Maverick has been tested to withstand more than +3.375 G’s. Aerobatic maneuvers are not authorized in the Maverick.

2.4. CONDITIONS OF FLIGHT The Maverick is equipped for day VFR flight and should be so limited. Maximum wind speed for taxiing and flying: 12 mph.


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2.5. ENGINE LIMITATIONS

This aircraft is designed for a Subaru MAV EJ22 127 hp and Subaru MAV EJ25 190 hp engines. Any other engine configuration must have factory approval. Maximum RPM 5,800 rpm for maximum 5 minutes

5,500 rpm for continuous operation Maximum Coolant Temp 220°F (105°C) for maximum 5 minutes 200°F (94°C) max, 172°F (78°C) for continuous operation Oil Pressure Limits 10 PSI Minimum below 2,000 rpm

25 PSI Minimum and 95 PSI Maximum above 2,000 rpm


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3 – EMERGENCY PROCEDURES

3.1. POWER LOSS In all cases of power loss, the aircraft will begin to descend. Seek to land into the wind in an open, level area. A full flare just prior to touchdown will slow the craft’s descent rate. Due to the fact that this aircraft has a lightweight composite propeller an air restart will require use of the starter.

3.2. LINE TANGLES Should line tangle be encountered on takeoff, abort the takeoff. Should line tangle be encountered during landing and taxi, turn into the prevailing wind and shut down the propeller.

3.3. FIRE ON-BOARD Land as soon as possible.

3.4. HOLE IN WING (PARACHUTE) If hole occurs or is discovered during flight, land as soon as safely possible. In all circumstances, inspect hole and repair as necessary for safe flight as determined by qualified wing repair station.

3.5. FLAT TIRE Flat tires on the ground should be repaired as required. In the event of deflation upon takeoff, track straight ahead and abort takeoff.

3.6. WING COLLAPSE RECOVERY The Maverick wing is by design stall and collapse resistant. Adverse meteorological conditions and pilot error can cause these conditions to exist. Refer to the FAA-H8083-29 Powered Parachute Flying Handbook for more information on the characteristics of powered parachutes wings and aerodynamic stability.


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4 – NORMAL PROCEDURES

4.1. PREFLIGHT

1. CABIN a. Verify all required documents on board aircraft b. Required charts/maps on board c. No loose items in cabin

2. LEFT SIDE – FUSELAGE

a. Visually inspect all connection points, cables, and tubing b. Pay attention to possible stress, cracking c. Ensure proper alignment and seating of eyebolts, cables, and carabiners

3. RIGHT SIDE - FUSELAGE a. Visually inspect all connection points, cables, and tubing b. Pay attention to possible stress, cracking c. Ensure proper alignment and seating of eyebolts, cables, and carabiners

4. NOSE SECTION

a. Check condition of hood and tuxedo b. Check condition of tires (inflation, wear) c. Check condition of nose gear (one or two wheels, as applicable)

5. INSPECT THE CHUTE

a. For wear and/or holes b. Mast system for proper installation and structural integrity c. Lines for tangles and/or broken lines d. Steering lines and mechanisms for proper routing and smooth operation

6. ENGINE / PROPELLER

a. Check security of propeller b. Check propeller for cracks, nicks (repair or replace as necessary) c. Verify fuel level and strain fuel to verify no presence of water or to remove water

from tank (fuel strainer is underneath the tank). d. Check engine oil and verify within acceptable range.

7. DEPLOY WING AND REPEAT PREFLIGHT #5

a. Check wing deployment and line control systems for functionality. b. Check security of mast foot, upper bracket clamp, and security of hoist line.

8. ENGAGE PROPELLER DRIVE AND VERIFY THAT IT IS ENGAGED TO ENGINE

4.2. STARTING ENGINE 1. All loose lines and cargo or miscellaneous items secured 2. Seatbelts and harnesses – adjusted and fastened 3. Master switch – ON 4. Check both fuel pumps for normal operation (by sound) 5. Propeller area – CLEAR 6. Starter – ENGAGE 7. Engage flight control switch and verify engagement and normal operation of flight

controls


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4.3. TAXI 1. Verify seatbelts/harnesses – ON 2. Taxiing with wing deployed should be done with care. Avoid back-loading the wing by

maintaining relative wind within 65° of direction of taxi with crosswind component not to exceed 5 mph. Use manual steering pedals to steer wing as needed.

3. Brake as needed

4.4. BEFORE TAKEOFF 1. Controls – FREE, CLEAR, CORRECT (air steering engaged and operating normally) 2. Verify engine water and oil temperature and pressure within normal operating range 3. Seatbelts/harnesses – ON

4.5. NORMAL TAKEOFF 1. Increase power steadily to full throttle 2. If applicable, disengage line control. 3. Verify chute is properly inflated with no line tangles 4. Climb at full throttle

4.6. CRUISE 1. Set power (RPM) for level cruise using either foot pedal or hand throttle control. (Caution

– either throttle can restrict deceleration of other throttle)

4.7. APPROACH 1. Reduce power as required for desired descent rate 2. Use gradual turns

4.8. NORMAL LANDING 1. Short final – descend toward planned touchdown 2. Add power to arrest descent prior to touchdown 3. Use throttle/flare to decrease vertical speed and ease landing 4. Power to idle 5. Engage line control, if applicable. 6. Taxi to shutdown position using normal taxi (with wing deployed) procedures (See 4.5.2 above)


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5 – PERFORMANCE

5.1. NORMAL SPEEDS weight = 1120 lbs at sea level 36 mph

weight = 1320 lbs at sea level 38 mph weight = 1320 lbs at 3,000 feet MSL 42 mph weight = 1430 lbs at 3,000 feet MSL 46 mph

5.2. CLIMB SPEEDS – Same as “normal speeds”

5.3. TAKE-OFF DISTANCE

– Approx. take-off distance over 50 ft obstacle is 220 ft.

5.4. LANDING DISTANCE – Approx. landing distance over a 50 ft obstacle is 350 ft.

5.5. RANGE

– Approx. Range 2.5 hours


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6 – WEIGHT AND BALANCE Note that this information is general. If a vehicle deviates from this information, a unit specific Weight and Balance (doc 500402) will be provided and should be referenced.

6.1. EMPTY WEIGHT – Standard empty weight is 987 lbs.

6.2. GROSS WEIGHT

ELSA/SLSA SLSA with FAA Exemption No. 10299

Empty Weight (lbs) 987 987 Max Gross Weight (lbs) 1320 1430 Useful Load (lbs) 333 443 If operating with FAA Exemption No. 10299, a copy of the Exemption must be carried on board the aircraft.

6.3. USEFUL LOAD – Useful load is 333 pounds (with FAA Exemption No. 10299, useful load 443 pounds)

6.4. WING ATTACHMENT

– The wing is attached to the fuselage as shown in the Appendix.

Note the balance of the fuselage is set by adjusting the wing arm CG adjustment mechanisms as shown in the following general chart:

Table 1: Maverick CG Chart

Wing Arm Position Pilot Weight Range (lbs) 1 (most forward hole) 244-300

2 222-243 3 189-221 4 174-188

5 (middle) 167-173 6 157-166 7 143-156 8 119-142

9 (most rearward hole) 100-118

6.5. MAXIMUM FLIGHT WEIGHT – 1320 pounds. 1430 pounds if operated in compliance with FAA Exemption No. 10299.

6.6. MINIMUM FLIGHT WEIGHT – 1142 pounds


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7 – DESCRIPTION OF THE AIRCRAFT AND ITS SYSTEMS

7.1. ENGINE

While it is recommend that you review the supplied engine operation manual, some basic information regarding the Maverick’s engine is as follows:

Engine Type: Subaru MAV EJ22 or Subaru MAV EJ25

Propeller Reduction Drive Type: MAV – Cogged Belt Reduction Drive

7.2. PROPELLER

The standard : Ground adjustable 5 blade Powerfin or Warp Drive 74”

7.3. FUEL / FUEL CAPACITY

Fuel: 87 octane (minimum octane) unleaded ‘auto

gasoline’

Capacity: 17 US gallons

7.4. OIL

Type: -Normal Operating Conditions:

-High Temperature or Severe Environment Operation: API Standard: SM or SL; SAE Viscosity #: 30, 40, 10W-50, 20W-40, 20W-50 (full synthetic) Capacity: 4.2 U.S. Quarts (4.0 Liters)

7.5. GENERAL

1. Fuselage – The frame is comprised mainly of welded 4130 steel tubes with welded on

tabs and brackets. The main chassis bolts to the lower and upper engine mount portions and the drag struts for the rear suspension, A-arms for the front suspension, and CG adjustment mechanisms are bolted to the frame. Cables on either side connect the CG adjustment mechanism to the frame.

Temperature (°C) -30 -20 -15 0 15 30 40 (°F) -22 -4 5 32 59 86 104 SAE Viscosity

5W-30

10W-30, 10W-40, 10W-50


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2. Wing Deployment System – The mast and spar system hold the wing in a position that, only with relative wind, is flight ready. The spar is attached to the mast and extends to form a semi-rigid support for the leading edge of the parachute. The mast has ropes internally and a mechanism that allows a user to raise the spar for flight and then lower it in a controlled manner for storing. These are not structural or safety of flight systems. ‘Line Control’ is also implemented to prevent lines from being caught in the propeller when the parachute is not inflated.

3. Wing – The Maverick ‘wing’ is a high-aspect ratio, elliptical, double canopy ram-air

pressurized, rip-stop nylon parachute. The suspension lines are made of a separate material as well as the steering lines. The parachute is connected to the aircraft by risers and working load rated carabiners.

4. Fuel System – The fuel system is comprised of a single welded aluminum fuel tank (with

a strainer on the bottom of the tank and fuel level sensor), fuel lines and fittings, two redundant fuel pumps (running in parallel and controlled), fuel pressure regulator, in-line fuel filter and a Subaru fuel injection system or carburetor. The throttle is controlled by the adjustable-position automotive-style gas pedal and/or a friction lever (primarily for in flight use). CAUTION: These controls operate in parallel, so releasing throttle on one will not decrease throttle held by the other and applying brakes will not decrease the throttle setting

5. Landing Gear and Brakes:

a. The front suspension system includes double A-frame suspension arms with shocks,

the front two wheels, and the suspension/wheel connection parts (wheel hub and spindle). A single front wheel may also be available.

b. The rear suspension system includes two struts, the rear two wheels, two rear axles connecting the wheels and transaxle, two air shocks, and the suspension/wheel connection parts (wheel hub, bearing holder, and adapters).

The air pressure can be varied in all the shocks. All wheels have hydraulic disc brakes actuated simultaneously by an automobile-style, foot-actuated brake pedal

6. Control Surfaces – In flight, the direction of flight is controlled by deflecting the outer trailing edges of the wing, as with a conventional PPC. Parachute lines connect the outer trailing edges to the steering lines, so pulling on the steering lines deflects the trailing edges of the parachute. The steering lines are pulled in by electronic linear actuators controlled by the steering wheel or with manual foot-steering pedals (similar to a conventional powered parachute) as a redundant, independent, or companion system. The manual foot-steering pedals are also needed to produce landing flare.

The electric cylinders and back-up pedal steering systems are connected to the wing drag flaps by high tensile strength, flexible steering lines.

7. Electrical System – The Maverick electrical system is powered by an engine-driven

alternator that charges a sealed 12 Volt (nominal) battery.

8. See Figure 1 and Figure 2 for Dash Instrument Pictorial


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8 – HANDLING, SERVICING, AND MAINTENANCE

8.1. AIRCRAFT MAINTENANCE MANUAL – Refer to Maintenance Manual (doc #500501)


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9 – ENVIRONMENTAL RESTRICTIONS

9.1. WIND AND TURBULENCE The Maverick should not be flown in winds beyond the pilot’s skill level. In most cases, the wind limit is 12 mph. Lower limits should be used if the wind is turbulent or gusty. Higher winds and stronger gusts make handling progressively more difficult. The concern exists that if wind rises too high, the aircraft will not be able to make headway from a downwind position to return to the airport.

9.2. RAIN Do not begin a flight in rain and avoid prolonged flights in rain. The wing can collect rainwater and become heavy. In an extreme case of water accumulation, the chute could even stall as a result of water accumulation in the closed ends of the cells. Land as soon as possible where shelter for the parachute is available.

9.3. SNOW Do not begin a flight in and avoid flying in heavy, wet snow. The wing can collect snow and water and become heavy. In an extreme case of snow accumulation, the chute could even stall as a result of snow/ice/water accumulation in the closed end of the cells. Land as soon as possible where shelter for the parachute is available.

9.4. TEMPERATURE EXTREMES Do not begin a flight in and avoid flying in temperatures exceeding 130°F or below -20°F.


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A – DATA LOCATION AND CONTACT INFO A.1 – DOCUMENT LOCATION All originals of this and any other Maverick documents are kept at; 10575 SW 147th Circle Dunnellon, FL 34432 USA Backup copies of this and any other Maverick documents are kept at: 21235 SW 102nd St Rd Dunnellon, FL 34431 USA To gain access to this data contact Troy Townsend at [email protected] or 352-489-4456. A.2 – DATA PLATE The required engraved steel data plate is secured to the exterior or the aircraft, visible from outside the aircraft. It is located on the rear drive plate. It includes at least the following information:

Make: ----------- Dunnellon, FL USA Model: Maverick -- S/N: --------------- Mfg Date: ------------


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B – MAINTENANCE MANUAL Refer to Maintenance Manual (doc #500501). The Maintenance Manual is provided with this aircraft at initial sale. To get updated information and new additions, see www.MaverickLSA.com for the latest version available. To complete condition inspection, the latest Maintenance Manual must be downloaded from the web site.


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C – MANUFACTURER’S STATEMENT OF COMPLIANCE

The document included below is a sample of document #500000.


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D – OPERATOR RESPONSIBILITY STATEMENT AND PLACARD

Passenger Warning

In addition, the below statement shall be posted in the aircraft passenger area so that it is visible to both the pilot and passenger upon entry or when seated in the aircraft. It must be maintained visible as a placard.

Gross Weight Placard

The following statement must be visible to the pilot at all times and be maintained visible as a placard:

If Exemption Number 10299 applies to the vehicle, the following statement must be visible to the pilot at all times and be maintained visible as a placard instead of the above statement:

Additional Warnings

For ELSA aircraft, the following placard must be displayed in the aircraft in full view of all occupants:

For ELSA aircraft, the pilot-in-command must advise passengers of the experimental nature of this aircraft and that it does not meet the certification requirements of a standard certificated aircraft.

There are inherent risks in the participation in recreational aviation aircraft. Operators and passengers of recreational aviation aircraft, by participation, accept the risks inherent in such participation which the ordinary prudent person is or should be aware. Pilots and passengers have a duty to exercise good judgment and act in a responsible manner while using the aircraft and to obey all oral or written warnings, or both, prior to or during use of the aircraft, or both.

“PASSENGER WARNING—THIS AIRCRAFT IS AN EXPERIMENTAL LIGHT-SPORT AIRCRAFT AND DOES NOT COMPLY WITH FEDERAL SAFETY REGULATIONS FOR STANDARD AIRCRAFT.”

NOT TO EXCEED GROSS WEIGHT (for flight): 1320 lbs

NOT TO EXCEED GROSS WEIGHT (for flight): 1430 lbs


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APPENDIX

Figure 1: Dashboard Instrument Diagram ECU 1


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Figure 2. Dashboard Instrument Diagram - ECU 2


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Figure 3. Parachute Attachment Points


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Figure 4. Adjusting CG

Documents

Pilot Operating Handbook - mavericklsa.com · CONDITIONS OF FLIGHT.....6! 2.5.! ENGINE LIMITATIONS ... The Maverick Pilot Operating Handbook is provided with this aircraft at initial