Maintenance Manual

Transcription

Maintenance Manual

Maintenance Manual
This Maintenance Manual belongs to aircraft serial numbers:
SP = MS9001 - MS9999
FT = MF8001 - MF8999
October 23, 2012
October 23, 2012
Date:
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Maintenance Manual
TABLE OF CONTENTS
TABLE OF CONTENTS..................................................................................................................... 2 Section I Revision Table.................................................................................................................. 4 Section II Table of Figures ................................................................................................................ 4 1 GENERAL.................................................................................................................................... 5 About this Manual ........................................................................................................................ 5 Terms and Definitions ................................................................................................................. 5 Approved Equipment List .......................................................................................................... 5 Required Instruments................................................................................................................. 5 Optional Instruments and Avionics........................................................................................... 5 Required/Standard Equipment ................................................................................................. 6 Optional Equipment.................................................................................................................... 6 Basic Guidance for All Maintenance and Repair Work....................................................... 6 Level of Certification Required to Perform Maintenance ................................................... 7 Type of Maintenance ................................................................................................................... 7 Sources to Purchase Parts ........................................................................................................ 8 Disposable Replacement Parts................................................................................................. 9 Engine Specifications – Subaru MAV EJ22 (for reference only)......................................... 9 Engine Specifications – Subaru MAV EJ25 (for reference only)......................................... 9 Weight and Balance Information .............................................................................................. 9 Tire Inflation Pressures............................................................................................................... 9 Approved Oils and Capacities ................................................................................................ 10 Recommended Fastener Torque Values .............................................................................. 10 General Safety Information ...................................................................................................... 11 Reporting Possible Safety of Flight Concerns ................................................................... 11 2 INSPECTIONS.......................................................................................................................... 12 Periodic Inspections .................................................................................................................. 12 Replacement Schedule ............................................................................................................. 12 ANNUAL CONDITION INSPECTION ....................................................................................... 13 Date:
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Annual Condition Inspection Checklist ................................................................................ 14 3 STRUCTURES.......................................................................................................................... 15 4 ENGINE ..................................................................................................................................... 22 5 FUEL SYSTEM ......................................................................................................................... 24 6 PROPELLER ............................................................................................................................. 24 7 UTILITY SYSTEMS .................................................................................................................. 25 8 INSTRUMENTS AND AVIONICS........................................................................................... 27 9 ELECTRICAL SYSTEMS ........................................................................................................ 27 10 STRUCTURAL REPAIRS.................................................................................................... 27 11 PAINTING AND COATINGS............................................................................................... 27 12 REVISIONS TO MAINTENANCE MANUAL ..................................................................... 28 13 FEEDBACK FORM............................................................................................................... 28 14 SAFETY DIRECTIVES ........................................................................................................ 30 15 ORIGINAL AND BACKUP DOCUMENT LOCATION: .................................................... 31 Appendix I.......................................................................................................................................... 31 Appendix II......................................................................................................................................... 32 Appendix III........................................................................................................................................ 42 Date:
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Section I Revision Table
Rev Level
NC
1
2
3
Reason for change
Initial Release
Production Release Update
Date Released
6/28/2010
7/8/2011
2/8/2012
10/23/2012
Approved
TT
TT
TT
TT
Section II Table of Figures
Figure 2: Rear Suspension and Tire (rear view) .......................................................................... 33 Figure 3: Front Suspension ....................................................................................................... 33 Figure 4: Rear Suspension and Tire ........................................................................................... 33 Figure 5: Front Tire .................................................................................................................. 33 Figure 7: Ground Drive Axle ...................................................................................................... 35 Figure 8: Drive Train................................................................................................................. 35 Figure 9: Ground Drive Continuously Variable Transmission......................................................... 35 Figure 10: Parachute Bottom View............................................................................................. 36 Figure 11: Parachute Side View ................................................................................................. 36 Figure 12: Parachute Front View................................................................................................ 36 Figure 13: Steering Wheel......................................................................................................... 37 Figure 14: Rack and Pinion Assembly ......................................................................................... 37 Figure 15: Brake and Accelerator Pedals .................................................................................... 37 Figure 16: Manual Override Pedals, Linear Stepper Motors, Wiring Connectors, Rigging ............... 38 Figure 17: Steering Input Sensor Located on Rack and Pinion...................................................... 38 Figure 18. Fuel Tank, Strainer, and Outlet ................................................................................... 39 Figure 19: Fuel Tank, In-Line Pumps, Fuel Filter ......................................................................... 39 Figure 20. Fuel System Schematic .............................................................................................. 39 Figure 21: Subaru MAV EJ22 Engine......................................................................................... 40 Figure 22. Subaru MAV EJ25 Engine ........................................................................................... 40 Figure 23: Propeller.................................................................................................................. 41 Table 1. Disposable Replacement Parts........................................................................................ 9 Table 2. Propeller Cogged Belt Tension Values ........................................................................... 18 Table 4: Maverick Wiring Diagram/Table (With ECU 1) – Also applies for fly by wire steering system
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1 GENERAL
About this Manual
IMPORTANT: REVIEW ALL MATERIAL IN THIS MANUAL PRIOR TO MAINTAINING YOUR
Maverick!
This manual is provided by Beyond Roads to communicate various procedures and methods for
maintaining your Maverick aircraft. Maintenance must be done consistently to keep your aircraft in
flying condition and to promote the safety of each flight. Before performing any maintenance, check
www.Mavericklsa.com for a new revision of this Maintenance Manual. All maintenance should follow
and is acceptable if performed according to FAA AC43.13-1B unless it contradicts the practices of
this manual, in which case the practices of this manual shall be followed.
This manual shall apply to all makes and models of Mavericks manufactured by Beyond Roads, and
practices that differ based on model or make will be noted as such.
Terms and Definitions
Manufacturer: generally refers to Beyond Roads, unless referring to the manufacturer of a specific
component.
Beyond Roads: Beyond Roads, LLC.
ELSA: Experimental Light Sport Aircraft
SLSA: Special Light Sport Aircraft
PPC: Powered Parachute
About the Aircraft
The Maverick is a powered-parachute Light Sport Aircraft (LSA). The two-seat chassis and
suspension members are made primarily of welded steel tubing and the wing is an elliptical ram-air
type parachute (parafoil). It features a mast and spar wing deployment system, electronic steering
(with redundant conventional steering controls), and basic engine instrumentation. The aircraft is
configured with four wheels, independent suspension, a Subaru MAV engine, and a transmission
capable of powering a propeller (in pusher configuration) or the rear wheels for ground mobility.
Approved Equipment List
Required Instruments
-EIS (Engine Information System) monitoring fuel level, oil pressure, coolant temperature and
engine RPM
-Engine Kill Switch – The key is used as a kill switch. To kill the engine, turn the key to the
straight up and down position.
Optional Instruments and Avionics -Mode C Transponder, compliant to FAA requirements
-P.S. Engineering (PM1000) intercom and wiring harness
-Garmin GPS (Aera 500 panel-mounted, air and ground) and wiring harness
-Garmin SL40 (“flip-flop”) communication radio and wiring harness
-Icom portable communication radio
-Emergency Transmitter Locator (ELT)
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Required/Standard Equipment
-Windshield
-Carbon Fiber Hood
-Occupant safety restraint system: All occupants have at least a 3 point attach system with a
lap belt and two shoulder harnesses for flight operations.
-Head lights, brake lights, turn signal lights, parking brake, horn
Optional Equipment
-“Tuxedo”: Sunbrella water-repellant fabric with clear vinyl side windows, standard color black
with custom colors optional
-High-speed tires on aluminum rims, 24”X5” (Front) 26”X8” (Rear)
-Off-Road tires on aluminum rims, 25”X8” (Front and Rear)
-Fenders – standard color black, custom colors available
-Custom-color, powder-coated frame paint (standard color black)
-Custom-color, painted hood (standard no painting)
-Rosen sun visors and mounting brackets
Basic Guidance for All Maintenance and Repair Work
Supporting the aircraft: Caution: Parts being worked on may be part of the supporting
structure. Each step that removes a bolt or other part must first be assessed to assure that
the subsequent assemblies will be stable and supported. Jacking in the rear is allowed
directly under the outboard most, lowest points on the frame where the lower engine mount
frames are bolted to the main chassis. Jacking in the front is allowed on the outboard most,
lowest tubes of the main chassis forward of the most aft attachment point of the front
suspension A-frames.
Fluid Systems: The three primary fluids are engine oil, fuel and engine coolant. Hydraulic fluid
(brakes) and transaxle oil are also used. For engine oil see drain points presented in the
engine manual - the primary drain point is at the bottom of the oil pan. For fuel, the drain
sump is on the bottom of the fuel tank. For coolant, there is a plug in the bottom of the
radiator or a coolant hose at a low point in the system may be detached to drain coolant.
Electrical Systems: In process of working on the aircraft’s electrical system, the negative
battery lead should be disconnected to assure that no short circuits are caused. In addition,
the main harness should be disconnected from the fly-by-wire steering system.
Verification Assessment: Although it may not be stated in the following work areas, it is the
responsibility of the person doing the maintenance, repairs, or alterations to complete their
work by doing a functional evaluation sufficient to guarantee that the maintenance/repairs will
function properly. The systems should function according to the manufacturer’s specification
or at least equally well as it did before the alteration was performed or before the problem
that was fixed. Contact the manufacturer for approval before performing maintenance for
which instructions are not included or provided for in this manual.
Tools Required: While some specific tools may be called for in the individual work areas of
this manual, it is assumed that the following tools are available for any given task:
SAE wrench set
Metric wrench set
SAE socket and ratchet set
Metric socket and ratchet set
#1, #2 and #3 Phillips screw drivers
Straight screw driver
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Drift punch
Hammer
Pop rivet puller
Safety wire pliers
Safety wire
Cotter pins
SAE Allen wrench set
Metric Allen wrench set
Torque Wrench
Level of Certification Required to Perform Maintenance
Listed in order of qualification, from lowest to highest:
Owner: Responsible owner who holds a pilot certificate but who has not necessarily received
any specific authorized training. This individual is not required to hold specific authorized
training certificate but should be mechanically inclined. Unless this maintenance manual
directs otherwise, FAA regulations authorize SLSA aircraft owners who hold at least a sport
pilot certificate to perform maintenance as outlines in 14 CFR part 43. Note: ELSA do not
require the individual performing maintenance to hold any FAA airman certificate in the U.S.,
so. for maintenance on an ELSA, items requiring ‘Owner’ certification may not require that the
individual own the aircraft being serviced or even hold a pilot certificate.
LSA Repairman Inspection: Items that can be expected to be completed on an ELSA by a
responsible owner, who holds an FAA repairman certificate (light sport aircraft), with an
inspection rating or equivalent. That is, an owner who is a U.S. FAA-certificated repairman
(light sport aircraft) with an inspection rating as defined by 14 CFR Part 65, authorized to
perform the annual condition inspection on ELSA, or an equivalent rating issued by other civil
aviation authorities.
LSA Repairman Maintenance: Items that can be expected to be completed on a SLSA by a
responsible individual, who holds a FAA repairman certificate (light sport aircraft), with a
maintenance rating or equivalent. That is, an individual who is a U.S. FAA-certificated
repairman (light sport aircraft) with a maintenance rating as defined by 14 CFR Part 65,
authorized to perform line maintenance on aircraft certificated as SLSA aircraft and
authorized to perform the annual condition/100-h inspection on an LSA, or an equivalent
rating issued by other civil aviation authorities.
A&P: Items that can be expected to be completed by a responsible individual who holds a
mechanic certificate with airframe or power plant ratings, or both, or equivalent. That is, an
airframe and power plant mechanic as defined by 14 CFR Part 65 in the U.S. or equivalent
certification in other countries. This individual may perform annual inspections and any
maintenance or repairs they are qualified for as an A&P.
Task Specific: Items that can be expected to be completed by a responsible individual who
holds either a mechanic certificate or a repairman certificate and has received task specific
training to perform the task. The specific training required must be as specified in this manual
or be an equivalent.
Engine overhaul or repair and wing repair/replacement is limited to those facilities approved
specifically by Beyond Roads. Please contact Beyond Roads for information on an approved
facility in your area.
Type of Maintenance
Line Maintenance: any repair, maintenance, scheduled checks, servicing, inspections, or
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alterations not considered heavy maintenance that is approved by the manufacturer and is
specified in this manufacturer’s maintenance manual.
Heavy Maintenance: any maintenance, inspection, repair, or alteration a manufacturer has
designated that requires specialized training, equipment, or facilities.
Major repair, Alteration, or Maintenance: any repair, alteration, or maintenance for which
instructions to complete the task excluded from this maintenance manual.
Sources to Purchase Parts
Parts listed with outside vendor/manufacturer part numbers or sufficient specifications for
purchase in the “Disposable Replacement Parts” and “Approved Oils and Capacities” sections of
this manual may be purchased from any reputable vendor. Contact Beyond Roads for all other
replacement parts, including those with Beyond Roads part numbers. Find current contact
information at Mavericklsa.com.
Additional suppliers may eventually be qualified and will then be shown here.
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Disposable Replacement Parts
For Engine:
a) Transaxle Oil:
b) Oil Filter:
Subaru MAV EJ22
Subaru MAV EJ25
SAE 85W90 API/GL-4
Purolator # PL14460 or
Purolator # PL14620 or
equivalent
equivalent
c) Air Filter:
NAPA # 2110 or equivalent K&N # E-3600 or
equivalent
d) Fuel Filter:
Beyond Roads Part # 405130
e) Tires:
1. Standard: All tires 25x8.00-12
2. Optional: Front: 24x5.00R15LT; Rear: 26x8.00R15LT
(Note: May increase “empty weight”, depending on tire
choice)
f) CVT Drive Belt:
Maverick Part # 200130
g) Main Shaft to CVT Belt:
h) Prop Drive Belt:
h) Nyloc Nuts:
Use appropriate AN hardware
i) Brake Fluid:
Any DOT 3 or DOT 4 rated brake fluid
Table 1. Disposable Replacement Parts
Engine Specifications – Subaru MAV EJ22 (for reference only)
•
•
•
•
•
•
•
Displacement: 2212 cm³
Bore: 96.9 mm
Stroke: 75.0 mm
Compression Ratio: 9.5:1 - 9.7:1
Valve train: SOHC
Fuel Delivery: Carbureted
Horsepower: 127 HP (95 kW) @ 5000 rpm
Engine Specifications – Subaru MAV EJ25 (for reference only)
•
•
•
•
•
•
•
Displacement: 2457 cm
Bore: 99.5 mm
Stroke: 79 mm
Compression Ratio: 10.0:1
Valve train: SOHC
Fuel Delivery: Fuel Injected
Horsepower: 190 HP (142 kW) @ 4900 rpm
Weight and Balance Information
E-LSA/SLSA
Empty Weight (lbs)
Max Gross Weight (lbs)
Useful Load (lbs)
987
1320
333
SLSA with FAA Exemption
No. 10299
987
1430
443
Refer to POH (Beyond Roads Document #500401) for balance and CG adjustment information.
Tire Inflation Pressures
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Standard Tires: 15 psi (cold) to start, then adjust based on operating conditions for handling and
traction performance. DO NOT EXCEED TIRE MANUFACTURER’S PRESSURE AND LOADING
GUIDELINES.
Optional Tires: 10 psi front, 30 psi rear (both cold). Adjust based on operating conditions for
traction and handling performance. DO NOT EXCEED TIRE MANUFACTURER’S PRESSURE
AND LOADING GUIDELINES.
Approved Oils and Capacities
a) Engine Oil and Capacity:
4.2 US Quarts if replacing engine oil and filter. 4.0 US
Quarts if only replacing engine oil.
Recommended oil: Those with API standard SM “Energy Conserving” logo. Those with
ILSAC standard GF-4 “starburst” mark on container.
Normal Operating Conditions:
Temperature
(°C) -30 -20 -15
(°F) -22
-4
5
SAE Viscosity
0
32
15
59
30
86
40
104
10W-30, 10W-40, 10W-50
5W-30
High Temperature or Severe Environment Operation:
API Standard: SM or SL; SAE Viscosity #: 30, 40, 10W-50, 20W-40, 20W-50
b) Transaxle Oil:
SAE 85W90 API/GL-4 – Fill to ½ in. below check plug.
Recommended Fastener Torque Values
Use aircraft torque values (See FAA AC43.13-1B) where applicable. For propeller, follow
manufacturer’s guidelines. For all engine bolts, follow standard factory Subaru torque guidelines.
In all cases, follow this manual if there is any contradiction between it and another standard.
Joints subject to rotation: Tighten until there is little gap, then the fastener must be a castellated
nut locked with a cotter key or equivalent.
Joints not specifying a torque: Tighten until the washer (if present) will not turn (until the bolt/nut
will not turn in the assembly if there is no washer) and then the nut should be tightened ¼ turn
more. If this is not a rotating joint, a nyloc nut will be sufficient, castellated nuts with cotter keys
are acceptable.
Joints having a torque value specified: Torque as specified on either the drawing or in the
maintenance manual. These will usually be in the area of the motor, gear box, propeller or similar
high-load parts.
Warning: DO NOT deform tubing by over tightening. If following recommended torque values or
manufacturer’s torque guidelines results in the onset of tubing deformation, stop before deforming
the tube and contact the manufacturer.
Wheel Lug Nuts: 55 ft*lb (40.6 N*m)
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General Safety Information
Drug and Alcohol Use: Do not mix alcohol consumption or drug use with the assembly,
operation, or maintenance of your aircraft.
Locking Nuts: All nyloc (nuts with a nylon locking insert held securely in place) or steel
locking nuts require 1 to 3 threads of the bolt showing past the nut past the nut. A self-locking
nut can be reused as long as a wrench is required to turn it onto the bolt. If it can be hand
tightened, however, replace the nut. If in doubt follow FAA AC43.13-1B chapter 7.
Difficulty with Bolt Fit: First make sure the difficulty is not due to misalignment, an incorrect
part, or an incorrect bolt. If necessary use a drift or pin punch to align. If misalignment is not
the cause of the difficulty, it is okay to lightly ream the hole with a drill bit or reamer the same
size of the hole. Only ream enough to get the bolt through.
Handling Cables: Do not leave cables where they might be stepped on and damaged. Also,
do not bend or bind them any tighter than the configuration in which they were shipped.
Parachute and Parachute Lines: When handling parachute lines, BE SURE that they are not
stepped on. This can introduce dirt and sand into the lines which can cause dramatic strength
reduction and premature failure. Do not step on the parachute fabric and avoid pinching it
between metal or other hard parts or snagging it on any sharp points as this can result in
damage, deterioration, and loss of strength. Store the parachute in the manufacturer provided
cover to avoid prolonged UV exposure from the sun. If wet or damp, allow the parachute to
dry completely before storage to avoid damage.
Reporting Possible Safety of Flight Concerns
For reporting safety of flight concerns found during inspection/maintenance see FEEDBACK
FORM section for details.
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2 INSPECTIONS
Periodic Inspections
To be performed as often as specified in item or as often as specified in list, whichever is more often.
All official inspections require the inspector to have a certification of LSA Repairman Inspection or
higher.
25 HOUR/MONTHLY
1. Tire Wear/ Pressure
2. Propeller balance, propeller pitch, and torque of all bolts. Re-torque bolts after the first hour of
operation, and then every 5-10 hours for the first 25 hours of operation. Then check every 25
hours of operation.
3. Coolant Fluid Levels and condition (any foreign matter or oil in system)
4. Brakes – fluid level and pad wear; inspect at every 50 hours after first 25 hours
5. Steering system
6. Drive system belts
50 HOURS
1. Inspect engine area for leaks or loose fasteners
2. Inspect drive system belts for excessive wear
3. Transmission fluid level and condition.
300 HOURS
1. Inspect all vibration isolators (engine mounts, transaxle mounts, etc.) and replace if
necessary
2. Inspect Throttle cables and replace if necessary
3. Inspect Radiator lines and replace if necessary
Replacement Schedule
It is recommended that the following items be replaced at the given intervals. Refer to an applicable
Subaru engine maintenance manual applicable for additional replacement requirements.
50 HOURS
1. Change Engine Oil and Filter
2. Brake Pads – if necessary (or after first 25 hour inspection)
300 HOURS
4. Vibration isolators – if necessary
5. Throttle cables - if necessary
6. Radiator lines - if necessary
7. Electric Fuel Pumps (both)
8. Drive System Belts
9. Overhaul Transmission
2 YEARS
1. Mandatory: contact Beyond Roads for parachute assessment by Beyond Roads or their
accepted personnel. The parachute reviewer shall specify intervals for test after this based on
the parachute condition. Assessment shall include tests/evaluations of porosity, strength, and
deformation according to manufacturer standards or, if non-contradictory, industry accepted
practices.
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Annual Condition Inspection
The following items should be inspected and/or replaced if necessary ANNUALY or every 100 hours
of service, whichever occurs first.
1.
2.
3.
4.
5.
6.
7.
8.
9.
10.
11.
12.
13.
14.
15.
16.
17.
18.
Perform Annual Inspection in accordance with FAR 43 Appendix D as applicable
Engine Compression
Engine Vibration Isolators (engine mounts)
Main (all) wheel bearings, inspect and replace if necessary
Throttle cable and linkage
Exhaust system
Fuel line
Propeller hub through-bolts
Propeller assembly
Inspect parachute lines and cloth for excessive wear, chafing or tears/holes – contact Beyond
Roads for parachute service
Radiator hoses
Redrive transmission, systems and belts
Remove and clean fuel filter and strainer
Inspect entire airframe for cracks, deformation, corrosion or wear
Inspect all fasteners for correct torque
Inspection all wiring for chafing and appropriate support and restraint
Check manufacturer’s online maintenance website for applicable service letters and
necessary modifications or revisions, and comply as necessary
Record Annual Inspection in Aircraft Maintenance Records
This is a sample form for recording of Annual or 100 Hour inspection (next page). The specifics
shown above are to be recorded as inspected by checking “pass” or by checking “fail” and showing
how it was corrected.
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Annual Condition Inspection Checklist
Aircraft Make/Model: __________________ S/N: _________________
Engine Make/Model: ___________________ S/N: _________________
Date of Inspection:_____________ TT Airframe: _______________________ TT Engine: _________________
Scope and Detail of Items (As Applicable to the Particular Aircraft) to be Included in Annual and 100-Hour Inspections:
(a) Each person performing an annual or 100-hour inspection shall, before that inspection, remove or open all necessary inspection plates,
access doors, fairing, and cowling. He shall thoroughly clean the aircraft and aircraft engine after initial visual inspection for oil, exhaust, or other
leaks as applicable is completed.
(b) Each person performing an annual or 100-hour inspection shall inspect (where applicable) the following components of the fuselage and hull
group:
Pass Fail (1) Fabric and skin-for deterioration, distortion, other evidence of failure, and defective or insecure attachment of fittings.
Pass Fail (2) Systems and components-for improper installation, apparent defects, and unsatisfactory operation.
(c) Each person performing an annual or 100-h inspection shall inspect (where applicable) the following components of the cabin and cockpit
group:
Pass Fail (1) Generally for uncleanliness and loose equipment that might foul the controls.
Pass Fail (2) Seats and safety belts/for poor condition and apparent defects.
Pass Fail (3) Windows and windshields/for deterioration and breakage.
Pass Fail (4) Instruments/for poor condition, mounting, marking, and (where practicable) improper operation.
Pass Fail (5) Flight and engine controls/for improper installation and improper operation.
Pass Fail (6) Batteries/for improper installation and improper charge.
Pass Fail (7) All systems/for improper installation, poor general condition, apparent and obvious defects, and insecurity of attachment.
(d) Each person performing an annual or 100-hour inspection shall inspect (where applicable) components of the engine and nacelle group as
follows:
Pass Fail (1) Engine section/for visual evidence of excessive oil, fuel, or hydraulic leaks, and sources of such leaks.
Pass Fail (2) Studs and nuts/for improper torqueing and obvious defects.
Pass Fail (3) Internal engine/for cylinder compression and for metal particles or foreign matter on screens and sump drain plugs. If there is weak
cylinder compression, for improper internal condition and improper internal tolerances.
Pass Fail (4) Engine components/for cracks, looseness of mounting, and looseness of engine to mount.
Pass Fail (5) Flexible vibration dampeners/for poor condition and deterioration.
Pass Fail (6) Engine controls/for defects, improper travel, and improper safetying.
Pass Fail (7) Lines, hoses, and clamps/for leaks, improper condition and looseness.
Pass Fail (8) Exhaust stacks/for cracks, defects, and improper attachment.
Pass Fail (9) Accessories/for apparent defects in security of mounting.
Pass Fail (10) All systems/for improper installation, poor general condition, defects, and insecure attachment.
Pass Fail (11) Engine Cowling/for fabric deterioration and defects, loose or damages hardware, and wear or defects in frame members.
(e) Each person performing an annual or 100-hour inspection shall inspect (where applicable) the following components of the landing gear
group:
Pass Fail (1) All units/for poor condition and insecurity of attachment.
Pass Fail (2) Shock absorbing devices/for improper air pressure.
Pass Fail (3) Linkages, trusses, and members/for undue or excessive wear fatigue, and distortion.
Pass Fail (4) Retracting and locking mechanism/for improper operation.
Pass Fail (5) Hydraulic lines/for leakage.
Pass Fail (6) Electrical system/for chafing and improper operation of switches.
Pass Fail (7) Wheels/for cracks, defects, and condition of bearings.
Pass Fail (8) Tires/for wear and cuts.
Pass Fail (9) Brakes/for improper adjustment.
Pass Fail (10) Floats and skis/for insecure attachment and obvious or apparent defects.
Pass Fail (f) Each person performing an annual or 100-hour inspection shall inspect (where applicable) all components of the wing and center
section assembly for poor general condition, fabric or skin deterioration, distortion, evidence of failure, and insecurity of attachment.
Pass Fail (g) Each person performing an annual or 100-hour inspection shall inspect (where applicable) all components and systems that make
up the complete empennage assembly for poor general condition, fabric or skin deterioration, distortion, evidence of failure, insecure attachment,
improper component installation, and improper component operation.
(h) Each person performing an annual or 100-hour inspection shall inspect (where applicable) the following components of the propeller group:
Pass Fail (1) Propeller assembly/for cracks, nicks, binds, bolt torque.
Pass Fail (2) Bolts/for improper torqueing and lack of safetying.
(i) Each person performing an annual or 100-hour inspection shall inspect (where applicable) the following components of the radio group:
Pass Fail (1) Radio and electronic equipment/for improper installation and insecure mounting.
Pass Fail (2) Wiring and conduits/for improper routing, insecure mounting, and obvious defects.
Pass Fail (3) Bonding and shielding/for improper installation and poor condition.
Pass Fail (4) Antenna including trailing antenna/for poor condition, insecure mounting, and improper operation.
Pass Fail (j) Each person performing an annual or 100-hour inspection shall inspect (where applicable) each installed piece of optional equipment
on this listing for improper installation and improper operation.
Pass Fail Option number one
Pass Fail Option number two
Pass Fail Option number three
Pass Fail Option number four
Pass Fail (k) Each person performing an annual or 100-hour inspection shall remove and inspect the ELT installed for proper operation of the “G”
switch and calendar date currency of the batteries installed in accordance with FAA Advisory Circular 91-44 current revision.
Notes and explanation of unairworthy items found (attach more information as needed):
Signed ________________________________
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3 STRUCTURES
3.0 Frame (Cart/Empennage)
3.0.1
Description: 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. The pilot seat is supported by the bulkhead behind it and tubes and in
the floor beneath, with passenger restraint seat belts connecting to the same locations. The rear
passenger seat is supported by the gas tank and the bulkhead behind it, with passenger
restraints in the bulkhead behind the seat.
3.0.2
Inspection: Inspect security of fasteners holding frame and drive system together.
Visually inspect frame for bending, cracking, or fatigue. If any of these are present DO NOT fly or
drive as they may precede failure of the frame. Contact the manufacturer. Especially inspect
connection points and surrounding frame area for the suspension and wing. Note that paint and
coatings can ide small cracks or deformation and that very small cracks in coatings may be
indicative of deformation in the metal beneath the coating. Cables and hardware they connect to,
as well as hardware in the CG adjustment mechanism (especially eyebolts) should not sound
and undeformed. Inspect the thimbles and swages on the cables for thimble deformation
(indicating overloading or beginning of failure) and cable slipping or fraying. No special tools are
required to accomplish this task. No parts are needed to perform this task.
3.0.3
Maintenance, Repair, and Alteration: All services MUST be performed by the
manufacturer or manufacturer approved facility or personnel. Owners require no special tools,
instructions, parts, or inspection procedures for these services. Manufacturer will test/inspect
services.
3.1 Landing Gear (Wheels and Suspension)
3.1.1
Description: The front suspension system includes four a-frame suspension arms,
two air shocks, the front two wheels and the suspension/wheel connection points. 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 points. See images
in Appendix 2.
3.1.2
Inspection:
3.1.2.1 Special Tools, :
3.1.2.2 Welded Tube Assemblies: All bolts should be secure and the A-frames and struts in
good condition. Rod end bearings should have no more than half of the threaded length on the
stud showing, should not be bent or deformed, and balls should allow free motion with minimal
slop. No special tools or parts are required to accomplish this task.
3.1.2.3 Bearing Holders, Hubs, Knuckles: All bearing holders, hubs, adapters, steering
knuckles, and miscellaneous joining parts should be undeformed, allow full range of motion of
the shock assemblies, and hold all bolts and parts tightly. No special tools or parts are
required to accomplish this task.
3.1.2.4 Shock Absorbers/Springs: Refer to the shock manufacturer’s manual. No special
tools or parts are required to accomplish this task unless otherwise specified.
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3.1.2.5 Wheels and Tires: Tires should have a fair amount of tread showing and have no
major cuts or cracks. Inspect for even wear across tire width and circumference. Replace tire if
less than 2/32” (1.6 mm) of tread remain (depth of shallowest indentation in tread pattern).
Tires positions should be changed if wear on front tires or on back tires is not even. If using
optional tires switch the sides the tires are on. If using standard tires, switch the right front with
left rear tire and left front with right rear tire (unless this would cause wear in the same location
it had been, in which case switch the tires to positions that would cause wear in different
positions). Valve stems should hold pressure and be operational. Rims should have a smooth
surface where the tire bead sits. No special tools or parts are required to accomplish this task.
3.1.3
Maintenance, Repair, and Alteration:
3.1.3.1 Checking/Adjusting Shock pressure
3.1.3.1.1
Recommended Special Tools: Shock Pump
3.1.3.1.2
Required Parts: None
3.1.3.1.3
Type of Maintenance: Line
3.1.3.1.4
Certification Required: Owner through A&P
3.1.3.1.5
Instructions:
3.1.3.1.5.1 Remove the air valve cap from the shock
3.1.3.1.5.2 Thread the pump’s valve chuck onto the shock’s air valve until pressure
registers on the pump gauge. This takes approx. 6 turns. Do not over tighten pump on air
valve, as this will damage the pumps chuck seal.
3.1.3.1.5.2.1
Stroke the pump a few cycles. The pressure should increase slowly.
If pressure increases rapidly check to make sure the pump is properly fitted and
tightened onto the air valve.
3.1.3.1.5.2.2
Pump to the desired pressure setting. Normal pressure range is 50
to 300 psi for front and 45 to 150 psi for rear. Do not exceed shock manufacturers
guidelines for pressure settings or travel. You can decrease pressure by pushing the
black bleed valve. Pushing the bleed valve half way down and holding it there will allow
pressure to escape from the pump and shock. Pushing the bleed valve all the way
down and releasing it will allow only a small amount of pressure to escape. When
unthreading the pump from the air valve fitting, the sound of the air loss is from the
pump hose, not from the shock.
3.1.3.1.5.2.3
3.1.3.1.6
Replace the air valve cap.
Test/Inspect: Visually confirm that the tires sit flat.
3.1.3.2 Changing Tires
3.1.3.2.1
Recommended Special Tools:
Jack sufficient to lift assembly
Lug Wrench
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Torque wrench (if available)
3.1.3.2.2
Required Parts:
Replacement tire on wheel (wheel assembly)
3.1.3.2.3
Type of maintenance: Line
3.1.3.2.4
3.1.3.2.5
Procedure
3.1.3.2.5.1 With tire on ground, loosen lug nuts.
3.1.3.2.5.2 Chock rear wheels when jacking the front of the vehicle, chock front tires
when jacking the rear of the vehicle.
3.1.3.2.5.3 Jack from acceptable jack point see “Basic Guidance for All Maintenance
and Repair Work” section of this manual.
3.1.3.2.5.4 Remove lug nuts.
3.1.3.2.5.5 Replace wheel with new assembly.
3.1.3.2.5.6 Hand tighten lug nuts
3.1.3.2.5.7 Tighten Lug nuts as practical off ground.
3.1.3.2.5.8 Lower vehicle.
3.1.3.2.5.9 Tighten lug according to torque specification.
3.1.3.2.6
Test/Inspect: Re-check torque on lug nuts with torque wrench.
3.2 Drive System
3.2.1
Description: The drive system is comprised of two cogged drive belts, one friction
drive belt, four major shafts, two drive axles, three aluminum structural plates, a welded 4130
steel tube frame, and miscellaneous bearing holders and supports.
As viewed from the rear of the vehicle, all shafts and components connected to them spin
CCW (counter clock wise).
A collar with in internal spline connects the main shaft driven by the engine to either a cogged
belt drive that drives the propeller or a cogged belt that drives the continuously variable
transmission (CVT). This collar is the means of transitioning between drive and flight modes,
and, if transitioned correctly, only allows the car to be in one mode at any time, not both. The
locking mechanism on this collar enables the user to verify this.
The propeller drive consists of a cogged belt and cogged pulleys configured so the propeller
runs at a lower RPM than the engine. Additionally, the entire engine and support plates that
bolt to it for the drive system are tilted relative to the vehicle chassis so that, in flight as the
cart is normally nose up, the thrust line of the propeller is closer to being parallel with the
relative wind and P-factor is reduced.
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The CVT has two sheaves that change in pitch diameter in response to RPM changes. The
primary section is driven by a cogged belt drive. The secondary section is connected to the
primary by a friction drive belt and drives the shaft entering the transaxle.
The transaxle is driven by the CVT and drives the rear axles. It has 3 modes: forward, reverse,
and neutral, which are selected by the shifter in the cockpit.
See images in Appendix II.
3.2.2
Inspection:
3.2.2.1 All bolts must be secure and torqued to specification (if applicable). Inspect especially
for major corrosion near steel bolts in contact with aluminum parts. No special tools or parts
are required to accomplish this task. This line maintenance may be performed by owners
through A&P.
3.2.2.2 All shafts should be centered and perpendicular to the support plates that their
bearings or bearing holders are in. Total Indicated Runout (TIR) must be less than 0.0015”
(0.04mm) on all shafts. A measuring device with sufficient resolution will be required. No parts
are required to accomplish this task.
3.2.2.3 Visually inspect belts for frayed edges, tears, cracks, or delamination. Inspect for
uneven wear on the belt (though a small degree of unevenness is usual), especially if one
spot is worn more than others or if edges of a cogged belt are worn unevenly (which may
indicate shaft or pulley misalignment). Contact manufacturer immediately for replacement or
further inspection instructions if any defects are found. No special tools or parts are required to
accomplish this task.
3.2.2.4 Inspect cogged pulleys and friction belt CVT pulleys. Sheaves should have smooth
surfaces that show minimal wear and even wear. Foreign matter underneath belts (e.g. sand,
dust, etc.) can rub on the sheaves and damage the surface the belts ride on. Guides should
not be damaged in ways that will cause belt damage. No special tools or parts are required to
3.2.2.5 Inspect bushings in pulleys and bushing tightening bolts. All bolts should be tight and
torque stripe between shaft and bushing and bushing and pulley should indicate no relative
motion between these parts. No special tools or parts are required to accomplish this task.
3.2.2.6 Check that the cog belts are properly tensioned. Use a belt tension meter and follow
the guidelines in the tables below. Notify the manufacturer if belt tension is below these values
by 10% or above by 5% for the propeller belt. The ground drive belt is not a safety of flight
component, so if not attainable even used belt specs may be used for new belts. If a used belt
is reinstalled, record the tension before removing and tension after re-installation must be the
same. Additionally, if a used belt is reinstalled, it should travel in the same direction as it did
before it was removed. No parts are required to accomplish this task. NOTE: Refer to
‘Maintenance and Repair’ section for any allowable maintenance to belts.
3.2.2.6.1
Propeller Cogged Belt Drive
Value
New Belt
Used Belt
Rib/Strand Deflection Distance (in.)
0.27
0.27
Rib/Strand Deflection Force (lb)
55 - 60
41 - 46
Sonic Tension Meter, belt frequency (Hz) 125 - 131 106 - 113
Table 2. Propeller Cogged Belt Tension Values
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3.2.2.6.2
Ground Drive Cogged Belt Drive
Value
New Belt
Used Belt
Rib/Strand Deflection Distance (in.)
0.12
0.12
Rib/Strand Deflection Force (lb)
42-52
30-40
Table 3. Ground Drive Cogged Belt Tension Values
3.2.3
Maintenance and Repair
3.2.3.1 Lubrication
3.2.3.1.1
Grease gun with appropriate fittings
3.2.3.1.2
Required Parts
High quality, general purpose automotive bearing grease (see U-Joint manufacturer’s
recommendations).
3.2.3.1.3
3.2.3.1.4
Level of Certification Required: Owner through A&P
3.2.3.1.5
Instructions: Grease U-Joints using installed grease fitting until full.
3.2.3.1.6
Test/Inspect: Confirm grease fitting is full.
3.2.3.2 All other maintenance: All maintenance shall be performed by Beyond Roads or a
facility, entity, or individual they approve. Contact the manufacturer for a current list. Owners
require no special tools, instructions, parts, or inspection procedures for these services.
3.3 Wing (Ram-Air Parachute)
3.3.1
Description: The Maverick ‘wing’ is a high-aspect ratio, elliptical, double canopy ramair pressurized, rip-stop nylon parachute. The suspension and steering lines are made of a
separate material as well. The parachute is connected to the aircraft by risers and working-load
rated carabiners. All parachute maintenance should be handled by the manufacturer or a
manufacturer approved facility.
See images in Appendix II.
3.3.2
Inspection:
3.3.2.1 Carabiners: Visually inspect the carabiners and threads for deep scratches, dents, or
defects. Carabiner nuts should be secure. If not secure note this in a report and tighten finger
tight plus ¼ turn with a wrench. Contact Beyond Roads for instructions before removing
parachute for recertification or maintenance. No special tools or parts are required to
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3.3.2.2 Risers: Inspect the risers for integrity of coating, frayed stitching or fabric, stress
marks on fabric or stitching, and any other deterioration or degradation. No special tools or
parts are required to accomplish this task.
3.3.2.3 Parachute: Layout the parachute flat on the ground behind the vehicle with the top
surface of the canopy facing the ground and the bottom surface facing up. Inspect the bottom
surface of the chute for any tears, holes, loose or frayed stitching, or discoloration (from
contaminants or UV degradation). Turn the canopy over and repeat for the upper surface. Also
inspect the ribs of the parachute, line loops, and crossports for damage, tearing, fraying, and
loose or frayed stitching. Also verify that there is no major debris inside the cells of the chute.
No special tools or parts are required to accomplish this task.
3.3.2.4 Parachute Lines: CAUTION: stepping on parachute lines and introducing dirt or sand
into them can severely degrade strength and lead to premature failure. Avoid stepping on or
pinching parachute lines. Shake the lines out and visually verify that the left and right sides are
symmetrical, that the A and B lines go to the same carabiner on either side, that the C and D
lines go to the same carabiner on either side, and that the lines go from their respective
carabiners to the canopy without being twisted or knotted. Usually, if correctly rigged and
installed, most apparent knots or twists can be remedied by simply shaking the lines out or by
rotating individual carabiners relative to the chute). Verify that there are no loose, frayed, or
torn lines (i.e. that all lines are connected at both ends to one of the following: the parachute,
the carabiners, other lines, or the steering system). No special tools or parts are required to
3.3.2.5 Steering Lines: Steering lines should be routed as shown in the illustrations and
should not be routed so that during normal travel they rub on sharp corners or surfaces that
would damage the lines. Inspect for fraying or other signs of wear and degradation. No special
tools or parts are required to accomplish this task.
3.3.3
Maintenance and Repair:
Except as specified, only the manufacturer or manufacturer approved facility, entity, or
individual may perform maintenance and repair of a Maverick parachute. Contact the
manufacturer for more information.
3.3.3.1 General Care
3.3.3.1.1
Recommended Special Tools: soft cloths for cleaning
3.3.3.1.2
Required Parts: none
3.3.3.1.3
3.3.3.1.4
3.3.3.1.5
Instructions:
3.3.3.1.5.1 If the chute is exposed to moisture and could remain damp or wet if stowed
conventionally on the Maverick, at soonest convenience lay out or hang the parachute in
a clean, dry, shaded location and allow the parachute to completely dry.
3.3.3.1.5.2 If dirt, mud, or organic debri (e.g. bugs and bird feces) soil the parachute, use
very mild soapy water and a soft cloth to dab/wipe the affected areas clean. Dab/wipe dry
with a clean cloth and allow to dry as above before stowing.
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3.3.3.1.6
Test/Inspect: Examine chute for cleanliness and dryness.
3.4 Control Systems
3.4.1
Description: The control system includes the steering, brake, throttle, and shifting
systems. See images in Appendix II
3.4.1.1 Steering: The steering wheel is connected to the rack and pinion through the steering
column. The electric fly-by-wire system has a sensor attached to the rack and pinion that
provides input to the steering circuit board which controls the linear actuator electric steering
motors. The steering wheel steers the front wheels on the ground and, with fly mode activated
in flight, will activate the steering motors to pull on the parachute steering lines in order to
steer the craft like a conventional PPC. The steering pedals function like those on a
conventional PPC aircraft for steering (or back up if the electric system fails) and are required
in normal operation for landing flare. The steering lines are routed through pulleys from the
trim lock devices to the parachute.
3.4.1.2 Brakes: Each wheel has a disk brake, which is activated by the adjustable-position
brake pedal through a master cylinder, proportioning valve, and brake lines. A parking brake
(NOT EMERGENCY BRAKE) is implemented by a valve that, if shut after applying braking
pressure, maintains braking pressure on the rear brakes after the brake pedal is released.
Pressure is released by opening the valve. CAUTION: If there is no pressure in the system
when the valve is closed, the parking brake will not be applied. Also, if the valve is closed and
no pressure was in the system only the front brakes will activate if the brake pedal is pressed.
Be sure to keep the valve open for normal driving and flying operation.
3.4.1.3 Throttle: The throttle is controlled by the adjustable-position 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.
3.4.2
Inspection:
3.4.2.1 General: Check that all bolts and connectors are secure, that all moving parts have
free and full range of motion (especially pulleys), and that no lines are frayed or damaged. All
castle nuts must have cotter pins installed correctly. No special tools or parts are required to
3.4.2.2 Steering: Check for full and interference free range of motion of the front wheels and
electric steering cylinders. Check for excess movement in rack and pinion - there should be
less than 1” of travel on the rim of the steering wheel before the wheels move or, when in flight
mode, before the steering cylinders move in response to the steering wheel. Check for full
articulation, smooth operation, and proper functionality of the manual steering pedals. Check
that the trim locks work correctly and grasp the steering lines. Check that wires for the electric
system are no frayed and connectors are secure. No special tools or parts are required to
3.4.2.3 Brakes: Check brake pads for excessive wear and braking system for functionality.
Check brake fluid level and system for leaks. Check parking break for correct functionality. No
special tools or parts are required to accomplish this task.
3.4.3
Maintenance and Repair:
3.4.3.1 Bleeding Brakes
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3.4.3.1.1
3.4.3.1.1.1 Collection device for excess brake fluid.
3.4.3.1.2
Required Parts: Approved brake fluid
3.4.3.1.3
3.4.3.1.4
3.4.3.1.5
Instructions: Follow industry accepted practices.
3.4.3.1.6
Test/Inspection: Follow industry accepted practices.
4 ENGINE
4.0 Description: The engine is a Subaru MAV 4 cylinder, horizontally opposed, single overhead cam
engine. See “GENERAL” section for more information and specification. The coolant routing is
modified so that the hoses that normally connect to a vehicle heater core simply connect to each
other because no heater core is present, but the majority of the engine is very similar to a stock
Subaru engine.
See Appendix II for illustrations.
4.1 Maintenance, Repair, and Overhaul: Except for routine engine maintenance as described below
or as allowed for individuals with the certifications listed in the “Level of Certification Required to
Perform Maintenance” section of this manual, all maintenance, repairs, and overhaul of the
engine must be performed by the Beyond Roads or one of its authorized repair facilities or
personnel. For a list of these facilities, contact the manufacturer.
4.1.1
Changing Oil and Filter
4.1.1.1
4.1.1.1.1
drain plug wrench (if applicable)
4.1.1.1.2
oil filter wrench
4.1.1.2
Required Parts:
4.1.1.2.1
Oil: See “Approved Oils and Capacities” section.
4.1.1.2.2
Filter: See “Disposable Replacement Parts” section.
4.1.1.3
4.1.1.4
4.1.1.5
Procedure:
4.1.1.5.1
Warm up the engine by letting the it idle for 10 minutes to ease draining of
the engine oil.
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4.1.1.5.2
Park aircraft on a level surface and stop the engine. Remove the oil filler cap.
4.1.1.5.3
Drain out the engine oil by removing the drain plug or opening the quick drain
valve (if equipped) while the engine is still warm. The used oil should be drained into an
appropriate container and disposed of properly. CAUTION: Engine Oil may be very hot
and could cause burns.
4.1.1.5.4
If equipped with a quick drain plug, wipe the seating surface of the drain plug
with a clean cloth and tighten it securely with a new sealing washer after the oil has
completely drained out. If equipped with a quick drain, check that no oil leaks after
closing the valve.
4.1.1.5.5
Remove the oil filter with an oil filter wrench.
4.1.1.5.6
Before installing a new oil filter, apply a thin coat of engine oil to the seal.
4.1.1.5.7
Clean the rubber seating area of the bottom of the engine and install the oil
filter by hand tuning. Be careful not to twist or damage the seal.
4.1.1.5.8
Tighten the oil filter by hand until the rubber seal contacts the mating surface.
Then tighten an additional half to three quarters of a turn.
4.1.1.5.9
Pour new engine oil through the filler neck.
4.1.1.5.10
Add the amount specified or until reaching fill line on dipstick.
4.1.1.5.11
Start the engine and make sure that no oil leaks appear around rubber oil
filter seal and drain plug or quick drain valve.
4.1.1.5.12
Let engine cool and recheck oil level and add oil as necessary.
4.1.2 Adding Coolant
4.1.2.1
Recommended Special Tools: None
4.1.2.2
Required parts:
Engine Coolant (Subaru Part Number:
SOA868V9270, or
equivalent approved by Subaru for engines specifying this part number)
4.1.2.3
Type of maintenance: Line
4.1.2.4
Certification Required: Owner/operator or above
4.1.2.5
Instructions:
4.1.2.5.1
Read warnings on Subaru Part Number: SOA868V9270, but do not drain and
flush the coolant system.
4.1.2.5.2
Remove reservoir cap and fill to appropriate line as marked on the coolant
reservoir.
4.1.2.5.3
Replace cap.
4.1.2.5.4
To drain and flush the coolant system, contact Beyond Roads.
4.1.2.6
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5 FUEL SYSTEM
5.0 Description: 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 fuel pumps, fuel
pressure regulator, in-line fuel filter and a Subaru fuel injection system or carburetor.
See images in Appendix II for illustrations.
5.1 Inspection: Visually check fuel tanks, lines, fittings, and injectors for damage, dents, and leaks.
Verify that the fuel level indicator reads full or nearly full with the tank full of gas and, periodically,
drain the gas to verify that it reads empty with no fuel in the tank. If damage or defects are
discovered DO NOT fly or drive and contact manufacturer. Periodically check fuel pressure with a
fuel pressure gage attached to the fuel pressure regulator. Proper pressure will depend on the
engine in the Maverick, so contact Beyond Roads for specific engine specifications. No special
tools or parts are required to accomplish this task other than those listed.
5.2 Maintenance, Repair, and Overhaul:
Except as specified below, all overhaul and repair must be performed by Beyond Roads or their
approved facilities or personnel.
5.2.1 Changing the Fuel Filter
5.2.1.1
Recommended Special Tools: None
5.2.1.2
Required Parts: New manufacturer recommended fuel filter or equivalent. See
“Disposable Replacement Parts” section.
5.2.1.3
5.2.1.4
5.2.1.5
Procedure:
5.2.1.5.1
Disconnect the negative terminal on the battery
5.2.1.5.2
Disconnect fittings on both sides of fuel filter
5.2.1.5.3
Replace old filter element with equivalent new filter element
5.2.1.5.4
Reconnect fittings and appropriate brackets
5.2.1.5.5
Reconnect the negative terminal on the battery
5.2.1.6
Test/Inspect: Ensure engine runs properly.
6 PROPELLER
6.0 Description: The propeller is comprised of five ground-adjustable pitch blades mounted in a
propeller hub which is in turn mounted to a splined adapter to connect to the propeller shaft.
See image(s) in Appendix II for illustrations.
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6.1 Inspection: Visually inspect attaching nut and cotter key for presence and security. DO NOT fly or
drive if damaged or loose. Inspect blades for nicks, cracks, delamination, or other damage. If
leading edge protection is installed, inspect for damage. Inspect pitch setting and pitch of blades
compared to each other. Follow all propeller manufacturer’s inspection guidelines, including
torque values for bolts. No special tools or parts are required to accomplish this task unless
otherwise noted.
6.2 Maintenance and Repair: Refer to and follow the propeller manufacturer’s maintenance manual
for any propeller maintenance not covered in this manual. No special tools or parts are required
to accomplish this task unless otherwise noted. Type of maintenance and level of certification is
controlled by the propeller manufacturer’s maintenance manual.
7 UTILITY SYSTEMS
7.0 Description:
7.0.1 Body: The Maverick has an (optional) fabric covering (“tuxedo”) that covers the main chassis
and engine compartment, a semi-rigid hood, optional fenders (front and rear), a windshield,
and optional sun visors. These are non-structural and not safety of flight components. A
storage compartment or bag (usually part of the tuxedo) is also provided for storing the
parachute.
7.0.2 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 semirigid 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 lower it in a controlled manner.
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.
7.0.3 Ground Operation Utilities: Head lights, brake lights, turn signal lights, parking brake, and
horn. These are not safety of flight components.
7.1 Inspection:
7.1.1 Body: The fabric covering should not show major fraying, tearing, degradation, or loose
stitching or fasteners. Inspect materials and all attachment points to the vehicle of all body
components to ensure that no part will come off in flight or interfere with safe operation of the
aircraft. All bolts should be secure. No special tools or parts are required to accomplish this
task.
7.1.2 Wing Deployment System: Inspect mast and spar components for cracking, delamination,
nicks, or other damage, especially at joints and mounting points. Inspect the attachment of the
parachute to the spar to ensure it is sound. Inspect all ropes for abrasion and fraying, as well
as the attachment of the spar to the mast and all knots/joints. Inspect all mechanisms for
functionality. No special tools or parts are required to accomplish this task.
7.1.3 Ground Operation Utilities: All utilities should function in response to their switches. No
7.2 Maintenance and Repair:
7.2.1 Body:
7.2.1.1
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7.2.1.1.1
Cleaning
7.2.1.1.1.1
Recommended Special Tools: Compressed air system with blow-off
tool. Soft brush.
7.2.1.1.1.2
Required Parts: None
7.2.1.1.1.3
7.2.1.1.1.4
7.2.1.1.1.5
Instructions: Use compressed air to blow off dirt from the fabric
covering and for more major cleaning, may use mild soap and water with a soft
brush.
7.2.1.1.1.6
Test/Inspect: Visually inspect.
7.2.1.1.2
Alteration (Heavy Maintenance): Owner through A&P may modify the tuxedo
as long as:
7.2.1.1.2.1
Recommended Special Tools: Varies by operation
7.2.1.1.2.2
Required Parts: Varies by operation
7.2.1.1.2.3
Type of Maintenance: Heavy
7.2.1.1.2.4
7.2.1.1.2.5
Instructions: Modification is allowed if:
7.2.1.1.2.5.1 It does not hinder the passengers from safe exit (specifically under
emergency conditions).
7.2.1.1.2.5.2 The tuxedo kit is firmly secured to the frame, (preventing the tuxedo
kit or internal items from falling off or out and damaging the Maverick, its
propeller, or other persons or property).
7.2.1.1.2.5.3 The modification does not change, remove, conceal or make
unusable the aircraft identification information or required placards and
markings.
7.2.1.1.2.5.4 Performed with specific consent of the manufacturer or performed by
the manufacturer or manufacturer approved facilities or personnel.
7.2.1.2
Windshield, hood, fenders, sun visors (line maintenance): Owner through A&P may
use cleaning products approved for these surfaces to clean them.
7.2.2 Wing Deployment System: Avoid grit between mating surfaces of the mast or spar
components as these can cause severe degradation. Use clean cloth and/or compressed air to
clean grit from these surfaces. Contact manufacturer for all other maintenance and repairs.
7.2.3 Ground Operation Utilities: Except for re-establishing any loose or disconnected connections
per the manufacturer’s wiring diagram, all maintenance and repair must be done by the
manufacturer or a manufacturer approved facility or personnel. Owners require no special tools
or parts for this service.
Date:
10-23-2012
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8 INSTRUMENTS AND AVIONICS
8.0 Description: See “Approved Equipment List” and instrument manufacturers’ descriptions. The
Engine kill switch is the key switch – turning the key to the up/off position kills the engine. The EIS
displays and monitors, through the ECU and its sensors (or independent sensors) fuel level, oil
pressure, coolant temperature and engine RPM.
8.1 Inspection: Check that all instruments and avionics are functioning correctly according to
manufacturer specifications using industry accepted practices or instrument manufacturers’
instructions. Verify that the fuel level indicator reads full or nearly full with the tank full of gas and,
periodically, drain the gas to verify that it reads empty with no fuel in the tank. EIS should display
values correctly, at a minimum fuel lever, oil pressure, coolant temperature and engine RPM. No
8.2 Maintenance, Repair, Replacement, and Installation: All service should be performed by the
manufacturer or manufacturer of the instrument. If applicable, owner through may follow the
instrument manufacturer’s guidelines for removal/reinstallation of previously installed instruments
for servicing by Beyond Roads or the manufacturer of the instrument. All permanent removal or
new installation of instruments/avionics must be approved by Beyond Roads. No special tools or
parts are required to accomplish this task unless otherwise noted.
9 ELECTRICAL SYSTEMS
9.0 Description: The electrical system consists of a sealed nominal 12 Volt battery; alternator with
voltage regulator; all wiring for utility, engine, instrument, and avionics systems; all electric
instruments and avionics; and the electric fly-by-wire steering motors and control board.
9.1 Schematic Diagram: See images in Appendix III.
9.2 Inspection: All wires should be held securely and protected from chafing and pinching. All wire
terminal connections and splices should be sound. All connectors should be intact and functional
and wires held securely to them. Wires should have sufficient strain relief and be protected from
extreme heat. No special tools or parts are required to accomplish this task.
9.3 Maintenance, Repair, and Alteration: All service should be performed by the manufacturer. As
such, owners require no special tools or parts for this service.
10 STRUCTURAL REPAIRS
10.0 Maintenance, Repair, and Alteration: All services MUST be performed by the manufacturer
or manufacturer approved facility or personnel. As such, owners require no special tools or
parts for this service.
11 PAINTING AND COATINGS
11.0
Description: The frame and suspension members are powder coated, as well as various
other pieces (mostly steel). The radiator shroud has an insulating coating. Some drive system
parts are anodized. The hood and fenders may be painted (optional). The floor may have a
covering for grip in some places. The exhaust system may have a high temperature coating.
11.1
Inspection: All coatings should completely cover the surfaces they are on and not be worn to
the bare surface. The frame coating and coating on steel parts are especially critical for corrosion
Date:
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protection. All adhesive coatings need to be secure and still adhere to the surface they are on. No
11.2
Repair, Replacement, or Alteration:
11.2.1
Powder Coat and Paint: Owner through A&P may use durable touch up paint to
recoat small damaged sections of any painted or powder coated part following industry
accepted practice. More extensive painting may be done with specific manufacturer approval
as long as required markings and placards are not concealed or marred.
11.2.2
All Other Coatings or for Major Service: Contact the manufacturer
12 REVISIONS TO MAINTENANCE MANUAL
(See Section I Revision Table and Appendix I)
13 FEEDBACK FORM
Please report service difficulty, component malfunction/failure, and safety concerns found during
maintenance or operation, including issues and anomalies in the maintenance manual, to Beyond
Roads. They will be recorded and evaluated and may be acted upon for the continued
airworthiness of the Maverick.
The following page includes the minimum information that an owner or maintainer must send to
Beyond Roads to report service difficulties and/or possible safety of flight issues. Please visit
www.Mavericklsa.com for a current version of this Feedback Form and follow the included
instructions for sending it to Beyond Roads.
Date:
10-23-2012
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Service Difficulty and Feedback Reporting Form
Mail to Beyond Roads at:
10575 SW 147th Circle
Dunnellon, FL 34432
Or
E-mail to [email protected]
Or
Fax to 815-377-3694
Name of reporting party _______________________________________
Date reported _______________ Date of event if any ________________
Make _________________ Model __________________ S/N_________
Address of reporting party _____________________________________
City, state, zip _______________________________________
Phone number
__________________________________
Alt Phone
_______________________________________
Email
_______________________________________
Name of owner, if different ______________________________________
Address of owner ____________________________________________
City, state, zip _______________________________________
Phone number ______________________________________
Alt Phone
_______________________________________
Email
__________________________________________
Circumstances: (e.g. Hard landing, gust front, etc.) _____________________
______________________________________________________________
______________________________________________________________
______________________________________________________________
Component or system at fault: _____________________________________
______________________________________________________________
FAA/NTSB contact if any (incl. date): ________________________________
______________________________________________________________
Beyond Roads use only
contacted __________________________________
Initial working issue ____________________________________________
Closure if any ______________________________________________
Closing date ________________________ Person __________________
Record number _______
Date:
10-23-2012
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14 SAFETY DIRECTIVES
14.0
General: An SLSA may have a safety directive issued against it or a component part. Beyond
Roads will issue the directive as outlined in the applicable ASTM continued airworthiness
specification. Beyond Roads will publish these safety directives on its web site and notify owners
who properly maintain valid contact information with the Beyond Roads. Failure by the aircraft
owner to maintain a proper address with Beyond Roads will void the aircraft’s airworthiness, until
corrected.
14.1
Requirement for Compliance: For SLSA, service and safety directives are considered as
mandatory tasks in order to maintain a condition of safe operation and compliance with the
applicable original manufacturer’s ASTM design specification. A notice of such directives will also
be issued to ELSA owners, but compliance will not be considered mandatory for continued
airworthiness.
14.2
Instructions: Beyond Roads will supply the applicable instructions to comply with any safety
directive, which will include:
14.2.1
A list of the tools needed to accomplish the task,
14.2.2
A list of the parts needed to perform the task,
14.2.3
Type of maintenance (for example, line, heavy, overhaul),
14.2.4
The level of certification needed to accomplish the task (for example, A&P, repairman
inspection, etc.),
14.2.5
Detailed instructions and diagrams as needed to perform the task, and
14.2.6
Method to test/inspect to verify the task was accomplished properly.
14.3
Safety directives are considered as mandatory tasks in order to maintain a condition of safe
operation and compliance with the applicable original ASTM design specification.
14.4
List of current safety directives, if any:
None, as of Sept 1, 2011
Date:
10-23-2012
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15 ORIGINAL AND BACKUP 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]
Appendix I
Change History Information: See Section I Revision Table.
Date:
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Appendix II
NOTE: Images are typical and actual appearance may vary based on options selected and stock
available.
Structure – Acceptable Jack Location
Figure 1. Acceptable Jack Point, rear
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Suspension System
Figure 5: Front Tire
Figure 3: Front Suspension
Date:
10-23-2012
Figure 4: Rear Suspension and Tire
Figure 2: Rear Suspension and Tire (rear view)
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Drive System, Transaxle
Figure 6: Transaxle
Date:
10-23-2012
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Drive System
Figure 7: Ground Drive Axle
Figure 8: Drive Train
Figure 9: Ground Drive Continuously Variable
Transmission
Date:
10-23-2012
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Wing
Figure 10: Parachute Bottom View
Figure 12: Parachute Front View
Date:
10-23-2012
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Figure 11: Parachute Side View
Maintenance Manual
Control System
Figure 13: Steering Wheel
Figure 15: Brake and Accelerator Pedals
Figure 14: Rack and Pinion Assembly
Date:
10-23-2012
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Figure 16: Manual Override Pedals, Linear Stepper Motors, Wiring Connectors, Rigging
Figure 17: Steering Input Sensor Located on Rack and Pinion
Date:
10-23-2012
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Fuel System
Figure 18. Fuel Tank, Strainer, and Outlet
Figure 19: Fuel Tank, In-Line Pumps, Fuel Filter
Date:
10-23-2012
Figure 20. Fuel System Schematic
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Engine
Figure 21: Subaru MAV EJ22 Engine
Figure 22. Subaru MAV EJ25 Engine
Date:
10-23-2012
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Propeller
Figure 23: Propeller
Date:
10-23-2012
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Appendix III
Maverick Wiring Diagram (with ECU 2 - AEM)
Date:
10-23-2012
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A-Y
A-P
A-P
A-L-N
12AWG Wh
18AWG Bk
Bus Power
Date:
10-23-2012
Master Sw
Fuel Pump #1 16AWG Rd
Fuel Pump #2 16AWG Rd
Starter
43 of 47
Male D-Sub
Male D-Sub
ECU - EC3 J1 Spliced to EMS
P-W
Injector 1
Male D-Sub
Red 1/4" Ring
ECU - EC3 J1
Ground on Engine
Panel - Key Switch Ign
Blue #8 Ring
P-WExtra
Yel/
18AWG Wh
Ignition Coil Gnd
A-WExtra
Panel - Left Flasher Red Female
Relay
Spade
Red Female
Spade
Ignition Coil - D 20AWG
18AWG Rd
Ignition Coil Power
A-L-N
Panel - Right
Flasher Relay
ECU - EC3 J1
18AWG Rd
Left
Blinker/Brake
A-L-M
Panel - Headlight Sw Red #6 Ring
P-WExtra
18AWG Rd
Right
Blinker/Brake
A-L-M
Ignition Coil - A 20AWG
18AWG Rd
Tail Lights
Red #6 Ring
Panel - Fuel Pump
Sw
Dsub 15
Male
Dsub 15
Male
Dsub 15
Male
Red 3/16" Ring
Master
Solenoid
Red Butt Splice
Ignition Coil
Ignition Coil
Injector 1
Signal
11 Ignition Coil
In Connector
Butt Splice
Butt Splice
In Connector
Butt Splice
Left Brake Light Red Butt Splice
Right Brake
Light
15 Ignition Coil
3
Red Female
Spade
Red #6 Ring
Right Tail Light Red Butt Splice
Starter
Fuel Pump #2
Red #6 Ring
Yel 5/16" Ring
Master
Solenoid
Fuel Pump #1
Terminal
To
Terminal
To
Pin
Panel - Key Switch Start
Red #8 Ring
Red #6 Ring
Panel - Fuel Pump
Sw
Conn.
Conn.
Pin
18AWG Rd
Red #6 Ring
Panel - Master Sw
Yel 3/16" Ring
Terminal
Terminal
Coil
Coil
Coil
Coil
Conn.
Conn.
D
A
B
C
Note
Pin towards rear of engine
when installed
Spliced with capacitor to
ground (.5 to 1 uF @ 250V+)
Spliced with 2 wires, 1 for
left & 1 for plate
Note
Pin
Panel - Fuse Block
From
From
Pin
A-Y
Color Route
Wire
Purpose
Color Route
Wire
Purpose
Maverick Main Wiring Harness
Maintenance Manual
Table 4: Maverick Wiring Diagram/Table (With ECU 1) – Also applies for fly by wire steering system
Document #:
500501
Date:
10-23-2012
ECU - EC3 J1
Rear Fuse Block
P-RExtra6
2R-P-v2W-X
P-A
16 Injector 4
17 Injector Power 18AWG Rd
22AWG
18 ECU Controller S-4C-1 Wh
44 of 47
Or
24 ECU Controller
22AWG
22 ECU Controller S-4C-2 Wh
Bl
P-A
Gr
21 ECU Controller
23 ECU Controller
P-A
Or
20 ECU Controller
P-A
P-A
P-A
Bl
19 ECU Controller
P-A
ECU - EC3 J1
P-R
15 Injector 2
ECU - EC3 J2
ECU - EC3 J2
ECU - EC3 J2
ECU - EC3 J2
ECU - EC3 J2
ECU - EC3 J2
ECU - EC3 J2
ECU - EC3 J1
P-WExtra6
Color
14 Injector 3
Wire
From
Purpose
Route
#
Male D-Sub
Male D-Sub
Male D-Sub
Male D-Sub
Male D-Sub
Male D-Sub
Male D-Sub
Red Female
Spade
Male D-Sub
Male D-Sub
Male D-Sub
Terminal
24
Dsub 25
Male
2
4
Dsub 25
Male
Dsub 25
Male
8
10
Dsub 25
Male
Dsub 25
Male
9
14
Dsub 25
Male
Dsub 25
Male
6
4
Dsub 15
Male
Dsub 15
Male
5
Pin
Dsub 15
Male
Conn.
Butt Splices
In Connector
In Connector
In Connector
Terminal
Conn.
2
1
#
#
Note - 15-Pin Female Dsub
6
is at A and 25-Pin Male is at
P
7
P
8
P
9
is at A and 25-Pin Male is at 10
P
Note - 15-Pin Female Dsub 11
P
12
P
13
ECU
Programmer/Co
Dsub 15
ntrol
Female D-Sub Female 2
ECU
Programmer/Co
Dsub 15
ntrol
ECU
Programmer/Co
Dsub 15
ntrol
ECU
Programmer/Co
Dsub 15
ntrol
ECU
Programmer/Co
Dsub 15
ntrol
ECU
Programmer/Co
Dsub 15
ntrol
1 wire from each injector into 3
Butt Splice at V to Fuse
Block
4
5
P
Pin towards front of engine
when installed
Pin towards front of engine
when installed
Pin towards rear of engine
when installed
Pin Note
ECU
Programmer/Co
Dsub 15
ntrol
4 Injectors Power
Injector 4
Signal
Injector 2
Signal
Injector 3
Signal
To
Maintenance Manual
Document #:
500501
Date:
10-23-2012
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ECU-EMS
37 Serial
Bl
P-P
P-P
20AWG
S-2C
Wh
ECU-EMS
36 Serial
P-R-U
Inlet Air Temp
34 +
20AWG Yel
P-R-U
P-S
33 Crank/Cam -
35 Inlet Air Temp - 20AWG Bk
P-S
32 Cam Sensor +
P-V-X
P-S
Bl
P-V-X
31 Crank Sensor +
30 ECU Power
20AWG
S-2C
Wh
Or
28 ECU Controller
29 ECU Power
P-A
Bl
27 ECU Controller
P-A
P-A
Route
22AWG
26 ECU Controller S-3C
Wh
Color
P-A
Wire
Gr
Purpose
25 ECU Controller
#
ECU - EC3 J2
Male D-Sub
Male D-Sub
Yellow Butt
Splice
Ground Stud on
ECU Case
ECU - EC3 J2
Male D-Sub
Male D-Sub
Male D-Sub
Male D-Sub
Male D-Sub
Male D-Sub
Male D-Sub
Male D-Sub
Male D-Sub
Male D-Sub
Terminal
ECU - EC3 J2
ECU - EC3 J2
ECU - EC3 J2
ECU - EC3 J2
ECU - EC3 J2
ECU - EC3 J2
ECU - EC3 J2
ECU - EC3 J2
ECU - EC3 J2
ECU - EC3 J2
From
6
15
Dsub 25
Male
Dsub 25
Male
Dsub 25
Male
Dsub 25
Male
13
12
17
5
Dsub 25
Male
Dsub 25
Male
19
Dsub 25
Male
25
Dsub 25
Male
20
7
Dsub 25
Male
Dsub 25
Male
23
22
Dsub 25
Male
Dsub 25
Male
Pin
Conn.
Terminal
Conn.
Pin Note
Red Female
Spade
Red Female
Spade
EMS AQM
EMS AQM
Bare Wire
Bare Wire
Left Rear of Red Male
Engine
Spade
Left Rear of Red Female
Engine
Spade
Crank & Cam
Sensor
In Connectors
Cam Sensor In Connector
Crank Sensor In Connector
Rear Fuse
Block
Rear Fuse
Block
TB4
TB4
4
10
Splice with Crank/Cam
Shields & Ground with Mass
Ground
Splice both into 1 with
extension for D-Sub Pin
On bolt side of crank sensor
On bolt side of crank sensor
ECU
Programmer/
Dsub 15
Control
Female D-Sub Female 15 P
ECU
Programmer/
Dsub 15
Control
ECU
Programmer/
Dsub 15
Control
ECU
Programmer/
Dsub 15
Control
To
Maintenance Manual
Document #:
500501
Purpose
Date:
10-23-2012
Color
46 of 47
Wh
Or
Bl
50 Steering
51 Steering
52 Steering
22AWG
S-3C
Wh
Bl
48 Steering
49 Steering
Or
47 Steering
A-Z
A-Z
A-Z
A-Z
A
A
A
22AWG3C
Wh
46 Steering
P-V-X
P-V-X
P-P
18AWG Rd
EMS AQM
43 Power
P-P
20AWG Bk
20AWG Yel
EMS AQM
42 Tach
A-P
EMS AQM
45 Ground
Gr
EMS AQM41 Display
A-P
18AWG Yel
Or
EMS AQM40 Display
A-P
A-P
Male D-Sub
Male D-Sub
Male D-Sub
Steering Board Grouped
Male D-Sub
Steering Board Program
Male D-Sub
Male D-Sub
Male D-Sub
Yellow Butt
Splice
Red 5/16" Ring
Red Female
Spade
Butt Splice
Male D-Sub
Male D-Sub
Male D-Sub
Male D-Sub
Terminal
Ground Stud on
ECU Case
Master Solenoid
Rear Fuse Block
ECU - EC3 J1 Spliced to EMS
EMS Display
EMS Display
EMS Display
EMS Display
Route From
EMS AQM
44 Voltage
Bl
22AWG
S-4C
Wh
Wire
EMS AQM39 Display
EMS AQM38 Display
#
Dsub 15
Male
Dsub 15
Male
Dsub 15
Male
Dsub 15
Male
Dsub 15
Male
Dsub 15
Male
Dsub 15
Male
Dsub 25
Male
Dsub 25
Male
Dsub 25
Male
Dsub 25
Male
Conn.
13
14
10
11
5
3
2
6
7
17
5
Pin
Steering Pot
CPC
Steering Pot
CPC
Steering Pot
CPC
Steering Pot
CPC
Programming
Connector
EMS AQM
EMS AQM
EMS AQM
EMS AQM
EMS AQM
EMS AQM
EMS AQM
EMS AQM
To
TB4
TB4
TB4
TB4
TB4
TB4
TB4
TB4
Conn.
CPC Female
CPC Female
CPC Female
CPC Female
CPC 4
CPC 4
Same as
Above
CPC 4
Dsub 9
Female D-Sub Female
Dsub 9
Female D-Sub Female
Dsub 9
Female D-Sub Female
Bare Wire
Bare Wire
Bare Wire
Bare Wire
Bare Wire
Bare Wire
Bare Wire
Bare Wire
Terminal
3
2
1
5
3
2
7
9
8
3
15
14
13
12
Grouped at A - Note Pin #
(--|diode) Grouped at A
(|--diode) Grouped at A
Leave 9-Pin hanging for
programming
programming
programming
Splice in with Mass Ground
Pin Note
Maintenance Manual
Document #:
500501
Date:
10-23-2012
Bl
16AWG Rd
16AWG Rd
16AWG Rd
16AWG Rd
58 Steering
59 Steering
60 Steering
61 Steering
62 Steering
Or
57 Steering
Male D-Sub
Male D-Sub
Bare Wire
Bare Wire
Bare Wire
Bare Wire
Steering Board Motor Side
Male D-Sub
Male D-Sub
Male D-Sub
Steering Board
Male D-Sub
Terminal
Steering Board
From
13
14
12
14
13
8
Terminal
Steering
Cylinder Left
Steering
Cylinder Left
Steering
Cylinder Left
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CPC Female
Steering
Screw Lug M2- Cylinder Right CPC Female
Steering
Screw Lug M2+ Cylinder Right CPC Female
Steering
Screw Lug M1- Cylinder Left
CPC Female
CPC Female
CPC Female
CPC Female
Steering
Cylinder Right CPC Female
Steering
Steering
To
Steering
Screw Lug M1+ Cylinder Left
Dsub 15
Male
Dsub 15
Male
Dsub 15
Male
Dsub 15
Male
Dsub 15
Male
Dsub 15
Male
Conn.
Pin
22AWG
S-3C
Wh
Bl
55 Steering
Route
CPC 9
CPC 9
CPC 9
CPC 9
CPC 9
CPC 9
CPC 9
CPC 9
CPC 9
CPC 9
Conn.
4
5
5
4
3
2
1
3
2
1
Pin
56 Steering
Or
Color
54 Steering
Wire
22AWG
S-3C
Wh
Purpose
53 Steering
#
(10K Resistor) Grouped at A
- Note Pin #
(10K Resistor) Grouped at A
- Note Pin #
Note
Maintenance Manual
Document #:
500501

Maintenance Manual

Transcription

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