Airplane Factory SLING LSA Maintenance Manual
MAINTENANCE MANUAL
THE AIRPLANE FACTORY SLING Manufacturer: THE AIRPLANE FACTORY Type of certificate: N/A Serial Number: Build year: Registration: This manual contains information to be furnished to the pilot as required by the FAA in addition to further information supplied by the manufacturer. The aircraft is to be operated and maintained in compliance with information and limitations contained herein. All sections follow the ASTM guidelines as amended from time to time.
Page | 1 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual
Record of revisions
Any revisions to this manual, except actual weighing data, must be recorded in the following table.
New or amended text in the revised pages will be indicated by a black vertical line in the left-hand margin. Revision No. and date will be shown on the right-hand side of the amended page.
Log of revisions
Revision No. Date released Chapters Approved by
Page | 2 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual Table of Contents
Introduction ...... 7 Authorizations ...... 7 1. General ...... 8 1.1. Description and General Characteristics ...... 8 1.2. Certification Basis ...... 10 1.3. Descriptive Data ...... 10 1.3.1. Airframe ...... 10 1.3.1.1. Wing ...... 10 1.3.1.2. Fuselage ...... 10 1.3.1.3. Empennage ...... 10 1.3.1.4. Landing Gear ...... 10 1.4. Systems ...... 12 1.4.1. Engine ...... 12 1.4.2. Propeller ...... 12 1.4.3. Fuel ...... 12 1.4.4. Oil system ...... 12 1.4.5. Cooling ...... 13 1.5. Weights...... 13 1.5.1. Maximum Weights ...... 13 1.5.2. Standard Weights ...... 13 1.5.3. Specific Loadings ...... 13 1.6. Instructions for Concerns Regarding Aircraft Flight Safety ...... 14 1.7. Purchasing of Spare Parts ...... 14 1.7.1. List of disposable replacement parts ...... 14 1.8. Standard Equipment ...... 14 1.8.1. Flight and Engine Instruments ...... 14 1.8.2. Warning Lights and Indicators ...... 15 1.8.3. Controls ...... 15 1.8.4. Interior ...... 15 1.8.5. Exterior ...... 15 1.8.6. Powerplant and Accessories ...... 15 2. Inspection and Servicing ...... 17 2.1. Ground Handling ...... 17 2.2. Parking and Tie down ...... 17
Page | 3 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual 2.3. Jacking ...... 17 2.4. Aircraft levelling and alignment ...... 17 2.4.1. Longitudinal levelling ...... 17 2.4.2. Transverse Levelling ...... 18 2.4.3. Control surface settings ...... 19 2.4.4. Trim-tab adjustment ...... 19 2.4.5. Aircraft alignments ...... 20 2.4.6. Datum ...... 20 2.4.7. Nominal distances ...... 20 2.5. Weighing and determination of Center of Gravity ...... 21 Determination of CG ...... 22 2.6. Corrosion Prevention ...... 23 2.7. Inspection ...... 23 2.7.1. Introduction ...... 23 2.7.2. Inspection panels ...... 24 2.7.3. Condition Inspection (100 hour / annual) ...... 25 2.7.3.1. Inspection panels and initial inspection and cleaning ...... 25 2.7.3.2. Fuselage group ...... 25 2.7.3.3. Cabin and cockpit group...... 25 2.7.3.4. Engine and cowling group ...... 25 2.7.3.5. Landing gear group ...... 26 2.7.3.6. Wing and center section assembly ...... 26 2.7.3.7. Empennage assembly ...... 26 2.7.3.8. Propeller group ...... 26 2.7.3.9. Radio group ...... 27 2.7.3.10. Optional equipment ...... 27 2.8. Lubrication ...... 27 2.8.1. Introduction ...... 27 2.8.2. Lubrication points and intervals ...... 27 2.9. Servicing ...... 27 2.9.1. Service Bulletins ...... 27 2.9.2. Daily servicing ...... 28 2.9.3. As needed ...... 28 2.9.4. Every 50 hours servicing ...... 28 2.9.5. Every 100 hours servicing ...... 28 3. Airframe ...... 30 3.1. The airframe consists of the following main groups as shown in figure 3.1 : ...... 30
Page | 4 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual 3.2. Wing ...... 30 3.2.1. Main wing section ...... 30 3.2.2. Ailerons and Flaps ...... 31 3.2.3. Installing and re-installing the wing ...... 31 3.2.4. Flap control ...... 33 3.2.5. Aileron control ...... 34 3.3. Empennage ...... 35 3.3.1. Horizontal Tail ...... 35 3.3.2. Elevator Control System...... 37 3.3.3. Vertical Tail ...... 38 3.4. Fuselage ...... 40 3.4.1. Rear fuselage ...... 40 3.4.2. Center and forward fuselage ...... 41 3.5. Landing gear ...... 43 3.5.1. Main gear ...... 43 3.5.2. Removal of Main Gear ...... 44 3.5.3. Removal of cup-bearing from main gear wheel ...... 45 3.5.4. Nosegear ...... 45 3.5.5. Removal of nose wheel ...... 46 4. Powerplant ...... 48 4.1. Cowling ...... 48 4.2. Engine Main Features ...... 49 4.3. General Servicing Procedures ...... 50 4.3.1. Idle speed synchronization ...... 50 4.3.2. Ordinary servicing ...... 50 4.3.3. Propeller ...... 51 4.3.3.1. Propeller removal ...... 51 4.3.3.2. Propeller installation ...... 51 4.3.4. Periodic inspection ...... 52 5. Systems ...... 53 5.1. Fuel System ...... 53 5.2. Instruments ...... 54 5.2.1. Engine Instrumentation (reflected on EFIS screen) ...... 56 5.3. Pitot and Static System ...... 56 5.4. Exhaust Manifolds ...... 57 5.4.1. Cabin heat and cooling...... 58 5.5. Brake System ...... 58
Page | 5 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual 5.5.1. Draining and replacing brake fluid ...... 58 6. Electrical System ...... 60 6.1. Battery ...... 62 6.1.1. Battery Removal ...... 62 6.1.2. Battery Check ...... 63 6.1.3. Battery Installation ...... 63 6.1.4. Internal AC Generator ...... 63 6.1.5. Regulator/Rectifier ...... 63 6.2. Exterior Lighting ...... 64 6.2.1. Positions Lights (if installed) ...... 64 6.2.2. Landing Light ...... 64 6.2.3. Strobe Light ...... 64 6.3. Flap System ...... 64 7. Markings and Placards – see POH for examples ...... 65 7.1. Magnetic compass compensation table ...... 65 7.2. Parking brake valve ...... 65 7.3. Engine throttle ...... 65 7.4. Cabin heat ...... 65 7.5. Trim switch ...... 65 7.6. Fuses ...... 65 7.7. Flaps ...... 65 7.8. Generator, Master, Starter ...... 66 7.9. Choke ...... 66 7.10. Generator Light ...... 66 7.11. Fuel selector valves ...... 66 7.12. Electric fuel pump (emergency) ...... 66 7.13. Baggage compartment ...... 66 7.14. Fuel tanks ...... 66 7.15. Oil tank reservoir ...... 66 7.16. Cooling system overflow tank ...... 67 7.17. Brake oil reservoir ...... 67 7.18. Tire pressures ...... 67 7.19. Identification plate ...... 67 7.20. Limitation Placards ...... 67 8. Structural Repair ...... 68 9. Painting & Coatings ...... 69 10. Feedback Form ...... 70
Page | 6 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual Introduction Before maintaining the Airplane Factory Sling we recommend careful reading of this Maintenance Manual, the Pilot’s Operating Handbook and the engine and propeller maintenance manuals. A thorough knowledge of the aircraft, its qualities and limitations will enable you to operate the machine with greater safety. The Airplane Factory Sling is a robust aircraft with a design that is intended to achieve not only excellent flying qualities, but also high reliability and ease of maintenance. This manual sets out the prescribed maintenance procedures for the aircraft. Compliance with the provisions of this manual will ensure that your Sling is maintained to the highest standard and provides you with reliable service. Information contained herein is based on available data at the time of publication. Any changes required will be captured in appropriate revisions and this manual should be updated with such revisions as and when required. This manual describes correct servicing of parts manufactured by The Airplane Factory and, in subordinate measure, of those components used in the aircraft but which are manufactured by other suppliers. For more complete information on such components it is necessary to refer to the component’s manufacturer’s manual.
Authorizations Please ensure that any person performing maintenance of any kind on the aircraft or any component thereof is authorized to do so in terms of the law. This is the responsibility of the aircraft owner and any person who is to perform any maintenance on the aircraft.
For additional information or explanations contact: The Airplane Factory Tel: +27 11 024 4304 Fax: +27 86 632 4493 Email : [email protected] Web : www.airplanefactory.co.za
The Airplane Factory, Inc. Tel : 310-721-9190 Email : [email protected] Web : www.airplanefactory.com
Page | 7 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual SECTION 1 GENERAL
1. General
1.1. Description and General Characteristics The Airplane Factory Sling is a two seat, single engine, low wing, metal structure monoplane with tricycle landing gear and steerable nose wheel. It is an ASTM F2245 compliant airplane designed to be flown by sport pilot rated pilots as well as higher rated pilots. This aircraft is designed and built in South Africa and as such, was built using the metric system. Therefore, the primary numbers are in metric and the US conversion is in parenthesis for your information. Figure 1 shows a three View drawing of the aircraft while tables below report main technical features and dimensions.
THREE-VIEW DRAWING
Page | 8 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual
Page | 9 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual 1.2. Certification Basis This aircraft complies with ASTM F2245, F2279, and F2295 and associated ASTM Light Sport Aircraft Standards.
1.3. Descriptive Data
1.3.1. Airframe
1.3.1.1. Wing
Wing span 30.1 ft. (9.165 m)
Wing surface 127.5 ft2 (11.845 m2)
Wing loading (600kg / 1320 lbs) 10.37 lbs/ft2 (50.654 kg/m2)
Aspect ratio 7.04
Taper ratio 0.746
Dihedral 5°
Washout 2°
1.3.1.2. Fuselage
Fuselage length 18.93 ft. (5.77 m)
Aircraft length 21.9 ft. (6.675 m)
Cockpit width 3.67 ft. (1.12 m)
Height overall 8.2 ft. (2.5 m)
1.3.1.3. Empennage
Horizontal stabiliser span 9.27 ft. (2.825 m)
Vertical tail span 4.82 ft. (1.47 m)
1.3.1.4. Landing Gear
Wheel track 6.4 ft. (1.95 m)
Page | 10 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual
Wheel base 4.63 ft. (1.41 m)
Main wheel tires : 15 X 6.00 - 6, 4 ply (22 psi (1.5 bar))
Nose gear tire : 5.00 – 5, 4 ply (20 psi (1.4 bar))
Main Gear Wheel & Brakes Matco wheels with hydraulic disc brakes
Page | 11 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual
1.4. Systems
1.4.1. Engine
Manufacturer Bombardier Rotax GmbH
Model 912 ULS
Certification basis ASTM Light Sport Aircraft
Type 4 cylinder, horizontally-opposed piston engine with 1,352 cc displacement
Maximum rating 98.5 hp at 5800 rpm
1.4.2. Propeller
Manufacturer Warp Drive
Model 70 inch 3 Blade composite ground adjustable
Number of blades 3
Diameter 70 inch (1.77 m)
Type 70 inch, right hand, composite, 3 blade, tapered tip
1.4.3. Fuel
Fuel grade Min. AKI 91 (RON 95) Auto Fuel or Avgas 100LL
Fuel tanks Wing tanks integrated within each wing’s leading edge
Capacity of wing tank 19.8 Gallons (75 Liters)
Total usable fuel 19.3 Gallons (73 Liters)
1.4.4. Oil system
Oil system Forced, with external oil reservoir
Page | 12 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual
Oil Automotive grade API “SF” of “SG” type oil, preferably synthetic or semi synthetic.
Oil capacity 3.7 Quarts (3.5 Liters)
1.4.5. Cooling
Cooling capacity 3.2 Quarts (3 Liters)
Coolant Antifreeze liquid (type BASF Glysanthin anticorrosion or equivalent) and distilled water mixture, 75:25
1.5. Weights
1.5.1. Maximum Weights
Maximum Takeoff weight 1,320 Lbs. (600 kg)
Maximum Landing Weight 1,320 Lbs. (600 kg)
Maximum Baggage Weight 77 Lbs. (35 kg)
1.5.2. Standard Weights
Standard empty weight 794 Lbs. (360 kg)
Maximum payload weight (useful 526 Lbs. (240 kg) load)
1.5.3. Specific Loadings
Wing loading 10.37 lbs/ft2 (50.65 kg/m2)
Power loading 13.23 lbs/hp (6 kg/hp)
NOTE Standard weights are estimates based on standard equipment.
Page | 13 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual 1.6. Instructions for Concerns Regarding Aircraft Flight Safety If any person should have any concerns regarding the safety of an Airplane Factory Sling LSA for flight, these should be emailed to [email protected]. The following information should be included in the email:
. Aircraft Make, Model, Serial Number . Engine Make, Model, Serial Number . Date of last inspection . Total Time on airframe and engine . Description of the un-airworthy items found . Owner of Aircraft
Alternatively, write to: The Airplane Factory, Inc., 3401 Airport Drive, Torrance, CA, 90505
1.7. Purchasing of Spare Parts Spare parts can be ordered from Airplane Factory at www.airplanefactory.com or send an email to [email protected]. Also, parts can be ordered through your local dealer.
1.7.1. List of disposable replacement parts
Air filter K & N Fuel filter Mesh filter, plastic 90 degrees Oil filter Rotax PN 924420 Nose wheel tire 5.00 – 5, 4 ply Main gear tire 15.00 x 6.00 – 6, 6 ply Oil See the Rotax Maintenance Manual Coolant See the Rotax Maintenance Manual Spark Plugs See the Rotax Maintenance Manual
1.8. Standard Equipment
1.8.1. Flight and Engine Instruments
MGL Voyager EFIS incorporating – Moving map GPS, Auto-pilot operating system, Airspeed Indicator, Altimeter, Vertical Speed Indicator, Compass, Tachometer, Oil Pressure, Fuel Pressure, Fuel Flow, Oil Temperature, Cylinder Head Temperature (x2), Exhaust Gas Temperature (x4), Hour Meter, Fuel Quantity, Volt Meter, Trim Indicator, Flap Indicator, G Meter, Artificial Horizon, Turn and Slip indicators, Time, Flight Time, Time since start-up,
Page | 14 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual Range, Endurance. MGL V6 panel mount aircraft radio incorporating an Intercom system. 2 1/4 inch analogue instruments as follows – Airspeed, Altimeter, Ball Type Slip Indicator, Panel Mount Compass
1.8.2. Warning Lights and Indicators
Generator Charge Warning Light, MGL EFIS warning light
1.8.3. Controls
Dual Stick Flight Controls, Dual Rudder Pedals, Center position Throttle, Engine Choke, Electric Flaps, Center brake lever operating Hydraulic Disc Brakes with Parking Brake, Fuel Selector Valve, Fuel Cross Feed Shut-off Valve, Direct Nose Wheel Steering.
1.8.4. Interior
Adjustable Pilot and Co-pilot Seats, Adjustable rudder/steering pedals, Adjustable Cabin Air Ventilators and heater, Carbon and fibreglass Roll Cage, 12V Power Outlet, Anodized aluminum Instrument Panel.
1.8.5. Exterior
All Aluminum structure, Landing Light, Strobe Light, Fixed Landing Gear, Nose Gear Strut Fairing, Nose and Main Wheel Fairings
1.8.6. Powerplant and Accessories
Rotax 912 ULS Engine, Output of 100HP, Oil Capacity of 3.7 Q (3.5 L), Coolant Capacity of 3.2 Q (3 L), Propeller Diameter of 70 in (1.7 m), Propeller Type is 3 Blade Ground adjustable Composite Warp Drive, Gear Reduction of 1:2.43
Page | 15 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual
Page | 16 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual SECTION 2 INSPECTION AND SERVICING
2. Inspection and Servicing
2.1. Ground Handling Move the aircraft on ground by pulling on the propeller blades close to hub. A specially made tow bar can be attached to the nose wheel axle ends. Aircraft can be steered using the rudder pedals or, for sharp turns, by lowering the tail to raise nose wheel off the ground. In this case press down on the rear upper fuselage and horizontal stabiliser (place your hands above the main spar - where the rivets are). Avoid dragging the nose wheel sideways and do not attempt to counter any movement of the aircraft by handling it by its wing tips.
WARNING As a general rule, apply force to aircraft structure only on main structural elements such as frames, ribs or spars.
2.2. Parking and Tie down It is recommended that chocks are used when parking outdoors or in a hanger. If chocks are not available, use the parking brake. If possible, park the airplane facing into the wind. Tie down at outer wing and rear fuselage tie down points to ground anchors. In severe weather and high wind conditions, aircraft tie-down is essential and in such conditions it is also preferable to tie down the nose wheel from the engine mount near the nose wheel strut attachment point.
2.3. Jacking Following removal of the main wheel spats, the aircraft can be jacked from under the ends of the main wheel struts just inside of the wheels. Ensure that steps are taken to locate the jack sturdily under the bottom edge of the wheel strut so as to prevent slippage. Given the light empty weight of the aircraft, lifting one of the main wheels can be easily accomplished by lifting a wing. If it is necessary to lift the nose gear, the engine cowling should be removed and the aircraft lifted using the engine mount as the attachment point. The nose wheel can also easily be lifted by pressing down on the rear fuselage (ordinarily on the dorsal fin) and the horizontal stabiliser above the main spar.
2.4. Aircraft levelling and alignment Occasional levelling of aircraft may be necessary to verify proper wing incidence and/or dihedral or for exact CG location.
2.4.1. Longitudinal levelling To check the longitudinal levelling proceed as follows. See figure Error! Reference source not ound. below: Open the canopy. Place a spirit, water or electronic level on the top of the canopy slider frames adjacent to the pilot or passenger seat.
Page | 17 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual Adjust the aircraft’s tilt through shims placed under wheels or by regulating tire pressure until a level reading is achieved on the instrument used.
Figure Error! Reference source not found.
2.4.2. Transverse Levelling To check the transverse levelling proceed as follows. See figure Error! Reference source not found. elow: Open the canopy. Place a spirit, water or electronic level across the top of the canopy slider frames from one side to the other and at right angles to the longitudinal axis of the aircraft. Adjust the aircraft’s tilt through shims placed under wheels or by regulating tire pressure until a level reading is obtained on the instrument used.
Page | 18 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual
Figure Error! Reference source not found.
2.4.3. Control surface settings Adjustment of control surfaces should be set as set out in the table below
AILERONS (starting from the tips Up 22° Down 22° ± 3° lined up with the wing tips)
ELEVATOR (starting from the horn Up 28° Down 20° ± 2° lined up with the leading edge)
TRIM (starting flush with elevator) Up 15° Down 20° ± 3°
RUDDER Left 25° Right 25° ± 2°
FLAPS (max. travel) 0° Down 32° ± 3°
CONTROL CABLE TENSION (when rudder straight) 15 N ± 3N
2.4.4. Trim-tab adjustment The following procedure lists the operation to be carried out to adjust the trim tab limits: Turn the Master switch ON. Trim to maximum pitch-up. Adjust thread of hinged control rod until tab is deflected downwards 15° relative to the elevator upper surface (use a protractor or measure downward displacement of trailing edge).
Page | 19 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual Tighten lock nut for adjustment thread and fasten connecting pin of control rod to trim-tab.
2.4.5. Aircraft alignments
Figure Error! Reference source not found.
2.4.6. Datum A – On the wing upper surface, the outside edge of the wing skins where trailing edge of the the leading edge skin overlays the trailing edge skin. (See figure Error! Reference source not found.). B – The 12 o’clock position on the front face of the propeller flange (ie: the top of the front face of the propeller flange. To get access it is necessary to remove the engine’s upper cowling. C – On the elevator upper surface, the outside rear corner of the horizontal stabiliser upper skin. (See figure Error! Reference source not found.). D – On the vertical stabiliser skin is the upper/aft rivet. It is the highest rivet shared between the skin and the rear spar flanges. (See figure Error! Reference source not found.).
2.4.7. Nominal distances The aim of the alignment control is mainly to compare the measures taken on both sides and to check if the difference between them, if any, is within the tolerances reported below.
Datum Nominal distances (mm)
Page | 20 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual
A – B 4 617mm (±20mm)
A – C 4 845mm (±20mm)
C – D 1 696mm (±20mm)
2.5. Weighing and determination of Center of Gravity When weighing the aircraft to determine the longitudinal center of gravity of the aircraft use the following guidelines: Carry out weighing procedure inside hangar so that there is no influence from wind Remove any unnecessary objects inadvertently left on board aircraft Make sure that all required paperwork is on board: (e.g. – Pilots Operating Handbook, Authority to Fly etc) Drain fuel Align nose wheel Make sure that the engine oil, hydraulic fluids and coolants at operating levels Move seats to rearmost position Flaps retracted (0°) Ailerons in neutral position, elevator in down position Position calibrated scales (min. capacity, 550 lbs / 250kg) under each tire Record weights of individual scales Calculate empty weight
Page | 21 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual
Determination of CG
Use the following table to determine the C.G. location and aircraft’s moment
Item Weight Arm Moment Lbs. / Kg Inches / mm (weight x arm)
Right Main Wheel WR = LR = -77.13” MR = WR x LR (-1959 mm)
Left Main Wheel WL = LL = -77.13” ML = WL x LL
(-1959 mm)
Nose Wheel WN = LN = -21.57” MN = WN x LN (-548 mm)
Computed CG Total aircraft Total aircraft moment empty weigh (WE) = = MR + ML + MN W + WL + W
Aircraft Aircraft EmptyCG R N
Page | 22 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual
Center of Gravity
CG = Total aircraft moment Total aircraft weight
Center of gravity reflected as a percentage of the Mean Aerodynamic Chord
%MAC = (Total aircraft moment + 1366) x 100 % Total aircraft weight (- 1 399)
2.6. Corrosion Prevention It is important to keep the aircraft clean and to remove any collection of corrosive agents such as water, anti-freeze, oil, grease, dregs and other foreign matter. To avoid damage to the finish, do not use polishing detergents. Original or equivalent corrosion prevention, if used, must be re-applied after any alteration or repair. If any trace of corrosion is detected it should be removed as soon as possible and part should be treated immediately to prevent further corrosion. (a) For steel parts, with the exception of highly stressed components or stainless steel, it is possible to use abrasives, power brushes, steel brushes if operated manually and steel wool. (b) For aluminium parts, treatment consists in mechanically removing as much as possible of any corrosion by-products, applying corrosion inhibitor and replacing any original finish. Steel wool, emery or steel brushes (unless stainless steel) along with other highly abrasive material should not be used since steel or emery particles become embedded in the softer material causing corrosion. 6061 T6 Aluminium, of which the aircraft is constructed is reasonably corrosion resistant and accordingly unlikely to corrode substantially. After cleaning surface corrosion, parts must be treated with an anti-corrosion finish prepared as follows: 4 litre solution containing 10% chromic acid with 20 drops of battery electrolyte Accurate brushing with a sturdy fibre brush will rid most of the corrosion and ensure that the anti- corrosion agent will penetrate completely in the cracks Leave the chromic acid solution on the part for at least five minutes and then remove excess with water or a damp cloth. Apply protective finish the same day in which treatment begins.
2.7. Inspection
2.7.1. Introduction The Airplane Factory considers the inspection schedule outlined below compulsory for the safe operation of the airframe and of the systems over an extended period of time. Described servicing requirements pertain to operation in non-extreme climatic conditions. For the Rotax 912 ULS engine, unless otherwise stated in the present manual, it is compulsory to adhere to maintenance requirements as reported in the Rotax Engine’s Operator’s Manual. For the Warp Drive propeller, refer to manufacturer’s maintenance manual.
The airframe and systems inspection schedule is as follows:
Page | 23 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual Inspections for airworthiness before first flight of day as specified in Pilot’s Operating Handbook. Periodic condition inspections at every 100 hours Special inspections, added to normal periodic inspections Singular inspection, when aircraft has been exposed to conditions that may have damaged one or more of its components If aircraft is rarely used, a “100 hour inspection” must be performed annually Replacement of parts subject to usage limitations are specified in par. 3.14. Inspections and checks, unless specifically indicated, apply to the following: o Structures in general : Condition of panel covers, ribs, frames, stringers etc., absence of cracks, deformation, rivet slackening, corrosion and any other apparent sign of damage o Moving parts : Lubrication, security of attachment, safetying of bolts, absence of excessive play, proper adjustment, proper travel, condition of attachments and hinges, absence of corrosion, deformation, rivet slackening, cleanliness o Fluid lines and hoses : Absence of leaks, cracks, dents, chafing, proper radius, deterioration o Bolts and attachments: Proper tightening and safetying, absence of cracks or nicks, damage to thread, wear and excessive play.
2.7.2. Inspection panels Inspection points that are not in plain view may be accessed through specific inspection holes and inspection hatches and/or removal of panels or fairings as detailed below: . Inspection hatches on wing underside – access to aileron bell-crank and flap torque tube and pushrod. . Covers at wing underside to fuselage underside connection point – access to engine fuel and return line connections to tank, tank level sender and sender-wiring connectors and flap and aileron control pass-throughs, main spar, rear spar connection. . Small round tail-cone side holes – access to elevator control horn and pushrod end. . Vertical and horizontal tail nacelle/fairing – access to vertical and horizontal tail mounting and connections. . Elevator left lower inspection hatch – access to trim tab motor and pushrod. . Aft cabin bulkhead and baggage compartment floor – inspection of aft fuselage section and attachments; inspection of elevator control system and of cable pulleys for rudder control; access to autopilot elevator servo. . Cabin longitudinal divider side inspection hatches – access to fuel lines, rudder cables, throttle cables, and the fuel valves. . Instrument panel cover – access to aircraft instrumentation. . Engine cowling – access to engine and related systems, access to forward of firewall components of electrical system, access to nose gear strut and steering assembly mechanism. . Propeller spinner – access to propeller hub.
Page | 24 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual 2.7.3. Condition Inspection (100 hour / annual)
Type of Maintenance Line
Level of Certification Required A&P
Parts Required None
Tools Required Standard Mechanic Toolset
2.7.3.1. Inspection panels and initial inspection and cleaning Each person performing an annual or 100-hour inspection shall, before that inspection: (a) Remove or open all necessary inspection plates, access doors, fairings and cowlings. (b) Clean the aircraft and aircraft engine after initial visual inspection for oil, exhaust or other leaks.
2.7.3.2. Fuselage group (c) Check skin for deterioration, distortion, other evidence of failure, and defective or insecure attachment of fittings. (d) Check systems and components for improper installation, apparent defects and unsatisfactory operation.
2.7.3.3. Cabin and cockpit group (a) Check for cleanliness and for loose equipment that might foul the controls. (b) Check the seats and safety belts for condition and/or any defects. (c) Check canopy and windows for deterioration and breakage. (d) Check instruments for poor condition, mounting, marking, and (where applicable) improper operation. (e) Check flight and engine controls for improper issues. (f) Check all systems for improper installation, poor general condition, apparent and obvious defects and insecurity of attachment.
2.7.3.4. Engine and cowling group (a) Check engine section for visual evidence of excessive oil, fuel or hydraulic leaks, and sources of such leaks. (b) Check studs and nuts for improper torque and obvious defects. (c) Check entire engine mount for cracks, looseness of mounting, and looseness of engine to mount. (d) Check flexible vibration dampeners for poor condition and deterioration. (e) Check engine controls for defects, improper travel and improper safetying. (f) Check lines, hoses and clamps for leaks, improper condition and looseness. (g) Check exhaust stacks for cracks, defects and improper attachment.
Page | 25 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual (h) Check accessories for apparent defects in security of mounting. (i) Check all systems for improper installation, poor general condition, defects and insecure attachment. (j) Check cowling for cracks and defects.
2.7.3.5. Landing gear group (a) Check all units for poor condition and insecurity of attachment. (b) Check shock absorbing devices for damage. (c) Check linkages, trusses and members for undue or excessive wear fatigue and distortion. (d) Check hydraulic lines for leakage. (e) Check electrical system for change and improper operation of switches. (f) Check wheels for cracks, defects and condition of bearings. (g) Check tires for wear and cuts. (h) Check brakes for improper adjustment.
2.7.3.6. Wing and center section assembly Check for: (a) Poor general condition. (b) Skin deterioration. (c) Distortion. (d) Evidence of failure. (e) Insecurity of attachment.
2.7.3.7. Empennage assembly Inspect all components and systems for: (a) General condition. (b) Skin deterioration. (c) Distortion. (d) Evidence of failure. (e) Insecure attachment. (f) Improper component installation. (g) Improper component operation.
2.7.3.8. Propeller group Check propeller assembly for: (a) Cracks (b) Nicks (c) Bolts for improper torque and lack of safetying.
Page | 26 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual 2.7.3.9. Radio group (a) Check radio and electronic equipment for improper installation and insecure mounting. (b) Check wiring and conduits for improper routing, insecure mounting and obvious defects. (c) Check bonding and shielding for improper installation and poor condition. (d) Check antenna/s for poor condition, insecure mounting and improper operation.
2.7.3.10. Optional equipment Check all optional equipment for proper operation.
2.8. Lubrication
2.8.1. Introduction Periodic lubrication of moving parts ensures proper operation and extends parts’ lives considerably. Lubrication type, points and intervals are indicated below. Avoid excessive lubrication as this may cause external surfaces of hinges and bearing to collect dirt and dust. If part is not lubricated using a grease gun, grease part by hand removing excess. To grease main gear wheel bearings, first remove thrust bearings from wheel hubs, then clean surface using solvent, apply grease and re-assemble. NOTE Use grease type MIL-G-3278 or equivalent (eg-. Mobil grease 27 Synthetic aviation grease)
2.8.2. Lubrication points and intervals
Thoroughly clean and then grease canopy’s sliding mechanism. Grease the remaining components reflected in the list at 100 hour or one yearly intervals, whichever comes first.
1 Rudder and pedal control cable terminals 2 Elevator pushrod in the centre where the guide is 3 Trim tab hinge (Q20) 4 Aileron pushrod guide in the centre of the wing 5 Flap torque tube supports (fine lubricant such as Q20) 6 Flap actuator ends 7 Rudder pedal supports (Q20) 8 Control stick lever and supports (Q20) 9 Nose gear support blocks 10 Main wheel bearings
2.9. Servicing
2.9.1. Service Bulletins
Page | 27 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual In addition to the service information contained herein, the following service bulletins should be complied with at all times-
No. Description Publication Validity Date
2.9.2. Daily servicing The following service requirements should be met on each day that the aircraft is operated - Pitot and static ports – Check for obstructions Oil – Check oil level Coolant – Check coolant level Fuel strainers – Drain fuel from strainers and check for any water and/or sediment Fuel tank vents – Check for obstruction
2.9.3. As needed The following service requirements should be met on an as required basis - Tires – Check condition and maintain proper tire pressure. 2 bar (29 psi)in all 3 tyres
2.9.4. Every 50 hours servicing The following service requirements should be performed after each 50 hours of flying or on an annual basis, whichever is the sooner - Carburettor flanges – Visually inspect the rubber flanges connecting the carburettors to the engine intake manifolds for cracks or hardening and replace if necessary.
2.9.5. Every 100 hours servicing The following service requirements should be performed after each 100 hours of flying or on an annual basis, whichever is the sooner -
Page | 28 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual Battery – Check for leakage, secure mounting, proper charge, connections and general condition Engine oil – Change engine oil and replace filter element (refer to Maintenance Manual of Rotax 912 ULS. Note – initial oil change is to take place after 25 hours. Note: If this engine is run on Avgas 100 LL then oil change interval is 50 hours. Refer to Rotax maintenance manual for complete details. Engine – perform all engine service requirements in accordance with the provisions of the Maintenance Manual for the Rotax 912 ULS. Brake fluid – Check level of brake fluid in the fluid resovoir located on the left upper side of the engine side of the firewall and top up as required. Fuel filter and lines - Visually inspect all of the fuel lines. Remove and visually inspect the fuel filter. Replace the fuel filter if necessary. Air filter – remove and clean or replace air filter, as may be appropriate. (Repeat this more often in particularly dusty conditions). Propeller – Check attachment bolts for integrity and torque (18Nm) and safety’ing (initially after 25 hours). Comply with the requirements of the propeller maintenance manual Ailerons, flaps, rudder and elevator – check visually for condition of hinges and smooth operation. Lubricate as required. Tires – Check condition and maintain proper tire pressure 2 bars/29psi on all three wheels. Inspection for condition – comply in full with the requirements of the 100 hour / annual inspection and correct all faults or failings.
Page | 29 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual SECTION 3 AIRFRAME
3. Airframe
3.1. The airframe consists of the following main groups as shown in figure 3.1 : Wings Fuselage Empennage Landing gear
Figure 3.1
3.2. Wing
3.2.1. Main wing section The wing main spar comprises a 1 mm web with caps solid riveted to the top and bottom to form a symmetric composite “I-beam”, as illustrated in Fig. 3.2 below. The caps are made from 3.2mm sheet material bent into angles. The rear spar comprises an aluminum C channel with the flanges facing forward.
Each wing is connected to the fuselage by means of eleven bolts (ten on the front spar, one on the rear). Wing attachment points and structure appear from figure 3.2.1 below. An integrated fuel tank is a part of the wing’s leading edge. The underside of the wing has two inspection panels, one to access the aileron
Page | 30 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual bell-crank and the other the flap bell-crank. There are also fore and aft inspection panels on the underside of the wing fuselage connection point. On the upper side of each tank there are fuel filler caps. Fuel tanks vent by means of a tube exiting the underside of the wing on the outer tank rib immediately in front of the main spar. Aileron and flap hinges comprise ¼ inch sealed ball bearings pressed into shaped 4.8 mm aluminum plates. Wing tips are moulded epoxy resin reinforced with glass fiber.
Figure 3.2.1
3.2.2. Ailerons and Flaps The aileron comprises a conventional stressed-skin semi-monocoque structure comprised of ribs and riveted sheet metal skin without a spar. An aluminum tube running inside the leading edge serves as a balancing weight. Flaps have the same structural arrangement as the ailerons save for the exclusion of the aluminum tubing in the leading edge. In each case hinge brackets comprise appropriately bent 2.4 mm (outside hinges) or 4.8 mm (inside bracket with bearing) aluminum.
3.2.3. Installing and re-installing the wing
Type of Maintenance Line
Level of Certification Required A&P or LSRM-M
Page | 31 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual
Parts Required
Tools Required
Drain fuel tank from the drain valve, remembering to shut off the cross feed valve in advance. (If the tank is nearly full approximately 10.57 Gallons (40 liters) can be siphoned through the filler cap hole). Close the opposite side tank fuel circuit. Remove all of the wing to fuselage fairings. Remove the seat on the side of the wing that is being removed. Remove the fuel tank outlet inspection panel from under the wing. Unfasten and remove the fuel hose from the tank’s outlet and also the return line. Place a temporary cap on the fuel line to prevent spillage. For the left wing remove the plastic Pitot tube tubes. Disconnect the fuel quantity sensor, navigation, taxi and landing light wiring. Disconnect flap torsion bar connector from inside the fuselage (1) by removing the four AN4 bolts. Disconnect the aileron pushrod inside the fuselage by removing the AN4 bolt from the rod end bearing (2). While supporting the wing, remove all the main spar wing bolts save for the outside bolt in the top cap and the outside bolt in the bottom cap. Remove the locknuts from the remaining two bolts in the main spar and from the bolt in the rear spar. While supporting the wing remove the 3 remaining bolts and then carefully remove the wing by pulling the main spar directly out of the center spar. Reverse above procedure for re-installation paying close attention to tighten main spar bolts to the recommended value (35 Nm-1 for the AN6 and 25 Nm-1 for the AN5 nuts).
Page | 32 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual
Figure 3.2.3
3.2.4. Flap control The flap control system is push-pull type with a linking torsion bar. The arrangement appears from figure 3.2.4 below.
Page | 33 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual
Figure 3.2.4
3.2.5. Aileron control The aileron control system uses push-pull rods and bell-cranks throughout. The arrangement appears from figure 3.2.5 below.
Page | 34 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual
. Figure 3.2.5
Type of Maintenance Line
Level of Certification Required A&P or LSRM-M
Parts Required None
Tools Required Standard Mechanics Toolset
To remove aileron, disconnect one end of push-pull rod and remove bolts from hinges. Reverse above procedure to re-install aileron, ensuring that, with stick vertical, the aileron’s trailing edge is aligned with wing’s trailing edge. Through access panels located on wing’s bottom, check that the bell-crank lever is in neutral position, (i.e. the inside arm at right angel with spar axis).
Removal of the flaps uses the same procedure as that applicable to the removal of the ailerons. Check for alignment and travels upon refitting.
3.3. Empennage
3.3.1. Horizontal Tail The horizontal stabilizer consists of a conventional semi-monocoque all-metal light alloy structure with front and rear spars. The arrangement appears from figure 3.3.1. The elevator has a similar structure, though with only a front spar. Bearings are again, as with all other control surface bearings, ¼ inch
Page | 35 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual sealed bearings. Elevator horns carry through to the leading edge the horizontal tail and the elevator tips comprise shaped epoxy resin and glass fiber composite. The arrangement of the elevator appears from figure 3.3.1
Figure 3.3.1
Type of Maintenance Line
Level of Certification Required A&P or LSRM-M
Parts Required None
Tools Required Standard Mechanics Toolset
Elevator mass balancing (10) is placed in the two horn leading edges. To inspect this part it is necessary to remove the composite tip. The elevator cannot be removed without the prior removal of the vertical stabilizer (see below). Prior to removal of the elevator the elevator push-rod must be freed from the elevator control horn which is located inside the rear fuselage tail-cone. The rod end bearing is accessed through the two small round access holes on the left and right sides of the rear fuselage tail-cone. The elevator is removed by way of removing the bolts from the 5 hinges while supporting the elevator. The elevator can then be pulled free of the horizontal stabilizer.
Page | 36 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual 3.3.2. Elevator Control System The elevator control system is push-pull type (see figure 3.3.2) and is controlled from the cabin via the control sticks. Control is transmitted through a push-pull rod and bell-crank arrangement which appears from Figure 3.3.2 below. All significant transmission elements such as bell-cranks, pushrods, supports and hinges can be easily accessed and inspected.
Figure 3.3.2
NOTE If unusual tolerance is found along transmission, replace parts displaying excessive wear.
Page | 37 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual 3.3.3. Vertical Tail The vertical stabilizer and rudder consists of all-metal light alloy structures (figure 3.3.3a). The rudder horn carries to the leading edge and has a composite tip on which navigation lights and aerial may be affixed. The vertical stabilizer consists of a twin spar with wrap-around stressed skin panelling. An attachment plate secures the vertical stabilizer’s front spar to a bracket attached to the penultimate tail-cone rib. The rudder consists of a spar with formed sheet metal rear and nose ribs and sheet- metal skin. The rudder rotates via three hinges, each with a ¼ inch bearing. Rudder control is effected by steel cable attached to a control horn on the bottom edge of the rudder and running (with a cross- over), to two control horns attached to the rudder pedal axle. Control stops limit movement of the pedal to cable attachment horns.
Figure 3.3.3a
Type of Maintenance Line
Level of Certification Required A&P or LSRM-M
Parts Required None
Page | 38 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual
Tools Required Standard Mechanics Toolset
Rudder mass balancing is placed under the leading edge of the rudder horn on the top rudder rib. To inspect this part it is necessary to remove the composite tip. To remove the rudder, disconnect the control cables from the control horn, loosen and remove the three hinge bolts while supporting the rudder and thereafter remove it by pulling it gently backwards, taking care to protect the horn. Control system layout (Figure 3.3.3b) is two steel cables attached to the rudder control horn at the foot of the rudder. The cables terminate on two rudder pedal control horns. These horns are in turn attached to two adjustable push-pull rods which are attached to a control horn on the nose wheel strut. Rudder pedals can be adjusted backwards and forwards to set positions on tubular slides with a bolt and lock- nut to fix them. At the front of the rear fuselage the rudder cables are attached to a spring loading device which provides a centering force on the rudder. This force can be adjusted. Cable tension must be checked periodically and adjusted to proper value using the turnbuckles (Tension = 20daN ± 2). Pulley condition and their smooth operation must also be checked. To access certain sections of the cable it may be necessary to remove cabin’s central tunnel. For speedier operation remove seats from railings.
Page | 39 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual
Figure 3.3.3b
3.4. Fuselage
3.4.1. Rear fuselage The aft part of the fuselage (tail-cone) is an aluminum alloy semi-monocoque structure which appears from figure 3.4. A number of stringers carry through to the center fuselage for strength and rigidity. At the tail section supporting brackets for the vertical and horizontal stabilizers are attached to the two rear ribs. A cross brace with guide for the elevator push-pull rod is riveted across rib 4 and the forward portion of the rear fuselage contains a luggage packing space with an aluminum skin floor supported by stringers.
Page | 40 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual
Figure 3.4.1
3.4.2. Center and forward fuselage The front part of the fuselage is also made up of a light-alloy semi-monocoque structure with skins on the inside and outside of supporting stringers and ribs. The arrangement appears from figure 3.4.2a. The diagram shows the location of attachment points for wing’s main spar, wing’s rear spar, tail-cone, main landing gear, engine mount and the portions of the control system which are housed in the center fuselage, including throttle and brake system. Cabin access is through a sliding rear canopy made of aluminum railings and composite roll-over frames. The rear canopy seals against a rubber tube seal mounted against the front composite roll-over bar which supports the Perspex windscreen. The canopy is fastened closed via three connectors, a latch system at the top of the front roll-over frame and two magnets at the sides. The Perspex canopy and windscreen are attached to their frames with high bond Sikoflex adhesive. Seat structures are aluminum skin around an aluminum frame with leather or cloth covered foam cushions. The two seats can be independently adjusted by sliding backward and forward along plastic runners fixed to the cabin truss structure. Seat release levers are located at seat fronts in the cut out space provided for joystick movement. The cabin floor is constructed of light alloy and features matting. The entire fuselage, wing and other exposed surfaces are painted with a highly resistant weatherproofing synthetic coating. Wash only using water, mild detergent and chamois. All parts in Perspex material must never be dusted dry, but washed with lukewarm soapy water. In any case, never use, on this kind of surface, products such as gasoline, alcohol or any kind of solvent.
Page | 41 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual
Figure 3.4.2a
The engine mount is constructed of steel tubing and is secured to the firewall/cabin truss via a four- point attachment. The arrangement is apparent from Figure 3.4.2b below. Bolts travel through welded bushings on the mount, pass through the firewall and exit through welded steel bushings which are in turn riveted to the cabin truss. Nose gear support assembly is attached to engine mount.
Page | 42 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual
Figure 3.4.2b
3.5. Landing gear
3.5.1. Main gear The main landing gear consists of a single section composite strut attached using four M10 bolts threaded through bushings laid into the struts. The arrangement appears from figure 3.5.2. Suspension is provided by the flexibility within the strut, which is attached transversely through a channel designed for purpose in the lower center fuselage.
Page | 43 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual
. Figure 3.5.2
Wheels are cantilevered on gear struts using a 4 bolt attachment plate. The system features hydraulically actuated disc brakes (see figure 3.5.2) controlled by a lever located on the cabin tunnel between seats. Main gear wheels mount 4 ply 15 x 6.00-6 tires inflated at 22 psi (1.5 bar). A hydraulic brake circuit shut-off valve is positioned between seats with circuit shut off to allow braking after release of the brake lever. Braking is simultaneous on both wheels via a brake lever situated on the cabin divider.
3.5.2. Removal of Main Gear
Type of Maintenance Line
Level of Certification Required A&P or LSRM-M
Parts Required None
Tools Required Standard Mechanics Toolset
Page | 44 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual Removal of a single wheel is carried out as follows: Hoist aircraft onto supports. Remove wheel pant by releasing all small Allen key bolts that hold fairing to support plate and inner and outer fairing sections to one another. Remove the 6 locking wheel nuts from the inside rim and remove wheel Removal of stub axle and braking mechanism Following removal of wheel, remove axle nut split pin and thereafter the wheel lock nut (6). Release parking brake. Unscrew 4 brake disc assembly bolts Carefully remove wheel assembly with both hands.
3.5.3. Removal of cup-bearing from main gear wheel
Type of Maintenance Line
Level of Certification Required A&P or LSRM-M
Parts Required None
Tools Required Standard Mechanics Toolset
Removal of cup-bearing from main gear wheel Removal of a wheel bearing becomes necessary when excessive friction occurs during wheel motion. Procedure is as follows: Using an appropriate tool, remove “Seeger” type snap ring. Remove the two ring-grease seals and the felt-grease seal. Remove the cup bearing. Clean the bearings accurately using appropriate solvent and wipe wheel rim side. Grease using FIAT ZETA2. Reverse procedure to re-install. Insert ring-grease and felt-grease seals by sliding them perpendicular to hole without forcing them.
3.5.4. Nosegear The nose gear is attached to the engine mount with two guide brackets and a circular suspension spring. The entire arrangement appears from figure 3.5.4 below. The steel strut attaches to a conventional U- shaped fork supporting a 5/8 inch axle bolt. The front wheel is un-braked and fits a 5.00-5 4 ply type tire. Steering motion is transmitted from the pedal control horns through two adjustable push-pull rods attached to the nose gear strut by means of two control horns. Ease of steering movement is ensured through the use of three 2 inch inside diameter needle roller bearings on the weight bearing surfaces of the strut, both on the ground and in the air.
Page | 45 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual
Figure 3.5.4
3.5.5. Removal of nose wheel
Type of Maintenance Line
Level of Certification Required A&P or LSRM-M
Parts Required None
Tools Required Standard Mechanics Toolset
Remove the rear portions of the wheel pant/fairing by removing all small Allen key bolts. Lift and support front of aircraft in such a manner as to lift nose wheel off ground (this can also be achieved through carefully weighting and supporting the rear of the fuselage and/or the horizontal stabilizer) Remove split pin from axle bolt and then remove nut. Remove axle bolt while supporting wheel, being careful not to lose spacers. Remove wheel from fork.
Page | 46 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual Reverse procedure to reinstall, being careful to place spacers correctly so as not to bend fork when tightening axle nut. Avoid damage to fiberglass fairing and rivnuts by not tightening small Allen bolt screws excessively.
Tire inflation pressures:
Nose tire 20 psi (1.4 bar)
Main tire 22 psi (1.5 bar)
Page | 47 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual SECTION 4 POWERPLANT
4. Powerplant
4.1. Cowling
Type of Maintenance Line
Level of Certification Required A&P, LSRM-M, Owner
Parts Required None
Tools Required Standard Mechanics Toolset
The engine cowling is made up of an upper and a lower part, both moulded fiberglass. See figure 4.1. The cowling top is easily removed by releasing 10 dzus fasteners, three on each side and four along the upper edge of the firewall. Once all dzus fasteners are loose, remove the front and then side fasteners from their seating holes prior to removing those over the firewall. When lifting off the upper half cowling, unlatch the air filter cover so that it can come away attached to the air filter hose which runs from the left intake in the nose to the air filter cover. (Alternatively, loosen the hose clamp from the air filter box inlet and remove the carry through pipe to the upper cowling intake). Removal of lower portion of the cowling requires the removal of 6 dzus fasteners around the firewall and on the bracket behind the nose wheel strut. Once the cowling is loose, it is necessary to release the catches on each side of the coolant and oil radiators in place. If any cracks are detected, immediately drill stop holes at crack ends. Air to the air filter is provided through the left nose intake, circulation over the engine is provided by the right nose intake, and additional circulatory air is supplied through the coolant and oil radiators. The outflow area is on the underside of the cowling by the firewall. When replacing the cowlings, ensure that all radiators and hoses are properly connected. The best method of lining up the short hose to the right nose intake is using one’s fingers once the top cowling is fully fastened in place.
Page | 48 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual
Figure 4.1
4.2. Engine Main Features The installed engine is a BOMBARDIER-ROTAX type 912 ULS horizontally-opposed four-cylinder, one central camshaft with pushrods and OHV. Other features include liquid cooled cylinder heads and ram air-cooled cylinders. Prop drive is via reduction gear with integrated shock absorber and overload protection. Electric starter, integrated AC generator and mechanical fuel pump are standard. See figure 4.2 below. Technical data:
Maximum power rating 98.5 hp (73.5kW)
RPM @ max power 5800 rpm
Cruise power rating 92.5 hp (69 kW) at 5500rpm
Bore 3.31 inches (84 mm)
Stroke 2.40 inches (61 mm)
Displacement 82.5 in3 (1,352 cm3) cc?
Compression ratio 10.5:1
Page | 49 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual
Firing order 1-4-2-3
Direction of rotation of prop shaft Clockwise (pilot’s view)
Max temp. cylinder heads 135 °C
Fuel See Flight Manual
Reduction ratio 1:4.4286
Figure 4.2
4.3. General Servicing Procedures
4.3.1. Idle speed synchronization With the exception of idle speed synchronization, no other carburetor regulations are required. Fuel mixture is controlled and set by manufacturer and requires no further adjustment.
4.3.2. Ordinary servicing Refer to the Engine Operator’s Manual furnished by the engine’s manufacturer (p/n 899370 Issue 0 of 1/7/1998 and later versions) for all servicing operations furnished along with the present manual.
Page | 50 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual 4.3.3. Propeller The propeller is manufactured by Warp Drive and is an all composite blade protective finished with special lacquer coating. See manufacturer’s maintenance manual for service.
4.3.3.1. Propeller removal
Type of Maintenance Line
Level of Certification Required A&P or LSRM-M
Parts Required None
Tools Required Standard Mechanics Toolset
To remove propeller use the following procedure: Remove screws holding spinner dome to spinner bulkhead. Remove safetying. Remove bolts that secure prop to hub.
NOTE After removal, do not lay propeller down on its tip but always lay flat and away from sources of humidity, heat or, in any case, away from areas subject to excessive temperature change.
4.3.3.2. Propeller installation
Type of Maintenance Line
Level of Certification Required A&P or LSRM-M
Parts Required None
Tools Required Standard Mechanics Toolset
To install propeller, follow procedure below ensuring propeller is correctly aligned with hub before tightening bolts: Carefully clean hub area ensuring no oil traces are present. Check bolts for cracks, rust, proper thread and cleanliness. Check spinner bulkhead for cracks or deformations. Check spinner for cracks or deformations. Install spinner spacer and prop. Insert washers and fasten locknuts (bolt torque = 20Nm).
Page | 51 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual Safety all bolts. Install spinner. NOTE After correct installation of propeller and before takeoff, let the engine run for a few minutes and, after turning it off, carry out further inspection (tightness, overall state, etc.).
4.3.4. Periodic inspection Refer to specific subsection in Periodic Inspection Schedule of Section 3. For further information refer to the propeller’s “Owner’s Manual” and to all the pertinent documents issued by the manufacturer.
Page | 52 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual SECTION 5 SYSTEMS
5. Systems
5.1. Fuel System
Type of Maintenance Line
Level of Certification Required A&P or LSRM-M
Parts Required None
Tools Required Standard Mechanics Toolset
The aircraft is equipped with two aluminum fuel tanks integrated within the wing leading edge and accessible for inspection through dedicated panels. The capacity of each tank is 19.8 Gallons (75 Liters). Figure 5.1 illustrates the components of the fuel system.
Figure 5.1
In the cabin, on the lower center instrument panel is a fuel selector valve. Fuel drain valves are found under the inner leading edge section of each wing just forward of the main spar. Fuel level indicators for each tank appear on the Electronic Flight Instrument System (EFIS). Each fuel tank is equipped with individual sensor-floats. Fuel feed is through an engine-driven mechanical pump and through an
Page | 53 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual emergency electric pump. An inline mesh fuel filter is fitted in front of the firewall in the fuel line ahead of the electric and mechanical pumps. A fuel return pipe is fitted to the main fuel supply line after the pumps, followed by a fuel flow sender. The main fuel pipe then splits to effectively form a fuel manifold, one end of each feed each carburetor. A fuel pressure sender is connected to one side of the “manifold” pipe and is connected to the EFIS via the RDAC unit. The fuel return pipe splits to return fuel to the upper inboard section of each tank. The fuel outlet is located at the lowest point of the inboard sidewall of each fuel tank. Potential fuel tank leaks can be readily detected by visible fuel traces. Repairs can eventually be made, only if cracks are small and using specific glue type (1422-B2 DMS 2082), after emptying tank and thoroughly and repeatedly rinsing the area with water. Periodically check fuel tank vents to ensure that their openings are unobstructed and repeat inspection more frequently if operating in dusty conditions. It is recommended, for inspection, to use a small rubber hose to blow through the vent to clear possible obstructions. Fuel system servicing includes also the periodic inspection of the filter in addition to the inspection of the entire fuel line. Figure 5.1 shows a schematic of the fuel system.
5.2. Instruments The aluminum instrument panel contains the bulk of the electrical, flight and engine instruments (see figure 5.2). They are described as follows:
1 Master switch 18 Slip indicator
2 Magneto switches left and right 19 MGL V10 radio
3 Generator light 20 Engine choke control knob
4 Analogue airspeed indicator 21 Cabin heat control knob
5 Analogue altimeter 22 Main fuse (25A)
6 Transponder 23 Instruments fuse (10A)
7 MGL Voyager switch 24 Radio fuse (5A)
8 Backup battery switch 25 MGL Voyager fuse (3A)
9 Electric fuel pump switch 26 Trim motor fuse (1A)
10 Taxi light switch 27 12V power socket and flap motor fuse (5A)
11 Landing light switch 28 Fuel pump fuse (5A)
12 Avionics switch 29 12V power source socket
13 Flap deployment switch
14 Fuel selector valve
15 MGL Voyager
Page | 54 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual
16 MGL Voyager warning light
17 Magnetic compass
Type of Maintenance Line
Level of Certification Required A&P or LSRM-M
Parts Required None
Tools Required Standard Mechanics Toolset
The instrument panel may be removed by removing the 8 button head screws on the outside edge of the panel. Access to the rear of the panel, however, may be more easily achieved by removing the face of the EFIS. Before removing individual instruments, use particular care in disconnecting wires, hoses or other links as the case applies. When installing instruments, follow recommendations below: Do not over-tighten bolts as plastic instrument casing may break. Ensure hoses are free of any foreign matter and that no tight radius turns are present as this may choke hose or cause malfunction. Ensure proper grounding and tightening of all electrical instruments.
Page | 55 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual
Figure 5.2
5.2.1. Engine Instrumentation (reflected on EFIS screen) Tachometer. Oil temperature. Oil pressure. Coolant / Cylinder temperature (cylinders 3 and 3) Fuel pressure Fuel flow
5.3. Pitot and Static System
Type of Maintenance Line
Level of Certification Required A&P or LSRM-M
Parts Required None
Tools Required Standard Mechanics Toolset
The system consists of a pitot tube mounted below the left wing and a static port behind the instrument panel. The Pitot tube includes a second port set on an angled bevel below the main port for use in determining aircraft angle of attack. Flexible plumbing connects Pitot tube and static ports to pressure
Page | 56 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual instruments, being an analogue airspeed indicator and the MGL EFIS. The arrangement appears from figure 5.3. Servicing the system is simple and is carried out in accordance with the schedule listed in the Periodic Inspection Table found in Section 3; simply remove tubes from instruments and blow air in tube in port direction and never vice versa, clearing possible obstructions and checking line condition.
Figure 5.3
For safety reasons and to ensure correct airspeed readings, it is important to check the airspeed system for leaks adopting the following procedure: Connect a piece of rubber hose approximately 12 inches (30 cm) long to the pitot tube, close off the opposite end of the hose and slowly roll it up until the airspeed indicator shows cruise speed. Constant reading is an indication of no leak in system.
WARNING Avoid blowing air through pitot or static ports, as this causes immediate damage to the airspeed indicator.
5.4. Exhaust Manifolds Exhaust manifolds are flanged to the engine and join the muffler separately. The muffler also works as a heat exchanger for cabin heat. The exhaust system must always be checked for possible cracks (ref. Periodic Inspection Table Section 3). Close attention must be given to the heat exchanger system which should be totally disassembled for inspection once each 5 years as cracks would allow noxious fumes to be mixed with cabin air heat.
Page | 57 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual 5.4.1. Cabin heat and cooling The heating system exhaust vent is located near the rudder pedals on the passenger side of the cabin. Two fresh air vents are found on the left and right sides of the instrument panel, each with a shut-off valve that can be directed through 180 degrees. The heating system is comprised of a heat exchanger on the exhaust muffler, a hot air shut-off valve connected to an on/off knob situated in the central instrument panel, and by the above mentioned exhaust outlet.
5.5. Brake System The brake system consists of a brake fluid reservoir, a master cylinder and two disc brake assemblies. An intercept valve activates the parking brake. Braking action is through a lever located on the cabin tunnel between seats. The hydraulic circuit intercept valve is also located between seats and, when closed with lever pulled, keeps circuit under pressure and aircraft’s parking brake on. The arrangement appears from figure 5.5.
Figure 5.5
5.5.1. Draining and replacing brake fluid
Type of Maintenance Line
Level of Certification Required A&P, LSRM-M, Owner
Page | 58 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual
Parts Required None
Tools Required Standard Mechanics Toolset
To replace the brake fluid, service one side first, then other. Remove reservoir cap. Unscrew line nipple from disk calliper. Using a manually operated pump, add brake fluid UNIVIS J43 until level reaches bottom of reservoir, reattach line to calliper avoiding fluid spill. Repeat the above operations for other side. Top fluid level ¾ and close cap. Drain the brake system as follows: Pull brake lever to pressurize circuit. Loosen small escape valve allowing fluid spurt. Close small valve and release brake lever. Repeat the above operations until fluid comes out clean and no longer in spurts proving absence of air bubbles. Top-off reservoir with needed amount of brake fluid. Close reservoir and repeat operation for other brake. Hydraulic fluid may also be replaced using gravity after disconnecting the circuit. This method is however more laborious and less reliable.
Page | 59 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual
SECTION 6 ELECTRICAL SYSTEM
6. Electrical System This aircraft’s electrical system consists of a 12 Volt DC circuit. An 18 Ah lead acid battery provides the energy necessary to start the engine and acts as an emergency standby supply of electrical power for electrical components in case of generator malfunction. The MGL Voyager has a 3 Ah back-up battery which charges from the Voyager backup battery connection terminals.
Page | 60 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual
Figure 6
A single-phase generator connected to a regulator/rectifier supplies DC power to the bus bar and to recharge the battery. The positive end of the rectifier is connected to the primary bus through a 50 Amp circuit fuse mounted on firewall. A red warning light on the instrument panel will turn on indicating to the pilot that the generator is not operating. Circuit protection is through resettable breakers or fuses located on lower right side of instrument panel. The schematic of the electrical system is shown in figure 0.
The following table lists a typical legend of electrical components:
Pos. Description
1 Battery
2 Fuses
3 Master switch
4 Ignition systems
5 Master relay
6 Starter
7 Regulator / rectifier
Page | 61 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual
8 Generator
9 Ignition switches
10 Flap switch
11 Flap actuator
12 Trim tab switch
13 Trim tab actuator
14 Strobe light switch
15 Strobe light power supply
16 Strobe light
17 Nav lights switch
18 Nav lights
19 Cylinder head temperature sensors
20 Oil temperature sensor
21 Oil pressure sensor
22 Landing light switch
23 Landing light
24 Generator light
25 RDAC
6.1. Battery The battery is a sealed lead-type and provides 12V DC current with a capacity of 18Ah.
6.1.1. Battery Removal
Type of Maintenance Line
Page | 62 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual
Level of Certification Required A&P, LSRM-M, Owner
Parts Required None
Tools Required Standard Mechanics Toolset
If battery needs to be removed, proceed as follows: Stop engine. Master switch OFF. Remove the cowling. First disconnect the ground cable (negative) and then the positive cable from the battery terminals.
6.1.2. Battery Check Battery check should be performed every 100 hours or more frequently if operating in warm climates. The battery check should be performed using a high quality testing device designed for the purpose
6.1.3. Battery Installation Thoroughly clean the battery bracket area. Master switch OFF. First connect positive cable and then the negative battery terminals.
6.1.4. Internal AC Generator The generator is a permanent magnet type and supplies alternate current to a regulator/rectifier. Servicing or repair of the generator must be carried out only by authorised personnel.
6.1.5. Regulator/Rectifier
Type of Maintenance Line
Level of Certification Required A&P or LSRM-M
Parts Required None
Tools Required Standard Mechanics Toolset
A regulator/rectifier (type Ducati 965 347) is installed on the firewall in the engine compartment. To remove the regulator/rectifier: Master switch OFF. Disconnect wires from terminals of component to be removed. Unscrew and release component. To install: Secure regulator/rectifier in place with supplied screws. Connect wires to terminals.
Page | 63 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual 6.2. Exterior Lighting Exterior lighting consists of: Navigation lights. Landing light. Strobe light.
6.2.1. Positions Lights (if installed) Navigation lights are installed on the wing tips and on top of vertical stabilizer. All navigation lights are controlled by a single switch located on instrument panel and are protected by a fuse. Green and white lights and a strobe are located on right wing tip, red and white lights and a strobe are located on left wing tip and there is a white light and strobe on the top of the rudder horn.
6.2.2. Landing Light The landing light is located on the LH wing leading edge. The landing light switch is located on the instrument panel. The light is protected by a 10 Amp fuse.
6.2.3. Strobe Light Strobe lights are installed on each wing tip and on the rudder horn. The strobe lights are activated by a switch and are protected by a fuse. The switch and fuse are located on the instrument panel. The signal reaches a strobe light trigger circuit box located beneath the pilot seat, from where it reaches the lights. Testing of the strobe light may have to be done with the engine running since the battery may or may not have enough voltage to energize the light.
6.3. Flap System The flap system is made up of an electric actuator which includes a position indicator. The actuator is installed under the rear part of the center channel between the seats. It controls a system of pushrods that initiate flap extension. Micro-switches positioned within the actuator automatically interrupt current flow when flaps reach “all-out” or “all-in” positions. The flap switch is supplied by the primary bus bar through a breaker and is located on the control stick. The switch must be activated until desired position is reached. During flap retraction the switch applies the actuator until the flaps are completely retracted.
Page | 64 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual SECTION 7 MARKING AND PLACARDS
7. Markings and Placards – see POH for examples
7.1. Magnetic compass compensation table To compensate the deviation errors of the magnetic compass, the following correction table is located just below the compass:
For N 30 60 E 120 150
Steer
For S 210 240 W 300 330
Steer
DATE RADIO ON AIRPATH
7.2. Parking brake valve On and off stickers are located on the central tunnel behind the two seats next to the parking brake shutoff valve.
7.3. Engine throttle A throttle control lever is located on the central cabin channel.
7.4. Cabin heat The cabin heat control knob is located on the instrument panel central area and is marked “Cabin heat”
7.5. Trim switch The trim motor control is located on the top of the control stick.
7.6. Fuses Fuses are located on the lower/right side of the instrument panel and each fuse is individually marked. All fuses are of a resettable nature.
7.7. Flaps The flap control switch is located on the control stick. The left button lowers the flap and the right button raises it.
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7.8. Generator, Master, Starter A key which acts as a master switch and starter is located on the left upper side of the instrument panel. It is marked “Off”, “On” and “Start”.
7.9. Choke A choke activation knob is found centrally on the instrument panel and marked “choke”.
7.10. Generator Light A generator warning light is located on the upper/left side of the instrument panel and is marked “Alternator”.
7.11. Fuel selector valves On the central tunnel, between the pilot and the passenger’s legs, a fuel selector valve is located marked “Off” and “On”.
7.12. Electric fuel pump (emergency) The electric fuel pump is activated by a switch on the lower left of the instrument panel and marked “Fuel Pump”.
7.13. Baggage compartment A placard indicating the maximum weight is present on the center front retainer wall of the baggage compartment.
MAX BAGGAGE WEIGHT – FRONT SECTION – 35KG MAX BAGGAGE WEIGHT – REAR SECTION – 25 KG MAX TOTAL BAGGAGE WEIGHT – 35KG
7.14. Fuel tanks Next to the fuel tank filler cap is located a placard (57x120mm) indicating the type of fuel and the total tank’s capacity.
FUEL 19.8 US GALS 91 OCT MOGAS 100LL AVGAS
7.15. Oil tank reservoir On the oil tank reservoir are present two placards (30x12mm) indicating the type and quantity of engine’s oil stored into the reservoir.
Page | 66 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual 7.16. Cooling system overflow tank Located on the overflow tank cap is the placard indicating the solution proportion between the antifreeze additive and the water.
7.17. Brake oil reservoir On the cap of the brake’s oil tank, is a placard indicating the type of oil that must be used.
7.18. Tire pressures On each wheel pant is a placard indicating the tires inflating pressure.
7.19. Identification plate The following placard is located on the center console inside the aircraft cabin. It is made of stainless steel. AIRCRAFT REGISTRATION CONSTRUCTOR – THE AIRPLANE FACTORY MODEL – SLING SERIAL NO – DATE OF MANUFACTURE - Additionally, there is an Identification placard on the exterior rear fuselage on the passenger side with the following information:
BUILDER: THE AIRPLANE FACTORY MODEL: SLING SERIAL NUMBER: MADE IN SOUTH AFRICA
7.20. Limitation Placards Located on the instrument panels are the following placards
PASSENGER WARNING THIS AIRCRAFT WAS MANUFACTURED IN ACCORDANCE WITH LIGHT SPORT AIRCRAFT AIRWORTHINESS STANDARDS AND DOES NOT CONFORM TO STANDARD CATEGORY AIRWORTHINESS REQUIREMENTS
FASTEN SEATBELTS NO INTENTIONAL SPINS
EMERGENCY BALLISTIC CHUTE REMOVE LOCKING PIN BEFORE FLIGHT PULL HANDLE TO FIRE
On the baggage space separator channel –
MAX BAGGAGE WEIGHT – 77 Lbs / 35 Kgs
On the exterior of the fuselage adjacent to the entrance to the cockpit –
LIGHT-SPORT
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On the forward wing to fuselage fairing is a placard that identifies the “No step” area.
NO STEP
SECTION 8 Structural Repair
8. Structural Repair Structural repairs require consultation with the manufacturer.
Type of Maintenance Heavy
Level of Certification Required A&P
Parts Required TBD
Tools Required TBD
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SECTION 9 Painting & Coatings
9. Painting & Coatings
Type of Maintenance Line
Level of Certification Required A&P
Parts Required TBD
Tools Required TBD
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SECTION 10 Feedback Form
10. Feedback Form Please use the following form to provide us with feedback about any issues or anomalies encountered during the operation or maintenance of your aircraft as well as feedback on the maintenance manual itself. Mail it to: The Airplane Factory, Inc. 3401 Airport Drive Torrance, CA 90505
Email it to us at: [email protected]
Or fill it out on our website at: www.airplanefactory.com
Thank you!
Name Aircraft Model & Serial Number Description of Issue
Page | 70 Revision Date: 20 February 2012 Revision Number:1.1 Airplane Factory SLING LSA Maintenance Manual Send your comments to:
The Airplane Factory PO Box 308 Eikenhof South Africa, 1472 Tel : +27 11 024 4304 Fax : +27 86 632 4499 Email : [email protected] Web : www.airplanefactory.co.za
The Airplane Factory 3401 Airport Dr, Ste. E Torrance, CA 90505 Tel: +1.310.721.9190 Fax: +1.310.534.2282 Email: [email protected] Web: www.airplanefactory.com
Page | 71 Revision Date: 20 February 2012 Revision Number:1.1