MAINTENANCE MANUAL Apollo FOX Aerodynamically Operated Ultralight Aircraft Name - Type: Apollo Fox Serial Number: Registration Mark: Date of Issue: 29.09.2014 Signature Stamp, This aeroplane can be operated in compliance with information and limitations contained herein. DATA OF THE AEROPLANES Type Production Serial Destination Number: and year of production Fuselage Apollo Fox Halley Ltd ROTAX BOMBARDIE Engine 912 UL/S R-ROTAX GMBH AUSTRIA PROPELLER Dm –prop Dusan dmp-3/3 Mihalides BRS Parachute GALAXY GALAXY 5/472,5 Holdig s.r.o. SOFT 0.1 RECORD OF REVISIONS Any revisions or amendments to this manual shall be issued in the form of bulletins with attached new pages. It is in the interests of every user to enter such revision into the table of revisions and to replace the existing page by the new one. The revised or corrected text shall be indicated by a vertical line on page left margin and the page shall bear revision number and date of its issue. Rev. Chapters Pages Date of Bulletin Bulletin New Page No. Affected Affected Issue Number Approved On Inserted On, Signature 0.2 LIST OF EFFECTIVE PAGES Chap. Page Date Chp. Page Date Chap. Page Date 0 1 03.12.10 4 4-4 03.12.10 6-12 03.12.10 2 03.12.10 4-5 03.12.10 6-13 03.12.10 3 03.12.10 4-6 03.12.10 6-14 03.12.10 4 03.12.10 4-7 03.12.10 6-15 03.12.10 5 03.12.10 6-16 03.12.10 6 03.12.10 5 5-1 03.12.10 6-17 03.12.10 1 1-1 03.12.10 5-2 03.12.10 6-18 03.12.10 1-2 03.12.10 5-3 03.12.10 6-19 03.12.10 2 2-1 03.12.10 5-4 03.12.10 2-2 03.12.10 7 7-1 03.12.10 2-3 03.12.10 6 6-1 03.12.10 7-2 03.12.10 2-4 03.12.10 6-2 03.12.10 7-3 03.12.10 2-5 03.12.10 6-3 03.12.10 7-4 03.12.10 2-6 03.12.10 6-4 03.12.10 7-5 03.12.10 2-7 03.12.10 6-5 03.12.10 7-6 03.12.10 2-8 03.12.10 7-7 03.12.10 3 3-1 03.12.10 6-6 03.12.10 7-8 03.12.10 3-2 03.12.10 6-7 03.12.10 7-9 03.12.10 3-3 03.12.10 6-8 03.12.10 4 4-1 03.12.10 6-9 03.12.10 4-2 03.12.10 6-10 03.12.10 4-3 03.12.10 6-11 03.12.10 0.3 TABLE OF CONTENTS Chapter General .................................................................................................................. 1 Technical Description ............................................................................................... 2 Basic Technical Data .............................................................................................. 3 Operating Limitations .............................................................................................. 4 Normal Procedures ................................................................................................. 5 Servicing and Maintenance ..................................................................................... 6 Supplements ............................................................................................................ 7 CHAPTER 1 1. GENERAL TABLE OF CONTENTS 1.1 Introduction 1.2 Certification Basis 1.3 Warning, Caution and Note 1.1 Introduction This manual is designed to acquaint personnel with information towards increasing safe and efficient operation of the aircraft. This manual contains information regarding ground servicing and maintenance of the aircraft, information necessary for pilots and engineers and additional data supplied by the manufacturer. 1.2 Certification Basis This airplane approved by Aviation Authority of Hungary according Type of certificate airworthiness .......9451/1999........., It is can be equipped with special equipment for towing gliders with MTOW 450 kg. 1.3 Warning, Caution and Note The following definitions and text formats apply to warnings, cautions and notes given throughout this manual: Non-observance or neglection of such warning may lead to WARNING an immediate or grave reduction of flight safety level. Non-observance or neglection may lead to a minor or major CAUTION reduction of flight safety level, or to a long-term degradation of flight safety. Draws attention to such items which do not directly relate to NOTE flight safety, however are important or unusual. CHAPTER 2 2. TECHNICAL DESCRIPTION TABLE OF CONTENTS 2.1 Introduction 2.2 Aircraft Framework 2.2.1 Fuselage 2.2.2 Wing 2.2.3 Tail Unit 2.3 Control System 2.4 Instrument Panel 2.5 Landing Gear 2.6 Seats and Safety Belts 2.7 Baggage Compartment 2.8 Door 2.9 Powe Unit 2.10 Fuel System 2.11 Elecrical System 2.12 Pitot-Static System 2.13 Equipment, Outfit 2.1 Introduction This chapter contains description of the ultralight and its systems. Furthermore, Chapter 7 includes diagrams of individual parts. 2.2 Aircraft Framework 2.2.1 Fuselage The main supporting structure of the fuselage is a lattice-work welded of steel tubes. In its middle section is located a crew compartment , accessible through large, upward-opening door hinged on both fuselage sides. A two-member crew sits side by side on an upholstered bench- seat the body of which is formed by a fiberglass skeleton. The crew members are fastened with four-point automobile safety belts anchored to the fuselage framework. The engine bay in the forward fuselage is divided from the crew compartment by firewall. Engine cowlings and the forward fuselage skin are made of fiberglass. Rear fuselage bears hinges and attachments of horizontal tail surfaces and an integral tail fin of vertical tail surfaces. On the upper fuselage behind the wing is located a detachable cover allowing to fold the wings backward. The whole fuselage surface except for the forward section is fabric-covered. Cockpit canopy and entrance door glazing is of MAKROLON material. 2.2.2 Wing The rectangular-plan wing is of a frame structure. It is composed of two aluminium carrying tubes and a system of aluminium ribs and diagonal stiffeners. The aluminium rib system comprises full ribs and false ribs stiffening the skin in the area of leading-edge assembly. As for its horizontal plane, the wing is strengthened with a system of steel diagonal tubular stiffeners. There is a 30 l fuel tank built in the wing root section. The tank is made of fuel and alcohol proof composite material. Proper shape of the wing leading edge is guaranteed owing to a die- formed part glued on the fore carrying tube. The trailing edge is formed of a duralumin shaped piece. The wing is fabric-covered. Below the wing trailing edge are located flaperons incorporating both function of ailerons and wing flaps; they are attached to the rib ends by means of hinges. The flaperon structure consists of a aluminium load- carrying tube swinging in the hinges and a fiberglass sandwich part itself of inversely moulded airfoil. The wings are attached to the fuselage in suspension points of load- carrying tubes in their upper section and are anchored by „V“ struts to