User manual TECNAM P92-S ECHO MAINTENANCE MANUAL

[. . . ] n° 92/115 2 Issue, September 10th, 2004 1st Revision, October 25th, 2004 nd P92 Echo & P92-S Echo Maintenance Manual INTRODUCTION Before flying the aircraft we recommend reading carefully this manual, the flight manual and the engine's manuals. A thorough knowledge of the aircraft, of its qualities and of its limitations will allow you to operate with greater safety. The P92 Echo and P92-S Echo are uncomplicated and sturdy machines whose features include simple servicing and superior flying qualities. This manual describes time and modes for correct servicing procedures. [. . . ] The stabilator control system is push-rod type (see fig. C-6) and is controlled from the cabin via the control sticks. Control is transmitted through a push-pull rod (1) linked to a bellcrank (2) and a shaft (3) that runs through (4) the tail cone, transmit movement to stabilator's hub lever (5). All significant transmission element such as bellcranks, pushrods, supports and hinges can be easily accessed and inspected. FIGURE C-6 STABILATOR CONTROL If unusual tolerance is found along transmission, replace parts presenting excessive wear. C-7) consists of, a steel tube (1) with welded horn assembly (2) and attachment for stabilator control shaft (3). Counterweight (4) is at the end of an arm joined control lever by means of two bolts. Arm entering tail stock through lightening hole of the last tail cone ordinate. Longitudinal trim is controlled by a switch located on cabin tunnel or (optional) by two push-buttons mounted on the stick handle; position is, in any case, monitored via an indicator located on dashboard. Control activates the linear actuator (5) connected to supports Ed. 2 Date: Sept. 2004 Page C-7 P92 Echo & P92-S Echo Maintenance Manual Section C AIRFRAME (6) and plates (7). Actuator's motion is transmitted to an adjustable push-pull rod (8) through a bellcrank (9). To remove stabilator's hub disconnect electric actuator frame assembly (7), from support (6), release aft bellcrank assembly (3) then release plates (2) from brackets(6). FIGURE C-7 HORIZONTAL TAIL CONTROL SYSTEM Ed. 2 Date: Sept. 2004 Page C-8 P92 Echo & P92-S Echo Maintenance Manual Section C AIRFRAME 5 - VERTICAL TAIL The vertical tail is an all-metal light alloy structure (fig. Rudder tip is fiberglass with cut-outs for navigation and strobe light. The vertical stabilizer consists of a twin spar with wrap-around load bearing skin paneling. An attachment plate to the fuselage tail cone (1) secures the stabilizer's front spar to the lower tip while the rear spar is extended to attach directly onto the last tail cone ordinate (2). The rudder consists of an aluminum alloy torque tube (3), formed sheet metal ribs (4) and sheet metal panel cover (5) held in place by rivets. FIGURE C-8 VERTICAL STABILIZER, RUDDER AND SUPPORTS The hubs (6) and (7) are to the ends of rudder provide by means of bushings (8) hinged rudder with vertical stabilizer. The lower hinge assembly is attached to a bellcrank controlled by cables from rudder pedals. Ed. 2 Date: Sept. 2004 Page C-9 P92 Echo & P92-S Echo Maintenance Manual Section C AIRFRAME To the upper ends rudder torque tube is joined steel arm with, to the end, counterweight and rotate freely onto vertical stabilizer tip. In case tip isn't profile two plastic fairing (one of this removable) counterweight fitting in slot. To remove rudder, after disconnected little stern and flying tail (see § 4), disconnect cables from bellcrank, remove lower bearing and release rudder with downward motion. C-9) is steel cable join rudder control lever with rudder pedals lever. [. . . ] Energy is supplied by an engine-driven generator and by a buffer battery. The 18 Ah capacity battery, is located in a distinct compartment on the right side of the tail cone. The compartment is suitably drained and vented, and access is through a small hatch secured by a screw. Every 50 hours, or more often during summer, add distilled water to keep electrolyte at correct level. [. . . ]