FLIGHT CONTROLS. Roll Control Hydraulically actuated Ailerons with mechanical backup via cable and pulleys Hydraulic neutral point adjustment
|
|
- Aron Roger Bryant
- 7 years ago
- Views:
Transcription
1 FLIGHT CONTROLS GENERAL Pitch Control Mechanically actuated Elevator via cable and pulleys Mechanically actuated Elevator Trim Tabs Electrically actuated Movable Horizontal Stabilizer Roll Control Hydraulically actuated Ailerons with mechanical backup via cable and pulleys Hydraulic neutral point adjustment Yaw Control Hydraulically actuated with mechanical backup via cable and pulleys Hydraulic neutral point adjustment Lift Devices Electrically actuated Fowler Flaps Spoilers Electrically controlled and hydraulically actuated Speed Brakes and Ground Spoilers ELEVATORS Each control yoke operates a set of cables, pulleys and bell cranks so as to operate its respective Elevator. The systems are linked together with a torque tube and a disconnect device. The disconnect device is used if there is a jam in the system. When the Elevators are disconnected: An ELEV DISC Light illuminates on the center pedestal. Stick Pusher is available only on the LEFT side. If disconnected do NOT use the Autopilot. The system can be reconnected only on the ground by maintenance. The Autopilot and Stick Pusher use the LEFT Elevator system ELEVATOR TRIM TABS Two types of Elevator Trim Tabs automatically function throughout the airspeed envelope to alleviate air loads required to control aircraft pitch. They are not controllable from the cockpit. Inboard Spring Tabs Activated by a torsion rod, bellcrank, torque tube assembly. Deflection is proportional to control column force and aerodynamic loads. Deflection is opposite that of Elevator travel. Used to assist smaller Elevator travel at high airspeed and high air loads. Remains neutral at low speeds. Outboard Servo Tabs Deflection is proportional to Elevator travel. Deflection is opposite that of Elevator travel. Used to assist larger Elevator travel at low airspeed and low air loads.
2 PITCH TRIM The Pitch Trim System uses electric motors and a jackscrew to move the leading edge of the stabilizer and change its angle of incidence. The position of the Horizontal Stabilizer can be confirmed visually with markings on the Vertical Stabilizer. The thick markings on the tail indicate 4 Nose DOWN, NEUTRAL, and 10 Nose UP. The thin markings indicate 2 intervals. The system is commanded electrically by Trim Switches located on the control yokes and center pedestal. The system can also be commanded automatically by the Autopilot. In both cases the pitch trim signal is processed in the Horizontal Stabilizer Control Unit (HSCU). The HSCU commands the Horizontal Stabilizer Actuator (HSA). The HSA uses two electric motors to move the Horizontal Stabilizer. One motor operates as Main Trim and the other as the Backup Trim. Each system sends commands to its respective motor. When one Motor is commanded it will simultaneously drive the other motor. The non-commanded Motor will run deenergized. Both control systems have a cutout relay. The MAIN SYS CUTOUT button deactivates the Main system, and the BACKUP SYS CUTOUT button deactivates the Backup system. Trim inputs can be made using: Trim switches on the control yokes (Main System) Auto Trim by Autopilot or Speed brakes (Main System) Backup Switches on the center pedestal (Backup System) The trim rate is based on airspeed received from the Air Data Computers (ADC). Below 160 KCAS the trim rate is 2 per second Between 160 KCAS and 250 KCAS the trim rate decreases as airspeed increases Above 250 KCAS the trim rate is 1 per second. During Stick Shaker activation, nose-up trim actuation is INHIBITED. PITCH TRIM PROTECTIONS A TAKEOFF TRIM warning is made if the stabilizer trim position is NOT in the GREEN when the TO CONFIG button is pressed or the Thrust Levers are advanced prior to takeoff. Both halves of a trim switch must be operated simultaneously to function. This prevents a pitch trim runaway due to a faulty switch. A trim switch will be inhibited if operated in a split condition for more than 7 seconds. The aircraft must be powered down and repowered to regain control of the switch. Excessive air loads could potentially stall the electric motor if the aircraft is allowed to accelerate in an untrimmed condition after takeoff. This would result in a temporary loss of pitch trim command. In the case of a stalled electric motor, and a cumulative unsatisfied pitch trim command of 16 seconds will result in the associated trim system to be de-activated. To minimize the effects of an inadvertent trim command, each trim switch is only effective for 3 seconds at a time. The pilot must release the switches every 3 seconds and then use them again. Should a pitch trim runaway ever occur, the Quick Disconnect button will override any trim activation. This button may be PRESSED and HELD until a full disengagement has been accomplished through the Main Cutout Button.
3 AILERONS The ailerons are positioned by the control wheels, which are linked together by a torque tube and cables to supply mechanical inputs to two separate hydraulic actuators. Each aileron actuator is supplied by both hydraulic systems. Either hydraulic system is capable of providing full power control. Each hydraulic system supply can be shut off if necessary via the overhead panel Aileron Shutoff Buttons. If both hydraulic systems are lost, rotating the control yoke mechanically positions the ailerons. The Artificial Feel System (AFS) provides tactile feedback on the aerodynamic loading of the Ailerons. The Artificial Feel System is installed in the RIGHT Aileron system. The systems are linked together with a torque tube and a disconnect device. The disconnect device is used if there is a jam in the system. When disconnected: An AIL DISC Light illuminates on the center pedestal. If disconnected do NOT use the Autopilot. The system can be reconnected only on the ground by maintenance. The Autopilot is installed in the LEFT Aileron system. ROLL TRIM SYSTEM An electro-mechanical Roll Trim Actuator is installed on the RIGHT side of the Torque Tube which is linked to the AFS. Roll Trim is accomplished by repositioning of the neutral point of the ailerons. The ROLL TRIM switch on the Trim Control Panel will energize the actuator in either direction. ROLL TRIM PROTECTIONS Both halves of a trim switch must be operated simultaneously to function. This prevents a pitch trim runaway due to a faulty switch. A trim switch will be inhibited if operated in a split condition for more than 7 seconds. The aircraft must be powered down and repowered to regain control of the switch. To minimize the effects of an inadvertent trim command, each trim switch is only effective for 3 seconds at a time. The pilot must release the switches every 3 seconds and then use them again. The Quick Disconnect button will override any trim activation. RUDDERS Yaw control is provided through two Rudders (Forward and Aft) which are mechanically linked together. The Rudder Pedals are linked together with a torque tube. However, each set of Rudder Pedals operates its own set of cables, pulleys and bell cranks which provide mechanical inputs to the Rudder Power Control Unit (PCU). The PCU hydraulically powers the Forward Rudder. There is an Artificial Feel System within the PCU which gives pilots aerodynamic loads feedback. RUDDER SYSTEM 1 AND 2 The PCU uses both hydraulic systems to provide pressure to two separate Rudder Actuators which divide Rudder control into Rudder System 1 and Rudder System 2. Normally both rudder systems are powered at speeds less than 135 knots. Above 135 knots, Rudder system 1 automatically shuts OFF. If the automatic shut off fails to shut off a system above 135 knots, a RUDDER OVERBOOST caution message is presented. It is then necessary to manually shut off Rudder System 1 or 2.
4 RUDDER SYSTEM SHUTOFF Each Rudder system can be shut off manually by the associated RUDDER SHUTOFF button on the FLIGHT CONTROL Panel. Manual reversion is provided by way of the conventional cables, pulleys and bell cranks. Greater control forces are to be expected since the pilot will deal directly with aerodynamic loads on the Rudder. The Artificial Feel System is not available in the mechanical reversion mode. If Rudder System 2 fails, the Rudder System 1 automatically takes over Rudder control. A caution message is presented until Rudder System 2 normal operation is re-established. The Autopilot is installed in the LEFT Rudder Pedal cable system YAW TRIM Yaw trim is accomplished by the PCU in repositioning of the neutral point. Pressing the ROLL TRIM switch on the Trim Control Panel will adjust the PCU in either direction. Yaw Trim is not available in the manual reversion mode. RUDDER HARDOVER PROTECTION The Rudder Hardover Protection system monitors Rudder Pedal forces applied by the pilots. Each Rudder Pedal is equipped with a 130 lb Spring Loaded Cartridge and a microswitch. If the system recognizes 130 Lbs. of Rudder Pedal force applied by the pilots, and at least a 5 Rudder deflection CONTRARY to the direction commanded by the Rudder Pedals, the Rudder Hardover Protection system disables both sides of the PCU and generates an EICAS Message. The pilots must then shut off each Rudder System manually. After a proper automatic shutoff during a Hardover occurrence, do not reset rudder systems. Rudder Hardover Protection is INHIBITED during single engine operations. FLAP SYSTEM Each wing has two double-slotted Fowler-type panels. The pilot chooses flap position with the Flap Selector Lever (FSL). There are four detent positions to set the Flaps at: 0, 9, 22, and 45. The Flaps 18 detent is blocked. Flap position, velocity and command signals are processed in the Flap Electronic Control Unit (FECU). The FECU compares FSL position and Flap positions and commands the FPDU to move the Flaps. Two electric motors are housed in the Flap Power Drive Unit (FPDU). The motors drive flexible drive shafts which actuate Ball Screw Actuators. If one electric motor fails, the other motor can operate the flaps at half speed. EICAS will present a FLAP LOW SPEED caution message. If both motors or control channels fail, an EICAS FLAP FAIL caution message is presented to indicate that the system is inoperative. FLAP SYSTEM PROTECTIONS If there is any disagreement on flap position or velocity between both systems, the FECU disables the system and informs EICAS and other related Systems. If the FSL Switch fails, the position(s) can NOT be selected. A protection circuit INHIBITS flap movement if the flap position and FSL disagree upon initial aircraft power-up. The FSL must lifted UP to release the protection. Flap actuators are torque limited to safeguard the structure against excessive loading should the flaps or the actuators jam. Velocity sensors installed at the end of the flexible shafts detect panel
5 asymmetry. The Flap System is disabled if the panels are asymmetric. Flap Transmission Brakes stop flap movement, locking them in place. It can only be reset on the ground by maintenance. If the flaps are not in the appropriate takeoff position (9 or 22 for the EMB-145, and 9 or 18 for the EMB-135 and 140) when the Takeoff Configuration Check Button is pressed or when either thrust lever angle is advanced for takeoff, the EICAS flap digits and box will turn red, and an aural warning TAKEOFF FLAPS and an EICAS NO TAKEOFF CONFIG warning message will be displayed in the cockpit. Two switches on the Flap Selector Lever send signals to the Landing Gear Warning System to alert pilots any time the aircraft is in a landing configuration and the landing gear are not down and locked. Flap position is displayed on Engine EICAS. Marks on the wing also indicate the 9 and 22 positions. GUST LOCK A Gust Lock system locks the elevator to avoid wind damage on the ground. It is either a mechanical lock which mechanically inhibits control column movement or an electro-mechanical lock which activates solenoid locking pins which engage the Elevator. The electro-mechanical type is identified by the yellow and black striped paint and the ELEC GUST LOCK inscription. Ailerons and Rudders do not require a lock as hydraulic pressure dampens any control surface movement. The GUST LOCK light on the glareshield illuminates during the unlocking cycle on the ground. It also indicates a system failure when in flight. LOCKING Pull the control column backwards to any position from neutral to full nose up. Lift the safety lock device Move the gust lock lever from the unlocked FREE to the LOCKED position Push the control column fully forward until the control column movement is restricted. UNLOCKING Lift the safety lock device and move the gust lock lever to its intermediate position. The locking pins are commanded to open when the gust lock lever is in the intermediate position. The elevators will be unlocked after approximately eight seconds. The indication lights will illuminate during the unlocking cycle, and then should remain off after unlocking. Lift the safety lock device Pull the gust lock lever from the intermediate position to its full forward FREE position GROUND SPOILERS AND SPEEDBRAKES Each wing is equipped with two spoiler panels, inboard and outboard. Speedbrake function uses outboard spoilers only. Ground Spoiler function uses both inboard and outboard spoilers. The Speedbrakes and Ground Spoilers are used as separate systems. The EICAS displays spoiler position as OPN or CLSD. Spoilers are controlled by a common Spoiler Control Unit (SCU). The SCU processes spoiler position, air/ground logic, wheel speed, Speedbrake Lever position, and Thrust Lever Angle signals, and commands hydraulic deployment and retraction of the panels. Hydraulic System 1 operates through the Ground Spoiler Valve. Hydraulic System 2 operates through the Spoiler/Speedbrake Valve.
6 GROUND SPOILERS SYSTEM The SCU automatically commands DEPLOYMENT when the following conditions are met: Aircraft on the ground Main Wheels > 25 knots N2 < 56.4% Thrust Lever Angle (TLA) of both Engines are less than 30 SPEEDBRAKE SYSTEM The SCU commands DEPLOYMENT when the following conditions are met: Flap position 0 or 9 Speedbrake Lever selected OPEN Thrust Lever Angle (TLA) of both engines less than 50 If any of the conditions are NOT met the deployment does NOT occur and EICAS SPBK LVR DISAGREE Message is displayed. If the speed brake panels are open and either of the speed brake open conditions are not met, the speed brake panels automatically close and an EICAS SPBK LVR DISAGREE is presented. The speed brake lever must then be moved to the CLOSE position to remove the EICAS message in both cases. Spoiler Aural Warning (Takeoff Spoilers) If any spoiler/speed brake panel is deployed when the TO CONFIG Check Button is pressed or when either thrust lever is advanced for takeoff, the EICAS spoiler OPN label will turn red, and an aural warning TAKEOFF SPOILERS and an EICAS NO TAKEOFF CONFIG warning message will be displayed in the cockpit.
7 PIT TRIM 1 (2) INOP: Respective Pitch Trim System is inoperative: 1 -- is the Main Trim System, 2 -- is the Backup System AIL SYS 1 (2) INOP: Respective Aileron System Actuator Hydraulic Power is inoperative. RUDDER SYS 1 INOP: Rudder System 1 is inoperative. Message is presented if: 1. Less than 135 kts 2. Greater than 135 kts if both ADC's airspeed information is invalid. RUDDER SYS 2 INOP: Rudder System 2 is inoperative. RUDDER SYS 1-2 INOP: BOTH Rudder Systems are inoperative. RUDDER OVERBOOST: BOTH Rudder Systems Hydraulic Actuators are pressurized above 135 kts. RUDDER HDOV PROT FAIL: 1. Disagreement between both FADEC of the same Engine. 2. Rudder Position Micro-switches indicate the Rudder is both LEFT and RIGHT at the same time. FLAP FAIL: BOTH Flap Channels are inoperative. SPOILER FAIL: Any Spoiler panel is: 1. Inadvertently OPEN, 2. FAILED to OPEN 3. Any failure in the input signals. SPBK LVR DISAGREE: Speedbrake Lever is at OPEN but the deployment logic is NOT satisfied. FLAP LOW SPEED: One Flap Channel is inoperative.
FLIGHT CONTROLS 1. GENERAL 2. MAIN COMPONENTS AND SUBSYSTEMS ROLL CONTROL. Smartcockpit.com BOEING 737 SYSTEMS REVIEW Page 1
Smartcockpit.com BOEING 737 SYSTEMS REVIEW Page 1 FLIGHT CONTROLS 1. GENERAL The primary flight controls, ailerons, elevators and rudders, are hydraulically powered. Hydraulic power is provided from hydraulic
More informationB777. Landing Gear DO NOT USE FOR FLIGHT
B777 Landing Gear DO NOT USE FOR FLIGHT Introduction The airplane has two main landing gear and a single nose gear. The nose gear is a conventional steerable two wheel unit. Each main gear has six wheels
More informationLANDING GEAR & BRAKES www.theaviatornetwork.com GTM 14.1 2005 1-30-05 CONTENTS INTRODUCTION... 14.2
www.theaviatornetwork.com GTM 14.1 CONTENTS INTRODUCTION... 14.2 GENERAL... 14.2 MAIN LANDING GEAR... 14.2 Landing Gear Latch Lever and Handle... 14.2 Landing Gear Pressure Gauge... 14.2 Landing Gear Warning
More information06 HYDRAULICS, FLIGHT CONTROLS, LANDING GEAR, BRAKES
Course overview N E X T G E N E R A T I O N Airplane General Air Systems Warning Systems, Communications, Ice & Rain Protection Electrical Engines, APU, Fuel System Hydraulics, Flight Controls, Landing
More informationA380 Flight Controls overview
Presented by Xavier Le tron Airbus Flight Controls A380 Flight Controls overview A380 Flight Control and uidance Systems main novelties Aircraft configuration and control surfaces Actuator technology Power
More informationSHIFT INTERLOCK SYSTEM SHIFT INTERLOCK SYSTEM
SHIFT INTERLOCK SYSTEM The shift lock system is designed to ensure the proper operation of the automatic transmission. The driver must depress the brake pedal in order to move the gear selector from Park
More informationB777. Automatic Flight DO NOT USE FOR FLIGHT
B777 Automatic Flight DO NOT USE FOR FLIGHT 4.10 Automatic Flight-Controls and Indicators Mode Control Panel (MCP) A/T ARM L R IAS MACH HDG TRK V/S FPA ALTITUDE A/P F/D ON OFF CLB CON IAS LNAV VNAV AUTO
More informationVARIABLE STABILITY FLIGHT OPERATIONS MANUAL
SPACE INSTITUTE VARIABLE STABILITY FLIGHT OPERATIONS MANUAL Prepared by the Aviation Systems and Flight Research Department September 2004 Index 1.1 General Description...1 1.2 Variable Stability System...5
More informationNomad WINGS FLAP OPERATING LIMITATIONS
WINGS FLAP OPERATING LIMITATIONS 1. PLANNING INFORMATION A. Effectivity (1) Aircraft affected: N22 Series line sequence numbers 1 to 9, 11 to 29, 31, 33, 35, 37, 39 to 41, 43, 45, 47 to 59, 63, 65 to 70,
More informationRevision Number Revision Date Insertion Date/Initials 1 st Ed. Feb 01, 00 2 nd Ed. Jun 24, 02 3rd Ed. Feb 15, 07
List of Effective Pages * Asterisk indicates pages changed, added, or deleted by current revision. Retain this record in front of handbook. Upon receipt of a Record of Revisions revision, insert changes
More informationVEHICLE SPEED CONTROL SYSTEM
PL VEHICLE SPEED CONTROL SYSTEM 8H - 1 VEHICLE SPEED CONTROL SYSTEM TABLE OF CONTENTS page DESCRIPTION AND SPEED CONTROL SYSTEM...1 SPEED CONTROL SERVO-PCM OUTPUT....2 SPEED CONTROL SWITCHES PCM INPUT...2
More informationElectro-Mechanical Landing Gear System. Landing Gear and Brakes
Electro-Mechanical Landing Gear System N O 2 D U A L F E D B U S LANDING RELAY 5A DOWN EMERGENCY EXTENSION DOWN LIMIT GROUND AIRBORNE DOWN LIMIT Landing Gear and Brakes DOWNLOCK HOOK ENGAGED GROUND AIRBORNE
More informationENGINE FIRE / SEVERE DAMAGE / SEPARATION ON TAKEOFF
ENGINE FIRE / SEVERE DAMAGE / SEPARATION ON TAKEOFF According to RYANAIR Procedures PF PM REMARKS Control the aircraft (FULL T/O thrust can be manually selected) Announce «ENGINE FAILURE» or «ENGINE FIRE»
More informationHydraulic Landing Gear System
Hydraulic Landing Gear System CENTER BUS MAIN POWER RELAY 60A 5A SERVICE VALVE 5 LANDING GEAR TIME DELAY PCB TIME DELAY 14 AUX. RETURN AUX. PRESS. UP SELECTOR VALVE POWER PACK ASSEMBLY REGULATED BLEED
More informationS-Tec System Thirty Autopilot
Cirrus Design Section 9 Pilot s Operating Handbook and FAA Approved Airplane Flight Manual Supplement for S-Tec System Thirty Autopilot When the S-Tec System Thirty Autopilot is installed in the Cirrus
More informationChapter 6 Lateral static stability and control - 3 Lecture 21 Topics
Chapter 6 Lateral static stability and control - 3 Lecture 21 Topics 6.11 General discussions on control surface 6.11.1 Aerodynamic balancing 6.11.2 Set back hinge or over hang balance 6.11.3 Horn balanace
More informationTOYOTA ELECTRONIC CONTROL TRANSMISSION
Electronic Control Transmission (ECT) The Electronic Control Transmission is an automatic transmission which uses modern electronic control technologies to control the transmission. The transmission itself,
More informationCONTINUOUSLY VARIABLE TRANSMISSION (CVT)
GROUP 23 CONTINUOUSLY VARIABLE TRANSMISSION (CVT) CONTENTS CVT........................... 23-2 GENERAL INFORMATION............. 23-2 ELECTRONIC CONTROL SYSTEM...... 23-3 EEPROM...........................
More informationMulti Engine Oral Exam Questions
Multi Engine Oral Exam Questions 1. What are the requirements for a multi-engine rating? 2. What is the max rated horse power at sea level? At 12,000 msl? 3. What is the rated engine speed? 4. What is
More informationProject Flight Controls
Hogeschool van Amsterdam Amsterdamse Hogeschool voor techniek Aviation studies Project Flight Controls ALA Group: 2A1Q Jelle van Eijk Sander Groenendijk Robbin Habekotte Rick de Hoop Wiecher de Klein Jasper
More informationAPPENDIX 3-B Airplane Upset Recovery Briefing. Briefing. Figure 3-B.1
APPENDIX 3-B Airplane Upset Recovery Briefing Industry Solutions for Large Swept-Wing Turbofan Airplanes Typically Seating More Than 100 Passengers Briefing Figure 3-B.1 Revision 1_August 2004 Airplane
More informationAIR - PNEUMATIC, AIR CONDITIONING, PRESSURIZATION
AIR - PNEUMATIC, AIR CONDITIONING, PRESSURIZATION PNEUMATIC SYSTEM The Pneumatic System is normally supplied by the Engine's compressor sections. The Pneumatic System may also be supplied by APU bleed
More informationRequirements to servo-boosted control elements for sailplanes
Requirements to servo-boosted control elements for sailplanes Aerospace Research Programme 2004 A. Gäb J. Nowack W. Alles Chair of Flight Dynamics RWTH Aachen University 1 XXIX. OSTIV Congress Lüsse, 6-136
More informationAviation Supplies & Academics, Inc. 7005 132nd Place SE Newcastle, Washington 98059-3153 www.asa2fly.com
The Pilot s Manual 1: Flight School Aviation Supplies & Academics, Inc. 7005 132nd Place SE Newcastle, Washington 98059-3153 www.asa2fly.com Originally published by Aviation Theory Centre 1990 1993. Fourth
More informationLancair Legacy Annual Condition Inspection Checklist
Lancair Legacy Annual Condition Inspection Checklist Performed by: Completion Date: Complete Maintenance/Inspection Item Comments Pre-Inspection Research AD and Service bulletins Inspect entire airframe
More informationELECTRICAL. Primary electrical power is provided by two engine driven generators which supply three-phase, 115 volt 400 cycle alternating current.
Smartcockpit.com BOEING 737 SYSTEMS REVIEW Page 1 ELECTRICAL 1. GENERAL Primary electrical power is provided by two engine driven generators which supply three-phase, 115 volt 400 cycle alternating current.
More informationAIRCRAFT GENERAL www.theaviatornetwork.com GTM 1.1 2005 1-30-05 CONTENTS
www.theaviatornetwork.com GTM 1.1 CONTENTS INTRODUCTION... 1.2 GENERAL AIRPLANE... 1.2 Fuselage... 1.2 Wing... 1.2 Tail... 1.2 PROPELLER TIP CLEARANCE... 1.2 LANDING GEAR STRUT EXTENSION (NORMAL)... 1.2
More informationInstruction Manual Bedienungsanleitung Manuel d utilisation Manuale di Istruzioni
Instruction Manual Bedienungsanleitung Manuel d utilisation Manuale di Istruzioni EN Getting Started To get more information, including details on downloading the Spektrum AS3X Mobile Programming Application,
More informationLab 8 Notes Basic Aircraft Design Rules 6 Apr 06
Lab 8 Notes Basic Aircraft Design Rules 6 Apr 06 Nomenclature x, y longitudinal, spanwise positions S reference area (wing area) b wing span c average wing chord ( = S/b ) AR wing aspect ratio C L lift
More informationAIRCRAFT SYSTEMS EQUIPMENT
Intentionally left blank PRELIMINARY PAGES - TABLE OF CONTENTS DSC-25-10 Flight Deck DSC-25-10-10 General GENERAL... A PRINCIPLES FOR PUSHBUTTONS WITH INTEGRATED INDICATIONS...B GENERAL ARRANGEMENT...C
More informationElectronic Manual Gearbox
Service. Self-Study Programme 221 Electronic Manual Gearbox Design and Function Taking the Lupo as the basis, Volkswagen has developed the world's first 3 L car that will also go into volume production.
More informationMaintenance manual DG-1000S. 0.1 Manual amendments No. Page Description Date 1 0.5, 0.6, 4.14-4.16 diagrams 7, 11, 12
Maintenance manual DG-1000S 0 General 0.1 Manual amendments No. Page Description Date 1 0.5, 0.6, 4.14-4.16 diagrams 7, 11, 12 Manual revision TN413/2 September 2003 2 0.6, diagrams 1 and 11 Manual revision
More information0 28 November 2011 N/A First Release of Manual 1 24 February 2012 Page 21 Error in FY31AP connection diagram corrected.
Rev 1: 24 February 2012 FEIYU TECH FY31AP Autopilot System Installation & Operation Guide Guilin Feiyu Electronic Technology Co., Ltd Rm. B305, Innovation Building, Information Industry Park, Chaoyang
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
UNSCHEDULED MAINTENANCE CHECKS 1. DESCRIPTION The following describes those maintenance checks and inspections on the aircraft which are dictated by special or unusual conditions which are not related
More informationAutomation at Odds. A 737 stalled when a radio altimeter malfunction caused the autothrottle and autopilot to diverge during an approach to Schiphol.
Automation at Odds The pilots of a Boeing 737-800 did not heed indications of a significant decrease in airspeed until the stick shaker activated on final approach to Runway 18R at Amsterdam (Netherlands)
More informationFlightlab Ground School 5. Longitudinal Static Stability
Flightlab Ground School 5. Longitudinal Static Stability Copyright Flight Emergency & Advanced Maneuvers Training, Inc. dba Flightlab, 2009. All rights reserved. For Training Purposes Only Longitudinal
More informationCessna 172SP & NAV III Maneuvers Checklist
Cessna 172SP & NAV III Maneuvers Checklist Introduction Power Settings This document is intended to introduce to you the standard method of performing maneuvers in Sunair Aviation s Cessna 172SP and NAV
More informationparts of an airplane Getting on an Airplane BOX Museum Aeronautics Research Mission Directorate in a Series
National Aeronautics and Space Administration GRADES K-2 Aeronautics Research Mission Directorate Museum in a BOX Series www.nasa.gov parts of an airplane Getting on an Airplane MUSEUM IN A BOX Getting
More informationMODULE 11B. PISTON AEROPLANE AERODYNAMICS, STRUCTURES AND SYSTEMS
MODULE 11B. PISTON AEROPLANE AERODYNAMICS, STRUCTURES AND SYSTEMS Note: The scope of this Module should reflect the technology of aeroplanes pertinent to the A2 and B1.2 subcategory. 11.1 Theory of Flight
More informationINSTRUCTION MANUAL. Specification: collective pitch 3D quadcopter. TYPE: Collective Pitch Electric 3D Quadcopter. Rotor Diameter: 118MM.
collective pitch 3D quadcopter INSTRUCTION MANUAL Specification: TYPE: Collective Pitch Electric 3D Quadcopter Rotor Diameter: 118MM Length:635 MM Width: 365 MM Weight: 986g w/out battery Flying weight
More informationAirglas, Inc. MANUAL NO. GLH3000-105-AHSA. MODEL GLH3000 Ski Kit Actuated by Wipaire, Inc. Amphibious Float Hydraulic System
Airglas, Inc. Amphibious hydraulic system addendum to Instructions for Continued Airworthiness Including Installation, Maintenance and Service Instructions MANUAL NO. GLH3000-105-AHSA MODEL GLH3000 Ski
More informationMcCAULEY FULL FEATHERING CONSTANT SPEED PROPELLER GOVERNING SYSTEM. Professor Von Kliptip Answers Your Questions About The
Professor Von Kliptip Answers Your Questions About The McCAULEY FULL FEATHERING CONSTANT SPEED PROPELLER GOVERNING SYSTEM FOR COUNTERWEIGHTED PRESSURE-TO- DECREASE PITCH PROPELLERS ON RECIPROCATING ENGINES
More informationAssembly and Operating Manual Nano warbirds FW 190 Specification: *Length: 18 1/2"(470mm) *Wing Span: 21 7/10"(550mm)
Assembly and Operating Manual Nano warbirds FW 190 Specification: *Length: 18 1/2"(470mm) *Wing Span: 21 7/10"(550mm) *Flying Weight: 6 1/2 oz (185g) Dear customer, Congratulations on your choice of a
More informationPneumatic Air Conditioning Pressurization
EMBRAER 135/145 Pneumatic Air Conditioning Pressurization GENERAL The pneumatic system can be supplied by the engines, APU or a ground pneumatic source. The APU or ground pneumatic source supplies the
More informationSECTION G2: CABLE PROCESSOR MODULE MAINTENANCE
SECTION G2: CABLE PROCESSOR MODULE MAINTENANCE Cable Processor Module overview WARNING! When tipping the Cable Processor Module back, (after removing the toggle arm pin), use extreme caution not to drop
More informationAviation Safety Prize ecfi Tasks
2008 NASA "The PAV Challenge" Aviation Safety Prize ecfi Tasks The Aviation Safety Prize (ASP) will be based upon a set of defined tasks that can be flight demonstrated to the CAFE Test Pilots by each
More informationConfiguring FSUIPC with the CH USB Yoke, Rudder Pedals and Throttle Quadrant. version 1.10. by John Cook
Configuring FSUIPC with the CH USB Yoke, Rudder Pedals and Throttle Quadrant. version 1.10 by John Cook This guide describes using FSUIPC to setup the CH USB Yoke, CH Pedals and CH Throttle Quadrant. FSUIPC
More informationServo Info and Centering
Info and Centering A servo is a mechanical motorized device that can be instructed to move the output shaft attached to a servo wheel or arm to a specified position. Inside the servo box is a DC motor
More informationGeneral Characteristics
This is the third of a series of Atlantic Sun Airways CAT C pilot procedures and checklists for our fleet. Use them with good judgment. Note, the start procedures may vary from FS9 Panel to Panel. However
More informationThis file contains the full script of the corresponding video, published on YouTube. November 2014: http://youtu.be/wbu6x0hsnby
This file contains the full script of the corresponding video, published on YouTube. November 2014: http://youtu.be/wbu6x0hsnby Background papers and links to formal FAA and EASA Aviation Regulations and
More informationElectric Landing Gear controllers and sequencer LGC12 / LGC 13C
Electric Landing Gear controllers and sequencer LGC12 / LGC 13C Users Guide. Torrent d en Puig, 31. 08358, Arenys de Munt, Barcelona,Catalonia,Spain E-mail: info@xicoy.com. Fax: +34 933 969 743 web: www.xicoy.com
More informationBrief introduction----------------------------------------------------------------------------03
A-1 skyraider Brief introduction----------------------------------------------------------------------------03 Specification----------------------------------------------------------------------------------03
More informationCertification Specifications for Very Light Aeroplanes CS-VLA
European Aviation Safety Agency Certification Specifications for Very Light Aeroplanes CS-VLA Amendment 1 5 March 2009 1-0-1 CONTENTS (Layout) CS VLA VERY LIGHT AEROPLANES BOOK 1 AIRWORTHINESS CODE SUBPART
More informationMicro. Pitts Special for the RFFS-100 by Chris O Riley
Micro Pitts Special for the RFFS-100 by Chris O Riley F1 F2 F3 F4 1 2 3 4 All wood 1/32 inch sheet unless otherwise stated. F1 F2 F3 F4 Small balsa blocks for LG reinforcement Small balsa blocks for LG
More informationFile Number MDRA C20 MANUAL of PROCEDURES for INSPECTION of COMPOSITE AMATEUR-BUILT AIRCRAFT, INSPECTION AND TECHNICAL INFORMATION RECORD
File Number MDRA C20 MANUAL of PROCEDURES for INSPECTION of COMPOSITE AMATEUR-BUILT AIRCRAFT, INSPECTION AND TECHNICAL INFORMATION RECORD GENERAL Section 1.4 FINAL INSPECTION 1. Have all re-inspection
More informationHigh Alpha 3D Maneuvers
High Alpha 3D Maneuvers Harrier Pass Elevator Back Flip Parachute Whip Stalls Rolling Harrier 3D Rolling Turn 3D Knife Edge C-82 Rudder Warmup Note: Every flight mode and maneuver presented in this section
More informationCENTURY III AUTOPILOT FLIGHT SYSTEM
CENTURY III AUTOPILOT FLIGHT SYSTEM PILOT S OPERATING HANDBOOK NOVEMBER 1998 68S25 NOTICE 68S25 This manual contains General Information on operation of Century III Autopilot. specific FAA approved information
More informationThis section includes performance data on the King Air B200. Information consists of:
King Air B200 POH Pilot's Operating Handbook: This section includes performance data on the King Air B200. Information consists of: 1. Critical Airspeeds 2. Operating NOTAMS 3. Fuel Loading Formula Checklists:
More informationFSI LOGO Revision 1.0
FSI LOGO Revision 1.0 HELICOPTER OPERATIONS MODERN HELICOPTERS MODERN HELICOPTERS MODERN HELICOPTERS MODERN HELICOPTERS HUMS Ground Station Overview Health and Usage Monitoring System Ground Station Help
More informationTroubleshooting Guide for Jacks Down LED Lights
Troubleshooting Guide for Jacks Down LED Lights Equalizer Systems Auto-Level systems manufactured after 2005 feature a pressure switch system that monitors the retracted state of leveling jacks and any
More informationKing Air C90A. Speeds (KIAS)
King Air C90A Speeds (KIAS) V MCA 90 V SSE 97 V X 101 V Y 111 V XSE 100 V YSE 107 V A 169 V REF 100 V MO 208 V FE 178 35% 137 100% V LE 156 129 Retraction only Other 95 Balked landing climb 125 Glide 161
More informationCompiled by Matt Zagoren
The information provided in this document is to be used during simulated flight only and is not intended to be used in real life. Attention VA's - you may post this file on your site for download. Please
More informationVolkswagen B3 Passat Manual Transmission 02A 34 Manual Transmission - Controls, Assembly (Page GR-34) 02A 5-speed. Gearshift cable/lever installing
34 Manual Transmission - Controls, Assembly (Page GR-34) 02A 5-speed Gearshift cable/lever installing Gearshift housing repairing Gearshift lever repairing lever/relay lever, installing Gearshift mechanism
More informationAUTO TRANS DIAGNOSIS Article Text 1998 Volkswagen Passat This file passed thru Volkswagen Technical Site - http://volkswagen.msk.
AUTO TRANS DIAGNOSIS Article Text 1998 Volkswagen Passat This file passed thru Volkswagen Technical Site - http://volkswagen.msk.ru ARTICLE BEGINNING 1997-98 AUTOMATIC TRANSMISSIONS Volkswagen Shift Interlock
More informationSERVICE PARTS LIST PAGE 1 OF 6 BASE ASSEMBLY SPECIFY CATALOG NO. AND SERIAL NO. WHEN ORDERING PARTS 12" DUAL BEVEL COMPOUND MITER SAW B27A
PAGE 1 OF 6 BASE ASSEMBLY 00 0 EXAMPLE: Component Parts (Small #) Are Included When Ordering The Assembly (Large #). SPECIFY CATALOG NO. AND NO. WHEN ORDERING PARTS 1 02-80-0050 Thrust Bearing (1) 2 05-80-0510
More informationINSTRUCTION MANUAL. Black Angel. www.copterx.com. Features. Kit Helicopter. Copyright 2009 KY MODEL Company Limited.
INSTRUCTION MANUAL Features - Carbon fiber main blade, tail blade, fly paddle, tail fin for extra weight saving and durability. - CNC machined high grade aluminum rotor head and tail gear box to ensure
More informationAVIATION OCCURRENCE REPORT
AVIATION OCCURRENCE REPORT REJECTED LANDING/LOSS OF CONTROL FIRST AIR DHC-6 SERIES 300 C-GNDN IQALUIT, NORTHWEST TERRITORIES 85 NM NW 12 AUGUST 1996 REPORT NUMBER A96Q0126 The Transportation Safety Board
More informationFUEL. Fuel is contained in three tanks located within the wings and wing center section.
Smartcockpit.com BOEING 737 SYSTEMS REVIEW Page 1 FUEL 1. GENERAL Fuel is contained in three tanks located within the wings and wing center section. There a 3 tanks : Main tanks No. 1 and No. 2 are integral
More informationVEHICLE THEFT/SECURITY SYSTEMS
DN VEHICLE THEFT/SECURITY SYSTEMS 8Q - 1 VEHICLE THEFT/SECURITY SYSTEMS TABLE OF CONTENTS page GENERAL INFORMATION INTRODUCTION...1 VEHICLE THEFT SECURITY SYSTEM....1 ENABLING...1 ARMING...1 DISARMING...2
More informationUnit 24: Applications of Pneumatics and Hydraulics
Unit 24: Applications of Pneumatics and Hydraulics Unit code: J/601/1496 QCF level: 4 Credit value: 15 OUTCOME 2 TUTORIAL 4 DIRECTIONAL CONTROL VALVES The material needed for outcome 2 is very extensive
More informationCYCLOPS OSD USER MANUAL 5.0
CYCLOPS OSD USER MANUAL 5.0 Thank you for choosing CYCLOPS OSD V5.0 New features: CYCLOPS OSD V5.0 is incorporated with Autopilot function and infrared attitude sensor capable of controlling aircraft's
More informationPUSH BUTTON START INSTALLATION MANUAL
PUSH BUTTON START INSTALLATION MANUAL ALTHOUGH THIS PRODUCT HAS BEEN THOROUGHLY TESTED KPIERSON TECHNOLOGIES ASSUMES NO RESPONSIBILITY FOR ANY DAMAGE THAT MAY RESULT BY THE INSTALLATION OF THIS PRODUCT.
More informationEuropean Aviation Safety Agency
European Aviation Safety Agency ED Decision 2003/2/RM Final 17/10/2003 The Executive Director DECISION NO. 2003/2/RM OF THE EXECUTIVE DIRECTOR OF THE AGENCY of 17 October 2003 on certification specifications,
More informationThe Starting System. Section 4. Starting System Overview. Starter. The starting system:
The Starting System Starter The starter motor drives the engine through a pinion gear that engages the ring gear on the flywheel. Fig. 4-01 TL623f401c Starting System Overview The starting system: Uses
More informationBOMBARDIER CRJ700. Bombardier CRJ700 Aircraft Reference
Bombardier CRJ700 Aircraft Reference V 1 Takeoff Decision Speed, dry runway 50,000 lbs, (flaps 8) 144 KIAS 50,000 lbs, (flaps 20) 134 KIAS V R Rotation Speed, dry runway 50,000 lbs, (flaps 8) 144 KIAS
More informationCertification Specifications for Large Rotorcraft CS-29
European Aviation Safety Agency Certification Specifications for Large Rotorcraft CS-29 11 December 2012 CS-29 CONTENTS (general layout) CS 29 LARGE ROTORCRAFT BOOK 1 CERTIFICATION SPECIFICATIONS SUBPART
More informationFlight Operations Briefing Notes
Flight Operations Briefing Note I Introduction Operations in crosswind conditions require strict adherence to applicable crosswind limitations or maximum recommended crosswind values, operational recommendations
More informationElectronic Flight Instrument System (EFIS)
Electronic Flight Instrument System (EFIS) An electronic flight instrument system (EFIS) is a flight deck instrument display system in which the display technology used is electronic rather than electromechanical.
More informationSET-UP AND INSTALLATION FOR LEAD SCREW CARTRIDGE ASSEMBLY
SET-UP AND INSTALLATION FOR LEAD SCREW CARTRIDGE ASSEMBLY 82-13-1 O-Ring (Rear) The Lead Screw Assembly is shipped separately. Note: Install Electrical and Pneumatic Circuitry. Be Sure electrical and pneumatic
More informationTOYOTA Tundra 2007 - BACK-UP CAMERA SYSTEM Preparation
Preparation Part Number(s): PT233-34070, PT923-35070-11, PT923-35070-43 NOTE: Part number of this accessory may not be the same as part number shown. Back Up Monitor Kit Contents PT923-35070-11 / PT923-35070-43
More informationReport. Incident on 2 May 2009 on approach to Antalya (Turkey) to the Boeing 737-300 registered F-GFUF operated by Europe Airpost
Report Incident on 2 May 2009 on approach to Antalya (Turkey) to the Boeing 737-300 registered F-GFUF operated by Europe Airpost Bureau d Enquêtes et d Analyses pour la sécurité de l aviation civile Ministère
More informationThe 02E Direct Shift Gearbox Design and Function
The 02E Direct Shift Gearbox Design and Function Self-Study Program Course Number 851403 Volkswagen of America, Inc. Service Training Printed in U.S.A. Printed 05/2004 Course Number 851403 2004 Volkswagen
More informationMcCAULEY CONSTANT SPEED PROPELLER GOVERNING SYSTEM
Professor Von Kliptip Answers Your Questions About The McCAULEY CONSTANT SPEED PROPELLER GOVERNING SYSTEM FOR NON-COUNTERWEIGHTED PRESSURE TO INCREASE PITCH PROPELLERS ON TYPICAL SINGLE ENGINE AIRCRAFT
More informationSection 9. Pitot Static System. 1 of 6
1 of 6 ITOT STATIC SYSTEM General The pitot static systems operate the Air Speed Indicator, Vertical Speed Indicator and the Altitude Indicator for each pilot. In addition, fitted into the Co-pilot's system,
More informationSignature and ISX CM870 Electronics
Signature and ISX CM870 Electronics Cummins West Training Center System Description General Information The Signature and ISX CM870 engine control system is an electronically operated fuel control system
More informationTOYOTA ELECTRONIC TRANSMISSION CHECKS & DIAGNOSIS
Checks and Adjustments The transmission requires regular maintenance intervals if it is to continue to operate without failure. As we discussed in previous sections, transmission fluid loses certain properties
More informationSuper King Air 200. Speeds (KIAS)
Super King Air 200 Speeds (KIAS) V MCA 86 V SSE 104 V X 100 V Y 125 V XSE 115 V YSE 121 V A 181 V REF 103 132 with no flap V MO 260 270 for old models M MO 0,52 0,48 for old models V FE 200 40% 146 100%
More informationThis is the third of a series of Atlantic Sun Airways CAT B pilot procedures and checklists for our fleet. Use them with good judgment.
This is the third of a series of Atlantic Sun Airways CAT B pilot procedures and checklists for our fleet. Use them with good judgment. Dimensions: Span 107 ft 10 in Length 147 ft 10 in Height 29ft 7 in
More informationCHAPTER 65 TAIL ROTOR DRIVE SYSTEM. Section Title Page
CHAPTER 65 TAIL ROTOR DRIVE SYSTEM Section Title Page 65-00 Description........................................ 65.1 65-10 Tail Rotor Drive Fan Shaft.............................. 65.1 65-20 Tail Rotor
More informationIntroduction to RC Airplanes. RC Airplane Types - Trainers, Sport RC Planes, 3D Acrobat RC Airplanes, Jets & More
Introduction to RC Airplanes RC Airplane Types - Trainers, Sport RC Planes, 3D Acrobat RC Airplanes, Jets & More RC Airplane Types RC airplanes come in a few distinct categories. Each category generally
More informationTRANSMISSION INSTALLATION CONTENTS
A Regal Beloit Company TRANSMISSION INSTALLATION CONTENTS RICHMOND 6-SPEED AND SUPER STREET 5-SPEED WITH OVER DRIVE TRANS AM, CAMARO, CHEVELLE, GTO, CUTLASS, WITH T-10/MUNCIE....2 RICHMOND 6-SPEED 1963
More informationR02GA. July 31, 2002. Dear Blue Bird Owner:
R02GA July 31, 2002 Dear Blue Bird Owner: This notice is sent to you in accordance with the requirements of the National Traffic and Motor Vehicle Safety Act. Blue Bird Body Company has determined that
More information38699 000 Page 1. Description
38699 000 Page 1 Description Tectron Surf for flushing cistern GD 2 concealed installation CE-approved front plate 156 x 197 mm infra-red control servo motor transformer for external installation operating
More informationElectrical Systems - IQAN Digital Control System. IQAN Control System Components... 5.1.3
Section 5.1 Electrical Systems - IQAN Digital Control System IQAN Control System Components........................... 5.1.3 IQAN Operational Description: At Machine Startup.....................................
More informationModel SETR-50 and SETR-51 Trim Tab Control
Model SETR-50 and SETR-51 Trim Tab Control Pictured above is the SETR-50 with black switches on a gray background. The SETR-51 is identical except for the color, wherein it has black switches on a black
More informationharbor cub Electric Remote Control Airplane Model 92906 assembly & Operating Instructions
harbor cub Electric Remote Control Airplane Model 92906 assembly & Operating Instructions IMPORTANT: If damage is caused due to a crash, your warranty is void. Visit our website at: http://www.harborfreight.com
More informationAdaptive cruise control (ACC)
Adaptive cruise control (ACC) PRINCIPLE OF OPERATION The Adaptive Cruise Control (ACC) system is designed to assist the driver in maintaining a gap from the vehicle ahead, or maintaining a set road speed,
More informationThis is the fourth of a series of Atlantic Sun Airways CAT B pilot procedures and checklists for our fleet. Use them with good judgment.
This is the fourth of a series of Atlantic Sun Airways CAT B pilot procedures and checklists for our fleet. Use them with good judgment. Dimensions: Wing Span: 112 ft 7 in Length: 129 ft 6 in Height: 41
More informationFor Information Only-Not approved for cockpit use.
For Information Only-Not approved for cockpit use. List of Effective Pages *The asterisk indicates pages changed, added, or deleted by current change. Record of Revisions REVISION REVISION NUMBER DATE
More information