AOPA PILOT Article

Total Page:16

File Type:pdf, Size:1020Kb

AOPA PILOT Article What Went Wrong? Strange Birds Beware the Vortex FUEL TANK CONFUSION p. 74 50 IMPROBABLE DESIGNS P. 27 ROTOR TECHNIQUE REVEALED P. 78 TURBINE EDITION The Voice of General Aviation aopa.org/pilot | February 2020 | $10.95 February 2020 February Pilatus PC–12 NGX | Phenom Icing Accident |World War II Nose Art | What Went Wrong? Wrong? II Nose Art | What Went War Accident |World NGX | Phenom Icing Pilatus PC–12 Icy Approach A PHENOM STALLS AT THE THRESHOLD p. T-11 PILATUS PC–12 NGX Farm to Fuel CAN JET BIOFUELS First to TAKE OFF? p. T-7 FADEC Turboprop Automation, Startup to Shutdown p. T-14 aopa.org TURBINE PILOT T-2 FROM THE EDITOR T-4 FINANCE T-7 JET BIOFUELS T-11 ACCIDENT T-14 PC–12 NGX A SPECIAL SECTION FOR THE TURBINE OWNER-PILOT First-class step up Sure, PC–12s are known for their utilitarian aspects, but Where: Stans, Switzerland the new PC–12 NGX brings a heavier emphasis on creature Photography: Courtesy of Pilatus Business Aircraft comforts. The seats, lighting, and environmental systems have all been given makeovers based on customer input. aopa.org/pilot AOPA PILOT | T-1 THE BEST TIME TO FLY THE BEST IS NOW Introducing the brand-new PC-12 NGX, the most advanced single-engine turboprop ever. Featuring general aviation’s first Electronic Propeller and Engine Control System, a digital autothrottle, enhanced avionics with smart touch screen controller, a completely redesigned cabin with larger windows and new BMW Designworks interior. And all that at reduced operating costs and more speed. With the PC-12 NGX, Pilatus just made the best even better. Pilatus Business Aircraft Ltd • USA • +1 303 465 9099 • www.pilatus-aircraft.com | PILATUS PC–12 NGX | DIGITAL PIONEER Optimizing an enduring favorite TO THE CASUAL OBSERVER, ALL PILATUS PC–12S MAY LOOK ALIKE. True, their basic appear- ance hasn’t changed a great deal since the original PC–12 made its 1994 debut, but deep down the airplane has gone through a series of gross weight increases and other significant improvements. In 2008, the PC–12 NG brought Honeywell’s Apex glass cockpit to the air- plane, among other performance and system upgrades. The Apex avionics suite replaced the original PC–12’s old-school Bendix/King panel, with its round gauges and KLN90B GPS navigator. But the biggest news came in 2019 with the introduction of the latest model: the PC–12 NGX. BY THOMAS A. HORNE PHOTOGRAPHY COURTESY OF PILATUS BUSINESS AIRCRAFT LTD. T-14 | AOPA PILOT February 2020 PIONEER aopa.org/pilot AOPA PILOT | T-15 THE NEW PC-12 NGX retains Pilatus’ TURBOPROP REVOLUTION addition to push-button start, this means signature large aft cabin door In a recent video (aopa.org/turbine/engine- that a digital electronic engine control (above) but there are many new enhancements as well—like the start), I explained the basic steps in starting (EEC) unit applies its logic to control and redesigned leather seats (above a Pratt & Whitney PT6 turboprop engine— monitor the -67XP. About to have a hot right) with optional footrests, new similar to the ones in PC–12s and PC–12 start? The FADEC will automatically shut sidewall ledges with oxygen mask stowage compartments, down- NGs. It featured the sequence familiar to the engine down. And for all the other wash lighting, and cabin windows many PT6 drivers: checking the battery for steps in a start sequence, the FADEC han- 10 percent larger than previous adequate power, spooling up to 13 percent dles them as well. There are still other models. All cabin seats are fitted with quick-release hardware, Ng, moving the condition lever to low idle, protections—against overtorques, surges, where before only the last two waiting for the lightoff, switching on the and flameouts, to name a few. If it’s above seats had this feature. generator at 50 percent Ng, and watching 26 degrees Celsius during shutdown, the out for an ITT rise that signals a hot start. engine will motor itself for a few seconds Well, the PC–12 NGX does away with all to help it cool down. that by automating the start with the sin- But wait, as the late-night TV ads say, gle flip of a switch. there’s more. The NGX’s PT6E-67XP Yes, for those pining away for a Pratt (the “E” is for electronic) also comes with & Whitney PT6 with a single-lever power autothrottle. Press the AT button and set control and full-authority digital engine a desired airspeed on the glareshield- controls (FADEC), the NGX has answered mounted flight guidance panel, and the their prayers. The airplane’s PT6E-67XP is autothrottle responds with the power the launch platform for Pratt & Whitney’s required, whether in climb, cruise, or first, and long-awaited, foray into the descent. Meanwhile, the power control world of turboprop engine automation. In lever (PCL) moves on its own as power T-16 | AOPA PILOT February 2020 SPEC SHEET Pilatus PC–12 NGX BASE PRICE: $4.39 MILLION TYPICAL EXECUTIVE CONFIGURATION PRICE: $5.37 MILLION SPECIFICATIONS Max operating altitude | 30,000 ft Powerplant | Pratt & Whitney PT6E-67XP, 1,200 shp Landing distance over 50-ft obstacle | 2,170 ft Propeller | Hartzell 105-in dia, 5-blade composite, feathering and reversible LIMITING AND RECOMMENDED AIRSPEEDS V (rotation) | Length | 47 ft 3 in R 82 KIAS V (best angle of climb) | Height | 14 ft X 120 KIAS V (best rate of climb) | Wingspan | 53 ft 6 in Y 130 KIAS V (design maneuvering) | Wing loading | 37.6 lb/sq ft A 166 KIAS V (max flap extended, 15 degrees) | Seats | 1 + 8-10 FE 165 KIAS Cabin length | 16 ft 11 in 30 degrees | 130 KIAS Cabin width | 5 ft 40 degrees | 130 KIAS V (max gear extended) | Cabin height | 4 ft 10 in LE 240 KIAS V (max gear operating) | Cabin volume | 330 cu ft LO 180 KIAS V (reference speed, final approach) | Basic empty weight | 6,173 lb REF 82 KIAS V (max operating speed below 16,300 ft) | Max ramp weight | 10,495 lb MO 240 KIAS M (max Mach number, above 16,300 ft) | Max takeoff weight | 10,450 lb MO M 0.49 V (stall, in landing configuration) | Max zero fuel weight | 9,039 lb SO 67 KIAS Max useful load | 4,277 lb Max landing weight | 9,921 lb FOR MORE INFORMATION contact pilatus-aircraft. Fuel capacity | 406.8 gal (402 gal usable) com/en/fly/pc-12 Max cargo weight, baggage area | 400 lb, 40 cu ft AOPA Finance estimates a monthly payment of Cabin | 3,300 lb, 330 cu ft $23,100 with 15 percent down, a 4.2-percent rate, a five-year term, and 20-year amortization. PERFORMANCE Takeoff distance over 50-ft obstacle | 2,485 ft All specifications are based on manufacturer’s calcu- Rate of climb, sea level | 1,920 fpm lations. All performance figures are based on standard Max cruise speed | 290 KTAS day, standard atmosphere, maximum weight conditions Max range, 4 pax | 1,803 nm unless otherwise noted. requirements rise or fall—as if a ghostly the electronic propeller governor’s normal, smaller-diameter, insulated fuel lines to a hand were in charge. Looking for a manual 1,700 propeller rpm and a lower, 1,550-rpm fuel filter attached to an engine-mounted override (MOR) or condition lever? Don’t mode for a quieter cabin. Except for take- fuel control unit. Before reaching that fuel bother. The dual-channel FADEC handles off—when the FADEC will automatically filter, fuel is warmed by an oil-to-fuel heat those functions as well. command 1,700 rpm—you can use low-speed exchanger. A fuel temperature gauge on the Digital engine control offers other ben- mode at any time. In cruise, Pilatus says that cockpit multifunction display indicates fuel efits in the PC–12 NGX. The PCL is linear the penalty is a paltry one to two knots. temperature as it enters the filter. in its power application, free of any of the The new engine also has the latest sin- flat spots or lags of the sort that can affect gle-crystal compressor blade metallurgy and ACE AVIONICS fuel control units managed by traditional, improved cooling for the power turbine sec- The PC–12 NGX retains the PC–12 NG’s manually controlled pushrod linkages. And tion. Together with the other enhancements, Honeywell Epic-based glass cockpit plat- although the NGX’s engine has the same this gives the PT6E-67XP a 5,000-hour time form, but in view of some added elements 1,200-shaft-horsepower maximum power between overhauls (it was 3,500 hours in ear- Pilatus calls the NGX’s panel the Advance output as previous PC–12s, its digital torque lier PC–12s), and maintenance intervals every Cockpit Environment (ACE)—which is also limiting function is much more precise, 600 hours—twice that of previous PC–12s. the name Pilatus gave to the avionics suite in which Pilatus says permits up to 10 percent its jet, the PC–24. more thrust in climb and cruise. This gives WARMER FUEL The ACE’s four huge display screens sure the airplane a published maximum cruise Changes to the fuel system yield another look like those of the EASy cockpits in newer speed of 290 knots—five knots faster than advantage: Prist, an anti-icing fuel addi- Falcon jets, especially the primary flight dis- earlier PC–12 models. tive, is not required. New, higher-pressure plays that show flight information, engine Another innovation is a low, 1,550-rpm jet pumps and boost pumps in the wing data, and nav/com frequencies on their split propeller setting.
Recommended publications
  • Mise En Page 1
    Military EC725 002 EC725 EC725 003 EC725 DESIGNED FOR THE MOST DEMANDING MISSIONS A COMBAT PROVEN MULTI-ROLE HELICOPTER Introduced in 2005, the EC725 has proven itself in combat service worldwide: Afghanistan, Lybia and Mali. An evolution from the experience gained with the Cougar family, the EC725 is the latest version of this medium lift (11-ton class) helicopter. The EC725 is equipped with: • Two latest generation Turbomeca Makila 2A1 engines • A five-blade rotor providing high levels of maneuverability • A state-of the-art glass cockpit and avionics • The most advanced Automatic Flight Control System. The EC725 excels in a full range of military missions: • Special Operations • Combat Search and Rescue • Tactical transport • Casualty / medical evacuation. As well as in public service missions: • Search and Rescue • Firefighting • Coast Guard • Exclusive Economic Zone (EEZ) protection. The EC725 - a truly multi-purpose, versatile military asset – has the capability to operate both from ships and from ashore. 004 EC725 The most demanding missions Special Ops, Combat SAR and Personal Recovery missions require performance, precise navigation and survivability; qualities for which the EC725 is outstanding. The French Forces are successfully operating the EC725 in the harshest environments. The success of the EC725 demonstrated in Afghanistan and Libya, reflects its excellent capabilities as a Force Multiplier and the ability of this aircraft to offer decisive tactical advantage to any operator. EC725 005 Mission Capabilities Major mission
    [Show full text]
  • Download the Pbs Auxiliary Power Units Brochure
    AUXILIARY POWER UNITS The PBS brand is built on 200 years of history and a global reputation for high quality engineering and production www.pbsaerospace.com AUXILIARY POWER UNITS by PBS PBS AEROSPACE Inc. with headquarters in Atlanta, GA, is the world’s leading manufacturer of small gas turbine propulsion and power products for UAV’s, target drones, small missiles and guided munitions. The demonstrated high quality and reliability of PBS gas turbine engines and power systems are refl ected in the fact that they have been installed and are being operated in several thousand air vehicle systems worldwide. The key sector for PBS Velka Bites is aerospace engineering: in-house development, production, testing, and certifi cation of small turbojet, turboprop and turboshaft engines, Auxiliary Power Units (APU), and Environmental Control Systems (ECS) proven in thousands of airplanes, helicopters, and UAVs all over the world. The PBS manufacturing program also includes precision casting, precision machining, surface treatment and cryogenics. Saphir 5 Safir 5K/G MI Saphir 5F Safir 5K/G MIS Safir 5L Safir 5K/G Z8 PBS APU Basic Parameters Basic parameters APU MODEL Electrical power Max. operating Bleed air fl ow Weight output altitude Units kVA, kW lb/min lb ft 70.4 26,200 S a fi r 5 L 0 kVA 73 → Up to 60 kVA of electric power Safír 5K/G Z8 40 kVa N/A 113.5 19,700 output Safi r 5K/G MI 20 kVa 62.4 141 19,700 Up to 70.4 lb/min of bleed air flow Safi r 5K/G MIS 6 kW 62.4 128 19,700 → Main features of PBS Safi r 5 product line → Simultaneous supply of electric
    [Show full text]
  • Propeller Operation and Malfunctions Basic Familiarization for Flight Crews
    PROPELLER OPERATION AND MALFUNCTIONS BASIC FAMILIARIZATION FOR FLIGHT CREWS INTRODUCTION The following is basic material to help pilots understand how the propellers on turbine engines work, and how they sometimes fail. Some of these failures and malfunctions cannot be duplicated well in the simulator, which can cause recognition difficulties when they happen in actual operation. This text is not meant to replace other instructional texts. However, completion of the material can provide pilots with additional understanding of turbopropeller operation and the handling of malfunctions. GENERAL PROPELLER PRINCIPLES Propeller and engine system designs vary widely. They range from wood propellers on reciprocating engines to fully reversing and feathering constant- speed propellers on turbine engines. Each of these propulsion systems has the similar basic function of producing thrust to propel the airplane, but with different control and operational requirements. Since the full range of combinations is too broad to cover fully in this summary, it will focus on a typical system for transport category airplanes - the constant speed, feathering and reversing propellers on turbine engines. Major propeller components The propeller consists of several blades held in place by a central hub. The propeller hub holds the blades in place and is connected to the engine through a propeller drive shaft and a gearbox. There is also a control system for the propeller, which will be discussed later. Modern propellers on large turboprop airplanes typically have 4 to 6 blades. Other components typically include: The spinner, which creates aerodynamic streamlining over the propeller hub. The bulkhead, which allows the spinner to be attached to the rest of the propeller.
    [Show full text]
  • FAA Advisory Circular AC 91-74B
    U.S. Department Advisory of Transportation Federal Aviation Administration Circular Subject: Pilot Guide: Flight in Icing Conditions Date:10/8/15 AC No: 91-74B Initiated by: AFS-800 Change: This advisory circular (AC) contains updated and additional information for the pilots of airplanes under Title 14 of the Code of Federal Regulations (14 CFR) parts 91, 121, 125, and 135. The purpose of this AC is to provide pilots with a convenient reference guide on the principal factors related to flight in icing conditions and the location of additional information in related publications. As a result of these updates and consolidating of information, AC 91-74A, Pilot Guide: Flight in Icing Conditions, dated December 31, 2007, and AC 91-51A, Effect of Icing on Aircraft Control and Airplane Deice and Anti-Ice Systems, dated July 19, 1996, are cancelled. This AC does not authorize deviations from established company procedures or regulatory requirements. John Barbagallo Deputy Director, Flight Standards Service 10/8/15 AC 91-74B CONTENTS Paragraph Page CHAPTER 1. INTRODUCTION 1-1. Purpose ..............................................................................................................................1 1-2. Cancellation ......................................................................................................................1 1-3. Definitions.........................................................................................................................1 1-4. Discussion .........................................................................................................................6
    [Show full text]
  • Comparison of Helicopter Turboshaft Engines
    Comparison of Helicopter Turboshaft Engines John Schenderlein1, and Tyler Clayton2 University of Colorado, Boulder, CO, 80304 Although they garnish less attention than their flashy jet cousins, turboshaft engines hold a specialized niche in the aviation industry. Built to be compact, efficient, and powerful, turboshafts have made modern helicopters and the feats they accomplish possible. First implemented in the 1950s, turboshaft geometry has gone largely unchanged, but advances in materials and axial flow technology have continued to drive higher power and efficiency from today's turboshafts. Similarly to the turbojet and fan industry, there are only a handful of big players in the market. The usual suspects - Pratt & Whitney, General Electric, and Rolls-Royce - have taken over most of the industry, but lesser known companies like Lycoming and Turbomeca still hold a footing in the Turboshaft world. Nomenclature shp = Shaft Horsepower SFC = Specific Fuel Consumption FPT = Free Power Turbine HPT = High Power Turbine Introduction & Background Turboshaft engines are very similar to a turboprop engine; in fact many turboshaft engines were created by modifying existing turboprop engines to fit the needs of the rotorcraft they propel. The most common use of turboshaft engines is in scenarios where high power and reliability are required within a small envelope of requirements for size and weight. Most helicopter, marine, and auxiliary power units applications take advantage of turboshaft configurations. In fact, the turboshaft plays a workhorse role in the aviation industry as much as it is does for industrial power generation. While conventional turbine jet propulsion is achieved through thrust generated by a hot and fast exhaust stream, turboshaft engines creates shaft power that drives one or more rotors on the vehicle.
    [Show full text]
  • PROPULSION SYSTEM/FLIGHT CONTROL INTEGRATION for SUPERSONIC AIRCRAFT Paul J
    PROPULSION SYSTEM/FLIGHT CONTROL INTEGRATION FOR SUPERSONIC AIRCRAFT Paul J. Reukauf and Frank W. Burcham , Jr. NASA Dryden Flight Research Center SUMMARY The NASA Dryden Flight Research Center is engaged in several programs to study digital integrated control systems. Such systems allow minimization of undesirable interactions while maximizing performance at all flight conditions. One such program is the YF-12 cooperative control program. In this program, the existing analog air-data computer, autothrottle, autopilot, and inlet control systems are to be converted to digital systems by using a general purpose airborne computer and interface unit. First, the existing control laws are to be programed and tested in flight. Then, integrated control laws, derived using accurate mathematical models of the airplane and propulsion system in conjunction with modern control techniques, are to be tested in flight. Analysis indicates that an integrated autothrottle-autopilot gives good flight path control and that observers can be used to replace failed sensors. INTRODUCTION Supersonic airplanes, such as the XB-70, YF-12, F-111, and F-15 airplanes, exhibit strong interactions between the engine and the inlet or between the propul- sion system and the airframe (refs. 1 and 2) . Taking advantage of possible favor- able interactions and eliminating or minimizing unfavorable interactions is a chal- lenging control problem with the potential for significant improvements in fuel consumption, range, and performance. In the past, engine, inlet, and flight control systems were usually developed separately, with a minimum of integration. It has often been possible to optimize the controls for a single design point, but off-design control performance usually suffered.
    [Show full text]
  • Fly-By-Wire - Wikipedia, the Free Encyclopedia 11-8-20 下午5:33 Fly-By-Wire from Wikipedia, the Free Encyclopedia
    Fly-by-wire - Wikipedia, the free encyclopedia 11-8-20 下午5:33 Fly-by-wire From Wikipedia, the free encyclopedia Fly-by-wire (FBW) is a system that replaces the Fly-by-wire conventional manual flight controls of an aircraft with an electronic interface. The movements of flight controls are converted to electronic signals transmitted by wires (hence the fly-by-wire term), and flight control computers determine how to move the actuators at each control surface to provide the ordered response. The fly-by-wire system also allows automatic signals sent by the aircraft's computers to perform functions without the pilot's input, as in systems that automatically help stabilize the aircraft.[1] Contents Green colored flight control wiring of a test aircraft 1 Development 1.1 Basic operation 1.1.1 Command 1.1.2 Automatic Stability Systems 1.2 Safety and redundancy 1.3 Weight saving 1.4 History 2 Analog systems 3 Digital systems 3.1 Applications 3.2 Legislation 3.3 Redundancy 3.4 Airbus/Boeing 4 Engine digital control 5 Further developments 5.1 Fly-by-optics 5.2 Power-by-wire 5.3 Fly-by-wireless 5.4 Intelligent Flight Control System 6 See also 7 References 8 External links Development http://en.wikipedia.org/wiki/Fly-by-wire Page 1 of 9 Fly-by-wire - Wikipedia, the free encyclopedia 11-8-20 下午5:33 Mechanical and hydro-mechanical flight control systems are relatively heavy and require careful routing of flight control cables through the aircraft by systems of pulleys, cranks, tension cables and hydraulic pipes.
    [Show full text]
  • Using an Autothrottle to Compare Techniques for Saving Fuel on A
    Iowa State University Capstones, Theses and Graduate Theses and Dissertations Dissertations 2010 Using an autothrottle ot compare techniques for saving fuel on a regional jet aircraft Rebecca Marie Johnson Iowa State University Follow this and additional works at: https://lib.dr.iastate.edu/etd Part of the Electrical and Computer Engineering Commons Recommended Citation Johnson, Rebecca Marie, "Using an autothrottle ot compare techniques for saving fuel on a regional jet aircraft" (2010). Graduate Theses and Dissertations. 11358. https://lib.dr.iastate.edu/etd/11358 This Thesis is brought to you for free and open access by the Iowa State University Capstones, Theses and Dissertations at Iowa State University Digital Repository. It has been accepted for inclusion in Graduate Theses and Dissertations by an authorized administrator of Iowa State University Digital Repository. For more information, please contact [email protected]. Using an autothrottle to compare techniques for saving fuel on A regional jet aircraft by Rebecca Marie Johnson A thesis submitted to the graduate faculty in partial fulfillment of the requirements for the degree of MASTER OF SCIENCE Major: Electrical Engineering Program of Study Committee: Umesh Vaidya, Major Professor Qingze Zou Baskar Ganapathayasubramanian Iowa State University Ames, Iowa 2010 Copyright c Rebecca Marie Johnson, 2010. All rights reserved. ii DEDICATION I gratefully acknowledge everyone who contributed to the successful completion of this research. Bill Piche, my supervisor at Rockwell Collins, was supportive from day one, as were many of my colleagues. I also appreciate the efforts of my thesis committee, Drs. Umesh Vaidya, Qingze Zou, and Baskar Ganapathayasubramanian. I would also like to thank Dr.
    [Show full text]
  • ICE PROTECTION Incomplete
    ICE PROTECTION GENERAL The Ice and Rain Protection Systems allow the aircraft to operate in icing conditions or heavy rain. Aircraft Ice Protection is provided by heating in critical areas using either: Hot Air from the Pneumatic System o Wing Leading Edges o Stabilizer Leading Edges o Engine Air Inlets Electrical power o Windshields o Probe Heat . Pitot Tubes . Pitot Static Tube . AOA Sensors . TAT Probes o Static Ports . ADC . Pressurization o Service Nipples . Lavatory Water Drain . Potable Water Rain removal from the Windshields is provided by two fully independent Wiper Systems. LEADING EDGE THERMAL ANTI ICE SYSTEM Ice protection for the wing and horizontal stabilizer leading edges and the engine air inlet lips is ensured by heating these surfaces. Hot air supplied by the Pneumatic System is ducted through perforated tubes, called Piccolo tubes. Each Piccolo tube is routed along the surface, so that hot air jets flowing through the perforations heat the surface. Dedicated slots are provided for exhausting the hot air after the surface has been heated. Each subsystem has a pressure regulating/shutoff valve (PRSOV) type of Anti-icing valve. An airflow restrictor limits the airflow rate supplied by the Pneumatic System. The systems are regulated for proper pressure and airflow rate. Differential pressure switches and low pressure switches monitor for leakage and low pressures. Each Wing's Anti Ice System is supplied by its respective side of the Pneumatic System. The Stabilizer Anti Ice System is supplied by the LEFT side of the Pneumatic System. The APU cannot provide sufficient hot air for Pneumatic Anti Ice functions.
    [Show full text]
  • A “Short Course” on Ice and the TBM
    A “Short Course” on Ice and the TBM. Icing is topical at the present time as a result of a recent accident in a TBM. I have had a number of conversations with pilots who I would consider knowledgeable and it is apparent that there is a lot of confusion surrounding this subject. Also noting on line posts this confusion is not limited to owner pilots. I have had occasion to be a victim of my own stupidity in a serious icing condition years ago and I can vouch that icing is a deadly serious situation in more ways than one. Before going on with the subject we want to stipulate that the data we are about to provide is a summary of information that is to be found on line, along with narrative and data provided from knowledgeable instructors, if any of the data provided conflicts with anything you have been taught we urge you to satisfy yourself as to which data is correct. TBM operators fly in the same airspace where we find Part 25 aircraft (Commercial Category) aircraft. There is a big difference in how these two categories of aircraft are affected by icing conditions. A 767 will often be climbing at over 300 kts and 4000+ ft/min at typical icing altitudes. This creates two very distinct advantages for the 767: first, their icing exposure time may be less than 1/3 of ours. Second, icing conditions are a function of TAT (Total Air Temperature), not SAT (static air temp). TAT is warmer than SAT because of the effects of compressibility as the airplane operates at faster and faster speeds.
    [Show full text]
  • Cessna Owner Magazine Article, October 2017
    The following article appeared in the October 2017 edition of CESSNA OWNER magazine, the official publication of the Cessna Owner Organization. Whether for business or pleasure, the Official Publication of the Cessna Owner Organization Since 1975 Cessna Owner Organization is dedicated to assisting CESSNA>> October 2017 aircraft owners in OWNER MAGAZINE their continual pursuit to become better, TKS smarter and safer ROTECTION owners and pilots. ICE P Since 1975, the Liquid Armor for the collective knowledge War on Icing and experience of its members has saved owners countless hours of downtime and thousands of dollars in operational expenses. www.cessnaowner.org www.facebook.com/ CessnaOwnerOrganization Est. 1975 Not a member? Learn more at www.CessnaOwner.org TKS Ice Protection Liquid Armor for the War on Icing By Scott Sherer here are many people out accumulation before launching. I wind is strong and the wind chill there who really like snow also have a heavy-duty tug for get- is very low. The winter cloud in Tsports; things like skiing, ting my bird in and out of the han- Wisconsin is dark and grey. (I say snowboarding, ice skating, hockey, gar quickly, and the Janitrol fur- “cloud” and not “clouds” because we snowmobiling and all of those other nace, along with an assortment of seem to have only one cloud here sports that you typically see during other engine and interior warming and it covers the entire state from the winter Olympics. I’m sure that contraptions, helps to get my plane November well into January!) many aviators enjoy some of these warm and ready fast.
    [Show full text]
  • Boeing Submission for Asiana Airlines (AAR) 777-200ER HL7742 Landing Accident at San Francisco – 6 July 2013
    Michelle E. Bernson The Boeing Company Chief Engineer P.O. Box 3707 MC 07-32 Air Safety Investigation Seattle, WA 98124-2207 Commercial Airplanes 17 March 2014 66-ZB-H200-ASI-18750 Mr. Bill English Investigator In Charge National Transportation Safety Board 490 L’Enfant Plaza, SW Washington DC 20594 via e-mail: [email protected] Subject: Boeing Submission for Asiana Airlines (AAR) 777-200ER HL7742 Landing Accident at San Francisco – 6 July 2013 Reference: NTSB Tech Review Meeting on 13 February 2014 Dear Mr. English: As requested during the reference technical review, please find the attached Boeing submission on the subject accident. Per your request we are sending this electronic version to your attention for distribution within the NTSB. We would like to thank the NTSB for giving us the opportunity to make this submission. If you have any questions, please don’t hesitate to contact us. Best regardsregards,, Michelle E. E Bernson Chief Engineer Air Safety Investigation Enclosure: Boeing Submission to the NTSB for the subject accident Submission to the National Transportation Safety Board for the Asiana 777-200ER – HL7742 Landing Accident at San Francisco 6 July 2013 The Boeing Company 17 March 2014 INTRODUCTION On 6 July 2013, at approximately 11:28 a.m. Pacific Standard Time, a Boeing 777-200ER airplane, registration HL7742, operating as Asiana Airlines Flight 214 on a flight from Seoul, South Korea, impacted the seawall just short of Runway 28L at San Francisco International Airport. Visual meteorological conditions prevailed at the time of the accident with clear visibility and sunny skies.
    [Show full text]