Standard Operating Procedures – Fixed Wing
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N87- 19393 CE Bith Ab AUTCEETIC TESMINAL EM (BASA) 21 P CSCL 17Ti Unclas H1/06 43501 NASA Tech Ni Ca I Paper 2669
) A SIPSCLATICL EVALUATION GP A N87- 19393 CE bITH Ab AUTCEETIC TESMINAL EM (BASA) 21 p CSCL 17ti Unclas H1/06 43501 NASA Tech ni ca I Paper 2669 1987 A Simulation Evaluation of a Pilot Interface With an Automatic Terminal Approach System David A. Hinton Langley Research Center Hampt o n, Virginia National Aeronautics and Space Administration Scientific and Technical Information Branch Summary with a high potential for mistakes and has limited time to detect and correct any errors. A successful A piloted-simulation study was performed to arrival depends on the correct interpretation of ap- evaluate the pilot interface with an automatic termi- proach chart details, the correct setting of numerous nal approach system (ATAS). The ATAS was con- cockpit controls, and precise aircraft guidance near ceived as a concept for improving the pilot inter- the ground. face with high levels of automation. It consists of Automation in the form of an autopilot has been instrument approach data storage, automatic radio used to reduce pilot work load and improve pilot tuning, autopilot, autothrottle, and annunciation of performance in the terminal area. Research studies These components allow the ATAS flight status. (ref. 2) and airplane accident and incident reports to automatically execute instrument approaches, in- suggest, however, that the probability of pilot error cluding procedure turns, altitude changes, missed actually increases with an increase in automation, approaches, and holding patterns, without requir- partially because of design limitations of the pilot- ing the pilot to set up navigation radios or change machine interface. Conventional autopilot interfaces autopilot modes. provide the pilot with many opportunities to make The results show that fewer pilot blunders were errors because of the requirements to change radio made during approaches when using the ATAS than frequencies and autopilot modes as the approach when using a baseline, heading-select autopilot. -
CRUISE FLIGHT OPTIMIZATION of a COMMERCIAL AIRCRAFT with WINDS a Thesis Presented To
CRUISE FLIGHT OPTIMIZATION OF A COMMERCIAL AIRCRAFT WITH WINDS _______________________________________ A Thesis presented to the Faculty of the Graduate School at the University of Missouri-Columbia _______________________________________________________ In Partial Fulfillment of the Requirements for the Degree Master of Science _____________________________________________________ by STEPHEN ANSBERRY Dr. Craig Kluever, Thesis Supervisor MAY 2015 The undersigned, appointed by the dean of the Graduate School, have examined the thesis entitled CRUISE FLIGHT OPTMIZATION OF A COMMERCIAL AIRCRAFT WITH WINDS presented by Stephen Ansberry, a candidate for the degree of Master of Science, and hereby certify that, in their opinion, it is worthy of acceptance. Professor Craig Kluever Professor Roger Fales Professor Carmen Chicone ACKNOWLEDGEMENTS I would like to thank Dr. Kluever for his help and guidance through this thesis. I would like to thank my other panel professors, Dr. Chicone and Dr. Fales for their support. I would also like to thank Steve Nagel for his assistance with the engine theory and Tyler Shinn for his assistance with the computer program. ii TABLE OF CONTENTS ACKNOWLEDGEMENTS………………………………...………………………………………………ii LIST OF FIGURES………………………………………………………………………………………..iv LIST OF TABLES…………………………………………………………………………………….……v SYMBOLS....................................................................................................................................................vi ABSTRACT……………………………………………………………………………………………...viii 1. INTRODUCTION.....................................................................................................................................1 -
Initiating a Missed Approach Below Mda
Issue No. 9 INITIATING A MISSED APPROACH BELOW MDA So there you are, on approach, inside the FAF and below MDA. You saw the runway and began descent, but it is raining, visibility is marginal and things are murky and scuddy (technical terms). Wind is directly across the runway at 11G18 and you are crabbing down, passengers are nervous. But you are holding the CDI in the center and maintaining control. Over the runway you go into your wing-low sideslip for the crosswind landing, things are going pretty well and then whoops a big gust destabilizes you so you abort the landing. Now what do you do, go missed or go around for another landing attempt? To provide some context, let’s attach the scenario to an interesting little airport, Andrews- Murphy Airport, NC (KRHP). The instrument approach procedure (IAP) and the takeoff minima and obstacle departure procedure are shown here. This airport is nestled in a scenic valley surrounded by mountains, which are quite close on the north. A topo map can be viewed here or just go to the TopoZone website and search for Andrews, NC, or go to the airport lat/long of 3512N/08352W. You will notice that the MDA is 2329 feet above the runway. Now remember that obstacle protection on a missed approach procedure is based on going missed at the MAP at MDA with a minimum climb gradient of 200 feet per nautical mile. No obstacle protection is assured when you go missed below MDA or past the MAP. In fact, you are not assured of obstacle protection even above MDA if the missed is initiated below MDA or after the MAP. -
Predictability of Top of Descent Location for Operational Idle-Thrust Descents
Predictability of Top of Descent Location for Operational Idle-thrust Descents Laurel L. Stell∗ NASA Ames Research Center, Moffett Field, CA 94035 To enable arriving aircraft to fly optimized descents computed by the flight management system (FMS) in congested airspace, ground automation must accurately predict descent trajectories. To support development of the trajectory predictor and its uncertainty mod- els, commercial flights executed idle-thrust descents at a specified descent speed, and the recorded data included the specified descent speed profile, aircraft weight, and the winds entered into the FMS as well as the radar data. The FMS computed the intended descent path assuming idle thrust after top of descent (TOD), and the controllers and pilots then endeavored to allow the FMS to fly the descent to the meter fix with minimal human intervention. The horizontal flight path, cruise and meter fix altitudes, and actual TOD location were extracted from the radar data. Using approximately 70 descents each in Boeing 757 and Airbus 319/320 aircraft, multiple regression estimated TOD location as a linear function of the available predictive factors. The cruise and meter fix altitudes, descent speed, and wind clearly improve goodness of fit. The aircraft weight improves fit for the Airbus descents but not for the B757. Except for a few statistical outliers, the residuals have absolute value less than 5 nmi. Thus, these predictive factors adequately explain the TOD location, which indicates the data do not include excessive noise. Nomenclature b Least -
Takeoff and Landing Weather Minimums
Federal Aviation Administration, DOT § 121.651 field elevation for 15 minutes upon VFR weather minimums of § 91.155 of reaching an ETOPS Alternate Airport this chapter apply at those locations. and then conduct an instrument ap- [Doc. No. 6258, 29 FR 19222, Dec. 31, 1964 as proach and land. amended by Amdt. 121–39, 33 FR 4097, Mar. 2, (3) Fuel to account for APU use. If an 1968; Amdt. 121–206, 54 FR 34331, Aug. 18, 1989; APU is a required power source, the Amdt. 121–226, 56 FR 65663, Dec. 17, 1991] certificate holder must account for its fuel consumption during the appro- § 121.651 Takeoff and landing weather priate phases of flight. minimums: IFR: All certificate hold- ers. [Doc. No. FAA–2002–6717, 72 FR 1882, Jan. 16, 2007, as amended by Amdt. 121–348, 75 FR (a) Notwithstanding any clearance 12121, Mar. 15, 2010] from ATC, no pilot may begin a takeoff in an airplane under IFR when the § 121.647 Factors for computing fuel weather conditions reported by the required. U.S. National Weather Service, a Each person computing fuel required source approved by that Service, or a for the purposes of this subpart shall source approved by the Administrator, consider the following: are less than those specified in— (a) Wind and other weather condi- (1) The certificate holder’s operations tions forecast. specifications; or (b) Anticipated traffic delays. (2) Parts 91 and 97 of this chapter, if (c) One instrument approach and pos- the certificate holder’s operations sible missed approach at destination. specifications do not specify takeoff (d) Any other conditions that may minimums for the airport. -
Chapter: 4. Approaches
Chapter 4 Approaches Introduction This chapter discusses general planning and conduct of instrument approaches by pilots operating under Title 14 of the Code of Federal Regulations (14 CFR) Parts 91,121, 125, and 135. The operations specifications (OpSpecs), standard operating procedures (SOPs), and any other FAA- approved documents for each commercial operator are the final authorities for individual authorizations and limitations as they relate to instrument approaches. While coverage of the various authorizations and approach limitations for all operators is beyond the scope of this chapter, an attempt is made to give examples from generic manuals where it is appropriate. 4-1 Approach Planning within the framework of each specific air carrier’s OpSpecs, or Part 91. Depending on speed of the aircraft, availability of weather information, and the complexity of the approach procedure Weather Considerations or special terrain avoidance procedures for the airport of intended landing, the in-flight planning phase of an Weather conditions at the field of intended landing dictate instrument approach can begin as far as 100-200 NM from whether flight crews need to plan for an instrument the destination. Some of the approach planning should approach and, in many cases, determine which approaches be accomplished during preflight. In general, there are can be used, or if an approach can even be attempted. The five steps that most operators incorporate into their flight gathering of weather information should be one of the first standards manuals for the in-flight planning phase of an steps taken during the approach-planning phase. Although instrument approach: there are many possible types of weather information, the primary concerns for approach decision-making are • Gathering weather information, field conditions, windspeed, wind direction, ceiling, visibility, altimeter and Notices to Airmen (NOTAMs) for the airport of setting, temperature, and field conditions. -
Go-Around Decision-Making and Execution Project
Final Report to Flight Safety Foundation Go-Around Decision-Making and Execution Project Tzvetomir Blajev, Eurocontrol (Co-Chair and FSF European Advisory Committee Chair) Capt. William Curtis, The Presage Group (Co-Chair and FSF International Advisory Committee Chair) MARCH 2017 1 Acknowledgments We would like to acknowledge the following people and organizations without which this report would not have been possible: • Airbus • Johan Condette — Bureau d’Enquêtes et d’Analyses • Air Canada Pilots Association • Capt. Bertrand De Courville — Air France (retired) • Air Line Pilots Association, International • Capt. Dirk De Winter — EasyJet • Airlines for America • Capt. Stephen Eggenschwiler — Swiss • The Boeing Company • Capt. Alex Fisher — British Airways (retired) • Eurocontrol • Alvaro Gammicchia — European Cockpit Association • FSF European Advisory Committee • Harald Hendel — Airbus • FSF International Advisory Committee • Yasuo Ishihara — Honeywell Aerospace Advanced • Honeywell International Technology • International Air Transport Association • David Jamieson, Ph.D. — The Presage Group • International Federation of Air Line Pilots’ Associations • Christian Kern — Vienna Airport • The Presage Group • Capt. Pascal Kremer — FSF European Advisory Committee • Guillaume Adam — Bureau d’Enquêtes et d’Analyses • Richard Lawrence — Eurocontrol • John Barras – FSF European Advisory Committee • Capt. Harry Nelson — Airbus • Tzvetomir Blajev — Eurocontrol • Bruno Nero — The Presage Group • Karen Bolten — NATS • Zeljko Oreski — International -
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AN MHM PUBLISHING MAGAZINE MArcH/APrIL 2017 [ INSIDE ] SKIES magaz • AIR CANADA REBRANDS • SPECIAL MISSION AIRCRAFT • NORTHERN OPS UPDATE mag.com • PILOT CAREER PATHWAYS I n E • CUSTOM GLOBAL REFURB • TURBOPROP COMEBACK SKIES • CELEBRATING CANADA 150 AvIAtIoN IS oUr PassioN PRESSURIZED PISTON CRUISER WE FLY THE PIPER M350! FAST™ SOLUTION PREVENTIVE, ACTIONABLE & WIRELESS FULL-FLIGHT INTELLIGENCE KNOW YOUR ENGINE FROM THE INSIDE OUT P&WC’s FASTTM solution captures, analyzes and sends full-flight data intelligence electronically to customers within moments of engine shutdown. By providing actionable preventative alerts and prognostics directly to the people who need it, we empower operators to make informed decisions, reduce costs and troubleshoot issues before they happen. With the FAST TM solution we take the words rapid response to a new level. It’s that easy. It’s that powerful. FAST™ Solution: Unparalleled dispatch availability and reduced operating costs. POWERFUL. EFFICIENT. VERSATILE. SOUND LIKE ANYBODY YOU KNOW? You demand continuous improvement in your business, so why not expect it from your business aircraft? Through intelligent design the new PC-12 NG climbs faster, cruises faster, and is even more quiet, comfortable and efficient than its predecessor. If your current aircraft isn’t giving you this kind of value, maybe it’s time for a Pilatus. Stan Kuliavas, Vice President of Sales | [email protected] | 1 844.538.2376 | www.levaero.com SKIES Magazine | March/April 2017 1 Levaero-Full-CSV6I6.indd 1 2016-09-29 1:12 PM March/April 2017 | Volume 7, Issue 2 IN THIS ISSUE 22 58 68 82 14 AIR CANADA 30 ASSESSING THE 58 TURBOPROP 82 IT’S THE SKIES REBRANDS APPROACH COMEBACK THAT BIND As it turns 80, the airline Nav Canada’s flight Simple economics have As Canada celebrates unveils a distinctive new inspection crews regularly revived the business case its 150 th anniversary this livery, stylish uniforms and test navigational aids at more for turboprop aircraft, with year, the nation’s aviation premium on-board products. -
Prediction of Top of Descent Location for Idle-Thrust Descents
Ninth USA/Europe Air Traffic Management Research and Development Seminar (ATM2011) Prediction of Top of Descent Location for Idle-thrust Descents Laurel Stell Aviation Systems Division NASA Ames Research Center Moffett Field, CA, USA [email protected] Abstract—To enable arriving aircraft to fly optimized descents enabling continuous descents is being pursued by several re- computed by the flight management system (FMS) in congested search groups. Most of the previous research has focused on airspace, ground automation must accurately predict descent tra- prediction of arrival time at a waypoint. While this helps with jectories. Development and assessment of the trajectory predictor lateral separation, accurate prediction of the vertical profile is and the concept of operations requires models of the prediction also essential to ensure vertical separation from aircraft at dif- error due to various error sources. Polynomial approximations ferent altitudes, including crossing traffic. In fact, error in pre- of the along-track distance of the top of descent (TOD) from the diction of the vertical profile is likely to have more impact than meter fix are given in terms of the inputs to the equations of mo- tion. Polynomials with three different levels of complexity are pre- along-track prediction error on procedures and data exchange sented, with the simplest being linear. These approximations were necessary to enable more fuel-efficient descents in congested obtained by analyzing output from one predictor. While this pre- airspace. Only the TOD location is analyzed in this paper, dictor’s thrust and drag models do not seem to agree well with which is the first step in understanding the entire vertical pro- those used by the FMS, both laboratory and operational data us- file. -
Cessna Model 150M Performance- Cessna Specifications Model 150M Performance - Specifications
PILOT'S OPERATING HANDBOOK ssna 1977 150 Commuter CESSNA MODEL 150M PERFORMANCE- CESSNA SPECIFICATIONS MODEL 150M PERFORMANCE - SPECIFICATIONS SPEED: Maximum at Sea Level 109 KNOTS Cruise, 75% Power at 7000 Ft 106 KNOTS CRUISE: Recommended Lean Mixture with fuel allowance for engine start, taxi, takeoff, climb and 45 minutes reserve at 45% power. 75% Power at 7000 Ft Range 340 NM 22.5 Gallons Usable Fuel Time 3.3 HRS 75% Power at 7000 Ft Range 580 NM 35 Gallons Usable Fuel Time 5. 5 HRS Maximum Range at 10,000 Ft Range 420 NM 22. 5 Gallons Usable Fuel Time 4.9 HRS Maximum Range at 10,000 Ft Range 735 NM 35 Gallons Usable Fuel Time 8. 5 HRS RATE OF CLIMB AT SEA LEVEL 670 FPM SERVICE CEILING 14, 000 FT TAKEOFF PERFORMANCE: Ground Roll 735 FT Total Distance Over 50-Ft Obstacle 1385 FT LANDING PERFORMANCE: Ground Roll 445 FT Total Distance Over 50-Ft Obstacle 107 5 FT STALL SPEED (CAS): Flaps Up, Power Off 48 KNOTS Flaps Down, Power Off 42 KNOTS MAXIMUM WEIGHT 1600 LBS STANDARD EMPTY WEIGHT: Commuter 1111 LBS Commuter II 1129 LBS MAXIMUM USEFUL LOAD: Commuter 489 LBS Commuter II 471 LBS BAGGAGE ALLOWANCE 120 LBS WING LOADING: Pounds/Sq Ft 10.0 POWER LOADING: Pounds/HP 16.0 FUEL CAPACITY: Total Standard Tanks 26 GAL. Long; Range Tanks 38 GAL. OIL CAPACITY 6 QTS ENGINE: Teledyne Continental O-200-A 100 BHP at 2750 RPM PROPELLER: Fixed Pitch, Diameter 69 IN. D1080-13-RPC-6,000-12/77 PILOT'S OPERATING HANDBOOK Cessna 150 COMMUTER 1977 MODEL 150M Serial No. -
Optimal Top of Descent Analysis in Respect to Wind Prediction Errors and Guidance Strategies*
Trans. JSASS Aerospace Tech. Japan Vol. 15, No. APISAT-2016, pp. a45-a51, 2017 Optimal Top of Descent Analysis in Respect to Wind Prediction Errors and Guidance Strategies* By Adriana ANDREEVA-MORI and Tsuneharu UEMURA (5mm) Aeronautical Technology Directorate, Japan Aerospace Exploration Agency, Tokyo, Japan (Received January 31st, 2017) Modern airliners use the profiles calculated by the onboard flight management system (FMS) to execute safe and efficient descents. Since the wind often varies greatly between the cruising altitude and the end-of-descent altitude, the FMS uses both predicted and measured wind to determine the descent profile. Even so, the actual wind encountered along the descent changes the profile. When a constant descent speed is maintained at idling thrust, the aircraft deviates from its path and needs to either fly an additional steady level flight segment to the metering fix or deflect speed brakes to ensure the speed constraints at the metering fix are met. This research analyses the optimal top of descent in respect to such wind prediction error and fuel burn. Numerical simulations for the Boeing 767-300 are done and it is shown that an early descent of 0.5 nm would save, on average, 0.9 lb of fuel for an idling descent from 30,000 ft to 10,000 ft and at a constant speed of 280 kt, and decrease the number of cases where the necessary deceleration could not be achieved due to lack of enough lateral distance by 77%, thus improving safety and easing operations. Key Words: Top of Descent, Flight Management System, VNAV-SPEED, Wind Disturbances, Fuel Optimal 1. -
Federal Aviation Administration, DOT § 91.175
Federal Aviation Administration, DOT § 91.175 a certificated and appropriately rated in paragraph (b)(1) of this section, is radio repair station or, outside the used, an entry must be made in the air- United States, a test signal operated or craft log or other record by the repair approved by an appropriate authority station certificate holder or the certifi- to check the VOR equipment (the max- cate holder's representative certifying imum permissible indicated bearing to the bearing transmitted by the re- error is plus or minus 4 degrees); or pair station for the check and the date (2) Use, at the airport of intended de- of transmission. parture, a point on the airport surface designated as a VOR system check- (Approved by the Office of Management and point by the Administrator, or, outside Budget under control number 2120±0005) the United States, by an appropriate authority (the maximum permissible § 91.173 ATC clearance and flight plan bearing error is plus or minus 4 de- required. grees); No person may operate an aircraft in (3) If neither a test signal nor a des- controlled airspace under IFR unless ignated checkpoint on the surface is that person hasÐ available, use an airborne checkpoint (a) Filed an IFR flight plan; and designated by the Adninistrator or, (b) Received an appropriate ATC outside the United States, by an appro- clearance. priate authority (the maximum per- missible bearing error is plus or minus § 91.175 Takeoff and landing under 6 degrees); or IFR. (4) If no check signal or point is (a) Instrument approaches to civil air- available, while in flightÐ ports.