Wings Over the Bay NEW ZEALAND DIVISION Journal of the Bay of Plenty Branch of the NZ Division, Raes: 02-17 ______

Total Page:16

File Type:pdf, Size:1020Kb

Wings Over the Bay NEW ZEALAND DIVISION Journal of the Bay of Plenty Branch of the NZ Division, Raes: 02-17 ______ Wings Over the Bay NEW ZEALAND DIVISION Journal of the Bay of Plenty Branch of the NZ Division, RAeS: 02-17 __________________________________________________________________________________________ Welcome to the newsletter for the Bay of was reflected in a graphic which noted composites Plenty Branch, NZ Division, RAeS for February at 50% and metal content down to 20% on leading 2017 edges, engine pylon mounts and elsewhere. Engine cowls too are made from composites. Meeting Recap The February meeting of the Bay of Plenty Branch was held at the clubrooms of the Tauranga Gliding Club on the north west of Tauranga airfield. This was the same venue we had used for the Branch meeting and BBQ last year which was a great place for the AGM and accompanying lecture this year, titled: B787 Operations. The lecture was delivered by Owen Bieleski who holds an ATPL with military transport experience with the RNZAF before embarking on a commercial The extensive use of electric-based systems has career with major airlines overseas. Recently, he almost entirely replaced bleed-air and a good returned home with his family to Tauranga from number of hydraulic-based services. Flight Dubai, where he had flown all six variants B777 controls, too, use fly-by-wire (FBW) with no with Emirates. manual back-up. Owen suggested with the extent of the changes to electrically-based systems, the B787 is sometimes called the ‘electric jet’. Owen explained the B787 is a very different design to its predecessors, with a heavy emphasis on electrical powered systems and multiple layers of automatically managed redundancy. Pilots are alerted to most failures via the EICAS (Engine Indicating and Crew Alerting System) as a Warning, Owen Bieleski showing an RNZAF F27 – Friendship at the start of his Caution or Advisory. In some failure cases, such as lecture – Photo Des Underwood the Flight Management Computer, switching to Owen has joined China Southern as a line captain the backup is automatic and only ‘flagged’ when flying the B787-800 Dreamliner service from one FMC remains. System alert logic is on a ‘need Auckland to Guangzhou in China. With extensive to know’ basis. airline experience on the B777, he is well qualified For passengers, too, Owen explained new features to discuss the features of the new Boeing 787 included lower cabin-altitude (to 6,000 feet) and wide-body ‘electric jet’. higher humidity levels to help reduce passenger While comparable in size to the B767-300, the fatigue on the long flights which the B787 is B787 is 35% lighter. This is due to substantial use capable of flying. of carbon-fibre composite materials and new He noted B777 pilots would be very at home in a electrically-based system and componentry to B787 with conversions to the new type taking just replace heavier heritage aircraft systems and five days. In the cockpit, the main change is head- services. The extent of use of composite materials Explore the marvels of aviation with the Bay of Plenty Branch Webpage: http://www.raes.org.nz/branches/bay_of_plenty Facebook - aerospace bay of plenty Wings Over the Bay NEW ZEALAND DIVISION Journal of the Bay of Plenty Branch of the NZ Division, RAeS: 02-17 __________________________________________________________________________________________ up displays (for take-off and landing) which he had starter generators have replaced the separate found easy to adapt to. pneumatic starters and generators. Two interchangeable VFSG’s are fitted on each engine and the APU, which together are capable of generating 1.4MW of electrical power. The aircraft has batteries and when all else fails a ram air turbine (RAT) provides essential power. Engine and electrically powered high pressure (5,000psi) hydraulics is used to power the primary flight control surfaces although some spoilers and the stabiliser are electrically actuated to provide system redundancy. The B787 cockpit with five multi-function displays (MFD’s) feature on the To conclude, Owen noted he had found the most with electronic flight bag (EFB) units to the side panel; new head-up displays (HUDs) are new which can be folded away. useful change on the B787 was the ergonomic inclusion of a rocker switch on the back of the While retaining the traditional control columns, all cockpit seats. These switches allowed the seats to flight controls are fly-by-wire (FBW) with no be moved back at the touch of the button. manual reversion. He confirmed throttles and other control handles physically moved whether Those attending the lecture came away better they were moved by the pilot or auto commanded. informed on the features of the B787 Dreamliners He identified some new flight control features of and why 64 airlines had ordered more than 1,200 the 787 which included: cruise flaps, asymmetry of the three variants to date. compensation, gust suppression, auto-drag and Thank you to Owen for his most enlightening landing attitude modifier. lecture covering an important aspect of the Nose-wheel steering tillers were available for both progress in new airliner design and operation. pilots that use ‘control by wire’ technology as opposed to mechanical sequencing. Owen explained while the Airbus ‘rate-control’ side-stick controller of the types, the ‘direct-sense’ conventional controls used by Boeing had their advocates but he preferred the Boeing approach. In answer to a later question about the retention of the traditional control column by Boeing in the 787, he thought it could be replaced by a side-stick control device at some stage. Engines used on the 787 include the GE GEnx-1B and Rolls Royce Trent 1000. These had been China Southern Airlines B2732 Boeing 787-81B on the Boeing pre- configured to have virtually eliminated engine delivery ramp at Paine Field, Washington – Photo Bill Shemley bleed-air to cater only for engine intake anti-icing, The meeting concluded with an enjoyable Branch allowing greater engine efficiency levels for BBQ. propulsion and the direct-driven twin variable frequency starter generators (VFSGs). These ***** Explore the marvels of aviation with the Bay of Plenty Branch Webpage: http://www.raes.org.nz/branches/bay_of_plenty Facebook - aerospace bay of plenty Wings Over the Bay NEW ZEALAND DIVISION Journal of the Bay of Plenty Branch of the NZ Division, RAeS: 02-17 __________________________________________________________________________________________ Aviation News As it is now, sadly, NZ5911 has suffered the effects of outside storage. Aviation News – February 2017 Continuing with the B787 lecture theme, Boeing has delivered its 500th 787 to Avianca at Everett, Seattle. NZ5911 at Ardmore, less ailerons and tail surfaces – Photo Geoff Jones It is due to be dismantled in preparation for shipping to the UK. This will apparently require the removal of the centre-wing to comply with road transport rules in the UK. It is sad that another part of both the RNZAF and NZ aviation history is about to leave NZ but good it will be restored and preserved elsewhere. Despite some delivery set-backs, the B787 is the Its return to the UK will close the loop on an aircraft quickest airliner to have reached the 500th delivery which was built by the Bristol Aeroplane Company at milestone having entered airline service five years Filton, Bristol as c/n 13135 (as a Mk 31M ) and rolled ago. out on 4 September 1952 before being handed over Unlike some other types, Boeing has planned dual to the RNZAF later the same month. Its departure for assembly plants, the second plant in B787 in North NZ was delayed until the following year to allow it to Charleston, South Carolina. The first of the type off be modified with as a dual-control trainer at RAF the SC line was the 250th 787 which was delivered Abingdon. For NZ5911, it is about to be embark on a Mar 17, 2015 and was a larger -9 variant. new beginning with restoration at a new home at Filton. It isn’t clear in what livery it will be painted. Of the 214 made at Filton, the return of c/n 13135 will be the only one of its type in the UK. As it once was, NZ5911 in jungle camouflage. Photo AMB Collection Article by Adrian M. Balch – this story covers the sale of Bristol 170 Freighter (formerly NZ5911) to the Bristol Aero Collection in UK. Having been assigned to 41 Squadron RNZAF in Singapore, it served in South East Asia including supply runs to in Viet Nam before being brought back to NZ for service eventually serving with 1 Squadron RNZAF at Whenuapai. Article by Nicholas McIndoe – covers the delivery of Having been replaced by the RAF HS Andover C Mk 1, reproduction RAF BE2c to Warbirds NZ from the the B170 fleet was sold to RS Dwen Airmotive Ltd at Vintage Aviator Ltd. The pic shows its maiden flight at Ardmore. Ardmore with Frank Parker at the helm. Explore the marvels of aviation with the Bay of Plenty Branch Webpage: http://www.raes.org.nz/branches/bay_of_plenty Facebook - aerospace bay of plenty Wings Over the Bay NEW ZEALAND DIVISION Journal of the Bay of Plenty Branch of the NZ Division, RAeS: 02-17 __________________________________________________________________________________________ City In The Sky – BBC TV Documentary – This recently to airliners and their passengers. released three-part series has screened in NZ and reviews the progress of aviation. The ‘city in the sky’ claimed to keep around a million people and their baggage aloft at any moment of a normal day. It noted while all-metal aircraft inherently possess the means to conduct the lightning strike to exit elsewhere, new methods to achieve the same level of safety is necessary for the next generation of mainly non-metal aircraft (made from carbon–fibre composite materials) such as the B787.
Recommended publications
  • 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]
  • GENERAL ENGINE BLEED Fokker 50
    Fokker 50 - Bleed Air System GENERAL Bleed-air is used for airconditioning, pressurization, airframe and engine air intake de-icing, and for pressurizing the hydraulic tank. Bleed-air is supplied by the engines. For aircraft equipped with APU On the ground bleed-air can be supplied by the APU for air conditioning. ENGINE BLEED Tappings Bleed-air is obtained via tappings on each engine, referred to as Low-Pressure (LP) bleed and High-Pressure (HP) bleed. LP-bleed is normally in use during flight. HP-bleed will be used at idling and low engine speeds, when LP-bleed is insufficient. The HP-bleed valve will open automatically provided the BLEED push button, located at the AIR CONDITIONING panel, is blank. Bleed-air from the HP-Bleed is prevented from flowing into the LP-bleed by a check valve. Duct leak detection A duct leak between the engine tappings and the firewall, resulting in a significant leakage of bleed-air, is monitored by the engine fire detection and warning system. Distribution Bleed-air from both engines is used to supply the following services: • Airframe, and engine air intake de-icing, see ICE AND RAIN PROTECTION • Hydraulic tank pressurization, see HYDRAULIC SYSTEM. • Airconditioning and pressurization, see below. • If mentioned in aircraft system deviation table: Watertank pressurization, see AIRCRAFT GENERAL. Page 1 Fokker 50 - Bleed Air System BLEED AIR FOR AIRCONDITIONING Supply Controls and indicators are located at the AIRCONDITIONING panel. Bleed-air is available when the engines are running and the BLEED push buttons are blank. When a BLEED push button is depressed to OFF, the Pressure Regulating/Shut-Off valve (PR/SO) and the HP- bleed valve close.
    [Show full text]
  • Analytical Design and Estimation of Conventional and Electrical Aircraft Environmental Control Systems
    Analytical Design and Estimation of Conventional and Electrical Aircraft Environmental Control Systems Hemanth Devadurgam , Soorya Rajagopal , Raghu Chaitanya Munjulury Division of Fluid and Mechatronic Systems, Department of Management and Engineering, Linköping University, Linköping, Sweden - 58183 Symbol Description Units ABSTRACT A Area m2 Environmental control system holds vital importance P Perimeter m as it is responsible for passenger’s ventilation and T Temperature degree C kg comfort. This paper presents an analytical design of k Thermal Conductiv- mK environmental control systems and represents the esti- ity mated design in three-dimensional. Knowledge-based K Kelvin K engineering application serves as the base for design- D Hydraulic Diameter m ing and methodology for the environmental control kg m Mass flow rate s systems. Flexibility in the model enables the user p Pressure Pa to control the size and positioning of the system and kg m Dynamics viscosity ms also sub-systems associated with it. The number of passengers serves as the driving input and three- dimensional model gives the exact representation with 1 Introduction respect to the volume occupied and dependencies on The Environmental Control System (ECS) is responsi- the number of passengers. It also provides a faster ble for passengers comfort and one of the most impor- method to alter the system to user needs with respect tant systems of an aircraft. Temperature and pressure to the number of air supply pipes, number of ducts and of the air vary on the altitude and ECS works on reg- pipe length. Knowledge-based engineering gives the ulating the air, takes-in the bleed air mixes it with the freedom to visualize various options in the conceptual recirculating air so that the pressure and temperature design process.
    [Show full text]
  • Depressurisation Event 246 Km South-West of Coolangatta, Queensland 17 November 2007 VH-VBC Boeing Company 737-7Q8
    ATSB TRANSPORT SAFETY REPORT Aviation Occurrence Investigation AO-2007-062 Final Depressurisation event 246 km south-west of Coolangatta, Queensland 17 November 2007 VH-VBC Boeing Company 737-7Q8 ATSB TRANSPORT SAFETY REPORT Aviation Occurrence Report AO-2007-062 Final Depressurisation event 246 km south-west of Coolangatta, Queensland 17 November 2007 VH-VBC Boeing Company 737-7Q8 Released in accordance with section 25 of the Transport Safety Investigation Act 2003 - i - Published by: Australian Transport Safety Bureau Postal address: PO Box 967. Civic Square ACT 2608 Office location: 62 Northbourne Ave, Canberra City, Australian Capital Territory, 2601 Telephone: 1800 020 616, from overseas +61 2 6257 4150 Accident and incident notification: 1800 011 034 (24 hours) Facsimile: 02 6247 3117, from overseas +61 2 6247 3117 Email: [email protected] Internet: www.atsb.gov.au © Commonwealth of Australia 2010. This work is copyright. In the interests of enhancing the value of the information contained in this publication you may copy, download, display, print, reproduce and distribute this material in unaltered form (retaining this notice). However, copyright in the material obtained from other agencies, private individuals or organisations, belongs to those agencies, individuals or organisations. Where you want to use their material you will need to contact them directly. Subject to the provisions of the Copyright Act 1968, you must not make any other use of the material in this publication unless you have the permission of the Australian Transport Safety Bureau. Please direct requests for further information or authorisation to: Commonwealth Copyright Administration, Copyright Law Branch Attorney-General’s Department, Robert Garran Offices, National Circuit, Barton, ACT 2600 www.ag.gov.au/cca ISBN and formal report title: see ‘Document retrieval information’ on page v - ii - CONTENTS THE AUSTRALIAN TRANSPORT SAFETY BUREAU ...............................
    [Show full text]
  • Comparison of Control Strategies for Aircraft Bleed-Air Systems
    View metadata, citation and similar papers at core.ac.uk brought to you by CORE provided by Archivio istituzionale della ricerca - Politecnico di Milano Comparison of Control Strategies for Aircraft Bleed-Air Systems Alexander Pollok ∗;∗∗ Francesco Casella ∗∗ ∗ DLR German Aerospace Center, Institute of System Dynamics and Control, Oberpfaffenhofen, Germany (e-mail: [email protected]) ∗∗ Politecnico di Milano, Dipartimento di Elettronica, Informazione e Bioingegneria, Milan, Italy (e-mail: [email protected]) Abstract: Bleed-air systems in passenger aircraft are often prone to limit cycle oscillations. Tuning of such systems makes additional flight-tests necessary, generating large expenses. In this paper, several control approaches to improve the performance of bleed-air systems are compared. These approaches combine a base-controller with stiction-compensation techniques. The different approaches are implemented, optimized and evaluated using a high-fidelity bleed- air system model, described in the equation-based modelling language Modelica. Results indicate that interaction between different valves should be reduced as much as possible. If a suitable base control approach is chosen, the influence of a superimposed stiction compensation technique seems to be small. Keywords: Friction, Stiction, Compensation, Limit Cycles, Modelica, Pistons, Modelling, Oscillation, Pneumatic, Valves 1. INTRODUCTION used to control the surge bleed valve of an auxiliary power unit. The technique is not expanded to the complete bleed- In modern passenger aircraft, the cabin is pressurized air system or to the main engines. and temperature-controlled by the Environmental Control System (ECS). Hot and dense air is bled from the engine In preliminary work, the authors developed a high-fidelity compressor stages.
    [Show full text]
  • Aircraft Clean Air Requirements Using Bleed Air Systems
    Engineering, 2018, 10, 142-172 http://www.scirp.org/journal/eng ISSN Online: 1947-394X ISSN Print: 1947-3931 Aircraft Clean Air Requirements Using Bleed Air Systems Susan Michaelis Faculty of Health Sciences Pathfoot Building R E010, University of Stirling, Stirling, UK How to cite this paper: Michaelis, S. Abstract (2018) Aircraft Clean Air Requirements Using Bleed Air Systems. Engineering, 10, There are certification and airworthiness requirements relevant to the provi- 142-172. sion of clean breathing air in the crew and passenger compartments. There https://doi.org/10.4236/eng.2018.104011 have been continuing reports and studies over the years regarding oil fumes in Received: February 22, 2018 aircraft, including impaired crew performance. Oil fumes are viewed in vary- Accepted: April 17, 2018 ing ways ranging from rare seal bearing failures, to low level leakage in nor- Published: April 20, 2018 mal flight. A Masters of Science (MSc) research degree was undertaken to as- Copyright © 2018 by author and sess whether there is any gap between the certification requirements for the Scientific Research Publishing Inc. provision of clean air in crew and passenger compartments, and the theoreti- This work is licensed under the Creative cal and practical implementation of the requirements using the bleed air sys- Commons Attribution International tem. A comprehensive literature search reviewed applicable certification License (CC BY 4.0). http://creativecommons.org/licenses/by/4.0/ standards, documented and theoretical understanding of oil leakage. Two Open Access types of interviews were conducted to address the research questions. Key aviation regulators were questioned about the process by which they certify and ensure compliance with the clean air requirements.
    [Show full text]
  • 1. INTRODUCTION the Environmental Control System (ECS)
    Canadair Regional Jet 100/200 - Environmental Control System 1. INTRODUCTION The environmental control system (ECS) provides temperature and pressure regulated air for heating, ventilating and pressurizing the flight and passenger compartments. Exhaust air, from the compartments, is used to ventilate the avionics and cargo compartments, before being dumped overboard through two outflow valves. For ground operations, pneumatic air to operate the ECS can be obtained from: A ground air supply cart connected to the aircraft The auxiliary power unit (APU) Either or both engines. During flight, the engines normally supply bleed air for operating the air-conditioning, pressurization, and avionics cooling systems. ECS warnings and cautions are displayed on the engine indication and crew alerting system (EICAS) primary page. ECS advisory and status messages are displayed on the EICAS status page. Views of the aircraft ECS temperature, pressure, valve positions and system status indications are displayed on the EICAS ECS synoptic page. Page 1 Canadair Regional Jet 100/200 - Environmental Control System AFT PRESSURE RAM AIR FLIGHT PASSENGER CABIN BULKHEAD INLET COMPARTMENT GASPER SYSTEM OUTFLOW VALVES (2) DUAL POSITION LEGEND VALVE Pressurized and conditioned by air conditioning system. Pressurized by air SOV DISTRIBUTION MANIFOLD exhausted from RAM cockpit/cabin AIR no temperature LP GROUND control. LEFT CONDITIONED RIGHT Heated by exhaust PACK AIR PACK air from CONNECTION electronics chassis. PACK PRSOV’s Unpressurized 10 TH 10 TH STAGE STAGE L/H ISOL R/H SOV SOV AUXILIARY GROUND POWER POWER UNIT UNIT (HIGH PRESSURE PNEUMATIC SUPPLY) Tvyvsvrq 7ypx 9vht h A v t r ' Page 2 Canadair Regional Jet 100/200 - Environmental Control System 1.
    [Show full text]
  • Bombardier Challenger 605 - Power Plant
    Bombardier Challenger 605 - Power Plant GENERAL The Challenger 605 is equipped with two General Electric CF34-3B high-bypass ratio turbofan engines. The dual-assembly engine consists of a fan rotor (N1) and a compressor rotor (N2). The N1 rotor is comprised of a single-stage fan connected through a shaft to a four-stage low-pressure turbine. The N2 rotor is a 14-stage axial flow compressor connected through a shaft to a two-stage high-pressure turbine. The accessory gearbox is mechanically driven by the N2 compressor. Normal takeoff thrust rating is 8,729 pounds per engine. During engine-out operation, the automatic performance reserve (APR) system increases thrust on the operable engine to 9,220 pounds. FLAT-RATED THRUST Outside air temperature and pressure altitude are determining factors in achieving takeoff and APR power. Increases in ambient temperature or pressure altitude adversely affect the engine’s ability to produce rated thrust. The CF34-3B is flat-rated to ISA + 15°C at sea level. ENGINE CONSTRUCTION Description The CF34 power plant has two independently rotating major assemblies. The N1 section consists of a fan rotor that is driven through a shaft by a four-stage low-pressure turbine. The N2 section is comprised of a 14-stage axial flow compressor, a combustor, an accessory gearbox and a two-stage high-pressure turbine. The compressor is driven by the high-pressure turbine. Flow Distribution Engine airflow passes through the single-stage fan, and is divided into two airflow paths: • Bypass air – Air is accelerated by the single-stage N1 fan only, and is ducted around the engine nacelle.
    [Show full text]
  • Ac 25-15 11/20/89
    Advisory us. Departmenf of Tronsportafion Federal Aviation Circular Administration Subject: APPROVAL OF FLIGHT MANAGEMENT Date: 11/20/89 AC No: 25-15 SYSTEMS IN TRANSPORT CATEGORY Initiated by: ANM-110 Change: AIRPLANES 1. PURPOSE. This advisory circular (AC) provides guidance material for the airworthiness approval of flight management systems (FMS} in transport category airplanes. Like all AC material, this AC is not mandatory and does not constitute a regulation. It is issued for guidance purposes and to outline a method of compliance with the rules. In lieu of following this method without deviation, the applicant may elect to follow an alternate method, provided the alternate method is also found by the Federal Aviation Administration (FAA} to be an acceptable means of complying with the requirements of Part 25. Because the method of compliance presented in this AC is not mandatory, the terms II sha11" and "must II used herein apply on1y to an applicant who chooses to follow this particular method without deviation. 2. RELATED DOCUMENTS. a. Related Federal Aviation Regulations {FAR}. Portions of Part 25 and a portion of Part 121, as presently written, can be applied for the design, substantiation, and certification of FMS for transport category airplanes. Sections which prescribe requirements for these types of systems include: § 25.101 Performance: General. § 25 .103 Stalling speed. § 25.105 Takeoff. § 25.107 Takeoff speeds. § 25.109 Accelerate-stop distance. § 25.111 Takeoff path. § 25.113 Takeoff distance and takeoff run. § 25.115 Takeoff flight path. § 25.117 Climb: general. § 25.119 Landing climb: All-engines-operating. § 25.121 Climb: One-engine-inoperative.
    [Show full text]
  • Pneumatic, Air Conditioning, Pressurization System
    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 air or by an external air source on the ground. Certain systems are given priority depending on aircraft operation and conditions. BLEED AIR FUNCTIONS Pressurization Air Conditioning Engine START Anti Ice Electronics Cooling PNEUMATIC SYSTEM DISTRIBUTION The Pneumatic System is divided by the Cross Bleed Valve (CBV). Normal flight procedures isolate the LEFT and RIGHT sides of the Pneumatic System after engine start. Normally, each engine supplies air to its respective: 1) Air Conditioning Pack; 2) ENGINE Anti Ice system; and 3) WING Anti Ice system. The STAB Anti Ice system uses air from the LEFT side of the Pneumatic System. CROSS BLEED VALVE The Cross Bleed Valve (CBV) permits the connection between the two sides of the Pneumatic System. The CBV allows bleed air to cross feed to the Packs in case of APU operation or engine pneumatic power supply failure. The CBV is electrically controlled by the XBLEED knob on the overhead panel. The CBV is pneumatically actuated. The CBV AUTO mode automatically selects the available pneumatic sources. If Anti Ice is used when operating below 24,600', the CBV AUTO mode will OPEN both HSV's and will automatically CLOSE the LEFT Pack Valve. If one Pack has failed then the logic will keep the operating Pack. ENGINE BLEED AIR The LP bleed air is taken from the 9th stage compressor section and passes through a Bleed Air Check Valve (BACV).
    [Show full text]
  • FJ44-3AP Engines and Wingtip STC Information Sheet
    FJ44-3AP Engines and Wingtip STC Information Sheet FAA STC# ST02371LA, Beechcraft Model 400A aircraft, one-time use, $25,000. • STC# ST02371LA allows for: • Replacement of Pratt & Whitney JT15D-5 series engines with Williams International FJ44-3AP engines. Includes Full Authority Digital Engine Control (FADEC) and associated systems. • Removal of existing wingtips which includes upgrading the existing red/green navigation lights and the anti-collision lights to LEDs, which incorporates anti-collision light power supply into the wingtip light. • Removal of the navigation light in the top section of the vertical stabilizer. • Removal of the aft fuselage anti-collision power supply. This eliminates a major source of EMI. No more high voltage. • Installation of new Wing-tip Assemblies, aka winglets. • Installation of new LED navigation and anti-collision light assembly. LEDs use less electrical power, and are more reliable. Equipment Description Part number QTY Full Authority Digital Engine Control (FADEC) 123866 2 Rotational Variable Differential Transducer (RVDT) 3A21200096 2 Beam Instl - Mod N530100-001 1 LH Wingtip Assembly (Winglet) NX0047-5720-0100-001 1 RH Wingtip Assembly (Winglet) NX0047-5720-0100-002 1 LH Wingtip LED Light 87-03916-001 1 RH Wingtip LED Light 87-03917-001 1 Locations: New Engine Fuel Control (LH and RH sides) Beam Instl – Mod (New engine mounts) LH Wingtip Assembly and Wingtip LED Lights Rotational Variable Differential (RH side not shown for clarity) Transducer (RVDT) Full Authority Digital Engine Control (FADEC) New Pylons Revision 1 • Williams FJ44-3AP Engines: o The installation of the FJ44 engines with FADEC is a pre-requisite for upgrading Autothrottles.
    [Show full text]
  • Engine Systems
    TRAINING MANUAL CFM56-5A ENGINE SYSTEMS APRIL 2000 CTC-045 Level 4 EFG CFM56-5A TRAINING MANUAL ENGINE SYSTEMS Published by CFMI CFMI Customer Training Center CFMI Customer Training Services Snecma (RXEF) GE Aircraft Engines Direction de l’Après-Vente Civile Customer Technical Education Center MELUN-MONTEREAU 123 Merchant Street Aérodrome de Villaroche B.P. 1936 Mail Drop Y2 77019 - MELUN-MONTEREAU Cedex Cincinnati, Ohio 45246 FRANCE USA EFFECTIVITY GENERAL Page 1 ALL CFM56-5A ENGINES FOR A319-A320 April 00 CFMI PROPRIETARY INFORMATION EFG CFM56-5A TRAINING MANUAL THIS PAGE INTENTIONALLY LEFT BLANK EFFECTIVITY GENERAL Page 2 ALL CFM56-5A ENGINES FOR A319-A320 April 00 CFMI PROPRIETARY INFORMATION EFG CFM56-5A TRAINING MANUAL This CFMI publication is for Training Purposes Only. The information is accurate at the time of compilation; however, no update service will be furnished to maintain accuracy. For authorized maintenance practices and specifications, consult pertinent maintenance publications. The information (including technical data) contained in this document is the property of CFM International (GE and SNECMA). It is disclosed in confidence, and the technical data therein is exported under a U.S. Government license. Therefore, none of the information may be disclosed to other than the recipient. In addition, the technical data therein and the direct product of that data, may not be diverted, transferred, re-exported or disclosed in any manner not provided for by the license without prior written approval of both the U.S. Government
    [Show full text]