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Technical Requirements ANNEXURE-A TECHNICAL REQUIREMENTS OF DESIGN, DEVELOPMENT AND SUPPLY OF AIRCRAFT INTERIOR ACOUSTIC SOLUTIONS & ENGINEERING SUPPORT FOR REDUCTION OF CABIN NOISE ON ONE CIVIL HAL DORNIER DO-228 AIRCRAFT HINDUSTAN AERONAUTICS LTD. TRANSPORT AIRCRAFT DIVISION POST CHAKERI KANPUR INDIA 208008 Design, Development and Supply of aircraft Interior Acoustic Solutions & Engineering support for reduction of cabin noise on one Civil HAL DO-228 aircraft 1. SCOPE: This document provides an overview of the technical requirements of aircraft interior acoustic solutions for reduction of cabin noise, engineering support for integration & system modification on Civil HAL DO-228 aircraft manufactured by HAL Transport Aircraft Division, Kanpur, India. The document is being circulated as a part of the Request for Information (RFI) to eligible vendors for inviting technical and budgetary commercial information for Design, Development and supply of aircraft interior acoustic solutions & Engineering support for reduction of cabin noise on one Civil HAL DO-228 aircraft. 1.1 INTRODUCTION This specification is applicable to the standard CIVIL DO-228 aircraft. This chapter provides general design characteristics and technical descriptions. Currently, Civil HAL DO-228 aircraft uses only acoustic insulations materials inside cabin for cabin interior noise reduction. Civil DO-228 aircraft does not have any active noise control system (ANC). Preliminary specifications for interior acoustics solution are shown in Table-1 below. TABLE 1: PRELIMINARY SPECIFICATION FOR INTERIOR ACOUSTIC SOLUTIONS SI. Parameters Specifications No 1. Operating Frequency 10 Hz-20000 Hz range 2. Current cabin noise 90-110 dbA level 3. Desirable cabin Noise 80-85 dbA Level 4. Power requirement Derived from +28V DC aircraft Power 5. Power/ Seat 15W (min) 6. Size (Dimensions) of To be specified acoustic solutions 7. Weight (in kg) Total weight penalty to be specified 8. Material Airworthy grade with material properties to be specified 9. System design To be specified if used any Assurance level Technical details of Acoustics solution offered along with compliance against Requirement Parameters to be provided. 1.2 LEADING PARTICULARS: Aircraft Type & Model CIVIL DO-228, Model 201(K) Number of Passengers 19 Number of Crew 2 Maximum Take-off Weight 6200 kg NUMBER DATE ISSUE REV PAGE HAL(K)/DO-228/TR-047 22/11/2019 NIL NIL 2 OF 12 This document is HAL Proprietary and should be treated in strict confidence. Reproduction/circulation without prior permission is prohibited. Design, Development and Supply of aircraft Interior Acoustic Solutions & Engineering support for reduction of cabin noise on one Civil HAL DO-228 aircraft Maximum Landing Weight 6100 kg Engines Two Honeywell TPE331-10GP-511D Fuel Aviation Turbine Fuel (JET-AI, JET-B. JP-4 & JP-5) Propellers Two five-bladed MT-Propeller Entwicklung GmbH Germany MTV-27-1-E-C-F-R (G)/CFRL250-55b 1.3 GENERAL REQUIREMENTS 1.3.1 TYPE CERTIFICATION This Aircraft is designed to meet the Level IV category requirements of FAA: FAR 23 including Amendment 64 The standard aircraft and the associated equipment, as described in this document, conforms to the certification requirements of the FAA 1.3.2 EXTERIOR PAINTING A polyurethane external finish with color scheme to customer’s choice is standard. 1.3.3 ENVIRONMENTAL CONDITIONS The aircraft is designed for normal operation within the temperature range -40 Deg. C (-40 Deg F) to +55 Deg C (+130 Deg F). For ground starting the ambient air temperature range is -40 Deg C (-40 Deg F) to + 45 Deg C (+113 Deg F). The lowest permissible air temperature will be that at which the fuel viscosity is 12 centistokes. 2. POWER PLANT 2.1 GENERAL The Civil DO-228 aircraft is powered by two Honeywell TPE331-10GP-511D engines (Fig.-1), each driving a five bladed, reversible pitch, fully feathering propeller. Nominal engine power is 715 SHP (flat rated. ISA + 18 Deg C (91 Deg F), sea level. Engine cowls are constructed of aluminium alloy and are easily removable for routine and major maintenance. The leading particulars of the engine are: Electrical System Requirements: Max. Electrical Power for Starting 28V DC, 600 Amp (1000 Amp momentary) Electrical Power for Operation 24V DC. 16 Amp Speed Max Climb Cruise RPM Percent 100% 98% 96% Propeller Shaft RPM 1591 1559 1527 Turbine Shaft RPM 41730 40895 40060 NUMBER DATE ISSUE REV PAGE HAL(K)/DO-228/TR-047 22/11/2019 NIL NIL 3 OF 12 This document is HAL Proprietary and should be treated in strict confidence. Reproduction/circulation without prior permission is prohibited. Design, Development and Supply of aircraft Interior Acoustic Solutions & Engineering support for reduction of cabin noise on one Civil HAL DO-228 aircraft 3 PROPELLERS Each engine drives a MTV-27-1-E-C-F-R(G)/CFRL250-55b five bladed, constant speed, feathering and reversible propeller with 2.394 m (95 in.) diameter. Propeller pitch is hydro mechanically adjusted. It consists of the five blades hub housing with hub spider, pitch adjustment mechanism and the spinner bulkhead with slip ring. The blades are made of composite material. Blade roots and pitch mechanism arc covered by a spinner. A propeller de-icing system is available as option. 4. DESIGN CHARACTERSTICS 4.1 DIMENSIONS, AREAS AND GENERAL DATA The HAL-DORNIER 228 is a high wing monoplane with rectangular section fuselage and a conventional empennage. Fig.-1 below shows three views of the aircraft with main dimensions. 4.1.1 WING Wing Span 16.97m (55ft 8in) Area 32.00 sq.m (344.3 sq.ft) Airfoil DO A5 Aspect Ratio 9.0 Taper Ratio 0.7 Sweepback (leading edges) Inboard 0 Deg Outboard 8 Deg THREE VIEW Fig.-1 NUMBER DATE ISSUE REV PAGE HAL(K)/DO-228/TR-047 22/11/2019 NIL NIL 4 OF 12 This document is HAL Proprietary and should be treated in strict confidence. Reproduction/circulation without prior permission is prohibited. Design, Development and Supply of aircraft Interior Acoustic Solutions & Engineering support for reduction of cabin noise on one Civil HAL DO-228 aircraft 4.1.2 FUSELAGE The fuselage is non-pressurized and is built in five sections. Overall external dimensions are: Length 16.56m (54ft 4in) Max Height 1.9m (6ft 3in) Max Width 1.5m (4ft 11in) 4.1.3 COCKPIT The cockpit is designed to accommodate two crew members. Interior dimensions (Fig.-2) provide generous head and legroom for the crew. The pilot seats are adjustable in aft and forward position and equipped with seat-belts and shoulder harnesses. The cockpit-flight instruments meet the requirements of IFR-standard. 4.1.4 CABIN The standard cabin is designed to accommodate 19 passengers. The entrance is at the rear section of the cabin on the left side. Main dimensions of the cabin interior are: Length 7.08m (23ft 3in) Width 1.35m (4ft 5in) Height 1.55m (5ft 1in) Floor Area 9.56 sq m (102.9 sq ft) Volume 14.70 cu m (519 cu ft) Seat Pitch 0.71m (29in) Entrance door (one door panel open) 1.34x0.64m (4ft 5in x 2ft 1in) Cargo door (both door panels open) 1.34x 1.60m (4ft 5in x 5ft 3in) CABIN CROSS SECTION Fig.-: 2 NUMBER DATE ISSUE REV PAGE HAL(K)/DO-228/TR-047 22/11/2019 NIL NIL 5 OF 12 This document is HAL Proprietary and should be treated in strict confidence. Reproduction/circulation without prior permission is prohibited. Design, Development and Supply of aircraft Interior Acoustic Solutions & Engineering support for reduction of cabin noise on one Civil HAL DO-228 aircraft 4.1.5 BAGGAGE COMPARTMENTS The aircraft has two baggage compartments, one in the fuselage front section and one at the rear of the cabin section (Fig.-3). Main dimensions and volumes are: Front Baggage Aft Baggage Compartment Compartment Max Length 1.32m (4ft 4in) 1.85m (6ft 1in) Max Width 1.20m (3ft 11in) 1.35m (4ft 5in) Max Height 0.72m (2ft 4in) 1.55m (5ft 1in) Volume 0.89 cu m (39 cu ft) 2.60 cu m (92 cu ft) Baggage Door 1.20x0.50m (4ft 1ft 7in) 0.90x0.53m (3ft 10in x 1ft 9in) Total volume of both baggage compartments provide an average baggage volume of 0.18 cu m (6.5 cu ft) for each passenger. DOORS, CABIN AND BAGGAGE COMPARTMENTS Fig.-3 NUMBER DATE ISSUE REV PAGE HAL(K)/DO-228/TR-047 22/11/2019 NIL NIL 6 OF 12 This document is HAL Proprietary and should be treated in strict confidence. Reproduction/circulation without prior permission is prohibited. Design, Development and Supply of aircraft Interior Acoustic Solutions & Engineering support for reduction of cabin noise on one Civil HAL DO-228 aircraft 4.2 SPEEDS Max diving speed VD: 255 KIAS Max operating speed upto 15000 ft VMO: 200 KIAS Max manoeuvring speed VA: 147 KIAS Max flap extended speed 1 VFE/VFO: 150 KIAS Max flap extended speed 2 VFE/VFO: 130 KIAS Max gear extended speed VLE/VLO: 160 KIAS Minimum control speed Flaps setting UP VMC: 81 KIAS 1 VMC: 81 KIAS 2 VMC: 76 KIAS 4.3 DESIGN WEIGHTS The design weights of the aircraft are as follows: Max Ramp Weight 6230 kg Max. Take-off Weight Flaps 1 6200 kg Max. Landing Weight Flaps 1 & 2 6100 kg Max. Landing Weight Flaps UP 5900 kg Max. Zero Fuel Weight 5590 kg 4.4 LOADING 4.4.1 CABIN Maximum permissible floor loading is 300 kg/sq.m (61 lbs/sq.ft). Cargo load on palettes is possible upto 1000 kg/sq.m (205 lbs/sq.ft) floor loading. 4.4.2 BAGGAGE COMPARTMENT The maximum loading capacity for the standard rear baggage compartment is 210 kg (463 lbs).
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