TCDS R00001RC

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET NO. R00001RC This data sheet which is part of type certificate No. R00001RC prescribes conditions and limitations under which the product for which type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder Bell Textron Canada Limited 12800 rue de l’Avenir Mirabel, Quebec J7J 1R4 Canada Type Certificate Holder Record: Bell Helicopter Textron Canada Limited was the previous name of TC holder. The company name history is presented below. Type Certificate Holder Period Bell Helicopter Textron Canada Limited, Mirabel Quebec Prior to 16 December 2019 Bell Textron Canada Limited, Mirabel Quebec 16 December 2019 to Present I. Model 427 (Normal Category), Approved January 24, 2000. Engine 2 Pratt and Whitney Canada PW207D Fuel ASTM-D-1655, Type Jet B, Jet A and Jet A-1; MIL-T-5624 Grade JP-4; MIL-T-5624 Grade JP-5 and MIL-T-83133 Grade JP-8. See Rotorcraft Flight Manual for fuel mixture and fuel temperature limitations. For all operations below 5 C (40F) ambient temperature, all fuel used must contain Phillips PFA- 55MB or MIL-L-27686 anti-icing additive in concentrations of not less than 0.06% or more than 0.15% by volume. Installed Engine Limits Torque Lb-ft (%) Turbine Temperature oC (oF) Gas Generator Speed % (RPM) Twin Engine Operation Take-Off (5 Min) 481 (68.6) 900 (1652) 99.8 (5790) Max. Continuous 481 (68.6) 850 (1562) 97.2 (56400) One Engine Inoperative 30 sec. OEI 569 (81.2) 990 (1814) 104.3 (60500) 2 min. OEI 569 (81.2) 950 (1742) 102.2 (59300) 30 min OEI 481 (68.7) 925 (1697) 101.2 (58700) Continuous OEI 481 (68.7) 900 (1652) 99.8 (57900) See Rotorcraft Flight Manual for transient limits Output shaft speed limit is 104.5% (6271 RPM) Rotor Limits Power Off Power On Maximum 423 RPM 107% Maximum 411 RPM 104% Minimum 356 RPM 90% Minimum 391 RPM 99% Transmission Torque Torque Limits % Limits Both Engines Operation Take Off 100 Maximum Continuous 100 One Engine Inoperative OEI 30 Seconds OEI 81.2 2 Minute OEI 75.6 Continuous OEI 57.5 Airspeed Limits Basic VNE (never exceed) is 140 KAIS. Decrease VNE for ambient conditions in accordance with the R00001RC Revision 6 Bell 427 February 11, 2022 Airspeed Limitations placard in the Rotorcraft Flight Manual. Autorotation VNE 80 KIAS C.G. Range (See NOTE 8 and NOTE 10) | Page No. 1 2 3 4 5 6 Rev. No. 6 1 3 6 3 5 Page 2 of 6 R00001RC 1) For approved MGW configuration of 2722 kg (6,000 lbs.) a) Internal Loading Longitudinal C.G. limits cm (in.) Forward limit 561.3 cm (221.0in) at 1724 kg (3800 lb.) changing linearly to 548.6 cm (216.0 in) at 2087 kg (4600 lb.), 548.6 cm (216.0 in) from 2087 kg (4600 lb.) up to 2495 kg (5500 lb.), changing linearly to 551.2 cm (217.0 in) at 2722 kg (6000 lb.). Aft Limit 576.6 cm (227.0 in) at 1724 kg (3800 lb.), up to 2495 kg (5500 lb.), changing linearly to 574.0 cm (226.0 in) at 2722 kg (6000 lb.) Lateral C.G Limits Left 2.8 cm (1.1 in) at 1724 kg (3800 lb.), changing linearly up to 5.3 cm (2.1 in) at 1814 kg (4000 lb.), changing linearly to 3.6 cm (1.4in) at 2722 kg (6000 lb.) Right 4.6 cm (1.8 in) at 1724 kg (3800 lb.) changing linearly up to7.1 cm (2.8 in) at 1814 kg (4000 lb.), changing linearly up to 4.8 cm (1.9 in) at 2722 kg (6000 lb.) b) External Loading Longitudinal C.G. Limits cm (in.) Forward Limit 561.3 cm (221.0 in.) at 1724 kg (3800 lb.) changing linearly to 548.6 cm (216.0 in) at 2087 kg (4600 lb.), 548.6 cm (216.0 in.) from 2087 kg (4600 lb.) up to 2495 kg (5500 lb.) changing linearly to 550.2 cm (216.6 in.) at 2948 kg (6500 lb.) Aft Limit 576.6 cm (227.0 in.) at 1724 kg (3800 lb.) up to 2495 kg (5500 lb.), changing linearly to 574.0 cm (226.0 in.) at 2948 kg (6500 lb.) Lateral C.G. Limits Left 2.8 cm (1.1 in.) at 1724 kg (3800 lb.) changing linearly up to 5.3 cm (2.1 in.) at 1814 kg (4000 lb.), changing linearly to 3.6 cm (1.4 in.) at 2722 kg (6000 lb.), changing linearly to 3.3 cm (1.3 in.) at 2498 kg (6500 lb) Right 4.6 cm (1.8 in.) at 1724 kg (3800 lb.) changing linearly up to 7.1 cm (2.8 in.) at 1814 kg (4000 lb.), changing linearly 4.8 cm (1.9 in.) at 2722 kg (6000 lb.), changing linearly to 4.3 cm (1.7 in.) at 2948 kg (6500 lb.) 2) For approved MGW configuration of 2880 kg (6350 lb.) a) Internal Loading Longitudinal C.G. Limits cm (in.) Forward Limit 561.3 cm (221.0 in.) at 1724 kg (3800 lb.) changing linearly to 548.6 cm (216.0in.) at 2087 kg (4600 lb.), 548.6 cm (216.0 in0.) from 2087 kg (4600 lb.) up to 2495 kg (5500 lb.), changing linearly to 553.0 cm (217.7 in.) at 2880 kg (6350 lb.) Aft Limit 576.6 cm (227.0 in.) at 1724 kg (3800 lb.) to 2495 kg (5500 lb.) varying linearly to 574.4 cm (226.15 in.) at 2880 kg (6350 lb.) C.G. Range (Cont’d) (See NOTE 8 and NOTE 10) Internal Loading (Cont’d) Lateral C.G. Limits Left 2.8 cm (1.1 in.) at 1724 kg. (3800 lb.), changing linearly to 5.3 cm (2.1 in.) at 1814 kg (4000 lb.), changing linearly to 3.4 cm (1.3 in.) at 2880 kg (6350 lb.) Page 3 of 6 R00001RC Right 4.6 cm (1.8 in.) at 1724 kg (3800 lb.) changing linearly to 7.1 cm (2.8 in.) at 1814 kg (4000 lb.), changing linearly to 4.5 cm (1.8 in.) at 2880 kg (6350 lb.) b) External Loading Longitudinal C.G. Limits cm (in.) Forward Limit 561.3 cm (221.0 in.) at 1724 kg (3800 lb.) changing linearly to 548.6 cm (216.0 in.) at 2087 kg (4600 lb.), 548.6 cm (216.0 in.) from 2087 kg (4600 lb.) up to 2495 kg (5500 lb.), changing linearly to 550.2 cm (216.6 in.) at 2948 kg (6500 lb.) Aft Limit 576.6 cm (227.0 in.) at 1724 kg (3800 lb.) up to 2495 kg (5500 lb.), changing linearly to 574.0 cm (226.0 in.) at 2948 kg (6500 lb.) Lateral C.G. Limits Left 2.8 cm (1.1 in.) at 1724 kg (3800 lb.), changing linearly to 5.3 cm (2.1 in.) at 1814 kg (4000 lb.), changing linearly to 3.3 cm (1.3 in.) at 2948 kg (6500 lb.) Right 4.6 cm (1.8 in) at 1724 kg (3800 lb.) changing linearly to 7.1 cm (2.8 in.) at 1814 kg (4000 lb.), changing linearly to 4.3 cm (1.7 in.) 2948 kg (6500 lb.) 3) For approved MGW configuration of 2971 kg (6550 lb.) a) Internal Loading Longitudinal C.G. Limits cm (in.) Forward Limit 561.3 cm (221.0 in.) at 1724 kg (3800 lb.) changing linearly to 548.6 cm (216.0 in.) at 2087 kg (4600 lb.), 548.6 cm (216.0 in.) from 2087 kg (4600 lb.) up to 2495 kg (5500 lb.), changing linearly to 554.0 cm (218.1 in.) at 2971 kg (6550 lb.) Aft Limit 576.6 cm (227.0 in.) at 1724 kg (3800 lb.) to 2495 kg (5500 lb.) changing linearly to 573.9 cm (225.95 in.) at 2971 kg (6550 lb.) Lateral C.G. Limits cm (in.) Left 2.8 cm (1.1 in.) at 1724 kg. (3800 lb.), changing linearly to 5.3 cm (2.1 in.) at 1814 kg (4000 lb.), changing linearly to 3.3 cm (1.3 in.) at 2971 kg (6550 lb.) Right 4.6 cm (1.8 in.) at 1724 kg (3800 lb.) changing linearly up to 7.1 cm (2.8 in.) at 1814 kg (4000 lb.), changing linearly up to 4.3 cm (1.7in.) at 2971 kg (6550 lb.) b) External Loading Longitudinal C.G. Limits cm (in.) Forward Limit 561.3 cm (221.0 in.) at 1724 kg (3800 lb.) changing linearly to 548.6 cm (216.0 in.) at 2087 kg (4600 lb.), 548.6 cm (216.0 in.) from 2087 kg (4600 lb.) up to 2495 kg (5500 lb.), changing linearly to 550.2 cm (216.6 in.) at 2971 kg (6550 lb.) Aft Limit 576.6 cm (227.0 in.) at 1724 kg (3800 lb.) up to 2495 kg (5500 lb.), changing linearly to 573.9 cm (225.95 in.) at 2971 kg (6550 lb.) Lateral C.G. Limits Left 2.8 cm (1.1 in.) at 1724 kg (3800 lb.), changing linearly to 5.3 cm (2.1 in.) at 1814 kg (4000 lb.), changing linearly to 3.3 cm (1.3 in.) at 2971 kg (6550 lb.) Right 4.6 cm (1.8 in) at 1724 kg (3800 lb.) changing linearly up to 7.1 cm (2.8 in.) at 1814 kg (4000 lb.), changing linearly to 4.3 cm (1.7 in.) at 2971 kg (6550 lb.) Page 4 of 6 R00001RC Empty Weight CG Range See Maintenance Manual Datum Model 427 station 0 datum is 203.2 cm (80 in) forward of the nose of the helicopter. Leveling Means Plumb line from underside of the engine pan through the access panel in the baggage compartment roof to an index plate on the floor of the baggage compartment Maximum Weight 2722 kg (6000 lb.) Internal Loading (Mass) 2948 kg (6500 lb.) External Loading 2880 kg (6350 lb.) Internal Loading (see NOTE 8) 2948 kg (6500 lb.) External Loading 2971 kg (6550 lb.) Internal Loading (see NOTE 10) 2971 kg (6550 lb.) External loading Altitude limits Maximum altitude at 2722 kg (6000 lb.) or less is 9000-ft density altitude. (See NOTE 8 and NOTE 10) Maximum altitude for approved MGW configuration of 2880 kg (6,350 lb.) is 10,000-ft pressure altitude. OAT Limits -20°C (-4°F) to 42.2°C (108°F) or (See NOTE 11) -20°C (-4°F) to 51.7°C (125°F) Minimum crew 1 pilot (right seat) Maximum occupants 8 (includes crew) Maximum Baggage Maximum allowable baggage compartment weight is 250 pounds (113.4 kilograms) with a maximum deck and cargo loading of 86 pounds per square foot (4.2 kilograms per 100 square centimeters). Maximum allowable cabin deck loading for cargo is 75 pounds per square foot (3.7 kilograms per 100 square centimeters). Fuel capacity 770.3 litres (203.5 US Gal.) usable, 12.5 litres (3.3 US Gal.) unusable. Oil capacity Each Engine 5.1 litres (4.5 Imp. Quarts) (5.4 US Quarts); Usable oil 1.1 litres (1 Imp. Quart) (1.16 US Quarts) included in capacity Undrainable oil 1.6 lbs. Transmission: 8.5 litres (7.5 Imp quarts) (8.98 US Quarts) Tail Rotor Gearbox: 0.31 litres (0.27 Imp Quarts) (0.33 US Quarts) Rotor blade and For rigging information refer to the 427 Maintenance Manual Control movement Serial numbers eligible 56001 and subsequent. Serial numbers 58001 and subsequent are not eligible for FAA Certificate of Airworthiness. Import Requirements To be considered eligible for operation in the United States, each aircraft manufactured under this Type Certificate must have a U.S. Airworthiness Certificate that may be issued on the basis of the Canadian Department of Transport Certificate of Airworthiness for Export signed by the Minister of Transport containing the following statement: “The rotorcraft covered by this certificate has been examined, tested and found to comply with the type design approved under Type Certificate R00001RC and to be in condition for safe operation.” The approved type design for the model 427 consists of data listed on Bell top drawing 427-100-001, Revision CY, or later approved revision and the incorporation of Bell kit 427-706-018 (fuel shut off valve kit). For helicopter serial numbers 56001 through 56043, either ASB 427-01-05 must be incorporated or Bell kit 427-706-019 (FAA Type Certification Kit) must be installed. See NOTE 9. The U.S. airworthiness certification basis for aircraft certificated under FAR section 21.29 and exported by the country of manufacture is FAR Section 21.183(c) or 21.185(c). Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used aircraft based on the scope of the agreement, to identify any required statements by the exporting authority on the export certificate of airworthiness (or equivalent document), and for procedures for coordinating exceptions to conformity statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certification of Aircraft, for requirements for issuance of an airworthiness certificate for imported aircraft. Page 5 of 6 R00001RC Certification Basis 1. For approved MGW configuration of 2722 kg (6000 lb.) a) FAR part 27, dated October 2, 1964, amendment 27-1 through 27-31FAR part 36 Amendment 36-1 through 36-20 b) The following paragraphs for FAR part 29 at amendment 29-1 through 29-40 (except 29- 38) as identified in FAA AC 27-1A section 780 are used for engine isolation: 29.861(a) 29.901(c) 29.903(b)(c)&(e) 29.908(a) 29.917(b)&(c)(1) 29.927(c)(1) 29.953(a) 29.1027(a) 29.1045 29.1047(a) 29.1181(a) 29.1189(c) 29.1191(a)(1) 29.1193(e) 29.1195(a)&(d) 29.1197 29.1199 29.1201 29.1305(a)(6)&(b) 29.1309(b)(2)(i)&(d) 29.1331(b) Equivalent Safety Findings made in accordance with FAA part 21.21(b)(1) are as follows: 29.903(b), 29.1181(a), 29.1191(a)(1) – Firewalls and Designated Fire Zones c) Additional Equivalent Safety Findings made in accordance with FAA part 21.21(b)(1) are as follows: 27.307(b)(5), 27.723, 27.725, 27.727 – Skid Type Undercarriages 27.963(g) – Fuel Tanks 27.995 – Fuel Valves 27.1191 – Firewalls 27.175(c) - Static Longitudinal Stability in Autorotation e) Special Condition made in accordance with FAR part 21.16 is as follows: 27-00S-SC High Intensity Radiated Fields (HIRF), dated May 11, 1999 2. For approved MGW configuration of 2880 kg (6350 lb.) The basis of certification is the same as in 1. above and in addition the following sections of FAA Part 27: 27.561 at Amendment 27-32 27.1 and 27.2 at Amendment 27-37 Production Basis None. See Import Requirements Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see certification basis) must be installed in the helicopter for certification. In addition, the following items of equipment are required: 1) For approved MGW configuration of 2722 kg (6000 lb.) Transport Canada approved Rotorcraft Flight Manual BHT-427-FM-1 dated November 19, 1999 or later approved revision. 2) For approved MGW configuration of 2880 kg (6350 lb.) Transport Canada approved Rotorcraft Flight Manual BHT-427-FM-2 dated April 27, 2000, or later approved revision. 3) For approved MGW configuration 2971 kg (6550 lb.) Transport Canada approved Rotorcraft Flight Manual BHT-427-FMS-7 dated May 10, 2002, or later approved revision. NOTE 1 Current weight and balance report including list of required equipment and list of equipment included in certificated empty weight, and loading instructions when necessary must be provided for each helicopter at the time of original certification. The certificated empty weight and corresponding C.G. locations must include undrainable oil and unusable fuel for the appropriate model. NOTE 2 The following placard must be displayed in front of and in clear view of the pilot: “THIS HELICOPTER MUST BE OPERATED IN COMPLIANCE WITH OPERATING LIMITATIONS SPECIFIED IN THE APPROVED FLIGHT MANUAL”. All placards listed in the approved flight manual must be installed in the specified locations. NOTE 3 The service lives of components are listed in the BHT 427 Maintenance Manual Chapter 4. This aircraft shall be maintained in accordance with the BHT-427 Maintenance Manual. NOTE 4 Modifications within the compartment, between the main transmission and the engine accessory section, may compromise the mitigating design features approved by an Equivalent Safety Finding to FAR part 27.1191.. The FAA Rotorcraft Directorate must approve all design changes in this area. Page 6 of 6 R00001RC NOTE 5 The model 427 rotorcraft employs electronic engine controls that are recognized to be more susceptible to Electromagnetic Interference (EMI) than manual (non-electronic) controls used on other rotorcraft. EMI may be the result of radiated or conducted interference. For this reason, modifications that add or change systems that have the potential for EMI, must either be qualified to an FAA acceptable standard or tested at the time of installation for interference to the engine controls. This type of testing must employ the particular engine control’s diagnostic techniques and external diagnostic techniques. This testing must be accomplished in accordance with FAA approved Bell Helicopter report No. 427-099-053 Rev. D, or an equivalent FAA approved alternate test plan. NOTE 6 Any changes to the type design of this helicopter by means of a amended type certificate (TC), supplemental type certificate (STC), or amended STC, requiring instructions for continued airworthiness (ICA's) must be submitted thru the project certification office for review and acceptance by the Fort Worth -Aircraft Evaluation Group (FTW-AEG) Flight Standards District Office (FSDO) prior to the aircraft delivery, or upon issuance of the first standard airworthiness certificate for the affected aircraft, whichever occurs later as prescribed by Title 14 CFR 21.50. Type design changes by means of a field approval that require ICA's must have those ICA's reviewed by the field approving FSDO. NOTE 7 The model 427 incorporates an emergency OEI limit override function. When this feature is selected, damage to the engine and transmission is experienced and continued flight is not permitted. Use of this emergency power invalidates the airworthiness of the aircraft and maintenance in accordance with the model 427 Maintenance Manual is required to return the aircraft to an airworthy condition. NOTE 8 1. Model 427 helicopters s/n 56001 to 56024, initially certificated at maximum gross weight (MGW) of 2722 kg (6000 lb), may be operated at MGW of 2880 kg (6350 lb) when Bell Helicopter kit number 427-704-002 (or later approved revision) is incorporated. Helicopters, once modified, must be operated in accordance with flight manual BHT-427-FM-2. 2. Model 427 helicopters s/n 56025 and subsequent (s/n 58001 and subsequent are not eligible for FAA Certificate of Airworthiness) are approved at MGW of 288 kg (6350 lb.) and will have the intent of the kit listed in 1. above incorporated during production. NOTE 9 Model 427 helicopters s/n 56001 through 56043 may be operated without the installation of Bell kit 427-706-019 (FAA Type Certification Kit) when Bell ASB 427-01-05 is incorporated. Model 427 helicopters 56044 and subsequent are modified on the production line. Note 10 Model 427 helicopters s/n 56001 and subsequent (s/n 58001and subsequent are not eligible for FAA Certificate of Airworthiness) with kit 427-706-021 (IGW to 6550 lbs) installed may be operated at a MGW of 2971 kg (6550 lbs). These helicopters must be operated in accordance with Flight Manual Supplement BHT-427-FMS-7. Maintenance instructions and life limited parts are listed in Maintenance Manual BHT-427-MMS-7. Note 11 Model 427 helicopters s/n 56001 through 56035 with kit 427-704-006 (IIDS Cooling Fans) and kit 427-704-010 (Oil Blower System Plenum Removal) and IIDS Data Acquisition Unit of part no. 427- 375-001-105 or higher may be operated at the higher OAT limit of 51.7°C (125°F) in accordance with BHT-427-FMS-22 including Temporary Revision TR-1. Helicopters of serial number 56036 and subsequent (s/n 58001 and subsequent are not eligible for FAA Certificate of Airworthiness) have the intent of these kits incorporated during production. Note 12 Effective December 16, 2019 the name Bell Helicopter Textron Canada Limited was revised to Bell Textron Canada Limited. ….END….