TCDS H5WE

Page No. 1 2 3 Rev. No. 2 1 1 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION H5WE Revision 2 LOCKHEED L-286 July 23, 2012 TYPE CERTIFICATE DATA SHEET NO. H5WE This data sheet which is a part of type certificate No. H5WE prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the Civil Air Regulations. Type Certificate Holder Lockheed Martin Aeronautics Company 86 South Cobb Drive Marietta, GA 30063 Lockheed-California Company A Division of Lockheed Aircraft Corporation Burbank, California I. Model 286 Normal Category He licopter, approved June 30, 1966 Engine United Aircraft of Canada PT6B-9 Fuel (See Note 6) Grade JP-1, JP-4, JP-5 Aviation Fuel conforming to P&WA Spec. 522 Engine Limits Takeoff (5 min.) Max. continuous Shaft H.P. 550 500 Torque 464 ft-lb. 421 ft.-lb. Gas Generator RPM, N1 38,100 (101.6%) 38,100 (101.6%) Output shaft RPM, N2 6230 (100%) 6230 (100%) Turbine Inlet Temp. 1820 F (994C) 1745 F (952C) Transient Limits Turbine Inlet Temp. during Start (2 second limit) 1900 F (1038C) Gas Generator RPM, N1 (10 second limit) 38,500 (102.6%) Output shaft RPM, N2 6853 (110%) Rotor limits and Power Off Power On engine operating speeds Ma ximum 108% RPM Maximum 104% RPM Minimum 92% RPM Minimum 100% RPM Airspeed limits Density altit ude Vne (never exceed speed) S.L. to 1500’ 136 KCAS 10000’ 103 KCAS (Linear variation between 1500 & 10000 feet) Altitude limits See FAA Approve d Rotorcraft Flight Manual. C.G. Range Most fwd 12000 in. lbs. at max. weight (4700 lbs. and below) (Hub offset moment about Most aft 0 in. lbs. at max. weight (4700 lbs.) main rotor shaft centerline) Most aft 17000 in. lbs. at reduced weight (4000 lbs. and below) Lateral 8000 in. lbs. right and left (4700 lbs. and below) (Linear aft longitudinal variation between 4700 & 4000 lbs.) Datum (Equipment arm 150’ fwd of main rotor shaft centerline H5WE 2 reference index) (See Rotorcraft Flight Manual for weight and balance computation.) Leveling means Plumb bob at Fuselage Sta. 73.5 Maximum weight 4700 lbs. Number of seats 2 (100.7” index arm), 3 (127.5” index arm) Maximum cargo 200 lbs. - fwd LH seat (100.7” index arm) 740 lbs. - aft floor area (127.4” index arm) at 125 lb/sq. ft. max floor landing Fuel capacity 520 lbs. - (151” inde x arm). See NOTE 1 for “unusable” fuel. Oil capacity Engine oil, 24 lbs. (210” index arm). Turbo Jet 35 Transmission oil, 14 lbs. (164” index arm) Turbo Jet 35 Other operating limitations FAA Approve d Rotorcraft Flight Manual. See NOTE 4 for Maintenance and NOTE 5 for Non-Icing Flight Limitations. Service life See NOTE 3 for list of Life Limited Components. Main rotor blade movements Collective pitch at 163” R, 15  up and 0 down (not to be used for rigging. Cy clic (measured with collective full up) Refer to Maintenance Manual Longitudinal  12 tolerance + 1, -0.50 for rigging procedure). Lateral  12 tolerance +1, -0.50 Tail rotor blade movements Collective 10  11’ (thrust to right) 14  45’ (thrust to left) (from neutral rig pin setting) Serial numbers eligible 2001 and up Certification basis CAR 6 dated December 20, 1956, including Amendments 6-1 through 6-7. Type Certificate H5WE issued June 30, 1966. Date of Application of Type Certificate July 15, 1964. Production basis Production Certificate No. 600. Equipment The basic required equipment as pr escribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the helicopter for certification. Lockheed Report 19208, Section IIA “Equipment List,” contains a list of all required equipment that must be installed as well as optional equipment installations approved by the FAA. NOTE 1. Current weight and balance report including lisdt of equipment included in certificated empty weight, and loading instructions, must be provided for each helicopter at the time of original airworthiness certification and at all times thereafter (except in the case of operators having an approved weight control system). Fuel and oil capacities as indicated are total tank capacities over and above “Trapped Fuel and Oil.” The indicated capacity of the fuel tank does not include “Unusable” fuel of 10 pounds which cannot be used safely in all flight attitudes, a nd which must be included in the empty weight. NOTE 2. The following placard must be installed in the Pilot’s Checklist: “This helicopter must be operated in compliance with the operating limitations specified in the FAA Approved Rotorcraft Flight Manual.” For additional placards, see FAA Approved Rotorcraft Flight Manual. 3 H5WE NOTE 3. The retirement times of critical parts are lis ted in the following table. These values of retirement or service life cannot be in creased without FAA Engineering Approval. Life limited components removed when life limit has been reached must be destroyed or permanently marked to prevent return to service. Component Part No . Hours Main rotor blade 542492-1 1800 Main rotor cuff 541464-1 4500 Blade to cuff attach bolts 541628-3, -5 3900 Main rotor T.T. pack 542484 20,000 Tension-Torsion pack bolts 542277-3, 542487-3 4500 Main rotor hub (inc. hub shaft bolts, MS21250) 542446-1 4500* Bearing, plain rod end (pitch link main rotor) 740286-101, -103 300 Inspect every 20 hours Main rotor pitch link rod end bearings DREM 6-087, 6-092 50 (Southwest) Gyro assembly (inc. mounting bolts, MS21250) 542099-1 3600 Gyro support assembly 542209-1 9600 Gyro centering bearings (KAHR) KSBY-7, -7G *** Tail rotor cuff and blade (Parsons) 6570-1100-02 or -03 15,000 Tail rotor assembly (including Cuff) 6570-1100-04 8200 Tail rotor hub 542477-5 1800 Tail rotor trunion (inc. nut 542113 & cone 542115-3) 542111-5 12,000 Bearing, plain rod end (pitch link tail rotor) 740285-101, 740286-105 300 Tail rotor pitch link rod end bearings (Southwest) AREM-5DUW & DREMS-6-092 50 Engine to Trans. Coupling (LORD) LC-5038-1 ** Tail rotor drive shaft assemblies 541375-3, -5, -7, -9 4500 Tail rotor gear box 541384-1 1500 Mach. Inst. swash plate controls 541479-3 26,000 Roll spring, positive 541604-3 5000 Collective actuator (Bertea) 541580-2 19,500 Cyclic pitch actuator (Bertea) 541580-1 19,500 Cyclic roll actuator (Bertea) 541580-1 19,500 Tail boom 541363 12,800* * Inspect per Lockheed Report 19224, pages B-1 and B-2 at 2100 hours and thereafter at periods not to exceed 300 hours from the last inspection. ** Inspect every 100 hours and replace on conditions (V isual check for any deformation or deterioration of core). *** Inspect every 50 hours per Lockheed Report 19224, page B-3. NOTE 4. This model helicopter must be serviced and ma intained in conformance with instruction given by Lockheed-California Company in the Maintenance and Inspection Manual. NOTE 5. This model helicopter is approved for fli ght in non-icing conditions only. See FAA Approved Rotorcraft Flight Manual. NOTE 6. Pnillips anti-icing fuel additive PFA-55MB may be used if concentration delivered to helicopter does not exceed 0.15% by volume. No fuel system anti-icing credit is allowed. -END-