TCDS H9WE

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION H9WE Revision 1 Invest in Opportunities HUS-1 Revised January 24, 2005 TYPE CERTIFICATE DATA SHEET NO. H9WE This data sheet which is a part of type certificate No. H9WE prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder: This Type Certificate (TC) has been designated as ABANDONED (See Note 6) Type Certificate Holder Record: Invest In Opportunities, Inc. P.O. Box 779 Sunset Beach, California 90742 I. - Model HUS-1 (Restricted Category) approved October 25, 1978 Engine Wright Cyclone, R-1820-84A/84C Fuel 100/130 or 115/145 minimum grade aviation gasoline Engine limits HP RPM M.P. IN HG ALT Fuel Grade 115/145 Max. Continuous 1275 2500 47.5 S.L. Max. Continuous 1275 2500 46.0 3500 ft. Takeoff (5 min.) 1525 2800 56.5 S.L. Takeoff (5 min.) 1525 2800 55.5 700 ft. (Straight line manifold pressure variation with altitudes shown) Fuel Grade 100/130 Max. Continuous 1275 2500 47.5 S.L. Max. Continuous 1275 2500 46.0 3500 ft. Takeoff (5 min.) 1325 2800 50.0 S.L. Takeoff (5 min.) 1325 2800 49.5 2000 ft. (Straight line manifold pressure variation with altitude shown) Rotor Limits Maximum 258 r.p.m. Minimum 170 r.p.m. Airspeed limits Vne (never exceed) 120 CAS (See Note 2 for required placard) C.G. range (+130.7) to (+146.7) Datum 137.7 inches forward of main rotor centroid Leveling means Plumb bob from top of cabin door frame to scale on lower door sill Maximum weight 12,700 lbs. Minimum Crew 1 (pilot) (See Note 2) Fuel capacity (usable) Location V olume (Gal.) Arm (Inches) Fwd. Tank 100.5 +121 Center Tank 70.0 +184 Page No. 1 2 3 Rev. No. 1 1 1 H9WE Page 2 of 3 Revision 1 Aft Tank 92.0 +223 Oil capacity 12.4 gals. (+75) Rotor Blade & Control Movements For rigging information refer to Maintenance Manual SA4045-15 Other Operating Limitations See Flight Manual NAVWEPS-01-230HLA-1 revised 12/15/60 Serial Numbers Eligible All Navy serial numbers DATA PERTINENT TO ALL MODELS: Certification basis FAR 21.25(a)(2) effective February 1, 1965. Type Certificate No. H9WE issued October 25, 1978 for the purpose of: Carriage of external loads, per FAR 133 Date of application for Type Certificate was May 1, 1978 The military helicopters certificated restricted category under Type Certificate No. H9WE with aluminum engine mount fittings P/N 1620-61435-series are not eligible for standard category S-58 configuration. Prior to standard airworthiness certification, information regarding eligibility and modification to be accomplished should be obtained from Sikorsky Aircraft. Production basis None. Prior to original airworthiness certification of each aircraft, FAA personnel must perform an airworthiness inspection determining condition for safe operation and determine the applicant has conducted a satisfactory flight test. See NOTE 4 for data on Service Bulletins and ADs. Equipment: The basic required equipment as prescribed for the special purpose operation and as necessary for safe operation must be installed in each helicopter. NOTE 1. Current weight and balance report including list of equipment included in certificated empty weight, and loading instructions when necessary, must be in each helicopter at the time of original airworthiness certification and at all times thereafter. NOTE 2. The following placard must be prominently displayed in the cockpit in full view of the pilot (On Instrument Panel): (a) "Avoid fast turns, 15 s ec. minimum for 360 degrees." (b) "During extended hovering, close windows and doors and turn vent system on. Close left windows during starting and taxiing." (c) "Avoid taxi turns below 2400 engine r.p.m." (d) "Never exceed speeds. Variation on Vne with altitude, engine r.p.m. and manifold pressure." 2200 r.p.m. 2300 r.p.m. 2400 r.p.m. 2500 r.p.m. Alt. IAS M.P. IAS M.P. IAS M.P. IAS M.P. S.L. 72 35.5 87 38.7 103 42.3 117 47.5 5,000 - - - - 60 37.0 76 41.0 90 F.T. 10,000 - - - - - - - - - - - - 63 F.T. Revision 1 Page 3 of 3 H9WE NOTE 2. (Cont'd) (e) "Maximum Approved Gross Weight 12,700 lbs." (f) "This helicopter has been certified in the restricted category only." NOTE 3. Replacement times for life-limited parts are specified in Sikorsky S-58 Maintenance Manual Publication No. SA4045-15 Part IV, Section IV, revised May 5, 1971, unless superseded by appropriate Airworthiness Directives. The replacement period can not be extended without FAA approval. NOTE 4. Prior to civil airworthiness certifi cation, the following must be accomplished: (a) The provisions of the following ADs and all subsequent applicable ADs. ADs 57-19-02, 59-16-04, 60-17-03, 60-24-04, 61- 01-03, 64-02-06, 66-19-04, 74-15-06, 75-07-07, 75- 07-08 and 75-13-01. (b) The provisions of the following Sikorsky Service Bulletins 58B: General-1, General-2, 10-2, 10-3, 10-5, 10-7, 10-10A, 15-1F, 15-2B, 15-3, 15-4H, 15-5C, 15-6A, 15-8, 15-9A, 15-14A, 20-1D, 20-2, 20-6B, 20-7A, 20-9A , 20-10, 20-11, 20-12H, 20-14B, 20-15, 20-17A, 25- 1, 30-1, 30-4, 35-1A, 35-2, 35-3B, 35-5A, 35-6, 35-7A, 35-8B, 35-9, 35-11, 35-16C, 35-17B, 35-18B, 35-19, 40-1, 40-2, 40-4, 65-1, 65-2A, 65-3B AND 65-4A. (c) Deactivate Automatic Flight Control System if installed. NOTE 5. Maintenance will be accomplished in acco rdance to the S-58 Maintenance Manual SA4045-15. Component overhaul intervals shall be in accordance with "Sikorsky Aircraft Engineering Recommended and Customer Approved Component Overhaul Intervals and Replacement Times," Parts I and II, dated 5 September 1956. NOTE 6. This Type Certificate (TC) has been designated "ABANDONED". A “Notice of Intent To Designate as Abandoned Certain Type Certificates Issued in the Restricted Category,” was published by the Federal Aviation Administration (FAA) in the Federal Register on August 8, 2003 (68 FR 47379). That Notice listed this TC. The FAA received no comments on the published Notice. The FAA has been unable to contact this TC holder. Hence, the FAA has determined that this TC holder is not complying with its Continued Operational Safety (COS) responsibilities. Therefore, no additional aircraft will be added to this TC and no additional original airworthiness certificates will be issued based on this TC. The effectiveness of this TC is limited to those aircraft that received original airworthiness certification prior to the incorporation of this note (Date of Incorporation, January 24, 2005). Subsequently, if the TC holder is located and assumes their COS responsibilities, the restriction(s) imposed by this note may be lifted. ...END...