# TCDS H7WE: Sterling Aircraft Industries Inc. - Type: Type certificate data sheet - Status: Current - Holder: Sterling Aircraft Industries Inc. - Revision: 2 - Revised: January 24, 2005 - Product: Aircraft, Rotorcraft - Certification basis: Part 21 - Data sheet PDF: https://openairdocs.org/files/sha256/41/35/41354514a9545ec81f08a9dd67b649cffc27b6cac016616552f7f418ad656845 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/B252DF4036E316EC86256F9C0055D3D2.0001 - Page: https://openairdocs.org/tcds/H7WE ## Models (2) As the data sheet lists them. - U.S. Navy HUP-3/Army H-25A - U.S. Navy HUP-2 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION H7WE Revision 2 Sterling Aircraft Industries, Inc. Piasecki (NAVY) HUP-2 (NAVY) HUP-3/ (ARMY) H-25A Revised January 24, 2005 TYPE CERTIFICATE DATA SHEET NO. H7WE This data sheet which is a part of type certificate No. H7WE 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 5) Type Certificate Holder Record: Sterling Aircraft Industries, Inc. 5060 East Falcon Drive Falcon Field Mesa, Arizona 85205 I - Model U.S. Navy HUP-2 (Restricted Category), approved January 13, 1971 Engine Continental R975-46 Fuel 115/145 or 100/130 Minimum grade aviation gasoline Engine Limits Normal Maximum (30 minute limit) 2350 RPM and 39 in. Hg. (475 HP) Maximum allowable continuous 2350 RPM & 37.5 in. Hg. (450 HP) Rotor Limits and Power Off (Rotor Tach.) Power on (Engine Tach.) engine operating Maximum 360 r.p.m. Maximum 2350 r.p.m. speeds Minimum 230 r.p.m. Minimum 2100 r.p.m. Airspeed limits Vne (never exceed) 75 KIAS C.G. Range 14 in. (167.5) forward to 5.5 in. (187.0) aft of datum Datum Point midway between rotors (181.5) Maximum weight 5400 lbs. Minimum Crew 1 (pilot) (56.0) Fuel capacity 150 gal. (900 lb.) (183.0) Oil capacity Engine oil 9.5 gal. (211.05) Forward transmission 3.0 quarts (50.0) Aft transmission 4.0 quarts (318.97) Other Operating Navy Flight Handbook NW01-250 HCA-1 revised July 1, 1960 and, the FAA Approved Limitations Rotorcraft Flight Manual Supplement (Thomas W. DeShong & Homer H. Helton) dated January 13, 1971 or subsequent FAA Approved Revision. Serial Nos. All Navy Bureau of Aeronautics Serial Numbers identified as Model HUP-2 are eligible Eligible for certification. Page No. 1 2 3 Rev. No. 2 1 2 H7WE Page 2 of 3 II - Model U.S. Navy HUP-3/ARMY H-25A (Restricted Category), Approved June 13, 1975 Engine Continental R975-46 Fuel 115/145 or 100/130 Minimum grade aviation gasoline Engine Limits Normal Maximum (30 minute limit) 2350 RPM and 39 in. Hg. (475 HP) Maximum allowable continuous 2350 RPM & 37.5 in. Hg. (450 HP) Rotor Limits and Power Off (Rotor Tach.) Power On (Engine Tach.) engine operating Maximum 360 r.p.m. Maximu m 2350 r.p.m. speeds Minimum 230 r.p.m. Minimum 2100 r.p.m. Airspeed Limits Vne (never exceed) 75 KIAS C.G. Range 14 in. (167.5) forward to 5.5 in. (187.0) aft of datum Datum Point midway between rotor (181.5) Maximum Weight 5400 lbs. Minimum Crew 1 (pilot) (56.0) Fuel Capacity 150 gal. (900 lb.) (183.0) Oil Capacity Engine oil 9.5 gal. (211.05 Forward transmission 3.0 quarts (50.0) Aft transmission 4.0 quarts (318.97) Other Operating Navy Flight Handbook NW01-250 HCA-1 revised July 1, 1960 and, the FAA Approved Limitations Rotorcraft Flight Manual Supplement dated June 13, 1975 or subsequent FAA Approved Revision. Serial Numbers All Navy Bureau of Aeronautics Serial Numbers identified as Model HUP-3/ARMY H- Eligible 25A are eligible for certification. DATA PERTINENT TO ALL MODELS Certification FAR 21.25(a)(2), effective February 1 1965 Basis Type Certificate No. H7WE reissued June 13, 1975 for the special purpose of: Actual aerial photography only. This does not include the transportation of passengers or cargo to and/or from ground sites. Date of application for Type Certificate March 1, 1969, Amendment September 17, 1970 and October 25, 1974. Production Basis None. No helicopter may be produced under this type approval. 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, equipment necessary for the particular special purpose must be installed. 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 disp layed in the cockpit in full view of the pilot: "This helicopter must be operated in complia nce with the operating limitations specified in NAVWEPS 01-250-HCA-1 and the F AA approved Supplement thereto." Revision 2 Page 3 of 3 H7WE NOTE 3. This helicopter must be serviced and main tained in compliance with Maintenance Handbook NWO1- 250HCA-2, revised July 1, 1960, and Inspection Requirements Handbooks NW01-250HCA-6, revised March 15, 1963, and NW01-250HCA-7, revised March 15, 1963. NOTE 4. Prior to Civil Airworthiness Certif ication, the following must be accomplished: (a) The alterations as shown on F AA Sealed Drawing Nos. 1202 sheet 1, and Sheet 2, and Sheet 3, and 1203 as applicable to the particular ve hicle being presented for Certification. (b) Inspect all rotor blade sets P/N 18R1010- 5, P/N 18R1010-6, P/N 18R1010-50, and P/N 18R1010-60 and rework or replace as necessary in accordance w ith instructions contained in "Handbook - Overhaul and Structural Repair," NAVWEPS 03-95A-501 Revi sed June 1, 1962, as specifically covered by Section II, paragraphs 2-16B through 2-16F, unless the inspection and rework have been accomplished within six (6) months prior to issu ance of the Airworthiness Certificate. (c) Determine that the HUP-2 confor ms to the following service documents: 1. Navy HUP Aircraft Service Ch ange 9, 14, 16, 18, 19, 20, 22, 23, 26, 27, 29, 30, 31, 32, 32A, 33, 34, 35, 36, 39, 41, 42, 44, 45, 46, 47, 47A, 48, 51, 53, 54, 55, 56, 57, 57A, 57B, 59, 60, 62, 66, 67, 68, 72, 73, 74, 75, 77, 77A, 82, 84, 85, 86, 86-1, 87, 88, 92, 94, 95B, 96, 97, 100, 101A, 102, 102A, 102B, 102C, 103, 103-1, 104, 104A, 106, 106A, 107, 107A, 108, 109, 111, 111A, 113, 114A, 115, 117, 119, 122, 123, 124, 125A, 126, 127, 127A, 130. 2. Navy HUP Helicopter Component Bu lletin Nos: 1, 4, 6, 7, and 8. 3. Navy HUP Aircraft Bulletin Nos: 5, 6, 8, 9, 10, 11, 15, 16, 17, 18, 19, 20, 24. (d) Determine that the HUP-2 and HUP-3/Army H-25A conforms to the following service documents: 1. Navy HUP Aircraft Servi ce Change 61, 64, 65, 71, 71A, 71B, 76, 76A, 78, 80, 83, 83A, 90, 91, 91A, 91B, 93, 93-1, 110, 116, 120, 120A, 121, 125, 125A, 125B, 128, 128C, 129, 131, 132, 135, 137. 2. Navy HUP Helicopter Component Bulletin No: 6. 3. Navy HUP Aircraft Bulletin Nos: 13, 21, 22, 25. (e) Determine that the HUP-3/Army H-25A conforms to the following Service Document Navy HUP Aircraft Service Change No. 133. NOTE 5. 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... ``` ## ADs None name its models. ## STCs approved under this data sheet (5) - [STC SA5581SW](https://openairdocs.org/stc/SA5581SW): Installation of ALCOR true-flow/ totalizer system. Alcor LLC - [STC SH3319NM](https://openairdocs.org/stc/SH3319NM): Installation of Precise Flight Pulselite Control Unit in the Landing /Taxi Recognition Visual Control Light system,. Precise Flight Inc - [STC SR00359BO](https://openairdocs.org/stc/SR00359BO): Installation of Parmetheus Plus LED PAR36 and PAR46 taxi and landing lights.. Whelen Aerospace Technologies - [STC SR02394AK](https://openairdocs.org/stc/SR02394AK): Replacement of existing landing and/or hover light bulbs with Light Emitting Diode (LED) lighting system. Seaplanes North LLC - [STC SH160WE](https://openairdocs.org/stc/SH160WE): Installation of agricultural spray system.. Sterling Aircraft Industries --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.