# TCDS R00004SE: Croman Corporation - Type: Type certificate data sheet - Status: Current - Holder: Croman Corporation - Revision: 3 - Revised: March 11, 2015 - Product: Aircraft, Rotorcraft - Certification basis: Part 21, Part 29 - Registered aircraft: 5, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/20/29/20297c030eeb71e92a40a61a56cbec3a115393541d472938fdc5e69c8f0cc795 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID145450500520230310143359.0001 - Page: https://openairdocs.org/tcds/R00004SE ## Models (1) As the data sheet lists them. - SH-3H ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Page No. 1 2 3 4 Revision No. 3 3 2 3 Page 1 of 4 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION R00004SE Croman Corporation SH-3H March 11, 2015 Revision 3 TYPE CERTIFICATE DATA SHEET NO. R00004SE This data sheet, which is part of Type Certificate R00004SE, prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the Title 14 Code of Federal Regulations (14 CFR). Type Certificate Holder: Croman Corporation 801 Ave. “C” White City, OR 97503 Type Certificate Holder Record: TC issued to Croman Corp. on June 2, 2004 Model SH-3H (Military Surplus, Restricted Category), Approved June 2, 2004 Engine: Two (2) General Electric T58-GE-402. Fuel: Aviation Kerosene, JP4, JP5, or Jet A fuels are acceptable, but whenever a change is made, readjustment of the fuel control to appropriate setting must be made. Engine Limits: Engine Limits for T58-GE-402 Engine. Refer to FAA-Approved Rotorcraft Flight Manual. Rotor Limits: Normal 91% to 112.5% Maximum 117% Airspeed Limits: V ne (Never exceed) speed 120 Knots IAS. Other Limits: The helicopters approved under this ty pe certificate are done so under the concept of limited exposure associated with escape from inadvertent ice encounters, and are prohibited against flight into known icing. The helicopter must be re-evaluated if certification to the General Ice Protection Airworthiness Regulations is requested. C.G. Range: Refer to Federal Aviation Administ ration (FAA) Approved Rotorcraft Flight Manual. Datum: 267.4 inches forward of main rotor centroid. Leveling Means: Leveling plates on sill and upper frame of cargo door. Maximum weight: 21,000 lbs. Minimum Crew: Two (2): Pilot and Copilot. No. Seats: Two (2) at Sta. +147.0 (Pilot and Copilo t); one (1) at Sta. +336; one (1) at Sta. + 348; one (1) at Sta. +370 (fold Down Crewmember Seats). Maximum Cargo: Refer to Navy Flight Manual NAVAIR 01-230 HLH-1 and to Note 6. R00004SE Page No. 1 2 3 4 Revision No. 3 3 2 3 Page 2 of 4 Fuel Capacity: 848 Gal. Total (347 Gal. at Sta 215.3, 148 Gal. at Sta. 263.7, 353 Gal. at Sta. 317.3) (Trapped/Unusable-3.1 gal.) Oil Capacity: 6.0 Gal. Total (2 tanks 3 Gal. Each at 181.0) (Trapped/unusable 0.67 Gal. Ref. NAVAlR 01-1B-40 Chart A) Rotor Blade & Control For rigging information, see note 3. Movements: Serial No. Approved: Refer to Croman Corporation R eport No. CC100, "SH-3H Eligible Serial Numbers,” Revision 0, dated February 12, 2003, or later FAA-approved revision. A current copy is on file at the Seattle Aircraft Certification Office. Certification Basis: 14 CFR sect ion (§) 21.25(a)(2), effective February 1, 1965, including Amendments 21-1 through 21-37. Type Certificate R00004SE issued June 2, 2004, for the Special Purpose of: (1) External Load Operations under §21.25(b)(7). Note: In accordance with §36.1(a)(4), compliance with the noise requirements was not shown for Croman Model SH-3H. Therefore, aircraft certificated under this type certificate are only eligible for External Load Operations excepted by §36.1(a)(4) and defined under §133.1(b). Any alteration to the helicopter for Special Purposes not identified above requires further FAA approval and in addition, may require noise and/or flight testing. General Note: Any subsequent modifications to the helicopters type certified under this Type Certificate are to have the certification basis for that modification established under §21.101 published June 7, 2000 which became effective June 10, 2003. Otherwise non-significant modifications are to meet the requirements of part 29 airworthiness standards, transport category, Amendment 1, effective August 12, 1965 and §29.1529, Instructions for Continued Airworthiness, Amendment 20, effective September 11, 1980. Production Basis: None. No helicopter may be produced under this approval. Prior to adding serial numbers to this type certificate, each candidate helicopter must undergo a conformity inspection. The conformity inspection will be conducted in accordance with a Type Inspection Authorization, Part 1, or a request for conformity. Also, a check by the type certificate holder of the flight characteristics in accordance with all applicable portions NATOPS Functional Check Flight Checklist NAVAIR 01-230 HLH-1F, dated August 15, 1997, or later FAA-approved revision, as appropriate for each aircraft, or other FAA approved manual. Date of Application: February 18, 2003. Equipment: The basic required equipment as prescribed in the applicable airworthiness regulations must be installed on each helicopter for certification. In addition, the following is required: (a) U.S. Navy Flight Manual NAVAIR 01- 230, HLH-1, dated January 15, 1991, or later FAA-approved revision must be available in each helicopter. The special purpose equipment and documents must be available in or on each helicopter. (b) Modification as specified in Croman Corporation SH-3H Configuration Report No. CCSH-3H-CONFIGREP-01, Revision IR, dated February 11, 2004, or later FAA-approved revision. R00004SE Page No. 1 2 3 4 Revision No. 3 3 2 3 Page 3 of 4 (c) Croman Corporation Rotorcraft Flight Manual Supplement RFMS-SH3H-2, dated June 22, 2005, or later FAA-approved revision must be available in each helicopter. NOTE 1 A current weight and balance report including a list of equipment included in the certificated empty weight, and loading instructions when necessary, must be provided for each helicopter at the time of original certification. Refer to U.S. Navy Flight Manual NAVAIR 01-230 HLH-1, dated January 15, 1991, or later FAA-approved revision. NOTE 2 The following placards must be prominently di splayed in the cabin in clear view of the pilot: Placard No. 1 "THIS HELICOPTER MUST BE OPERATED IN COMPLIANCE WITH THE OPERATING LIMITATION SPECIFIED IN THE APPROVED HELICOPTER OPERATION'S MANUAL. REFER TO U.S. NAVY FLIGHT MANUAL NAVAIR 01-230 HLH-1. Placard No.2 "THIS ROTORCRAFT MUST BE OPERATED IN ACCORDANCE WITH THE RESTRICTED CATEGORY OPERATING LIMITATIONS OF FAR 91.313." Placard No. 3. "EXTERNAL LOAD OPERATIONS: Vne WILL BE DETERMINED FOR EACH PROPOSED EXTERNAL LOAD APPLICATION" Placard No. 4. "NO PERSON MAY BE CARRIED IN THIS HELCOPTER UNLESS HE IS A FLIGHT CREWMEMBER, FLIGHT CREWMEMBER TRAINEE, OR HE PERFORMS AN ESSENTIAL FUNCTION IN CONNECTION WITH THE MISSION OR IS NECESSARY FOR THE WORK ACTIVITY DIRECTLY ASSOCIATED WITH THE OPERATION." Placard No. 5 "VFR OPERATIONS ONLY" The Type Certificate holder’s data plate required by part 45, § 45.13, must be installed in accordance with Croman Corporation SH-3H Eligible Serial Numbers Report No. CC100, Revision 0, dated February 12, 2003, or later FAA-approved revision. NOTE 3 Aircraft shall be serviced, maintained, in spected, and overhauled in accordance with Croman Corporation Instruction for Continued Airworthiness Report No. CCSH-3HICAR-1, Revision 0, dated September 8, 2003, or later FAA-accepted revision. NOTE 4 Prior to obtaining an orig inal Airworthiness Certificate: A. Each helicopter must satisfactorily pass an inspection for conformity, possible hidden damage, and for workmanship and materials used in making any repairs and or alterations. B. The maintenance, overhaul and modification re cords of each helicopter must be reviewed for military changes that may affect the airworthiness of the helicopter. Modifications and changes of equipment which affect the safety or performance of the helicopter must be approved by the FAA. C. After the required inspections, the aircraft mu st be found to be in a good state of preservation, repair, and in a condition for safe operation. NOTE 5 The Maximum Allowable Operating Time (M AOT) schedule for service life limited part overhaul and retirement intervals are specified in Croman Corporation Instructions for Continued Airworthiness Report No. CCSH-3HICAR-1, Revision 0, dated September 8, 2003, or later FAA-accepted revision. NOTE 6 This aircraft is prohibited from carrying cargo for compensation or hire. Carriage of cargo is limited to such cargo that is incidental to the aircraft owner/operator's business, which is other than air transportation. R00004SE Page No. 1 2 3 4 Revision No. 3 3 2 3 Page 4 of 4 NOTE 7 Restricted category aircraft may not be operated in a foreign country without the express written approval of that country. NOTE 8 This aircraft has not been shown to meet the requirements of the applicable comprehensive and detailed airworthiness code as provided by Annex 8 to the Convention on International Civil Aviation. NOTE 9 Military to Civil or Military to Military engi ne changes are allowed, provided the replacement engine is of the same make and model as identified in this TCDS. The military or civil replacement engine must have proper military or civil records and have the applicable FAA Airworthiness Inspection accomplished and is in an airworthy condition. NOTE 10 Aircraft shall be operated in accordance with U.S. Navy Flight Manual NAVAIR 01-230 HLH-1, dated January 15, 1991, or later FAA-approved revision, and Croman Corporation Rotorcraft Flight Manual Supplement RFMS-SH3H-2, dated June 22, 2005, or later FAA-approved revision, and is limited to VFR Operations only. NOTE 11 Continued Airworthiness of the SH-3H series helicopters listed by serial number in this TCDS is contingent upon compliance with all FAA airworthiness directives as listed in Croman Corporation's SH-3H Airworthiness Directive Report No. CCSH-3HADR-1, Revision 1, dated December 12, 2003, or later FAA-approved revision. NOTE 12 Helicopters that do not have documentation showing they were surplus from an Armed Force of the United States are not eligible for certification under this type certificate. Engines and appliances that do not have documentation showing they were surplus from an Armed Force of the United States are not eligible for installation on a helicopter under this type certificate. Helicopter(s), engine(s), and appliance(s) that have records indicating time-in-service by a foreign military or a foreign government will be presumed to be ineligible for certification or installation under this type certificate. This presumption may be overcome by the applicant substantiating, to the satisfaction of the FAA, through documentation, tests, computations, evaluations, analyses, or other means or methods that the helicopter, engine, or appliance, during its time-in-service by the foreign military or foreign government, was maintained by an extent and in a manner equal to that of an Armed Force of the United States. NOTE 14 No person may be carried in this helicopter duri ng flight unless that person is essential to the purpose of the flight. NOTE 15 Any alteration to the type design of this aircra ft may require Instructions for Continued Airworthiness. If so, these instructions must be submitted and accepted by the FAA Fort Worth Evaluation Group (FTW -AEG), prior to approval for return to service. NOTE 16 Total power for two engine operation is limit ed to 2,500 hp. For takeoff, maximum continuous total power for two engine operation is limited to 2100 hp. These engine power limitations are due to the main gearbox rating. NOTE 17 The 86% Engine Torque limit is due to the maximum continuous main gearbox rating. NOTE 18 Overspeed limits for the T58-GE-402 engine: 108% Ng not to exceed 15 seconds. If less that 15 seconds, corrective action is required to bring RPM within limits. If more than 15 seconds, overspeed inspection is required >108% - Not allowed NOTE 19 For the T58-GE-402 Engine: Maximum allowabl e at all power levels(± 1%); oscillations may be higher in access drive mode. Limits do not apply during autorotations. ``` ## ADs None name its models. ## Registered aircraft by registry model (OpenAirDocs) - [Croman SH-3H](https://openairdocs.org/model/croman-sh-3h): 5 aircraft (registry code 2490000) ## STCs approved under this data sheet (13) - [STC SR01517SE](https://openairdocs.org/stc/SR01517SE): Fabrication and installation of an internal fire retardant tank. Croman Corporation - [STC SR01127SE](https://openairdocs.org/stc/SR01127SE): Modification of main rotor blade part number 61170-20201 in accordance with Master Drawing List RR 9633-08, Revision A, dated September 17, 2002, or later FAA approved revision. Retirement life for the modified main rotor blade, part number RR-61170-20201 is 21,200 total time in service.. Park Technologies, LLC - [STC SR01051DE](https://openairdocs.org/stc/SR01051DE): Installation of Croman Corporation Electric Heater. Croman Corporation - [STC SR04401NY](https://openairdocs.org/stc/SR04401NY): Increase of Out of Ground Effect (OGE) Hover Performance. Carson Helicopters Inc - [STC SR04122NY](https://openairdocs.org/stc/SR04122NY): The Installation of Carson Helicopters, Inc. Composite Tail Rotor Blade and Pitch Sleeve, part number 428-600-1,. Carson Helicopters Inc - [STC SR02077SE](https://openairdocs.org/stc/SR02077SE): Installation of the Observer Seat CRCS100-01. Croman Corporation - [STC SR01755SE](https://openairdocs.org/stc/SR01755SE): Installation of the Main Rotor Head Modification. Croman Corporation - [STC SR01427SE](https://openairdocs.org/stc/SR01427SE): Installation of S-61L fixed main landing gear. Croman Corporation - [STC SR02267SE](https://openairdocs.org/stc/SR02267SE): Fabrication of replacement transmission fittings. Croman Corporation - [STC SH5125NM](https://openairdocs.org/stc/SH5125NM): Installation of Croman 10,000 lbs. cargo sling system and associated fuselage mounting hardpoints.. Croman Corporation - [STC SR01426SE](https://openairdocs.org/stc/SR01426SE): Fabrication and installation of components for a left seat pilot-in-command operation.. Croman Corporation - [STC SR02037SE](https://openairdocs.org/stc/SR02037SE): Fabrication and installation of improved pressure refueling shut-off system. Croman Corporation - [STC SR01288SE](https://openairdocs.org/stc/SR01288SE): Fabrication of Ag-Air Systems Model 36000 Auxiliary Hydraulic System.. Kawak Aviation Technologies Inc --- 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.