# TCDS H13NM: Chet Raspberry Inc. (CRI) - Type: Type certificate data sheet - Status: Current - Holder: Chet Raspberry Inc. (CRI) - Revision: 1 - Revised: January 23, 2002 - Product: Aircraft, Rotorcraft - Certification basis: Part 21, Part 45, Part 91 - Data sheet PDF: https://openairdocs.org/files/sha256/aa/77/aa77e8190745e211b2cf3eb105e158b3194d723479eac79dfaff62bd287d3bd5 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/648ED57B724ABA1586256D740063BB95.0001 - Page: https://openairdocs.org/tcds/H13NM ## Models (1) As the data sheet lists them. - CH-54A ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text SURRENDERED January 23, 2002 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION H13NM Revision 1 Chet Raspberry Inc. (CRI) CH-54A Surrendered January 23, 2002 TYPE CERTIFICATE DATA SHEET NO. H13NM This data sheet, which is a part of Type Certificate No. H13NM, 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: Chet Raspberry Inc. (CRI) 19378 Central Road Apple Valley, CA 92307 I.- Model CH-54A (Restricted Category Rotorcraft) Approved October 5, 1993 See NOTE 6 Engines 2 Pratt & Whitney JFTD12A-4A (T73-P-1) Fuel Aviation Kerosene JP4 or JP5 Engine Limits Power Gas Gen. Power Turbine Speed Inlet Shaft Speed (N1) (T6) Horsepower (N2) Military Power (30 Min.) 4500 105% 104% 688-C Normal Continuous Cruise 4000 104% 104% 655-C Rotor limits Max. 204 rpm (110% Nr) Min. 167 rpm ( 90% Nr) Airs peed VNE (Never Exceed Speed): 99 knots between 38,000 lbs. and 42,000 lbs. gross weight. 115 knots up to 38,000 lbs. gross weight Center of Gravity 324.0 to 352.0 at 23,000 lbs. (C.G.) Range 324.0 to 352.0 at 30,000 lbs. 328.0 to 352.0 at 38,000 lbs. 328.0 to 346.0 at 38,000 lbs. 328.0 to 346.0 at 42,000 lbs. Straight line variation between points given. Page No. 1 2 3 Rev. No. 1 - - H13NM 2 32 4 328 34 6 352 23 ,000 30, 000 38, 000 42 ,000 Gr oss We ight (Pou nds ) In ch es fro m Datum Datum 336 inches forward of main rotor centeroid. Leveling Means Plumb line from top level plate inside cockpit aft door. Maximum Weight 42,000 lbs. Minimum Crew 2 (pilot and co-pilot) Number of Seats 5 - 2 at (+92.9), 1 at +(108.5), 1 at (+127.0), 1 at (+130.0) Maximum Cargo See NOTE 5. Fuel Capacity 1351 gal. 454 gal. at (+280.8), 454 gal. at (+397.3), 443 gal. at (+461.3). Oil Capacity 3.2 gal. at (+234.0), (2 tanks 1.6 gal. each). Rotor Blade & Control For rigging information, see NOTE 7. Movements Other Operating See NOTE 4. Lim itations Serial No. Eligible 68-18447 Certification Basis FAR 21.25(a)(2) effective February 1, 1965, including Amendments 21-1 through 21-42, FAR 36.1(a)(4), Type Certificate No. H13NM issued October 5, 1993, for Agricultural aircraft operations, for dispensing fire fighting materials or carrying external loads. Production Basis None. Prior to certification of each aircraft, a representative must perform a detailed inspection for workmanship, materials, and conformity with approved technical data, and will verify that a maintenance flight test has been completed for each aircraft by qualified maintenance personnel in accordance with the Department of the Army Technical Manual TM 55-1520-217-MFT-1, dated June 17, 1985. Equipment Equipment necessary for the particular special purpose operation must be installed. NOTES 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 in each helicopter at the time of original airworthiness certification and at all times thereafter. 3 H13NM NOTE 2. The following modifications are required. A placard must be prominently displayed in the cockpit in full view of the pilots, in accordance with drawing CRI-01. "THIS ROTORCRAFT MUST BE OPERATED IN ACCORDANCE WITH THE RESTRICTED CATEGORY OPERATING LIMITATIONS OF FAR 91.313" The builders data plate required by FAR 45.13 must be installed in accordance with drawing CRI-02. NOTE 3. The Maximum Allowable Operating Time (MAOT) sc hedule for Service Life Limited Part overhaul and retirement intervals are specified in Chapter 1, Section VI, of Technical Manual No. TM 55-1520-217-23-1, "Aviation Unit and Intermediate Maintenance Manual CH-54A Helicopter," with Changes 1 through 21, dated September 23, 1987. T73 Engine TBO was increased from 1500 to 1800 hours in accordance with Dept. of Army message 0619452 dated April 13, 1988. Additional MAOT extensions were granted to specific CH-54A T-73 engines in accordance with Dept. of the Army, AVSCOM (AMSAU-ED) letters. These T-73 engine MAOT extensions may not be exceeded. NOTE 4. This helicopter must be operated in accordan ce with a Flight Manual comprised of the following: (1) Department of the Army Technical Manual No. TM 55-1520-217-10-1, "Operators Manual, Army Model CH-54A Helicopters," dated April 8, 1977, with Changes 1 through 8, revised September 25, 1986. (2) Department of the Army Technical Manual No . TM 55-1520-217-CL-1, "Operator's & Crewmember's Checklist, Army Model CH-54A Helicopter s, Pilot's Checklist," dated June 2, 1985. Day VFR Restricted Category operations only. NOTE 5. Provisions for the carriage of external loads are availa ble in the form of structural hard points on the fuselage and main landing gear; single and four-point hoists; and a four-point load-leveler suspension system. Information concerning the operating limitations with this equipment is contained in the Flight Manual. NOTE 6. Prior to civil airworthiness certification, CRI Helicopter Inc. Engineering Report No. 001 must be incorporated. NOTE 7. These helicopters must be serviced and maintain ed in compliance with CRI Helicopters Inc. Continued Airworthiness Maintenance Report No. 002. NOTE 8. This TCDS surrendered January 23, 2002. ...END... ``` ## ADs None name its models. ## STCs approved under this data sheet (1) - [STC SA4302NM](https://openairdocs.org/stc/SA4302NM): Installation of Electronics Int'l digital automatic engine analyzer.. Electronics International --- 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.