TCDS H17NM

Page No. 1 2 3 4 Rev. No. 1 1 1 - DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION H17NM REVISION 1 SILVER BAY LOGGING, INC. CH-54A June 30, 1995 TYPE CERTIFICATE DATA SHEET NO. H17NM This data sheet, which is part of Type Certificate No. H17NM, 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: Silver Bay Logging, Inc. Cube Cove #2 Juneau, Alaska 99850-0360 I - Model CH-54 A (Restricted Category Rotorcraft) Approved June 29, 1994 (see note 6) Engines: Quantity 2 - Pratt & Whitney JFTD12A-4A (T73-P-1) Fuel: Aviation Kerosene JP4 or JP5 Engine Limits: Shaft Horsepowerr Power Turbine Speed (N2) Gas Gen. Speed (N1) Power Inlet (T5) Military Power (30 min.) 4500 105% 104% 688 oC Normal Continuous Cruise 4000 104% 104% 655 oC Rotor Limits Max: 204 rpm (110% Nr) Min: 167 rpm (90% Nr) Airspeed: 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 H17NM 2 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. STA GROSS WT (lbs) 20000 25000 30000 35000 40000 45000 320 325 330 335 340 345 350 355 Datum: 336 inches forward of main rotor centroid. 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 U.S. gal. total ; 454 gal. at (+280.8), 45 4 gal. at (+397.3), 443 gal. at (+461.3). Oil capacity 3.2 U.S. gal. at (+234.0), (2 tanks at 1.6 gal each) Rotor Blade & Control For rigging information, see NOTE 7. Movements Other Operating See NOTE 4. Limitations Serial Nos. Eligible 68-18433, 68-18459 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. H17NM issued June 29, 1994, for agricultural, forest and wildlife conservation or carrying external loads. 3 H17NM Production None. Prior to certification of each aircraft, an FAA representative must perform a Basis detailed inspection for workmanship, materials, and conformity with approved technical data. 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. NOTE 2. The following modifications are required: The placard shown below must be prominately displayed in the cockpit of CH-54A Serial Number 68-18459 in full view of the pilots, in accordance with Aviaton Classics Ltd. Drawing Number ACL94-CH54A/MODP dated May 2, 1994. For CH-54A Serial Number 68-18433and other CH-54A Serial Numbers determined to be eligible, the placard must be displayed in accordance with Silver Bay Logging, Inc. Drawing Number SBL CERT CH-54A-1002 dated 15 June, 1995 or later FAA Approved Revision. "THIS ROTORCRAFT MUST BE OPERATED IN ACCORDANCE WITH THE RESTRICTED CATEGORY OPERATING LIMITATIONS OF FAR 91.313." The builder's data plate required by FAR 45.13 must be installed on CH-54A Serial Number 68- 18459 in accordance with Aviatoin Classics Ltd. Drawing Number ACL94- CH54A/MODR dated April 11, 1994. For CH54A Serial Number 68018433 and other CH-54A Serial Numbers determined to be eligible, the builder's data plate required by FAR 45.13 must be installed in accordance with Silver Bay Logging, Inc. Drawing Number S.B.L. CERT CH-54A-1001 dated 15 June 1995 or later FAA Approved Revision. NOTE 3. The maximum allowable operating time (MAOT) schedule 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. The Maximum Allowable Operating Time (MAOT) for Life Limited Parts (LLP) on the Main Rotor Head are specified in the following list: MAIN ROTOR HEAD PART NO' S 6410-20004, -029, -031, -035: ITEM NOMENCLATURE PART NUMBER RETIREMENT INTERVAL (MAOT) 1 Upper Plate 6410-23010-011 3000 2 Lower Plate 6410-23007-011 3000 3 Spacer 6410-23016-041 -23006-012 9000 4175 4 Hub 1510-23001-4 1030 5 Rod And Bushing 6410-21090-011 5745 6 Sleeve Locknut 1510-23357-0 18300 7 Rot. Swashplate 6410-24002-102 4560 8 Spindle Locknut 1510-23031-1 -23031 10500 750 9 Sleeve 1510-23351 10200 11 Control Horn 1510-23350-2 1600 12 Horiz. Hge. Pin 1510-23099-1 3500 13 Vert. Hge Pin 1510-23022 2800 H17NM 4 NOTE 3. (cont) 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 T73 engines in accordance with Dept. of the Army, AVSCOM (AMSAU-ED) letters. These T73 engine MAOT extensions may not be exceeded. NOTE 4. This helicopter is approved for VFR Operations only and must be operated in accordance with a flight manual comprised of the following: (1) Department of the Army Technical Manual No. TM 55-1520-217-10-1, "Operator's 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 and Crewmember's Checklist, Army Model CH-54A Helicopters, Pilot's checklist", dated June 2, 1985. Restricted category aircraft may not be operated in a foreign country without the express written approval of that country. 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 of International Civil Airworthiness. NOTE 5. Provisions for the carriage of external loads are available in the form of structural hard points on the fuselage and main landing gear; single point hoist : four lashing reels; and four load-leveler suspension systems. Information concerning operating limitations with this equipment is contained in the Flight Manual. NOTE 6. Prior to civil airworthiness certification, each rotorcraft must conform to the data contained in Aviation Classics Limited Engineering Report No. AL-ER 101, dated 20 June 1994 or later FAA approved revisions. NOTE 7. Rotorcraft covered by this Type D ata Sheet must be serviced and maintained in compliance with Aviation Classics Limited Instructions for Continued Airworthiness Report No. AL-MR 102, dated 20 June 1994 or later FAA approved revisions. .....END.....