# TCDS H3EA: Boeing Defense & Space Group - Type: Type certificate data sheet - Status: Current - Holder: Boeing Defense & Space Group - Revision: 2 - Revised: September 8, 2003 - Product: Aircraft, Rotorcraft - Certification basis: Part 1, Part 21, Part 29, Part 36, Part 91 - Data sheet PDF: https://openairdocs.org/files/sha256/18/08/18089bbba4523997c88fb101cbfde36a78089613300803d3e9fde87ec2743831 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/374AA3CBFAA3509D86256DD30050793F.0001 - Page: https://openairdocs.org/tcds/H3EA ## Models (1) As the data sheet lists them. - 114A ((U.S. Army CH-47A)) ## 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 H3EA Revision 2 BOEING-VERTOL 114A (U.S. Army CH-47A) 08 September 2003 TYPE CERTIFICATE DATA SHEET NO. H3EA This data sheet which is a part of ty pe certificate No. H3 EA prescribes conditions and lim itations under which the product for which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder The Boeing Company Integrated Defense Systems U.s. Army Programs & Military Rotorcraft Stewart Avenue & Industrial HWY. Ridley Park, Pennsylvania 19078 I - Model 114A (Restricated Category), approved July 30, 1968 Engine 2 Lycoming T55-L-5, T55-L-7, or T55-L-7B Fuel AVJET (wide-cut), JPA (MIL-J-5624). (See Operators Manual foralternate fuels for T55-L-5 engine only). Engine limits Sea level static - Standard Day Shaft hp Power Turbine rpm Gas Producer rpm Power Turbine Inlet Temp Output at 230 rpm Torque 230 Rotor - (lb. ft.) L-5, L-7/7B L-5, L-7/7B L-5 L-7/7B --- --- --- --- --- --- Takeoff (Sea level static - standard only) 2200 2650 * ** 638°C 735°C 800 860*** Maximum continuous 1850 2200 * ** 602°C 635°C 680 780 * A direct relationship to rotor r.p.m. exists. 230 rotor r.p.m. corresponds to 15,150 power turbine r.p.m. Power turbine tachometer not installed. ** Limit established for each engine - refer to engine acceptance test log. *** Transmission torque limit is reached before engine power limit. Refer to pages 7-10 and 7-11 of the Operator's Manual, TM55-1520-209-10, for transient limits. Rotor Limits Power off Power on Minimum 204 r.p.m. Minimum 204 r.p.m. Maximum 261 r.p.m. Maximum 230 r.p.m. Airspeed limits Never exceed 110 knots IAS. For increased airspeed limits at gross weights below 33000 lbs. refer to Operator's Manual TM55-1520-209-10. Page No. 1 2 3 4 5 6 7 Rev. No. 2 2 2 2 2 2 2 H3EA Page 2 of 7 C.G. Range (+314.0) to (+337.0) at 33,000 lb. (+303.5) to (+349.0) at 28,550 lb. (+301.0) to (+349.0) at 27,500 lb. or less 301.0 314.0 337.0 349.0 27,500 28,550 33,000 Fuselage Station -- Inches Gro ss Weight (Poun ds) Datum Fuselage Station 331.0 Leveling means Plumb bob from top of forward door coaming. M aximum weight 33,000 lb. Minimum Crew 2 (Pilot, copilot) Fuel capacity 4095 lb. (+317.3) (non-self-sealing tanks) 4030 lb. (+317.3) (self-sealing tanks) See Operator's Manual TT755-1520-209-10. Oil capacity 5.9 gals. (+480.7), 3.3 gals. unusable See NOTE 1 for data on system fuel and oil. Rotor blade and For rigging information, refer to Department of the Army Technical Manual Control Movements TM55-1520-209-20, "Organizational Maintenance Manual, Army Models CH-47A and CH-47B helicopters," including changes Nos. 1 through 23 dated April 11, 1968. Other operating limitations Department of the Army TM55-1520-209-10, "Operator's Manual Army Models CH-47A and CH-47B helicopters" dated April 1967 including changes Nos. 1 through 3. Flight hours are counted from takeoff to landing. The helicopters approved under this ty pe certificate are done so under the concept of limited exposure associated with escape fro m inadvertent ice encounters, and are prohibited against flight into known icing. The helicopters must be er-evaluated if certification to the General Ice Protection Airworthiness Regulations is requested. Serial Nos. Eligible Boeing Model 114A (CH-47A) Military Helic opters, serial num bers of which are contained in FAA approved Boeing Letter 8-7000-FAA-979, dated September 19, 2003 or later FAA approved revision. H3EA Page 3 of 7 Certification basis Federal Aviation Regulati ons FAR 21.25(a)(2) including amendment 21-1 through 21- 13, effective November 1, 1967.Type Certifi cate No. H3EA issued July 30, 1968 for the special purposes of (1) External Cargo Operations under FAR 21.25(b)(7). Note: In accordance with FAR 36.1(a)(4), compliance with the noise requirements was not shown. Therfore aircraft certified under this type certificate are only eligible for external load operations excepted by FAR 36.1(a)(4) and defined under FAR 137. Any alteration to the helicopter for Special Purpose not identified above require 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 14 CFR 21.101 published June 7, 2000 which became effective June 10, 2003. Otherwise non-significant modifications are to meet the requirements of Civil Aeronautics Manual (CAM) 7, Amendment 7, dated May 3, 1962 and 14 CFR 29.1529, Instructions for Continued Airworthiness, Amendment 20, effective September 11, 1980. Date of Application January 5, 1968 Production basis None. No helicopter may be produced under this approval.(See Note 4). 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 re quest for conformity that will include as a minimum the inspections contained in the FAA Rotorcraft Directoraste Restricted Category conformity document dated September 25, 2001. Equipment: he basic equipment as prescribed in the applicable airworthiness regulations (see certification basis) must be installed in or on each helicopter for certification. See NOTE 6. NOTE 1. A current weight and balance report containing a list of the 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. Refer to Department of the Army Technical Manual TM55-1520-209-10, "Operator's Manual, Army Models CH-47A and CH-47B helicopters" dated April 1967 and including changes Nos. 1 through 3. NOTE 2. The following placard must be prominently displa yed in the cockpit in full view of the pilots: "This rotorcraft must be operated in accordance with the restricated category operating limitations of FAR 91.39." NOTE 3. Service-life-limited components must be retired from serv ice in accordance with the schedule of Chapter 3. Section IV of Department of the Army Technical Manual TM55-1520-209-20: Organizational Maintenance Manual, Army Models CH-47A and CH-47B Helicopters" including changes Nos. 1 through 23 dated April 11, 1968. NOTE 4: In addition to the standard helicopter requirement s, the following additional data and/or helicopter configuration requirements must be met for each individual Boeing Company, helicopter upon application for an original Special Airworthiness Certificate. (a) A completed Application for Airworthiness Certif icate, FAA Form 8130-6 that has correctly identified the type certificate holder’s helicopter and its intended special purpose(s). (b) Written confirmation from the certifying office that the affected serial number has been added to The Boeing Company’s Type Certificate. (c) The application for airworthiness certification a nd the helicopter’s registration certification match the information on The Boeing Company. data plate. H3EA Page 4 of 7 (d) The condition and limitations specified in The Bo eing Company Type Certificate Data Sheet H3EA dated September 8, 2003, or later FAA approved revisions are met. (e) Each helicopter must be inspected by FAA repres entatives or authorized designees to determine the following: (1) Conformance to the requirements of this Type Certificate Data Sheet. (2) In a condition of safe operation. (f) The maintenance, overhaul and modification records of each helicopter must be reviewed for changes made by the military that may affect the airworthin ess of the aircraft. Modifications and changes of equipment, which affect the safety or perform ance of the helicopter must be approved by FAA. NOTE 5. These helicopters must be serviced and maintained in compliance with the following Department of the Army Technical Manuals: TM55-1520-209-20 "Organizational Maintenance Manual, Army Models CH-47A and CH-47B Helicopters" including changes Nos. 1 through 23, dated April 11, 1968. TM55-1520-209-35 "DS, GS, and Depot Maintenance Manual, Army Models CH-47A and CH-47B Helicopters" including changes Nos. 1 through 9, dated February 1, 1968. TM55-1520-209-20 PMD "CH-47A and CH-47B Helicopters, Preventive Maintenance Daily Inspection Checklist" dated November 30, 1967. TM55-1520-209-20 PMI "CH-47A and CH-47B Helicopters, Preventive Maintenance Intermediate Inspection Checklist," dated November 30, 1967. TM55-1520-209-20 PMP "CH-47A and CH-47B Helicopters Preventive Maintenance Periodic Inspection Checklist," dated January 9, 1968. NOTE 6. Modifications to these rotorcraft or special equipment will be necessary, reference FAR 21.25(a)(2), prior to civil airworthiness certification for the special purpose of carriage of external loads and for any other FAA approval special purpose operations. NOTE 7. Prior to civil airworthiness certification complia nce with the following Department of the Army Modification Work Orders must be accomplished: MWO's: 55-1520-209-20/1 MWO's: 55-1520-209-30/4 MWO's: 55-1520-209-34/24 55-1520-209-20/24 55-1520-209-30/28 55-1520-209-34/51 55-1520-209-20/30 55-1520-209-30/29 55-1520-209-34/58 55-1520-209-20/31 55-1520-209-30/41 55-1520-209-34/59 55-1520-209-20/41 55-1520-209-30/48 55-1520-209-34/63 55-1520-209-20/57 55-1520-209-30/55 55-1520-209-34/71 MWO's: 55-1520-209-34/85 MWO's: 55-1520-209-34/107 MWO's: 55-1520-209-34/125 55-1520-209-34/92 55-1520-209-34/109 55-1520-209-34/130 55-1520-209-34/95 55-1520-209-34/111 55-1520-209-34/132 55-1520-209-34/104 55-1520-209-34/118 55-1520-209-34/135 55-1520-209-34/105 55-1520-209-34/124 55-1520-209-34/137 NOTE 8. The following kits must be installed prior to i ssuance of the original Airworthiness Certificate: Kits: 114DK007-1, 114DK205-1, 114E3030-43 and Inspection Kit: 114G5226-1. H3EA Page 5 of 7 NOTE 9. The following transmission configurations are required to be installed prior to issuance of the original Airworthiness Certificate: 114D1001-26, 114D2001-27, 114D5001-18 and 114D6001-18. NOTE 10. The retirement times of critical parts are listed in the following table: (Reference TM55-1520-209-20). COMPONENT PART NO. HOURS Synchronizing Drive 114D3067-2 300 Shaft Adapters Fwd. 114D3067-4 1200 Forward Rotary Wing Blades 114R1002-27 3600 114R1002-29 3600 114R1002-31 3600 114R1002-33 3600 114R1002-35 3600 114R1002-37 3600 Aft Rotary Wing Blades 114R1002-28 2400 114R1002-30 2400 114R1002-32 2400 114R1002-34 2400 114R1002-36 2400 114R1002-38 2400 Forward and Aft Drive 114R3388-5 700 Shaft Collar Assy Forward and Aft Upper 114R3414-1 700 Drive Arm Assy 114R3414-4 700 114R3414-5 700 Aft Vertical Drive 114D3002-1 through -6 600 Shaft Assy Serial No. A-102 through A-114, A-149 through A-151 A-154, A-155, M-103, M-104, M-106 thru M-111, M-115 M-117 through M-119 M-121 M-124 through M-130 M-132 M-134 M-135 M-137 through M-143 M-145 through M-160 M-163 through M-165 M-167 through M-174 M-179, M-180, M-185 M-187, M-188, M-190 through M-194 M-197, M-198, M-200 M-201, M-203 through M-205, M-210, M-213, M-214, M-217, M-221, M-224, M-225 through M-227, M-234, M-236, H3EA Page 6 of 7 COMPONENT PART NO. HOURS Aft Vertical Drive M-255 through M-258 Shaft Assy M-274 Aft Vertical Drive Shaft Assy 114D3002-1 800 through -6 Serial No. A-118, M-162, M-166, M-176, M-182, M-183, M-189, M-209, M-218, M-222, M-223, M-228, M-230 through -232, M-235, M-237, M-238, M-240, M-242, M-246, M-251, through M-253 Aft Vertical Drive 114D3002-1 1000 Shaft Assy through -6 Serial No. A-115 through A-117 Aft Vertical Drive Shaft Assy 114D3002-1 1000 through -6 Serial No. A-119 thru A-148, A-152, A-153, A-156 thru A-189 A-191 and subsequent "A" shaft assy's M-177, M-178, M-184, M-186, M-195, M-196, M-199, M-202, M-206, thru M-208, M-211, M-212, M-215, M-216, M-219, M-220, M-229, M-233, M-239, M-243 thru M-245, M-247 thru M-250, M-254, M-259, thru M-273, M-275 thru M-278, M-280, M-282 thru M-290, M-292 and subsequent "M" shaft assy's. Bolt NAS 1308-50DW 600 *Blade Lag 114HS6800-1 Damper Assy *Periodic inspection of this unit is required in acco rdance with Item 6.7 Page 16 of TM55-1520-209- 20 PMI. NOTE 11 This helicopter is prohibited from carrying cargo for compen sation or hire. Carriage of cargo is limited to such cargo that is incidental to the helicopter owners/operator’s business, which is other than air transportation. H3EA Page 7 of 7 NOTE 12: A restricted category helicopter may not be operated in a foreign country without the express written approval of that country. NOTE 13: This helicopter 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 the International Civil Aviation Organization. NOTE 14: Helicopters that do not have documentation showing they were surplus from an Armed Force of the United Stetes are not eligible for certification under this type cerficate. Engines and appliances that do not have documentation showing they were surplus from an Armed Foce of the United States are not eligible for installation on a helicopter under this type certificate. Helicopter(s). engine(s), and appliances 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 maybe overcome by the applicant substantiating to the satisfaction of the FAA through documentation, tets, computations, evaluations, analysis or other means or methods that the helicopter, engines or appliance during its time–in-service by the foreign military or foreign government, was maintained to an extend and in a manner equal to that of an Armed Forces of the United States. NOTE 15: No person may be carried in this helicopter during fli ght unless that person is essential to the purpose of flight. NOTE 16: Any alteration to the type design of this aircraft may re quire Instructions for Continued Airworthiness. If so, these instructions must be submitted and accepted by the FAA Fort Worth Aircraft Evaluation Group (FTW-AEG), prior to approval for return to service. NOTE 17: Carriage of hazardous materials is prohibited unless compliance is shown with applicable regulations in Code of Federal Regulations Title 49, Part 175. NOTE 18: For mailing and correspondence purposes use the following address: The Boeing Company, Integrated Defense Systems, U.S. Army Programs & Military Rotorcraft P.O. Box 16858 Philadelphia, PA 19078. ...END... ``` ## ADs (1, in force first) - [AD 75-08-17](https://openairdocs.org/ad/75-08-17): Digital Flight Data Recorders · BAE Systems HS 748 Series 2A, HS 748 Series 2B, 727-100 Series and 90 more. Effective Dec 19, 1975 ## Registered aircraft by registry model (OpenAirDocs) - [Boeing 114A](https://openairdocs.org/model/boeing-114a): 0 aircraft (registry code 1380200) ## STCs approved under this data sheet (2) - [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 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 --- 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.