# TCDS R0014DE: Tandem Rotor LLC - Type: Type certificate data sheet - Status: Current - Holder: Tandem Rotor LLC - Revision: 1 - Revised: November 3, 2025 - 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/ed/01/ed01e0c8fea264f33368eaf7637d8f79dbf06baf8f675ec05752f89c2c211fa4 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID166651046620260810171854.0001 - Page: https://openairdocs.org/tcds/R0014DE ## Models (1) As the data sheet lists them. - CH-47D ## What the data sheet says Some pages are OCR from the scanned FAA data sheet. OCR can misread letters and numbers. ```text DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION R0014DE Revision 1 Tandem Rotor, LLC CH-47D August 30, 2018 TYPE CERTIFICATE DATA SHEET NO. R0014DE This data sheet, which is a part of type certificate No. R0014DE, prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the 14 Code of Federal Aviation Regulations (14 CFR). Type Certificate Holder Tandem Rotor, LLC 124 W. Pine Street Missoula, MT 59802 Type Certificate Holder Record: N/A I - Model CH-47D (Restricted Category Military Surplus Helicopter) Approved August 16, 2016 Engine Two (2) Honeywell T55-GA-714A Fuel ASTM-D1655 JP-8, JP-5, JP-4, (Jet A, Jet A-1, Jet B) (See Note 11 for Alternative and Emergency Fuels) Engine Operating Limits - (Normal Operation) Rating Torque (% Q) Gas Gen. Speed (%Ng) Power Turbine Speed (%Np) Power Turbine Inlet Temp (PTIT) oC Dual Engine Limits Take-Off (10 Min.) 100% 111% 111.5% 899 Military Power (30 Min.) 100% -------- -------- 854 Normal Continuous 100% -------- -------- 815 Contingency Power (Max. for not more than 2.5 minutes) -------- -------- -------- 932 Maximum Transient (for not more than 12 seconds) 100% 111% 111.5% 943 One Engine Limits One Engine Inop (10 Min.) 123% 111% 111.5% 899 One Engine Inop (30 Min.) 123% -------- -------- 854 Normal Continuous 123% -------- -------- 815 Contingency Power (Max. for not more than 2.5 minutes) -------- -------- -------- 932 Maximum Transient (for not more than 12 seconds) 123% 111% 111.5% 943 Rotor Limits Airspeed limits Vne (never exceed): 170 KIAS at Sea Level. See the appropriate Tandem Rotor, LLC, CH- 47D Rotorcraft Flight Manual per Note 5 for variations of Vne with rotor r.p.m., gross weight, pressure altitude and temperature. Sideward Flight (maximum): 45 KIAS Rearward Flight (maximum): 45 KIAS Page No. 1 2 3 4 5 Rev. No. - - 1 - 1 Power Off Power On Minimum 91% r.p.m 91% r.p.m Maximum 108% r.p.m 111% r.p.m RO014DE Page 2 of 5 C.G. range Most forward C.G. Sta. +310.00 Most Aft C.G. Sta. +349.00 (+322.00) to (+331.00) at 50,000 1b. (+319.00) to (+336.00) at 44,800 lb. (+310.00) to (+343.0) at 33,000 lb. (+310.00) to (+349.0) at 28,550 lb. or less CENTER OF GRAVITY LIMITS ARM - INCHES STA ЗST.00 322.00 52,000 EXAMPLE WANTED DETERMINE IF LOADING LIMITS 50,000 - 16300_ ARE EXCEEDED AND DETERMINE C.G. POSITION - 15900 48,000 KNOWN 319.00 15500- 336.00 GW = 43200 LBS 44800 lb 44800 lb MOMENT/1000 46,000 15100 = 13900 _14700 METHOD 44,000 ENTER GROSS 714300 WEIGHT HERE MOVE RIGHT TO TOTAL MOMENT - 42,000 13900 13900. READ LOAD WITHIN LIMITS 13500- MOVE DOWN READ ARM = 321.8 40,000 - 13100_ FORWARD LIMIT -12700__ 38,000 12300_ 36,000 11900 STA 33000 lb 310.00 "11500 343.00 STA 33000 lb. 34,000 - 11100 -10700- GROSS WEIGHT - POUNDS 32,000 10300 -9900- 30,000 -9500_ 28,000 -9100_ 8700_ 26,000 330 350 FUSELAGE STATION OPD30151 Empty weight C.G. range None R0014DE Page 3 of 5 Datum Station 0 (datum is 21.5 inches forward of the most forward point of the nose section) Leveling means Plumb bob hook at top of main cabin door interior trim forward of Sta. 150. Plumb target under main cabin door sill forward of Sta. 150 at BL 48.3. Plumb line from upper hook to target. Maximum weight 50,000 lb. Cargo Hook Limitations The limits presented below are structural limitations only. a. The structural limit of the forward and aft hook is 17,000 pounds each. b. The maximum single load that can be suspended as a tandem load from the forward and aft hooks is 25,000 pounds. c. The center cargo hook is limited to a maximum load of 26,000 pounds. Minimum Crew 3 – (1) pilot (+75), (1) copilot (+75), (1) Crewmember (+135) 2 – (1) pilot (+75), (1) copilot (+75), with embodiment of MDLTAN-300-102 (see note 14) No. of Seats Refer to Tandem Rotor Operators Manual no. TAN-210 “Rotorcraft Flight Manual for the Tandem Rotor, LLC CH-47D Helicopter” Rev. IR, Dated October 20, 2016. No. of Passengers None (see Note 10) Maximum Compartment Weights Refer to the Operators Manual no. TAN-210 “Rotorcraft Flight Manual for the Tandem Rotor, LLC CH-47D Helicopter” Rev. IR, Dated October 20, 2016. Fuel Capacity 1028 gal. (total); 278 gal. (Left Main Tank) Sta. +317.30 274 gal. (Right Main Tank) Sta. +317.30 122 gal. (Left Fwd Aux Tank) Sta. +214.00 119 gal (Right Fwd Aux Tank) Sta. +214.00 118 gal. (Left Aft Aux Tank) Sta. +414.00 117 gal. (Right Aft Aux Tank) Sta. +414.00 Unusable fuel; 1) 4.0 gal. Sta. +316.00 2) 5.8 gal. Sta. +357.00 The full tank usable fuel weight will vary depending upon fuel specific weight. See the appropriate Tandem Rotor, LLC, CH-47D Rotorcraft Flight Manual per Note 5. Oil capacity 3.75 gal. per engine, Sta. +480.7 These are maximum capacities which include residual and trapped oil/fuel. Servicing capacities will be less. See the appropriate Tandem Rotor, LLC, CH-47D Rotorcraft Flight Manual per Note 5. Rotor Blade and For rigging information see Note 3. Control Movements Serial No. Approved U.S. Military Surplus CH-47D helicopters as identified in Tandem Rotor, LLC, Serial Number Report, Restricted Category Type Certificate, Model CH -47D Helicopter, no. TAN-204 Rev. 0 or later FAA approved revision. Date of Application 24-February-2016 R0014DE Page 4 of 5 Certification basis Part 21 § 21.25(a)(2) for the special purpose of: 1) Agricultural § 21.25(b)(1) 2) Forest and Wildlife Conservation Operations under § 21.25(b)(2). Note: In accordance with § 36.1(a)(4), compliance with the noise requirements was not shown. Therefore, aircraft certificated under this type certificate are only eligible for aerial dispensing of liquids and forest conservation material excepted by § 36.1(a)(4) and defined under § 137.3. 3) Other Special-Purpose Operations under § 21.25(b)(7). Includes external load operations for the carriage of cargo external to the fuselage. Note: In accordance with § 36.1(a)(4), compliance with the noise requirements was not shown. Therefore, aircraft certificated under this type certificate are only eligible for carrying external loads excepted by § 36.1(a)(4) and defined under § 133.1(b). Any alteration to the aircraft for Special Purposes not identified above require further FAA approval and in addition, may require noise and/or flight testing. This aircraft approved for Day or Night VFR operations only. Flight into known icing conditions is prohibited. 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. Non-significant modifications are to meet the requirements of 14 CFR § 29 dated February 1, 1965, including Amendments 29-1 through 29-20 and 14 CFR § 29.1529, Instructions for Continued Airworthiness, Amendment 20, effective October 11, 1980. Production basis None. No helicopters may be produced under this approval. No helicopter serial number may be added to this type certificate unless approved by the cognizant Aircraft Certification Office. 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, the appropriate Tandem Rotor, LLC, CH-47D Rotorcraft Flight Manual per Note 5 is required with each helicopter. 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. The certified empty weight and corresponding C.G. locations must include unusable fuel. Refer to the appropriate Tandem Rotor, LLC, CH-47D Rotorcraft Flight Manual per Note 5. NOTE 2. The following placards must be displayed in front of and in clear view of the pilots: Placard No. 1 THIS HELICOPTER MUST BE OPERATED IN COMPLIANCE WITH THE OPERATING LIMITATIONS SPECIFIED IN THE APPROVED ROTORCRAFT FLIGHT MANUAL. Placard No. 2 THIS ROTORCRAFT MUST BE OPERATED IN ACCORDANCE WITH THE RESTRICTED CATEGORY OPERATING LIMITATIONS OF 14 CFR PART 91 § 91.313. NOTE 3. These helicopters must be serviced, maintained, inspected, repaired, and overhauled in compliance with the documents specified in Tandem Rotor, LLC, Applicable ICA, CH-47D Helicopter, document TAN-202 Rev. IR, Dated 5-April-2016, or later FAA approved revision or in accordance with any other FAA accepted maintenance program. Retirement times and FAA required inspections are listed in FAA approved Airworthiness Limitations Section III of the ICA. An FAA approved/accepted copy must accompany each helicopter on delivery. R0014DE Page 5 of 5 NOTE 4. The builder’s data plate must be installed in accordance with Tandem Rotor, LLC, Serial Number Report, Restricted Category Type Certificate, Model CH-47D Helicopter, document TAN-204 Rev. IR Dated October 20, 2016. or later FAA approved revision. NOTE 5. This helicopter must be operated in accordance with Tandem Rotor, LLC, CH-47D Rotorcraft Flight Manual no. TAN-210 Rev. IR, Dated October 20, 2016., or later FAA approved revision. NOTE 6. This helicopter is prohibited from carrying cargo for compensation 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. NOTE 7. A restricted category helicopter may not be operated in a foreign country without the express written approval of that country. NOTE 8. 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 9. The U.S. Army Safety Messages for the helicopter and engine contained in Tandem Rotor, LLC, Configuration Report, Restricted Category Type Certificate, Model CH-47D Helicopter, document TAN- 205 Rev. IR, Dated 09 -April-2016, or later FAA approved revision, must be complied with prior to original airworthiness certification. NOTE 10. No person may be carried in this helicopter during flight unless that person is essential to the purpose of flight. NOTE 11: Alternative and emergency fuels are listed in Chapter 8 of the appropriate Tandem Rotor, LLC, CH- 47D Rotorcraft Flight Manual per Note 5. NOTE 12: Any alteration to the type design of this aircraft may require Instructions for Continued Airworthiness. Changes to the type design by means of a Supplemental Type Certificate requiring ICAs or changes too existing ICAs must be submitted and received by the Fort Worth Evaluation Group (FTW-AEG). Type design changes by means of an FAA Field Approval that require ICA’s must have those ICA’s reviewed by the Flight Standards District Office managing the Field Approval or the FTW-AEG. NOTE 13: No helicopter may obtain a Restricted Category Airworthiness Certificate under this type certificate unless it is included in the “Serial No. Approved List” document no. TAN-204 Rev. IR or later approved revision. NOTE 14: Modification Under Master Data List TAN-002 Rev. E, dated August 27, 2018, FAA approved August 30, 2018 or later FAA approved revision, reduces the required crew from 3 – (1) pilot, (1) copilot, (1) Crewmember to 2 – (1) pilot, (1) copilot. For two crew operation, modification must be embodied and operated in accordance with: a) Master Drawing List TAN-300-102 Rev. IR, dated May12, 2018, FAA approved August 30, 2018 or later FAA approved revision, b) Rotorcraft Flight Manual for CH-47D, TAN-210 Rev. 2, dated August 7, 2018, FAA Approved, August 27, 2018, or later FAA approved revision ...END... ``` ## ADs None name its models. ## Registered aircraft by registry model (OpenAirDocs) - [Tandem Rotor CH47D](https://openairdocs.org/model/tandem-rotor-ch47d): 5 aircraft (registry code 8840351) ## STCs approved under this data sheet (4) - [STC SR02510SE](https://openairdocs.org/stc/SR02510SE): Installation of a Supplemental Lighting System. Aviation Specialties Unlimited Inc. - [STC SR02599SE](https://openairdocs.org/stc/SR02599SE): Installation of a Kawak Aviation Technologies Model 41300 auxiliary hydraulic system.. Kawak Aviation Technologies, Inc. - [STC SR00788DE](https://openairdocs.org/stc/SR00788DE): Installation of Bubble Windows on BFS CH-47D Chinook Rotorcraft for Left and Right sides of the Pilot and Co-Pilot doors respectively. Billings Flying Service Inc. - [STC SR00836DE](https://openairdocs.org/stc/SR00836DE): Modification and Installation of the Pilot Left Seat Cyclic Stick and Thrust Lever Flight Controls. Tandem Rotor, 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.