# TCDS R00115SE: Billings Flying Service Inc. - Type: Type certificate data sheet - Status: Current - Holder: Billings Flying Service Inc. - Revision: 0 - Revised: March 13, 2025 - Product: Aircraft, Rotorcraft - Certification basis: Part 21, Part 29 - Data sheet PDF: https://openairdocs.org/files/sha256/b6/66/b6660d6b1b68bb8ff943ab0c826df47b461456e95dc89992b5f04b2dbf863232 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID178558725320250314201527.0001 - Page: https://openairdocs.org/tcds/R00115SE ## Models (2) As the data sheet lists them. - CH-47D - Honeywell 55-L-714A ## What the data sheet says Some pages are OCR from the scanned FAA data sheet. OCR can misread letters and numbers. ```text Page No. 1 2 3 4 5 6 Rev. No. 0 0 0 0 0 0 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION R00115SE Billings Flying Service, Inc. CH-47D Revision 0 March 13, 2025 TYPE CERTIFICATE DATA SHEET NO. R00115SE This data sheet, which is a part of Type Certificate No. R00115SE, prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of Title 14, Code of Federal Regulations (14 CFR). Type Certificate Holder: Billings Flying Service, Inc. 3655 A J Way Billings, MT 59106 Type Certificate Holder Record: N/A I – Model CH-47D (Restricted Category Military Surplus Rotorcraft) Approved March 13, 2025 (See NOTES Section) Engines (2) Honeywell 55-L-714A Fuel ASTM-D1655 (Jet A, Jet A-1, Jet B); JP-8, JP-5, JP-4, Alternative and emergency fuels are listed in Rotorcraft Flight Manual BFS-610, Rev. IR, dated February 11, 2025, or later FAA approved revision. Engine and Transmission Limits Rating Torque (% Q) Gas Gen. Speed (%Ng) Power Turbine Speed (%Np) Power Turbine Inlet Temp Dual Engine Limits Maximum Transient 101% 112% 111.5% 943°C Maximum (10 Min.) 101% 112% 111.5% 899°C Intermediate Power (30 Min.) 101% 112% 111.5% 854°C Maximum (Normal) Continuous 101% 111% 111.5% 816°C Single Engine Limits One Engine Inoperative 123% 112% 111.5% 899 °C Contingency Power (2.5 Min.) 123% 112% 111.5% 932 °C Refer to Billings Flying Service, Inc., Rotorcraft Flight Manual BFS-610, Rev. IR, dated February 11, 2025, or later FAA approved revisions for additional limitation data. R00115SE Page 2 of 6 Rotor Speed Limits Limit Minimum Transient power-on, low NR 91% Maximum transient power-on, high NR 106 % Maximum during autorotation 108% Maximum transient 111% Airspeed Limits 1. Airspeed limitations with an operative cruise guide indicator are per the following indicator displays (not to exceed 170 KIAS): a. Pointer must be kept in the green region. b. Transient pointer excursions into the yellow region are permissible but should be minimized. c. Pointer excursions into the red region are to be avoided. 2. Airspeed limitations with an inoperative cruise guide indicator are per the airspeed limitations shown in figure 6.5-1 Billings Flying Service, Inc., Rotorcraft Flight Manual BFS-610, Rev. IR, dated February 11, 2025, or later FAA approved revision. Flight at or below 98% NR with an inoperative cruise guide indicator is prohibited. 3. The following airspeed limitations apply with an operative or inoperative cruise guide indicator: a. Maximum airspeed in sideward flight is 45 knots. b. Maximum airspeed in rearward flight is 45 knots. c. Maximum crosswind or tailwind for hover is 45 knots. d. Maximum airspeed with the lower section of the cabin entrance door open and locked is 60 KIAS. e. The rescue hatch door shall not be opened or closed above 90 KIAS. f. The windshield wiper control should be at the FAST position for airspeeds above 100 knots and at the OFF position for airspeeds above 130 knots. g. The lower cabin door plug can be installed or removed in-flight at airspeeds up to 40 knots. No airspeed restrictions apply with the door plug completely removed or installed. h. Cabin door, upper section — Ensure that the airspeed is less than 100 KIAS before closing door in flight. R00115SE Page 3 of 6 Center of Gravity Limits EXAMPLE WANTED CENTER OF GRAVITY LIMITS DETERMINE IF ARM - INCHES LOADING LIMITS ARE EXCEEDED AND DETERMINE 24000 C.G. POSITION KNOWN 23000 AUM - 20600 KG MOMENT/1000 - 6722 22000 METHOD 21000 ENTER ALL UP MASS HERE MOVE RIGHT TO TOTAL MOMENT - 20000 6722. READ LOAD WITHIN LIMITS MOVE DOWN READ ARM - 326.3 19000 ALL UP MASS - KG 18000 17000 16000 15000 14000 13000 12000 11000 10000 306 311 316 321 326 331 336 341 346 351 FUSELAGE STATION - INCHES 112-10-910000-A40526 Figure 1 Refer to Rotorcraft Flight Manual BFS-610, Rev. IR, dated February 11, 2025, or later FAA approved revision for specific C.G. range and limits. Datum Station 0 (Datum is 5.5 inches forward of the nose). Leveling Means Plumb bob from upper aft corner of cabin doorway. Maximum Weight 54,000 Ibs. (24,494 kg) Cargo Hook Limitations The limits presented below are structural limitations only. a. The structural limit of the forward and aft hook is 20,000 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 28,000 pounds. R00115SE Page 4 of 6 Minimum Crew 3 – (1) pilot (+75), (1) copilot (+75), (1) Crewmember (+135) (See Note 12). Maximum Cargo Refer to Rotorcraft Flight Manual BFS-610, Rev. IR, dated February 11, 2025, or later FAA approved revision for various configurations. No. of Seats See Note 10 Fuel Capacity Left Main – 1050 Liters (277.4 gal) Right Main – 1055 Liters (278.7 gal) Left Fwd Aux – 432 Liters (114.1 gal) Right Fwd Aux – 428 Liters (113.1 gal) Left Aft Aux – 429 Liters (113.3 gal) Right Aft Aux – 426 Liters (112.5 gal) Note: These are maximum capacities which include residual and trapped fuel. Servicing capacities will be less. Refer to Rotorcraft Flight Manual BFS-610, Rev. IR, dated February 11, 2025, or later FAA approved revision for various configurations. Engine Oil Capacity 14.2 Liters (15 Qts) Includes 7 liters (7.4 qt) of useable oil, 4.2 liters (4.4 qt) of unusable oil, and 3.0 liters (3.2 qt) of expansion space. This is maximum capacity which includes residual and trapped oil. Servicing capacities will be less. Refer to Rotorcraft Flight Manual BFS-610, Rev. IR, dated February 11, 2025, or later FAA approved revision for additional information. Rotor Blade and Control Movements For rigging information, refer to Boeing Helicopters International CH47D (RNLAF) Maintenance Systems Manual, document number ICH-47D-MS, Revision 10, dated September 24, 2019, or later FAA-accepted revision. Other Limits This helicopter must be operated in accordance with the following: (1) Billings Flying Service, Inc. Rotorcraft Flight Manual, BFS-610, Rev. IR, dated February 11, 2025, or later FAA approved revision. (2) Billings Flying Service, Inc. Functional Check Flight Manual, BFS-608, Revision IR, dated September 6, 2024, or later FAA accepted revision. (3) Billings Flying Service, Inc. Crewmember’s Checklist, Report No. BFS-606, Revision A, dated January 23, 2025, or later FAA accepted revision. Serial No. Approved Royal Netherlands Air Force (RNAF) surplus CH-47D helicopters as identified in Type Certificate Data Sheet R00115SE Approved Serial Number List, Billings Flying Service, Inc., Report Number BFS-604, Rev. A, dated February 19, 2025, or later FAA approved revision. Only those serial numbers identified in Exemption 21911, issued October 24, 2024, are eligible to be added to this Type Certificate. Certification Basis 14 CFR Part 21, Section (§) 21.25(a)(2), for the special purposes of: 1) Agricultural operations under § 21.25(b)(1) 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 agricultural operations excepted by § 36.1(a)(4) and defined under § 137.3. 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) External Cargo Operations under § 21.25(b)(7) 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 external load operations excepted by § 36.1(a)(4) and defined under § 133.1(b). R00115SE Page 5 of 6 Any alterations to the helicopter for Special Purposes not identified above require further FAA approval and in addition, may require noise and/or flight testing. 14 CFR § 29.1529, Amendment 29-20, effective October 14, 1980 Exemption 21911, issued October 24, 2024 (See Note 13) This aircraft is 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 § 21.101. Otherwise, non-significant modifications are to meet the requirements of 14 CFR, Part 29, Amendment 29-20, effective October 14, 1980. . Date of Application June 10, 2024 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 FAA Certification Branch. Each helicopter must pass a conformity inspection in accordance with this TCDS, plus any additional special instructions attached to the Request for conformity, FAA 8120-10. In addition, a check by the Type Certificate holder or its agent, of the flight characteristics in accordance with applicable portions of the Billings Flying Service, Inc. Functional Check Flight Manual, BFS-608, Revision IR, dated September 6, 2024, or later FAA accepted revision, is required. Equipment The basic required equipment necessary for the special purpose operation must be installed for certification. NOTES NOTE 1. A current weight and balance report including a list of equipment included in the certified empty weight, and loading instructions, when necessary, must be provided for each helicopter at the time of original airworthiness certification. NOTE 2. The following placards must be prominently displayed in the cockpit in full view of the pilots: Placard No. 1 THIS HELICOPTER MUST BE OPERATED IN COMPLIANCE WITH THE OPERATING LIMITATIONS SPECIFIED IN THE FAA APPROVED HELICOPTER FLIGHT MANUAL NO. BFS-610 “CH-47D HELICOPTER”, REV. IR OR LATER FAA APPROVED REVISION. Placard No. 2 THIS ROTORCRAFT MUST BE OPERA TED IN ACCORDANCE WITH THE RESTRICTED CATEGORY OPERATING LIMITATIONS OF 14 CFR PART 91.313. Placard No. 3 ICE DETECTOR DEACTIVATED NOTE 3. The helicopter(s) may be serviced, maintained, inspected, repaired and overhauled in accordance with the requirements specified in Billings Flying Service, Inc. Instructions for Continued Airworthiness Report BFS-602, Revision A, dated February 12, 2025, or later FAA accepted revision, or other FAA approved programs. The life-limited parts, overhaul, and retirement intervals for these helicopters are specified in Maintenance Manual Chapter 4, document number ICH-47D-MS/BFS, Revision B, dated February 12, 2025, or later FAA approved revision. R00115SE Page 6 of 6 NOTE 4. The builder’s data plate required by 14 CFR § 45.13 must be installed in accordance with Billings Flying Service, Inc. Drawing BFS47Z0001, Rev B, dated February 11, 2025, or later FAA approved revisions. NOTE 5. A Rotorcraft Flight Manual BFS-610, Rev. IR, dated February 11, 2025 copy must accompany each helicopter on delivery. The certification life limits for the helicopter, its engine and appliances were based on satisfactory service history as designed and operated by the RNAF. Therefore, cycle counting and operational time tracking is required on certain critical components, to operate and maintain the aircraft to the original acceptance criteria, and maintain its safe for intended use requirement (Ref BFSED-24-0606 Rev B or later FAA approved revision). NOTE 6. Billings Flying Service, Inc. Engineering Configuration Report BFS-601, Rev. A, dated January 17, 2025, or later FAA accepted revision identifies the de-configuration, addition of equipment, and military airframe changes necessary for the special purpose helicopter. 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 on International Civil Aviation. NOTE 9. The Safety messages for the helicopter contained in Billings Flying Service, Inc., Airworthiness Directives and Safety Messages report no. BFS-605, Revision IR, dated June 27, 2024, or later FAA accepted revision, must be complied with prior to original airworthiness certification. NOTE 10. 1) No person may be carried in this helicopter during flight unless that person is essential to the purpose of the flight. See Rotorcraft Flight Manual BFS-610, Rev. IR, dated February 11, 2025, or later FAA approved revision for approved seating locations. 2) This helicopter is prohibited from carrying cargo for compensation or hire. Carriage of internal cargo is limited to such cargo that is incidental to the helicopter owners/operator’s business, which is other than air transportation. 3) Carriage of hazardous material is prohibited unless compliance is shown with applicable regulations in Title 49, Code of Federal Regulations, Part 175. NOTE 11. Any Alteration to the type design of this aircraft may require Instructions for Continued Airworthiness (ICA ’s). Changes to the Type Design by means of a Supplemental Type Certificate (STC) requiring ICA ’s or changes to existing ICA’s must be submitted and reviewed by the FAA Rotorcraft Aircraft Evaluation Division (AED). Type Design Changes by means of a Field Approval that require ICA ’s must have those ICA’s reviewed by the Flight Standards District Office (FSDO) managing the Field Approval or the Rotorcraft AED. NOTE 12. Non-Pilot crewmembers will be trained in accordance with the Billings Flying Service, Inc. Rotorcraft Flight Manual BFS-610, Rev. IR, dated February 11, 2025 or later FAA approved revision as amended; the Billings Flying Service, Inc. Functional Check Flight Manual, BFS-608, Revision IR, September 6, 2024, or later FAA accepted revision; and the Billings Flying Service, Inc. Crewmember’s Checklist, Report No. BFS-606, Revision A, dated January 23, 2025, or later FAA accepted revision. NOTE 13. Rotorcraft certificated under this TC are surplus of the Royal Netherlands Air Force (RNAF). Airworthiness certification in accordance with 14 CFR 21.185(b) is subject to the terms of Exemption 21911, issued October 24, 2024. END ``` ## ADs None name its models. ## STCs approved under this data sheet (2) - [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. --- 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.