# TCDS LTC-1: Transcontinental and Western Air Inc. - Type: Type certificate data sheet - Status: Current - Holder: Transcontinental and Western Air Inc. - Revision: 3 - Revised: December 2, 1946 - Product: Aircraft, Large Airplane - Data sheet PDF: https://openairdocs.org/files/sha256/f6/4a/f64af48dc78477bc1c1fbbd663fb30d7b3a392ff5b7b5092c888d4ab8d6a2bb8 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/CDD86EEC114116F58525672200677986.0001 - Page: https://openairdocs.org/tcds/LTC-1 ## Models (2) As the data sheet lists them. - Army B-17G - Army B-17F ## What the data sheet says This is OCR from the scanned FAA data sheet. OCR can misread letters and numbers. ```text MODELS: Boeing (Army) B-17P, B-17G (Approved 12/2/46) SPECIFICATION NUMBER: L-1-3 (Holder of Limited Type Certificate: Transcontinental and Western Air, Inc., Washington, D.C.) Engines 4 Wright Cyclones R1820-97 Fuel 100 minimum octane (CFR) aviation grade gasoline Engine limits Maximum, except take-off (low blower plus turbo), 39.5 in. Hg., 2300 rpm (1000 hp) (sea lerel to Take-off (five minutes), 55 in. Hg.. 2500 rpm Propellers 1° (for interchangeable Hamilton Standard 23850 hub, 6153A-18 blades blades see Aircraft Propeller Specification No. 603, NOTE 6). and Governor 2° (for interchangeable blades see Aircraft Propeller Hamilton Standard 23E50 hub, 6477A-0 blades Specification No. 603, NOTE 6), and Governor Airspeed limits Level flight or climb - 225 mph True Ind. Glide or dive - 274 mph True Ind. Maximum flap speed: with power off - 144 mph True Ind. with power on Maximum weight C.G. range 20 percent MAC to 32 percent MAC Datum Leading edge wing at root chord (196.16 in. fron HAC 177.5 in. L.E. MAC (+30.3) Other operating limitations: ANO1-20EG-1 (Model B-17G) (See NOTE 2) Certification basis Limited Type Certificate Production basis None may be produced under this approval Export eligibility Not eligible for a Certificate of Airworthiness EQUIPMENT: we sicate to tho proper specion of no aleat me to intal co. Regulations Part 43.30 for In addition, the aircraft may incorporate such military equipment (except armament) as was originally incorporated in the type for military or naval service. Additional equipment may be installed when it is substantiated that it presents no hazard to safety. Weight and Balance Report including list of equipment included in the certificated empty weight must be obtained for each aircraft. or Navy weight recoted in lieu of an actual weight. The equipment list when available and in reasonably current condi- tion include no more than the followine: Reguired equipment as defined under "EQUIPMENT" above. items as may be reasonably considered removable and are so located or of such weight that their removal or addition could noticeably affect the weight and balance of the aircraft. built into the aircraft structure need not be listed. The equipment list must be prepared by the applicant for the approval of the certificating C.A.A. representative and in such form that it can be attached to the C.A.A. Operation Limitations. The following statement must appear on the Operation Limitations: ‚This airplane must be operated at all times within the limitations set forth in I.O. ANO1-BP-1 (for Model B-17F) or T.O. AN01-EG-1 (for Model except in cases of maximum loadings and airspeed limits in which cases the values given in Aircraft Specification No. AL-1 must be reaponest tty of the applicant to secure a copy of the cottact too A copy of the T.O. and the In all cases it will be the The C.A.A. does not have these documents available for distribution. All structural repairs should be made in accordance with Army T.O. No. 01-20E-3. If any repairs or modifications (other than those covered in the pertinent Army or Navy repair manual) sheel to chow char ene not ed die plane sint in the sat degrace- of airworthiness as the original. The C.A.A. can give no technical assistance on such matters since complete structural data for Ni aircraft are not required by Part 9 and therefore are not available in the C.A.A. NOTE 4. The following placard should be prominently displayed in the assenger compartment "This is a military type aircraft and under the ivil Air Regulations shall not be used for the carriage of passenger or cargo for compensation or hire. NOTE 5. Deleted. Eligible for 59,000 pounds with outer wing tanks filled (Tokyo tanks). With outer wing tanks empty maximum weight limited to 54,000 With outer wing tanks partially filled use a straight line variation of weight between 54,000 and 59,000 pounds. For certification for night flying the following must be Replace the wing position lights with certificated units or satis- factorily modify the lights if pertinent. (Type A-9 wing lights (AN-3033-5 through -8) may be satisfactorily modified by painting the inside of the frosted cover black. Type A-9 (AN-3033-1 through -4) are satisfactory without modification. Replace the tail light with a certificated unit. If "Bright and Dim" conditions are provided for the position lights, either the resistors should be disconnected from the circuits and a single-pole-single-throw switch should be used to replace the two single-pole-double-throw switches presently installed for wing-tip and tail lights, or the switches should be placarded to indicate that only the "bright condition" should be used. In either case the tail light and wing-tip lights should operate on one switch. obtained from CAA Aircraft Service, Washington, D.C. ``` ## ADs (4, in force first) - [AD 2023-10-04](https://openairdocs.org/ad/2023-10-04): Wings · Transcontinental and Western Air Army B-17F and Army B-17G. Effective Jun 1, 2023 - [AD 2001-22-06](https://openairdocs.org/ad/2001-22-06): Wing Spar · Transcontinental and Western Air Army B-17F and Army B-17G. Effective Nov 30, 2001 - [AD 73-20-02](https://openairdocs.org/ad/73-20-02): Front Spar Lower Cap Center Section · Transcontinental and Western Air Army B-17F and Army B-17G. Effective Jan 26, 1979 - [AD 77-17-11](https://openairdocs.org/ad/77-17-11): Rear Spar Lower Chord · Transcontinental and Western Air Army B-17F and Army B-17G. Effective Jan 23, 1979 ## STCs approved under this data sheet (7) - [STC SA2622NM](https://openairdocs.org/stc/SA2622NM): Installation of Precise Flight Pulselite Control Unit in landing/taxi system. (767-200 B17) (DHC-8 101). Precise Flight Inc. - [STC SA4503NM](https://openairdocs.org/stc/SA4503NM): Remove original cloth covering and install Ceconite covering. Ceconite Division of Poly-Fiber Inc. - [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc. - [STC SA1351WE](https://openairdocs.org/stc/SA1351WE): Replace existing fabric on wings, fuselage, empennage, and/or control surfaces, with Ceconite101 material. (262A Series -12). Ceconite Inc - [STC SA4-1210](https://openairdocs.org/stc/SA4-1210): Installation of Eonnex cover on aircraft surfaces.. Ceconite, Inc - [STC SA4-1088](https://openairdocs.org/stc/SA4-1088): Cargo door.. Fairchild Aerial Survey - [STC SA4-1520](https://openairdocs.org/stc/SA4-1520): Ceconite 101 covering of all fabric covered surfaces.. Cooper Engineering Corporation --- 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.