# TCDS LTC-18: Prevost Christopher - Type: Type certificate data sheet - Status: Current - Holder: Prevost Christopher - Revision: 3 - Revised: January 20, 2006 - Product: Aircraft, Small Airplane - Certification basis: Part 15 - Data sheet PDF: https://openairdocs.org/files/sha256/c2/31/c2318df1230f822c8181a28322f46585c195247ee59a8be5ee03a5e4a8cf781c - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/0F2F90D673EE85C186257106006FD4AB.0001 - Page: https://openairdocs.org/tcds/LTC-18 ## Models (1) As the data sheet lists them. - Army P-40N ## 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 LTC-18 Revision 3 Christopher Prevost Army P-40N January 20, 2006 TYPE CERTIFICATE DATA SHEET NO. 18 This data sheet, which is part of Limited Type Certificate No. 18, 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: Christopher Prevost 23982 Arnold Drive Sonoma, CA 95476 Type Certificate Ownership Boardman C. Reed was previous holder of LTC-18. Effective Record October 8, 2004 Christopher Prevost became TC holder Army-Model P-40N (Limited Category),Approved May 8 1947 Engine Allison V-1710 – 81, –99 or –115. Fuel Grade 100/ 130, 100LL Engine Limits Maximum, except take- off: (Sea level) 38 in. Hg., 2600 rpm (870 hp) (14,600 ft) 38 in. Hg., 2600 rpm (1000 hp) Maximum take-off (sea level) 52.in Hg., 3000 rpm (1200 hp) Propeller and Curtiss C532D hub, 89303-24W blades Propeller limits Maximum diameter 11.0 feet. Minimum diameter 10.0 feet Number of blades; 3 Low Pitch; 24.3 degrees measured at 42 inches from the flange High pitch; 54.5 degrees measured at 42 inches from the flange Airspeed limits Glide or Dive 485 mph (See note 2 for additional placarded limitations.) C.G. Range 19 percent MAC (gear down) to 30 percent (gear up) (MAC 81.6 inches, L.E. MAC +102.2 Inches.) Datum 101.5 inches forward of jig point on leading edge of wing, or 108.3 inches forward of wing jack point. Leveling means Cockpit canopy rail, right side at pilot’s seat. Maximum weight 8260 lbs. Minimum crew One (1) Pilot Number of seats Two (1) at 145.5 inches aft of datum, (2) at 191.5 inches aft of datum. Maximum Baggage 60 lbs at 211.5 inches aft of datum. Fuel capacity Forward tank, 35 gal., 126 inches aft of datum; aft tank, 54 gal., 151 inches aft of datum Oil capacity 8 gal., 116 inches aft of datum Maximum Operating Altitude 20,000 feet This revision updates the TC holder, reformats the TCDS, and removes any reference to model P-40L. LTC-18 Page 2 of 3 Control Surface Movements Wing flaps Up 0° Down 45° Aileron Up 18 3/4 ° Down 10 ½° Elevators Up 30° Down 20° Elevator trim Up 3° Down 26° Rudder Left 30° Right 30° Rudder trim Left 15° Right 15° Serial numbers Eligible P40N 42-104429 to 42-106428 and 43-22752 to 43-23751. Certification basis CAR 09 effective November 21, 1946 (Limited Type Certificate No. 18 issued May 8, 1947) Production basis None may be produced under this approval. Export Eligibility Not eligible for a Certificate of Airworthiness for export. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. In addition, the aircraft may incorporate such military equipment (except armament) as was originally incorporated in this type of military service. Additional equipment may be installed as can be substantiated on the basis that it presents no obvious hazard to safety. The equipment list must be prepared by the applicant for the approval of the certificating FAA representative, and in such form that it can be attached to the FAA Operations Limitations. The equipment list need include no more than the following: a. Required equipment as defined under “Equipment” above. b. Additional 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. Items built into the aircraft structure need not be listed. Notes Note 1. – A current weight and balance report including list of equipment included in the certificated empty weight and loading instructions when necessary must be provided for each aircraft at the time of original certification. Note 2. – The following placards must be prominently displayed in the position indicated: a. In the cockpit full view of all passengers: “This is a military type aircraft and under the Federal Aviation Regulations shall not be used for the carriage of passengers or cargo for compensation or hire.” The placard and lettering shall be of type which can be read easily from any seat in the cabin. b. In the cockpit in full view of the pilot: “Do not lower landing gear above 175 mph.” “Do not lower flaps above 140 mph.” “Do not execute snap rolls above 140 mph.” “Do not execute slow rolls above 285 mph.” “Aerobatics prohibited: inverted flight, intentional spins, outside loops.” Note 3. – The following statement must appear on the operations Limitations: “This airplane must be operated at all times within the limitations set forth in the Army Technical Order No. AN-01- 25CN-1 except for limitations specifically called out in Type Certificate Data Sheet LTC-18 in which the values given in the specification must be observed. A copy of the pertinent Army Technical Orders and Type Certificate Data Sheet LTC-18 must be carried during flight.” In all cases it will be the responsibility of the applicant to secure a copy of the correct Technical Orders. The FAA does not have these documents available for distribution. Note 4. – If any repairs or modifications are made prior to or subsequent to airworthiness certification, it is the responsibility of the owner to furnish sufficient evidence to an FAA representative to show that the modified airplane maintains the same degree of airworthiness as the original. The FAA can give no technical assistance on such matters since complete structural data for military aircraft are not required by the regulations and therefore are not available in the FAA Note 5. – For certification of night flyi ng, the following must be accomplished: Prior to obtaining certification for “Night Flying” the airplane must be equipped with type certification position lights, installed in compliance with the requirements of CAR, Parts 15.2 and 03.538. The position lights required are wing tip lights and tail lights, and they shall be controlled by one S.P. ST Switch. The circuit should be protected by its own fuse or circuit breaker. Individual wing tip and tail switches with dim and bright positions and dimming resistors, if presently installed, shall be removed. With the exception of the landing lights, any other exterior lights are not required and may be removed or made inoperative, if so desired. LTC-18 Page 3 of 3 Note 6. – The following Mandatory Technical and Service Change Orders pertinent to models and serial numbers as indicated are listed for your information and must be complied with prior to certification. The FAA does not have copies of these publications for distribution. Also, FAA inspectors do not have such material. The applicable Technical Orders and compliance data are also listed in the airplane’s “Historical Records”, AAF Forms 60A, 60B and 61 accompanying the airplane: N u m b e r a n d d a t e T i t l e S e r i a l N u m b e r s 01-25C-10 Inspection of Lower Rudder Hinge Access Doors P-40 series May 23, 1943 All serial numbers 01-25C-122 Removal of Duffle Bag Installation P-40 series January 27, 1944 All serial numbers 01-25C-176 Inspection of Elevator Trim Tab Rod P-40 series November 25, 1944 All serial numbers 01-25C-177 Modification of Cockpit Enclos ure Canopy Installation P-40 series December 15, 1944 All serial numbers 01-25C-N-31 Fusing Radio Range Receiver P-40N January 18, 1945 All serial numbers 01-25CN—14 Installation of Stronger Main La nding Gear Axle Serial numbers October 15, 1943 42-104829 to 42- 106078 01-25C-154 Modification of the Lord Type and Fabreeka Type Engine All serial numbers July 20, 1944 Vibration Absorbers 01-25C-199 Inspection of Wing Bulkheads Station No s. 185, 164, 143, and 122 All serial numbers May 11, 1945 02-5AB-19 Installation of Flexible Line for O il Drain Tube on Automatic All equipped with April 21, 1945 Manifold Pressure Regulator V-1710-115 e n g i n e s …..END….. ``` ## ADs None name its models. ## STCs approved under this data sheet (5) - [STC SA4503NM](https://openairdocs.org/stc/SA4503NM): Remove original cloth covering and install Ceconite covering. Ceconite Division of Poly-Fiber Inc. - [STC SA04776NY](https://openairdocs.org/stc/SA04776NY): The HIPEC Covering and Finishing System must be performed and maintained. HIPEC Aircraft Coatings Inc. - [STC SA8075SW](https://openairdocs.org/stc/SA8075SW): Installation of fiberglass covering. (M-62 SERIES PT-19) (G-73 SCHWEIZER). Razorback Fabrics Inc - [STC SA1008WE](https://openairdocs.org/stc/SA1008WE): Installation of Poly-Fiber covering material.. Poly-Fiber 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 --- 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.