# TCDS A32NM: USDA Forest Service - Type: Type certificate data sheet - Status: Current - Holder: USDA Forest Service - Revision: 2 - Revised: April 26, 2011 - Product: Aircraft, Large Airplane - Certification basis: Part 21, Part 21, Part 25, Part 25, Part 91, CAR 4b - Registered aircraft: 3, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/db/eb/dbebdf0c9c6eb61a841d1f0588443a284a809c9bb27b5396a0320867a253351a - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/AF60597ADEC1DE6F8625788800510C0F.0001 - Page: https://openairdocs.org/tcds/A32NM ## Models (1) As the data sheet lists them. - P-3A ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Page No. 1 2 3 Rev. No. 1 1 - DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A32NM Revision 2 USDA Forest Service P-3A April 26, 2011 TYPE CERTIFICATE DATA SHEET NO. A32NM This data sheet which is a part of Type Certificate No. A32NM prescribes the 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 USDA Forest Service 2 nd Floor, SW Wing 201 14 th Street SW Washington DC 20090-6090 I. Model P-3A (Restricted Category), Approved January 31, 1990 Engines 4 Allison turboprop T-56-A-10W Fuel Commercial aviation turbine fuels conf orming to ASTM Specification No. D 1655-59T, types Jet B, Jet A-1, Jet A, or commercia l equivalents of MIL-T-5624, grade JP-4 or JP-5. Lubricating Oil Synthetic oil conforming to Allison Specification EMS-35 or MIL-L-7808 Engine Limits Static, Standard Day, Sea Level: Turbine Inlet Temp H.P. Oil Temp Takeoff (5 minutes) 971C Max 4300 100C Max Maximum Continuous 932C Max 3950 90C Max Propeller and Propeller Limits 4 Hamilt on Standard hydromatic propellers Hub 54H60-77 Blade A7121B-2 Diameter 13ft. 6 in. 2% reduction allowable for repair Constant speed propeller, full feathering and reverse pitch Single rotation, four blade assembly with governing speed setting 1020 rpm (13820 erpm). Propeller assembly is complete with sp inner, feathering and reversing provisions, constant speed control, negative torque control, synchrophaser, and electrical ice control. Blade Angles Feather 86.65  .10 Low-pitch stop (min. flt idle) 9.5  .5 - 1 Ground idle, beta -7  Reverse -14   .5 Propeller Oil MIL-H-5606B Airspeed Limits (knots IAS) V MO (Maximum operating) 367 knots at sea level See NAVAIR (01-75PAA-1) V A (Maneuvering) V B (Turbulent air penetration) 220 knots V FE (Takeoff & Approach) 190 knots V FE (Landing) 170 knots V LO (Landing gear operation) 190 knots V LE (Landing gear extended) 300 knots V LL (Landing light extended) 260 knots Heated Windshield If electric windshield heat is operativ e, it must be used for all flight operations. Operation without windshield heat on any or all portions of the windshield is permissible provided (1) The airplane is not flown in known icing conditions and (2) The maximum speed limit below 10,000 feet is 240 knots. C.G. Range See Figure 1-82, NAVAIR 01-75PAA-1 Datum 573.7 inches forward of jig points (white ci rcled screws) located .75 inches outboard of wing station 65 joint, 2.5 inches aft of leading edge joint. MAC 168.7, leading edge 545.9 inches aft of Datum Maximum Takeoff Weight 127,500 lbs Maximum Landing Weight 91,320 lbs Maximum Zero Fuel Weight 71,584 lbs. Leveling Means Plumb-bob leveling suspension fitting is located in the cabin ceiling at station 723 on the centerline. The leveling grid is directly below the plumb bob fitting under the floor. Minimum Crew Pilot and Co-Pilot Passengers None, limited to the flight crew a nd number of persons essential to operations. Fuel Capacity See NAVAIR 01-75PAA-1 Oil Capacity Four nace lle tanks (ARM 492.0) Capacity for each tank 8.65 gallons. Cargo Capacity None Maximum Operating Altitude 30,000 ft. Control Surface Movements See NAVAIR 01-75PAA-2-2 Serial Numbers Eligible US Navy Bureau Numbers: 150510, 150513, 151361, 151369, 151372, 151385, 151387, 151391 Certification Basis 14 Code of Fede ral Regulations (CFR) part 21 § 21.25 (a) (2) and (b) (2). CAR Part 4B as effective Oct. 1, 1959. FAR 21.50 (b), 25.571 and 25.1529 to Amendment 25-96 as effective March 31, 1998 (see Note 3). Type Certificate No. A32NM issued 29 June 1990 for the special purpose of forest and wildlife conservation under FAR Part 91. Production Basis None - Prior to original certificati on of each aircraft, an FAA representative must perform an inspection for workmanship, ma terials, and conformity with the approved technical data. All applicable Technical Orders affecting airworthiness must be accomplished. A32NM 3 Equipment The basic required equi pment as prescribed in the applicable Airworthiness Regulations (see Certification Basis), must be inst alled in the aircraft for certification. NOTE 1 This approval applies to: A. Basic United States Navy P-3A airplane with no major modifications except as required by Aero Union Report AUC 1137, dated December 22, 1989, or later FAA approved revisions. B. Airplane certified for the special purpose of Fo rest and Wildlife Conservation with the following limitations: 1. The following placard is to be in stalled in clear view of the pilot. “RESTRICTED CATEGORY” “This airplane must be operated as a restricted category airplane and in compliance with the operating limitations stated in NAVAIR 01-75PAA-1, Section I, Part 4, and in the form of placards, markings and manuals.” 2. Carriage of hazardous materials is prohibite d unless compliance is shown with FAR 91 and the applicable regulations in Title 49 of the Code of Federal Regulations, Part 175. NOTE 2 A. Current Weight and Balance Report including list of equipment included in certificated weight empty, and loading instructions when necessary, must be in each aircraft at the time of original certification and at all times thereafter. B. The location of the center of gravity for any gross weight configuration, determined from NAVAIR 01-1B-40, Technical Manual, Weight and Balance Data, must fall within the percent of the mean aerodynamic chord (MAC) shown on the Center of Gravity Table, Chart E. For information and method of calculating the airplane center of gr avity refer to NAVAIR 01-1B-40, Technical Manual, Weight and Balance Data. C. The weight of the system (unusable) fuel and oil as defined in NAVAIR 01-1B-40, Chart E, must be included in the airplane empty weight. D. Fuel loading and usage. 1. Fuel must be loaded and used to provi de compliance with the “Fuel Unbalance” limitation contained in NAVAIR 01-75PAA-1 for normal fuel management procedures. 2. Phillips fuel additive PFA-55MB may be used in concentrations not to exceed 0.15 percent by volume. No fuel system anti-icing credit is allowed. NOTE 3 Latest revisions of the following documents are required: A. NAVAIR 01-75PAA-1 must be available in th e P-3A aircraft for all flight operations. B. NAVAIR 01-1B-40, “Technical Ma nual, Weight and Balance Data.” NOTE 4 NOTE 4 For continued airworthiness, the aircraft must be maintained to the latest revision of the Airworthiness Limitations contained in the following document AAS-ALS-07-001 USFS P3A Airworthiness Limitations Section The Airworthiness Limitations contained in the above document are certified to the requirements of FAR 25.571 and 25.1529. This document specifies mandatory replacements and inspection intervals which are not subject to change without the express approval of the FAA. All maintenance, structural repair, alteration and modification to those areas specified in AAS-ALS-07-001 must be performed to the requirements of FAR 25.571 and FAR 25.1529. For all other maintenance, the aircraft must be serviced in accordance with the following documents: NAVAIR 01-75PAA-2-1 thru 01-75PAA-2-20 . NOTE 5 FAA airworthiness directives for all Lockheed L-188 series aircraft and Hamilton Standard 54H60 series propellers must be reviewed for applicability and complied with accordingly. Compliance with applicable Time Compliance Technical Orders for the aircraft and engines must be shown. NOTE 6 Prior to civil airworthiness certification, it must be shown that the following has been accomplished : (a) Incorporation of all applicable NAVAIR Technical Directives which affect airworthiness and which are not already covered by AAS-ALS-07-001. (b) Inspect all wing joints between planks for sealant deterioration and repair as necessary NOTE 7 Aircraft approved under this type certificate can onl y be used for the special purpose of forest and wildlife Conservation which includes the aerial dispensing of liquids. NOTE 8 The FAA representative responsible for the issuance of Restricted Airworthiness Certificates shall make NOTE 4 part of the operating limitations issued with the Airworthiness Certificate. ….... .....END..... ``` ## ADs None name its models. ## Registered aircraft by registry model (OpenAirDocs) - [Lockheed P-3A](https://openairdocs.org/model/lockheed-p-3a): 3 aircraft (registry code 5260103) ## STCs approved under this data sheet (5) - [STC ST04186AT](https://openairdocs.org/stc/ST04186AT): Incorporation of P3A Airworthiness Limitation Section for aircraft operated in Restricted Category for the special mission of aerial dispensing of liquids. Avenger Aerospace Solutions Inc - [STC SA4861NM](https://openairdocs.org/stc/SA4861NM): Installation of Retardant Tanks for the special purpose of Forest and Wildlife Conservation. United Aeronautical Corporation - [STC SA6012NM](https://openairdocs.org/stc/SA6012NM): Installation of a Champion or Unison engine ignition system. United Aeronautical Corporation - [STC ST03718AT](https://openairdocs.org/stc/ST03718AT): Incorporation of P3A Airworthiness Limitation Section for aircraft operated in Restricted Category for the special mission of aerial dispensing of liquids in accordance with Avenger Aircraft and Services Report No. AAS-MDL-09-002, Revision NC dated April 30, 2009, or later FAA approved revision.. Avenger Aircraft and Services - [STC SA308EA](https://openairdocs.org/stc/SA308EA): Installation of carburetor ice detection system 105AP in single and twin engine aircraft and single engine helicopters powered by Continental, Franklin, and Lycoming type engines equipped with Marvel-Schebler MA-2, MA-3, MA-4, MA-4-5, MA-6 and HA-6 series carburetors. (Normal,Utility and Acrobatic Category airplanes and helicopters equipped with engines and carburetors as described.). Alfred R Puccinelli --- 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.