TCDS A15SW

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A15SW Revision 2 Lockheed SP-2H (P2V-7) June 7, 2004 TYPE CERTIFICATE DATA SHEET NO. A15SW This data sheet which is a part of Type Certificate No. A15SW prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the Federal Aviation Administration. Type Certificate Holder Neptune Aviation Service, Inc. 5225 Hwy. 10 West, Box 17 Missoula, Montana 59802 I-Model SP-2H (P2V-7) (Restricted Category) Approved May 3, 1984 Engine (a) Curtiss-Wright R3350-32WA eduction gear ratio 16:7 (b) Westinghouse J34WE-36 Fuel* MIL-G-5572 Grade 115/145 Engine limits* (a) -3350-32WA (Fuel Grade 115/145 Low Blower) BHP RPM MAN. PRESS IN. HG. ALTITUDE (FT) Takeoff (5 minutes wet) 3700 2900 59.0 Sea level Takeoff (5 minutes wet) 3700 2900 59.0 2000 Takeoff (5 minutes dry) 3400 2900 61.5 Sea level Takeoff (5 minutes dry) 3400 2900 60.5 2000 Maximum continuous 2800 2600 51.5 Sea level Maximum continuous 2800 2600 50.0 4000 *Fuel grade 100/130 is also eligible at lower power ratings. High blower and reverse pitch operation are restricted to a maximum of 2600 RPM. See Navair 01-75EEB-1 for Engine Operating Limits Tables. (b) J34 WE-36 Static Thrust lb. RPM Exhaust Gas Temp. °F/°C Takeoff (5 minutes) 3050 12,500 (100%) ** Maximum continuous 2650 12,000 (96%) ** Starting: First 5 seconds only 1760°/960° Next 30 seconds only 1562°/850° Acceleration 1661°/905° **These limits are individually calibrated and, therefore, must be obtained from the log book for each engine Page. No. 1 2 3 4 5 Rev. No. 2 - - - 2 A15SW Page 2 of 5 Propeller and Hubs-2 Hamilton Standard 24260-313 or 24260-337 or 24260-223 propeller limits Blad es-4 2J17H3-36S or 2FJ17C3-36S Diameter Limits: 14ft. 2 in. – No cutoff permitted Continuous ground operation between 2000 and 2400 is prohibited Pitch Setting at 72-inch station: Low Pitch +14° (±0.5°) Feathered +82° Reverse -22° Interchangeable Blades-These blades can be used interchangeably in the same propeller provided they are used in pairs and installed in opposite arms and that the prefix letters for opposite blades and the cutoff dash numbers for all blades are the same. Airspeed Limits Vmo (Maximum Operating) as sea level 406 m.p.h. (350 knots) Vfe (Flaps Extended 5°) 242 m.p.h. (210 knots) Vfe (Flaps Extended 10°) 242 m.p.h (210 knots) Vfe (Flaps Extended 15°) 230 m.p.h (200 knots) Vfe (Flaps Extended 20°) 201 m.p.h. (175 knots) Vfe (Flaps Extended 25°) 178 m.p.h. (155 knots) Vfe (Flaps Extended 32°) 167 m.p.h. (145 knots) Vfe (Maximum speed gear extended) 178 m.p.h. (155 knots) Va (Maximum Speed) 184 m.p.h. (160 knots) Vmc (Minimum control speed) 124 m.p.h. (108 knots) Fire retardant dumping envelope (see note 2) 120 knots to 145 knots (full flaps) 230 knots to 150 knots (all other flap settings) C.G. range Aft of datum, landing gear extended 362.91 to 375.53 @ 80,000 354.71 to 375.53 @ 61,400 Straight line variation between points given. Empty weight C.G. range None Datum The reference datum is located at fuselage station 0. Mean aerodynamic chord The leading edge of th e M.A.C. is located at fuselage station 330.1. (MAC) The length of the M.A.C. is 126.2 inch. Leveling means Level the aircraft by dropping a plumb bob from the leveling hook through the leveling grid in the nose wheel well. Maximum weight Takeoff 80,000 lbs. Landing 67,000 lbs. Minimum crew Two (Pilot and Co-Pilot) at +158”. Number of seats One at +180” occupancy limited to persons essential to perform the special purpose operation. Fire retardant 2700 gal. (V.S.) 24,300 lbs. A +398”. A15SW Page 3 of 5 Fuel Capacity TOTAL FUEL No. Tanks U.S. Gal. U.S. Gal Lbs. ARM Center section 2 790 1580 9,480 +382.5” Wing (main) 2 715 1430 8,580 +376.5” Total Permanent Tankage 3010 18,060 Oil Capacity TOTAL OIL No. Tanks U.S. Gal. U.S. Gal Lbs. ARM Nacelle tank 2 80 160 1136 +382.7” (expansion space) 20 - - Jet Pool Oil Tank 2 2.75 5.5 41 +311” Water injection tank capacity TOTAL ADI No. Tanks U.S. Gal. U.S. Gal Lbs. ARM 2 25 50 376 +316” Fluid-AMS-3006 Type I which specifies 48-52% methyl alcohol by volume and 48-52% water by volume. Control surface movement Aileron Up 22° +-1° Down 15°30’+1° Aileron Tab Up 15°45’+-2° Down 16°20’+-2° Elevator Up 27°37’+-1°30’ Down 27°+-1°30’ Elevator Trim Panel Up 7° (+1/4°-0°) Down 3° (+1/4°-0°) Spoiler Up 55°-60° Rudder Trim Tab Left 10° Right 10°30’ Rudder Left 21° Right 21° Aileron Spring Tab: Adjust aileron spring tab in accordance with NAVWEPS 01-76EEB-2-3 figure 3-16. Serial Nos. eligible All U.S. Navy Serial Numbers Certification basis FAR 21.25(a)(2) and (b) (2) Type Certificate issued May 3, 1984 for the special purpose of forest and wildlife conservation (fire fighting). Date of application, 2 February 1984. Production basis-None Prior to original airw orthiness certification of each aircraft, FAA personnel must perform an airworthiness inspection to determine the aircraft to be in condition for safe operation, and determine that a satisfactory flight test has been conducted. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) msut be installed in the aircraft for certification. Equipment necessary for the particular special purpose operation must be installed. In addition, an FAA approved Airplane Flight Manual Supplement is required. See Note 2. A15SW Page 4 of 5 NOTE 1. The current weight and balance report including a list of equipment included in certificated empty weight, and loading instructions when necessary must be provided for in each aircraft at the time of original certification. NOTE 2. The aircraft shall be operated in accordance with: a. NATOPS Flight Manual NAVAIR 0175EEB-1 dated September1, 1969, changed April 15, 1973, and including change #64 dated July 28, 1975, and change #66 dated February 17, 1976 Flight Manual Supplement dated April 23, 1982, Revision B, dated May 2, 1984. NOTE 3. Prior to civil certification, compliance with the following Department of the Namy Service Bulletins, Aircraft Bulletins, Aircraft Service Changes, Engine and Propeller Bulletins and Po werplant changes. SP-2H (P2V-7) Airframe Bulletins—Nos. 1, 3, 4, 5, 6, Int 7, Int 8, Int 9, Int 10, Int 11 and Amend 1, Int 12, Int 13, Int 14, Int 17, Int 18, Int 19, Int 20 rev B, Int 21 and Amend 1, Int 22, Int 23, Int ,24 Int 25, Int 26, and Amend 1, Int 27 Rev A, Int 29 and Amend 1, Int 31 and Amend 1, Int 32, Int 33 and Amend 1, Int 36, 37 Int 38, Int 39, Int 40, Int 41, 42, Int 43, Int 44, 45, Int 46, Int 47, Int 48, Int 49 and Amend 1, Int 51 Rev A, Int 53, Int 55, Int 56, Int 59, Int 60 and Amend 1, Int 61, Int 62, Int 63, Int 54, Int 67, Int 69 and Amend 1, Int 72, Int 74, Int 75, Int 78, Int 81, Int 82, 83 Amend 1, 86, Int 88, Int 90, Int 91, Int 92, Int 93, 94, 95, and Amend 1, Int 98, 100, Int 101, 102, 103, Int 104, Int 105, 107, 108, Int 110, Int 114, Rev A, Int 115, Int 116 and Amend 1, Int 117, Int 118, and Int 119. P2V-7 Aircraft Service Changes—Nos. 605, 676, 681, 688, 693, 694, 697, 699, 706, 709, 711, 714, 721, 722, 724, 726, 733, 735, 736A, 737, 746, 751, 752, 753A, 758A, 765A, 767C, 768, 770, 773, 781, 783, 785, 787A, 793, 975, 798, 799 802, 803A, 806A, 807, 808, 812, 815, 816, 817, 819, 822, 825A, 826, 831B, 839C, 841, 843, 845A, 847, 848A, 851, 856, 861A, 862,864,877B, 878, 882, 885, 894 Amend 1, 896 Amend 1, 898, 900, 901, 903, 904, 906, Amend 1, 912, 920, 923, 924,Amend 1, 928, 929, Int 931, Amend 1, 932, 934, 935, 937, 940, 941, 948, 952, 953 Amend 1, 955A, 959 Amend 2, 971, 974, 979, 980, 981, 984, 987, 988, and 991. Wright R3350-32WA Engine Bulletins—Nos. 115 Rev B, 296 Amend 2, 360 rev B, 396 Amend 2, 461 Amend 1, 420, 423 rev B, 445 Rev C, 469 Rev A, Amend 2, 474 Rev A, 485 rev A, 486 Amend 1, 489 Rev B, 490 rev A, 491 Rev A, 515, 516, 517, 518, 519 Amend 1, 520 Amend 1, 562 Rev A, 563 Amend 2, 564 Rev B, Amend 2, 566 Rev B, 599 Rev A. 622 Rev A, 625 Rev A, Amend 1, 635 Rev C, 642, 646 Rev A, 653 Amend 1, 656 Rev A, 663, 680 Rev A, 681, 682 Rev A 685, 686, 688, 689, 691 Amend 1, 693, 694 Amend 1, 697, 698, 699, 700, 702, 703, 705, 706, 707, 708, 709, 710, 711 Amend 1, 713 Rev A, 714 Rev B, 715, 716, Amend 1, 717, 718, 719, 720, 721 Rev B, Amend 1, 722, 726 Amend 1, 727, 731, 732, 735, 736, 737, 742 Amend 2, 748, 750, 751 Rev A, and 752. J-34-WE-36 Turbo-Jet Engine Bulletins—Nos. Engine Bulletin No. 0, 181, 183, 199, 202, 208, 232, 236, 241, 244, 245, 246, 247, 265, 266A and Amend 1, 275 and Amend 3, 279, 280, 291, 296 Rev B, 303, 308 Rev A, 312, 313, 314, 320, 322, 323 Rev A, 326 Rev A, 328 Amend 1, 332, 333, 334, 335, 338 Rev A, 339, 341, 342, 343 Amend 1, 345, 346, 347, 349 Rev A, Amend 1, 350, 351, Amend 1, 353, 354 Rev A, 355 Rev B, Amend 1, 356, 361, 363, 364, 365, 366, 368, 370 Rev A, 371 Rev A, 374, 376 Amend 1, 3378, 380, 381 Rev A, Amend 1, and 382. A15SW Page 5 of 5 Hamilton Standard Propeller P/N 24260 Propeller Bulletins—Nos. 270, 272, 275, 276, 277, 293, 311, 312, 317, 318, 324, 338, 346A, 360, 361A, 362, 368A, 370, 373A, 376, 377, 390, 401, 402, 405, 415A Amend 3, 417, 419, 422B, 429, 432, 435 and Amend 1, 436, 440A and Amend 1, 447, 450, 462, 463, 467 Amend 2, 474, 486, 488, 489, 491, 492, Rev A, 494, 502,505A, 506A, 509, 515A, 516, 527A, 531, 532, 535A, 541, 544A, 551, 555, 600A. NOTE 4: Modification to these ai rcraft or special equipment will be necessary, reference FAR 21.25(a)(2) or (b) (2), prior to civil airworthiness certification for the special purpose of forest and wildlife conservation (fire fighting) and for any other FAA approved special purpose operation. NOTE 5: Restricted aircraft Airworthiness Certificates issued are effective under FAR 21.181 (a) (1) as long as maintenance and preventive maintenance are performed in accordance with FAR 43 and FAR 91, Subpart E. NOTE 6: All autopilot equipment must be removed. …..END…..