# TCDS A15SW: Neptune Aviation Service Inc.

- Type: Type certificate data sheet
- Status: Current
- Holder: Neptune Aviation Service Inc.
- Revision: 2
- Revised: June 7, 2004
- Product: Aircraft, Large Airplane
- Certification basis: Part 21
- Data sheet PDF: https://openairdocs.org/files/sha256/89/90/8990be7e6670d4759eef67c64d47574f9a9ceb19af8e12dc880eb049946fbcbe
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/BD148740B4DC295886256ECB005E7C39.0001
- Page: https://openairdocs.org/tcds/A15SW

## Models (1)

As the data sheet lists them.

- SP-2H (P2V-7)

## 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 
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…..
```

## ADs

None name its models.

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