AIRCRAFT SPECIFICATION NO. A-800
Piper PA-15 Vagabond · Pilot's Operating Handbook
Overview
This document is the Aircraft Specification No. A-800 for the Piper PA-15 Vagabond, issued by the Federal Aviation Administration. It provides essential operational and technical information for pilots and maintenance personnel. The handbook includes specifications on the aircraft's engine, weight limits, airspeed limits, control surface movements, and required equipment. It serves as a critical reference for safe operation and compliance with regulatory standards. The document is particularly useful for understanding the performance characteristics and limitations of the PA-15, ensuring that pilots can operate the aircraft safely and effectively.
- Engine: Lycoming O-145-B2, 65 hp at 2550 RPM.
- Maximum weight: 1100 lbs; maximum baggage: 40 lbs.
- Airspeed limits: Maneuvering - 87 mph (76 knots), Max Cruising - 100 mph (87 knots), Never exceed - 126 mph (110 knots).
- C.G. range: +12.5 to +19.0 inches; Empty weight C.G. range: +12.9 to +17.6 inches.
- Control surface movements: Elevator - 24° Up, 23° Down; Aileron - 17° Up, 17° Down; Rudder - 16° Left, 16° Right.
Document
Source
Originally published by www.john2031.com. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Pilot's Operating Handbook
- Year
- 2006
- Pages
- 4
- File size
- 46 KB
- Publisher
- www.john2031.com
Specifications & performance
Extracted from this document.
Specifications
- Engine (hp)
- 65
- Propeller
- Sensenich 70LY34, 70LY38
- Engine model
- Lycoming O-145-B2
- Max speed (kt)
- 110
- Cruise speed (kt)
- 87
- Fuel capacity (gal)
- 12
- Max takeoff weight (lb)
- 1,100
V-speeds
- VNE
- 110
- VNO
- 87
Weight & balance
- Baggage allowance (lb)
- 40
- Max takeoff weight (lb)
- 1,100
Common. Rarer than 6% of the aircraft models we track.
Most owners only have the POH. Here's the essential set for the Piper PA-15 Vagabond.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins
- Type Certificate (TCDS)
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In this document
Engine Specifications
The Piper PA-15 Vagabond is powered by a Lycoming O-145-B2 engine, which has a maximum output of 65 horsepower at 2550 RPM. The aircraft requires a minimum fuel grade of 80 octane aviation gasoline.
Weight and Balance
The maximum weight for the Piper PA-15 Vagabond is 1100 lbs, with a maximum baggage capacity of 40 lbs. The center of gravity (C.G.) range is from +12.5 to +19.0 inches, and the empty weight C.G. range is from +12.9 to +17.6 inches.
Airspeed Limits
The aircraft has specific airspeed limits: the maneuvering speed is 87 mph (76 knots), the maximum structural cruising speed is 100 mph (87 knots), and the never exceed speed is 126 mph (110 knots).
Control Surface Movements
The control surface movements for the Piper PA-15 Vagabond are as follows: Elevator Trim Tab - 25° Up, 41° Down; Elevator - 24° Up, 23° Down; Aileron - 17° Up, 17° Down; Rudder - 16° Left, 16° Right.
Required Equipment
In addition to the basic required equipment specified in CAR 3, the PA-15 must have specific items installed for landplane and skiplane configurations. These include various landing gear components and safety equipment.
Safety notes
- Ensure compliance with the operating limitations specified in the CAA Approved Airplane Flight Manual.
- Acrobatics, including spins, are prohibited.
Full document text
DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A-800 Revision 11 Piper Aircraft, Inc PA-15 August 7, 2006 AIRCRAFT SPECIFICATION NO. A-800 Type Certificate Holder Piper Aircraft, Inc. 2926 Piper Drive Vero Beach, Florida 32960 Type Certificate Holder Record The New Piper Aircraft, Inc transferred TC A-800 to Piper Aircraft, Inc on August 7, 2006. I- Model PA-15, 2 PCLM (Normal Category), Approved July 1, 1948 Engine Lycoming O-145-B2 Fuel 80 minimum octane aviation gasoline Engine Limits For all operations, 2550 r.p.m. (65 hp) Airspeed Limits Maneuvering 87 mph (76 knots) (True Indicated) Max. Structural Cruising 100 mph (87 knots) Never exceed 126 mph (110 knots) C. G. Range (+12.5) to (+19.0) Empty Weight C. G. Range (+12.9) to (+17.6) When empty weight C. G. falls within this range, computation of critical fore and aft C. G. positions is unnecessary. Range is not valid for non-standard arrangements. Datum Wing leading edge Leveling Means Plumb from hole in upper door channel to center punch mark on front seat cross tube. Maximum Weight 1100 lbs. Number of Seats 2 (+22) Maximum Baggage 40 lbs. (+48) Fuel Capacity 12 gallons (-9) fuselage tank Oil Capacity 1 gallon (-31) Control Surface Elevator Trim Tab 25° Up 41° Down Movements Elevator 24° Up 23° Down Aileron 17° Up 17° Down Rudder 16° Left 16° Right Serial Numbers Eligible 15-1 and up Required Equipment In addition to the pertinent required basic equipment specified in CAR 3, the following items of equipment must be installed: Landplane: Items 1, 201(a), 202(a), 204(a), and 401(a). Skiplane Items 1, 208, 211, 401(a), and 401(b). Page No. 1 2 3 Rev. No. 11 11 11 A-800 Page 2 of 4 Page 3 of 4 A-800 Specifications Pertinent to All Models Certification Basis Type Certificate No. 800 (CAR 3) Production Basis Approved for manufacture of spare parts only under Production Certificate No. 206. Export Eligibility Deleted as of - August 14, 1995. Equipment A plus (+) or minus (-) sign preceding the weight of an item of equipment indicates net weight change when that item is installed. Approval for the installation of all items of equipment listed herein has been obtained by the aircraft manufacturer except those items preceded by an asterisk (*). The asterisk denotes that approval has been obtained by someone other than the aircraft manufacturer. An item marked with an asterisk may not have been manufactured under an FAA monitored or approved quality control system, and therefore attention should be paid to workmanship and conformity with pertinent data called for in this specification. Propellers and Propeller Accessories 1. Propeller - Sensenich 70LY34, 70LY38, or any other fixed-pitch wood propeller which is eligible for the engine power and speed and which meets the following limits: Static r.p.m. at max. permissible throttle setting: Not over 2370, not under 2110. No additional tolerance permitted. Diameter: Not over 70 inches, not under 66 inches. +11 lbs. (-44) Engines and Engine Accessories - Fuel and Oil Systems *101. Auxiliary fuel tank (6 gallon capacity) installed in accordance with Kit and Dwgs. P-17 and P-17-1 supplied by J. J. Villnove, 5607 Virginia, Kansas City, Missouri. +6 lbs. (+24) Landing Gear 201. Two main wheel-brake assemblies, 8.00-4, Type III (a) Goodrich Model 841A Wheel Assembly #D-3-13-A-1 Brake Assembly #D-2-113 +10 lbs. (0) 202. (a) Two main wheel 4 ply-rating tires, 8.00-4, Type III with regular tubes The following placard required: "Tire Pressure 11 lbs." +21 lbs. (0) 204. Tail wheel assembly (a) Scott Model 3000-A1, Steerable +6 lbs. (+167) *208. Two skis (a) Wollam W1650 (b) Federal A-1500, A-1500A, A-1850, A-2000, A-2000A per Federal Dwg. 11R262 with Item 211 or 212 installed. (c) Federal CA-1850-8 per Federal Dwg. 11R262 (d) Wesco per Western Aircraft Equipment Co. Dwg. Nos. 12 and 148: (1) A-15, (2) A-20, (3) A-25, (4) AS-2, (5) AS-2A or (6) AS-2B. Use Actual Weight Change *210. Consolidair Model 17 wheel fenders installed in accordance with Consolidair Dwg. No. 0045. +9 lbs. (0) 211. Two shock struts installed in accordance with Piper Dwg. 11550. +5 lbs. (0) *212. Two L.C.N. shock struts per L.C.N. Corp. Dwg. No. 11550 and Installation Instructions No. A-49101. Each shock strut must either have a CAA Form ACA-186 attached, or be identified with the symbol "CAA-PMA" or "FAA-PMA" +10 lbs. (0) *213. La Tour wheel fenders installed in accordance with La Tour Dwg. LAP-1700 and Installation Instructions. Use Actual Weight Change A-800 Page 4 of 4 Electrical Equipment 301. Landing lights in wing leading edge installed in accordance with Piper Dwg. 12534. +4 lbs. (+5) Interior Equipment 401. (a) Airplane Flight Manual, CAA (FAA) Approved July 1, 1948. (b) Skiplane Supplement to manual as follows: "Performance Information with Ski Installation: Climb: Skiplane climb performance is essentially equal to that of the landplane. Take-off and landing: Under the most favorable conditions of smooth packed snow, temperatures approximating 30°F, skiplane take-off distance is essentially equal to the landplane distance. Landing distance is approximately 20% greater than the landplane distance. In applying the performance data, caution should be exercised in that lower temperatures or other snow conditions will increase the ski friction and hence increase the take-off run and decrease the landing run." 402. Dual controls installed in accordance with Piper Dwg. 11810. +10 lbs. (+10) NOTE 1. 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 (except in the case of air carrier operators having an approved weight control system). NOTE 2. The following placards must be displayed on the instrument panel in full view of the pilot:
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(a) "This airplane must be operated in accordance with the operating limitations specified in the CAA Approved Airplane Flight Manual." (b) "Operate in Normal Category in compliance with Approved Flight Manual. Acrobatics (including spins) Prohibited." (c) "No Smoking." .....END.....