TYPE CERTIFICATE DATA SHEET NO. A7SO

Piper PA-34 Seneca III · Type Certificate

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Overview

This Type Certificate Data Sheet (TCDS) No. A7SO provides essential information regarding the Piper PA-34 Seneca III and its variants, including the PA-34-200, PA-34-200T, and PA-34-220T. It outlines the airworthiness requirements as prescribed by the Federal Aviation Administration (FAA) and includes details on engine specifications, weight limits, performance data, and operational limitations. This document serves as a reference for pilots, maintenance personnel, and aviation enthusiasts interested in understanding the specifications and operational capabilities of the Seneca III. The TCDS is crucial for ensuring compliance with safety regulations and for the proper operation of the aircraft.

Maximum takeoff weight for PA-34-200 is 4000 lb; for PA-34-220T, it is 4200 lb.
Engine limits are set at 2700 RPM with a total output of 200 hp.
VNE is 217 mph (188 knots); VNO is 190 mph (165 knots).
Fuel capacity is 98 gallons, with 93 gallons usable.
Control surface movements include ailerons up to 30° and down to 15°.

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Document details

Type: Type Certificate
Year: 2019
Pages: 3
File size: 37 KB
Publisher: static1.squarespace.com

Documentation completeness

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Most owners only have the POH. Here's the essential set for the Piper PA-34 Seneca III.

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-34 Seneca III is equipped with two Lycoming engines: a Lycoming LIO-360-C1E6 (right engine) and a Lycoming IO-360-C1E6 (left engine). The engine limits are set at 2700 RPM, providing a total output of 200 horsepower. The aircraft requires 100/130 minimum grade aviation gasoline for operation.

Airspeed Limits

The airspeed limits for the Seneca III include a Never Exceed speed (VNE) of 217 mph (188 knots), a Maximum Structural Cruise speed (VNO) of 190 mph (165 knots), and a Minimum Control Speed (VMC) of 80 mph (69 knots). The aircraft also has specific speeds for landing gear operation and flap extension.

Weight and Balance

The maximum takeoff weight for the Seneca III varies by serial number. For S/N 34-E4 and 34-7250001 through 34-7250214, the maximum takeoff weight is 4000 lb, while for S/N 34-7250215 through 34-7450220, it is 4200 lb. The maximum landing weight is consistently 4000 lb across all serial numbers.

Control Surface Movements

Control surface movements include ailerons with a maximum deflection of 30° up and 15° down, stabilator movements of 12.5° up and 7.5° down, and rudder movements of 35° left and right. The aircraft also features specific trim tab settings for stabilator and rudder.

Fuel Capacity

The fuel capacity of the Piper PA-34 Seneca III is 98 gallons, with 93 gallons usable. Fuel is stored in two wing tanks.

Safety notes

Avoid continuous operation between 2200 and 2400 RPM unless equipped with Hartzell propellers with dampers.
Ensure compliance with weight limits to maintain aircraft performance and safety.

Full document text

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 Rev No. 24 14 12 12 12 12 15 15 18 21 22 24 24 24 24 16 19 19 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A7SO Revision 24 Piper Aircraft, Inc PA-34-200 PA-34-200T PA-34-220T April 9, 2019 TYPE CERTIFICATE DATA SHEET NO. A7SO This data sheet which is a part of type certificate No. A7SO, 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 Piper Aircraft, Inc. 2926 Piper Drive Vero Beach, Florida 32960 Type Certificate Holder Record The New Piper Aircraft, Inc transferred TC A7SO to Piper Aircraft, Inc on August 7, 2006 I. - Model PA-34-200 (Seneca), 7 PCLM (Normal Category), Approved 7 May 1971. Engines S/N 34-E4, 34-7250001 through 34-7250214: 1 Lycoming LIO-360-C1E6 with fuel injector, Lycoming P/N LW-10409 or LW-12586 (right side); and 1 Lycoming IO-360-C1E6 with fuel injector, Lycoming P/N LW-10409 or LW 12586 (left side). S/N 34-7250215 through 34-7450220: 1 Lycoming LIO-360-C1E6 with fuel injector, Lycoming P/N LW-12586 (right side); and 1 Lycoming IO-360-C1E6 with fuel injector, Lycoming P/N LW-12586 (left side). Fuel 100/130 minimum grade aviation gasoline Engine Limits For all operations, 2700 r.p.m. (200 hp) Propeller and Propeller Limits Left Engine 1 Hartzell, Hub Model HC-C2YK-2 ( ) E, Blade Model C7666A-0; 1 Hartzell, Hub Model HC-C2YK-2 ( ) EU, Blade Model C7666A-0; 1 Hartzell, Hub Model HC-C2YK-2 ( ) EF, Blade Model FC7666A-0; 1 Hartzell, Hub Model HC-C2YK-2 ( ) EFU, Blade Model FC7666A-0; 1 Hartzell, Hub Model HC-C2YK-2CG (F), Blade Model (F) C7666A (This model includes the Hartzell damper); or 1 Hartzell, Hub Model HC-C2YK-2CGU (F), Blade Model (F) C7666A (This model includes the Hartzell damper). Note: HC-( )2YK-( ) may be substituted by HC-( )2YR-( ) per Hartzell Service Advisory 61. A7SO 2 of 18 Propeller and Propeller Limits Right Engine (continued) 1 Hartzell, Hub Model HC-C2YK-2 ( ) LE, Blade Model JC7666A-0; 1 Hartzell, Hub Model HC-C2YK-2 ( ) LEU, Blade Model JC7666A-0; 1 Hartzell, Hub Model HC-C2YK-2 ( ) LEF, Blade Model FJC7666A-0; 1 Hartzell, Hub Model HC-C2YK-2 ( ) LEFU, Blade Model FJC7666A-0; 1 Hartzell, Hub Model HC-C2YK-2CLG (F), Blade Model (F) JC7666A (This model includes the Hartzell damper); or 1 Hartzell, Hub Model HC-C2YK-2CLGU (F), Blade Model (F) JC7666A (This model includes the Hartzell damper). Note: HC-( )2YK-( ) may be substituted by HC-( )2YR-( ) per Hartzell Service Advisory 61. Pitch setting: High 79° to 81°, Low 13.5° at 30" station. Diameter:Not over 76", not under 74". No further reduction permitted. Spinner: Piper P/N 96388 Spinner Assembly and P/N 96836 Cap Assembly, or P/N 78359-0 Spinner Assembly and P/N 96836-2 Cap Assembly (See NOTE 4) Governor Assembly: 1 Hartzell hydraulic governor, Model F-6-18AL (Right); 1 Hartzell hydraulic governor, Model F-6-18A (Left). Avoid continuous operation between 2200 and 2400 r.p.m. unless aircraft is equipped with Hartzell propellers which incorporates Hartzell damper on both left and right engine as noted above. Airspeed Limits VNE (Never exceed) 217 m.p.h. (188 knots) VNO (Maximum structural cruise) 190 m.p.h (165 knots) VA (Maneuvering, 4200 lb.) 146 m.p.h. (127 knots) VA (Maneuvering, 4000 lb.) 146 m.p.h. (127 knots) VA (Maneuvering, 2743 lb.) 133 m.p.h (115 knots) VFE (Flaps extended) 125 m.p.h (109 knots) VLO (Landing gear operating) Extension 150 m.p.h. (130 knots) Retract 125 m.p.h. (109 knots) VLE (Landing gear extended) 150 m.p.h (130 knots) VMC (Minimum control speed) 80 m.p.h. ( 69 knots) C.G. Range (Gear Extended) S/N 34-E4, 34-7250001 through 34-7250214 (See NOTE 3): (+86.4) to (+94.6) at 4000 lb. (+82.0) to (+94.6) at 3400 lb. (+80.7) to (+94.6) at 2780 lb. S/N 34-7250215 through 34-7450220: (+87.9) to (+94.6) at 4200 lb. (+82.0) to (+94.6) at 3400 lb. (+80.7) to (+94.6) at 2780 lb. Straight line variation between points given. Moment change due to gear retracting landing gear (-32 in.-lb.) Empty Weight C.G. Range None Maximum Weight S/N 34-E4, 34-7250001 through 34-7250214: 4000 lb.- Takeoff 4000 lb. - Landing See NOTE 3. 3 of 18 A7SO Maximum Weight S/N 34-7250215 through 34-7450220: 4200 lb. - Takeoff 4000 lb. - Landing No. of Seats 7 (2 at +85.5, 3 at +118.1, 2 at +155.7) Maximum Baggage 200 lb. (100 lb. at +22.5, 100 lb. at +178.7) Fuel Capacity 98 gallons (2 wing tanks) at (+93.6) (93 gallons usable) See NOTE 1 for data on system fuel. Oil Capacity 8 qts. per engine (6 qts. per engine usable) See NOTE 1 for data on system oil. Control Surface Movements Ailerons (±2°) Up 30° Down 15° Stabilator Up 12.5° (+0, −1°) Down 7.5° (±1°) Rudder (±1°) Left 35° Right 35° Stabilator Trim Tab (±1°) Down 10.5° Up 6.5° (Stabilator neutral) Wing Flaps (±2°) Up 0° Down 40° Rudder Trim Tab (±1°) Left 17° Right 22° (Rudder neutral) Nose Wheel S/N 34-E4, 34-7250001 through 34-7350353: Travel (±1°) Left 21° Right 21° Nose Wheel S/N 34-7450001 through 34-7450220: Travel (±1°) Left 27° Right 27° Manufacturer's Serial Number 34-E4, 34-7250001 through 34-7450220 (See NOTE 7). II. - Model PA-34-200T (Seneca II), 7 PCLM (Normal Category), Approved July 18, 1974. Same as Model PA-34-200 series except engine installation, maximum gross weight, and other minor changes. Engines 1 Teledyne Continental TSIO-360-E or TSIO-360-EB (left engine), 1 Teledyne Continental LTSIO-360-E or LTSIO-360-EB (right engine). Fuel 100/130 minimum grade aviation gasoline Engine Limits For all operations, 2575 r.p.m. and 40" Hg. Manifold pressure, 200 hp @ S.L. and 215 hp @ 12,000 ft. Propeller and Propeller Limits Left engine 1 Hartzell, Hub Model BHC-C2YF-2 ( )F (See NOTE 10) or BHC-C2YF-2 ( )UF; Blade Model FC8459-8R or FC8459B-8R. Right engine

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1 Hartzell, Hub Model BHC-C2YF-2 ( )L ( )F (See NOTE 10) or BHC-C2YF-2 ( )L ( )UF; Blade Model FJC8459-8R or FJC8459B-8R. Pitch setting at 30" station: Hub Serial Numbers prior to AN3943: High 79.3° ± 2.0°, Low 14.4° ± 0.2° or High 80.0° to 81.5°, Low 14.4° ± 0.2°. Hub Serial Numbers AN3943 and subsequent: High 80.0° to 81.5°, Low 14.4° ± 0.2°.

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