Piper PA-38 Tomahawk Model Guide
Piper PA-38 Tomahawk · Model Guide
Overview
The Piper PA-38 Tomahawk is a two-seat, single-engine piston trainer built from 1978 to 1982. It has a 112 hp Lycoming O-235 four-cylinder engine and a fixed-pitch Sensenich propeller. The handbook is FAA approved in the Normal and Utility categories. The source material is mostly maintenance and accident information, so a buyer should focus on airworthiness directives, takeoff performance and spin awareness.
- The Piper PA-38 Tomahawk seats two. It is powered by a 112 hp Lycoming O-235-L2C (Slick magnetos) or O-235-L2A (Bendix magnetos) at 2600 rpm, with a fixed-pitch propeller.
- Maximum takeoff weight and maximum landing weight are both 1670 lbs in the Normal and Utility categories. Baggage is limited to 100 lbs.
- Piper Service Bulletin 1284B lists all PA-38-112 aircraft. It requires compliance with Lycoming SB 622A on Slick magnetos at the next maintenance event, not to exceed 50 hours.
- Fatigue life limits apply to the vertical fin forward spar attachment plate (Piper P/N 77553-05). Check the serial number and whether Piper Kit 764421 is installed.
- Several accident reports involve poor takeoff performance from short or grass strips, an engine failure after a magneto fault, and a spin during slow-flight training.
Summary written by AI from the source document. Check the original before relying on it. See which parts of Sprinkle are written by AI.
Reference only, not for flight. Use the current approved manual for your aircraft. See terms, section 5.
Document
Source
Copy found at sprinkle.com. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type ·
- Model Guide
- Year ·
- 2026
- File size ·
- 54 KB
- Copy found at ·
- sprinkle.com
Specifications & performance
Extracted from this document.
Specifications
- Seats ·
- 2
- Engine model ·
- Lycoming O-235-L2C or O-235-L2A
- Engine power (hp) ·
- 112
- Propeller model ·
- Sensenich 72CK-0-56
- Min turning radius (ft) ·
- 26
- Propeller diameter max (in) ·
- 72
- Propeller diameter min (in) ·
- 70
V-speeds
- ROTATION_SPEED_KTS ·
- 53
Weight & balance
- Max baggage (lb) ·
- 100
- Max landing weight (lb) ·
- 1,670
- Max takeoff weight (lb) ·
- 1,670
How many people does the Piper PA-38 Tomahawk carry?
The Piper PA-38 Tomahawk seats two. Maximum takeoff weight is 1670 lbs, and the baggage compartment is limited to 100 lbs.
What engine does the Piper PA-38 Tomahawk use?
The Piper PA-38 Tomahawk uses a Lycoming O-235-L2C (with Slick magnetos) or O-235-L2A (with Bendix magnetos). It is rated at 112 hp at 2600 rpm and drives a fixed-pitch propeller.
Which airworthiness items should I check on a Piper PA-38 Tomahawk?
On the Piper PA-38 Tomahawk, check the fatigue life of the vertical fin forward spar attachment plate (3000 or 5000 hours depending on serial number and Piper Kit 764421). Also check the Slick magneto bulletin (Piper SB 1284B / Lycoming SB 622A) and the other ADs in the national schedules.
Are there takeoff performance concerns on the Piper PA-38 Tomahawk?
Accident reports on the Piper PA-38 Tomahawk describe poor acceleration and climb from short or grass runways at or near maximum weight. The handbook rotation speed is 53 kt, and a CAA change sheet says to add 5% to takeoff field lengths.
What is the Piper PA-38 Tomahawk Model Guide?
The Piper PA-38 Tomahawk Model Guide is a model guide for the Piper PA-38 Tomahawk, dated 2026.
What year was the Piper PA-38 Tomahawk Model Guide published?
The Piper PA-38 Tomahawk Model Guide — the Piper PA-38 Tomahawk model guide on file — is dated 2026.
Most owners only have the POH. Here's the essential set for the Piper PA-38 Tomahawk.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins on file
- Type Certificate (TCDS)
More Piper PA-38 Tomahawkmanuals & documents
See all 28 →- SERVICE BULLETIN NO. 1284BService Bulletins
- PA38-112 PIPER TOMAHAWK PREFLIGHTPilot's Operating Handbook
- AAIB Bulletin: 4/2015 G-BNDE EW/C2014/08/03Other Documents
- AAIB Bulletin: 3/2014 G-BGBN EW/C2013/06/01Other Documents
- AAIB Bulletin: 7/2013Other Documents
- Airworthiness Directive ScheduleService Bulletins
- AAIB Bulletin: 7/2009 G-RVRG EW/C2008/07/03Other Documents
- SERVICE BULLETIN NO. 1200Maintenance Manual
- AAIB Bulletin: 9/2009 G-BOLF EW/C2008/10/03Other Documents
- AIRWORTHINESS DIRECTIVE AD/PA-38/21 Amdt 1Service Bulletins
- AIRWORTHINESS DIRECTIVE AD/PA-38/16 Amdt 2Service Bulletins
- AIRWORTHINESS DIRECTIVEAirworthiness Directives
Related documents
- PIPER PA - 38 - 112 “TOMAHAWK”Piper PA-38 Tomahawk · Specifications
- Emergency Procedures for the Piper PA-38 TomahawkPiper PA-38 Tomahawk · Emergency Procedures
- CESSNA 172M SKYHAWK Model GuideCESSNA 172M SKYHAWK · Model Guide
- EMERGENCY PROCEDURESPiper PA-38 Tomahawk · Emergency Procedures
- Normal Procedures for the Piper PA-38 TomahawkPiper PA-38 Tomahawk · Normal Procedures
In this document
What it is and what it carries
The Piper PA-38 Tomahawk was built from 1978 to 1982 and seats two. Its engine is a four-cylinder, air-cooled Lycoming O-235-L2C (Slick magnetos) or O-235-L2A (Bendix magnetos). It is rated at 112 hp at 2600 rpm, displaces 233.3 cubic inches and has an 8.5:1 compression ratio. The propeller is a fixed-pitch Sensenich 72CK-0-56, 72 in maximum and 70 in minimum diameter. Maximum takeoff weight and landing weight are 1670 lbs, and the baggage compartment is limited to 100 lbs. Fuel is 100/130 green, with 100LL blue listed as an alternate. Use the empty weight and useful load in the individual airplane's weight and balance records, because the handbook says standard values vary from one aircraft to another.
Takeoff performance cautions
The recommended rotation speed in the handbook is 53 kt for a normal or short-field takeoff, with one notch of flap (21 degrees) for short or soft fields. One UK report (G-BTOD) describes a departure at about maximum takeoff weight (1,670 lb) from a damp grass runway with a takeoff run available of 490 metres. The aircraft failed to accelerate and the pilot lifted off close to a hedge. Another report (G-OLFC) notes that a CAA change sheet to the handbook says to add 5% to takeoff field lengths. A third (G-RVRG) describes an aircraft that left a hump in a grass runway at 53 kt, did not accelerate and climb, and stalled at about 50 feet. Plan grass and short-field departures with margin.
Airworthiness directives and bulletins to check
The Australian AD/PA-38/21 Amdt 1 sets replacement life limits for the vertical fin forward spar attachment plate (P/N 77553-05). For S/N 38-81A0001 to 38-82A0101 without Piper Kit 764421, the limit is 3000 hours time in service. With the kit, or on S/N 38-82A0102 to 38-82A0122, it is 5000 hours. The New Zealand CAA AD schedule lists 26 items for the type, including the aft fuselage, rudder hinges, control wheel, engine mount, main landing gear attachment, wing skin, throttle control, oil pressure line fitting, and gascolator valve. Confirm the status of each AD against the aircraft's logbooks. Also confirm that Piper SB 1284B (Slick magneto bulletin) has been complied with.
Pre-purchase and preflight points
A club preflight checklist for the type includes checking brake fluid, oil level (club checklist: minimum 4, maximum 5), the alternator belt, the fuel strainers and sumps, the nose gear, and the flow strips on the wings. It also includes the pitot tube holes, the stabilator and rudder, and the door latches. Check the handbook revision status: the handbook was issued January 20, 1978 and revised May 2, 2012, and it must be kept current. Ask for the engine history, especially magneto condition and the maintenance records for the airworthiness directives.
Summary written by AI from the source document. Check the original before relying on it. See which parts of Sprinkle are written by AI.
Safety notes
- Spin risk: the G-BODP accident involved a spin during slow-flight training at an estimated 2,000 to 3,000 ft. The May 2012 handbook revision added advice on the altitudes at which slow flight and stall manoeuvres should be started.
- Magneto faults: in the G-BGBN accident the engine ran roughly after a magneto problem and failed after takeoff. Do not accept an unresolved magneto drop on the run-up check.
- Takeoff performance: add the 5% field-length margin from the CAA change sheet where it applies, and allow extra distance for grass, damp surfaces and obstacles.
- Comply with Piper SB 1284B (Lycoming SB 622A) on Slick magnetos by the next maintenance event, not to exceed 50 hours.
Summary written by AI from the source document. Check the original before relying on it. See which parts of Sprinkle are written by AI.
Full document text
Piper PA-38 Tomahawk Model Guide The Piper PA-38 Tomahawk is a two-seat, single-engine piston trainer built from 1978 to 1982. It has a 112 hp Lycoming O-235 four-cylinder engine and a fixed-pitch Sensenich propeller. The handbook is FAA approved in the Normal and Utility categories. The source material is mostly maintenance and accident information, so a buyer should focus on airworthiness directives, takeoff performance and spin awareness. • The Piper PA-38 Tomahawk seats two. It is powered by a 112 hp Lycoming O-235-L2C (Slick magnetos) or O-235-L2A (Bendix magnetos) at 2600 rpm, with a fixed-pitch propeller. • Maximum takeoff weight and maximum landing weight are both 1670 lbs in the Normal and Utility categories. Baggage is limited to 100 lbs. • Piper Service Bulletin 1284B lists all PA-38-112 aircraft. It requires compliance with Lycoming SB 622A on Slick magnetos at the next maintenance event, not to exceed 50 hours. • Fatigue life limits apply to the vertical fin forward spar attachment plate (Piper P/N 77553-05). Check the serial number and whether Piper Kit 764421 is installed. • Several accident reports involve poor takeoff performance from short or grass strips, an engine failure after a magneto fault, and a spin during slow-flight training. What it is and what it carries The Piper PA-38 Tomahawk was built from 1978 to 1982 and seats two. Its engine is a four-cylinder, air-cooled Lycoming O-235-L2C (Slick magnetos) or O-235-L2A (Bendix magnetos). It is rated at 112 hp at 2600 rpm, displaces 233.3 cubic inches and has an 8.5:1 compression ratio. The propeller is a fixed-pitch Sensenich 72CK-0-56, 72 in maximum and 70 in minimum diameter. Maximum takeoff weight and landing weight are 1670 lbs, and the baggage compartment is limited to 100 lbs. Fuel is 100/130 green, with 100LL blue listed as an alternate. Use the empty weight and useful load in the individual airplane's weight and balance records, because the handbook says standard values vary from one aircraft to another. Takeoff performance cautions The recommended rotation speed in the handbook is 53 kt for a normal or short-field takeoff, with one notch of flap (21 degrees) for short or soft fields. One UK report (G-BTOD) describes a departure at about maximum takeoff weight (1,670 lb) from a damp grass runway with a takeoff run available of 490 metres. The aircraft failed to accelerate and the pilot lifted off close to a hedge. Another report (G-OLFC) notes that a CAA change sheet to the handbook says to add 5% to takeoff field lengths. A third (G-RVRG) describes an aircraft that left a hump in a grass runway at 53 kt, did not accelerate and climb, and stalled at about 50 feet. Plan grass and short-field departures with margin. Airworthiness directives and bulletins to check The Australian AD/PA-38/21 Amdt 1 sets replacement life limits for the vertical fin forward spar attachment plate (P/N 77553-05). For S/N 38-81A0001 to 38-82A0101 without Piper Kit 764421, the limit is 3000 hours time in service. With the kit, or on S/N 38-82A0102 to 38-82A0122, it is 5000 hours. The New Zealand CAA AD schedule lists 26 items for the type, including the aft fuselage, rudder hinges, control wheel, engine mount, main landing gear attachment, wing skin, throttle control, oil pressure line fitting, and gascolator valve. Confirm the status of each AD against the aircraft's logbooks. Also confirm that Piper SB 1284B (Slick magneto bulletin) has been complied with. Pre-purchase and preflight points A club preflight checklist for the type includes checking brake fluid, oil level (club checklist: minimum 4, maximum 5), the alternator belt, the fuel strainers and sumps, the nose gear, and the flow strips on the wings. It also includes the pitot tube holes, the stabilator and rudder, and the door latches. Check the handbook revision status: the handbook was issued January 20, 1978 and revised May 2, 2012, and it must be kept current. Ask for the engine history, especially magneto condition and the maintenance records for the airworthiness directives. Safety notes: • Spin risk: the G-BODP accident involved a spin during slow-flight training at an estimated 2,000 to 3,000 ft. The May 2012 handbook revision added advice on the altitudes at which slow flight and stall manoeuvres should be started. • Magneto faults: in the G-BGBN accident the engine ran roughly after a magneto problem and failed after takeoff. Do not accept an unresolved magneto drop on the run-up check. • Takeoff performance: add the 5% field-length margin from the CAA change sheet where it applies, and allow extra distance for grass, damp surfaces and obstacles. • Comply with Piper SB 1284B (Lycoming SB 622A) on Slick magnetos by the next maintenance event, not to exceed 50 hours.