TYPE CERTIFICATE DATA SHEET NO. 3A23

MAULE M-6 · Type Certificate

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Overview

This document is a Type Certificate Data Sheet (TCDS) for various Maule aircraft models, primarily detailing the specifications, limitations, and operational requirements for each model. It serves as a regulatory document issued by the Federal Aviation Administration (FAA) to ensure that the aircraft meet airworthiness standards. The TCDS includes information on engine types, fuel requirements, weight limits, seating configurations, and control surface movements. It is intended for aircraft owners, operators, and maintenance personnel to understand the operational limits and requirements of the aircraft models listed.

Maximum weight for M-4 models is 2100 lbs; M-5 models can go up to 2300 lbs.
M-4 models typically use the Continental O-300 engine; M-5 models use the Continental IO-360.
Control surface movements include wing flaps with a first notch of 15º and a second notch of 35º for M-4 models.
C.G. range for M-4 models is (+15.0) to (+23.0) at 2100 lbs.
Maximum baggage allowance is 100 lbs for M-4 models.

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Source

Originally published by www.sensenich.com. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.

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Document details

Type: Type Certificate
Year: 2006
Pages: 48
File size: 144 KB
Publisher: www.sensenich.com

Specifications & performance

Extracted from this document.

Specifications

Engine (hp): 145
Propeller: McCauley 1A170-DM7460
Engine model: Continental O-300-A
Fuel capacity (gal): 43
Max takeoff weight (lb): 2,100

Weight & balance

Baggage allowance (lb): 100
Max takeoff weight (lb): 2,100

How rare is it?

1MAULE M-6 registered worldwide

Common. Rarer than 24% of the aircraft models we track.

Documentation completeness

0/7

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Pilot's Operating Handbook / AFM
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Maintenance Manual
Parts Catalog (IPC)
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Service Bulletins
Type Certificate (TCDS)

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In this document

Model Specifications

The document outlines specifications for several Maule models including the M-4 and M-5 series, detailing engine types, fuel requirements, and maximum weights. For example, the M-4 models typically have a maximum weight of 2100 lbs, while the M-5 models can go up to 2300 lbs.

Engine and Propeller Limits

Each model has specific engine and propeller limits. For instance, the M-4 models use the Continental O-300 engine, while the M-5 models utilize the Continental IO-360 engine. Propeller specifications include diameter limits and RPM settings.

Weight and Balance

The TCDS specifies weight limits and center of gravity (C.G.) ranges for each model. For example, the M-4 has a C.G. range of (+15.0) to (+23.0) at 2100 lbs. and a maximum baggage allowance of 100 lbs.

Control Surface Movements

Control surface movements are detailed for each model, including wing flap angles and aileron movements. For example, the M-4 has a first notch flap setting of 15º and a second notch of 35º.

Seating and Baggage Capacity

The document specifies seating configurations, indicating that the M-4 models can accommodate four seats, while the M-5 models can also accommodate four but with variations in baggage capacity.

Full document text

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 Rev. No. 30 29 30 29 29 29 29 29 29 29 29 29 29 30 26 29 30 30 30 29 29 Page No. 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 Rev. No. 27 30 29 29 29 29 29 30 29 29 30 29 30 30 30 30 29 29 30 30 30 Page No. 43 44 45 46 47 48 49 Rev. No. 30 30 30 30 29 29 29 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 3A23 Revision 30 MAULE Bee Dee M-4 M-5-180C MXT-7-160 M-4-180V M-4 M-5-200 MX-7-180A M-4C M-5-210C MXT-7-180A M-4S M-5-210TC MX-7-180B M-4T M-5-220C M-7-235B M-4-180C M-5-235C M-7-235A M-4-180S M-6-180 M-7-235C M-4-180T M-6-235 MX-7-180C M-4-210 M-7-235 M-7-260 M-4-210C MX-7-235 MT-7-260 M-4-210S MX-7-180 M-7-260C M-4-210T MX-7-420 M-7-420AC M-4-220 MXT-7-180 MX-7-160C M-4-220C MT-7-235 MX-7-180AC M-4-220S M-8-235 M-7-420A M-4-220T MX-7-160 MT-7-420 January 26, 2006 TYPE CERTIFICATE DATA SHEET NO. 3A23 This data sheet which is part of Type Certification No. 3A23 prescribes conditions and limit under which the product for which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder: MAULE AEROSPACE TECHNOLOGY, INC. 2099 GEORGIA HIGHWAY 133 SOUTH MOULTRIE, GEORGIA 31768 I. Model Bee Dee M-4, 4 PCLM (Normal Category), Approved August 10, 1961 Model M-4, 4 PCLM (Normal Category), Approved February 21, 1963 Model M-4C, 4 PCLM (Normal Category), Approved October 7, 1965 (Same as Model M-4 except for modified right fuselage truss, larger rear doors to facilitate cargo loading, and other minor changes.) Model M-4S, 4 PCLM (Normal Category), Approved March 15, 1966 (Same as Model M-4 except for minor changes.) Model M-4T, 2 PCLM (Normal Category), Approved March 15, 1966 (Same as Model M-4C except no rear seats or rear door and other minor changes.) Engine Continental O-300-A or B Fuel 80/87 minimum grade aviation gasoline Engine limits For all operations, 2700 rpm (145 hp) (See NOTE 3) 3A23 Page 2 of 48 Propeller and McCauley 1A170-DM7460 propeller limits Diameter: Not over 74 in., not under 73 in. No further reduction permitted. Static rpm at maximum permissible throttle setting: Not over 2200, not under 2100 No additional tolerance permitted. McCauley 1C172-MDM7647 to 7656 (Eligible on s/n 24, 46-94, 1C-11C, 1S-3S, 1T-3T ) (Eligible on s/n 3-23, 25-45 when modified per Maule Modification Kit No. 36) Diameter: Not over 76 in., not under 74.5 in. No further reduction permitted. Static rpm at maximum permissible throttle setting: Not over 2250, not under 2100 No additional tolerance permitted. Airspeed limits (CAS) Landplane and Skiplane: (See NOTE 11) C.G. range Landplane: (+15.0) to (+23.0) at 2100 lbs. (+11.0) to (+23.0) at 1400 lbs. or less NOTE: With fuel in optional auxiliary tanks, aft C.G. restricted to (+18.0). See Service Bulletin No. 18, Airplane Flight Manual Supplement (AFMS) No. 4 is required. Skiplane: Models M-4, M-4C with Fli-Lite 3000 MK IIIA Skis (+13.0) to (+23.0) at 1850 lbs. (+10.6) to (+23.0) at 1550 lbs. or less Models M-4, M-4C with FluiDyne A2000A Skis (+15.0) to (+23.0) at 2100 lbs. (+11.0) to (+23.0) at 1400 lbs. or less Straight line variation between points given. Empty weight C.G. range None Maximum weight Landplane: 2100 lbs. Skiplane: Fli-Lite 3000 MK IIIA Skis: 1850 lbs. Federal A2000A Skis: 2100 lbs. Number of seats 4 (2 at +18 to +21, 2 at +53) (Bee Dee M-4, M-4, M-4C, M-4S) 2 (+18 to +21) (M-4T) Maximum baggage 100 lbs. (+72) (Bee Dee M-4, M-4) 100 lbs. (+20), 350 lbs. (+42) (M-4C, M-4S, M-4T) 250 lbs. (+70) (M-4C, M-4S) Fuel capacity 43 gal. (40 gal. usable; two 21.5 gal. tanks in wings at +24) (See NOTE 1 for data on system fuel.) Oil capacity 8 qt. (-37), 4 qt. Minimum (See NOTE 1 for data on system oil.) Control surface Wing flaps Down 1st Notch 15º +3º movements 2nd Notch 35º +3º Aileron Up 20º + 1 Down 20º +1º Elevator Up 25º + 2º Down 21º +1º Elevator tab Up 14º + 1º Down 25º +1º (Bee Dee M-4, s/n 3-14, M-4, s/n 15- 43, unless modified by Maule SL#9 dated 11/8/65) Up 8º + 2º/-1º Down 25º + 1º (M-4, s/n 44-94, unless modified by Maule SL#9 dated 11/8/65) Up 11º + 3º Down 25º +1º (All M-4C, S, and T and M-4, s/n 3-94 modified by Maule SL#9 dated 11/8/65) Rudder Right 21º + 1º Left 21º +1º Rudder tab Right 48º + 4º Left 48º +4º Page 3 of 48 3A23 Serial numbers eligible Model Bee Dee M-4, 3-14 Model M-4, 15 and up Model M-4C, 1C and up Model M-4S, 1S and up Model M-4T, 1T and up Production basis (No longer in production) II. Model M-4-210, 4 PCLM (Normal Category), Approved September 24, 1964 Model M-4-210C, 4 PCLM (Normal Category), Approved October 7, 1965 Model M-4-210S, 4 PCLM (Normal Category), Approved March 15, 1966 Model M-4-210T, 2 PCLM (Normal Category), Approved March 15, 1966 (Same as M-4, M-4C, M-4S, and M-4T except for the installation of a Continental IO-360-A or D engine.) Engine Continental IO-360-A Continental IO-360-D for s/n 1086C and up, also eligible on s/n 1001-1045 and s/n 1001C-1085C when modified in accordance with Maule Service Letter #42 Fuel 100/100LL minimum grade aviation gasoline Engine limits IO-360-A: Maximum continuous hp, rpm, in. Hg. alt. Critical altitude 195-2800-26.2-2250 ft. Sea level 195-2800-26.5 Takeoff hp (5 min.) 210-2800 F.T. IO-360-D: F.T. all operations 210 hp - 2800 rpm Propeller and McCauley constant speed model D2A3467/76C-2 (used on A engine) or propeller limits D2A34C67N/S76C-2 (used on A or D engine) Diameter: 74 in., no further reduction permitted. Pitch settings at 30 in. sta.: low 12.5º high 23º Spinner: Cessna 0552016-1 McCauley D-2771-1 assembly (used on A or D eng.) Governor (hydraulic): Woodward F210452 or B210680 Airspeed limits (CAS) Landplane, Floatplane, and Skiplane: (See NOTE 11)

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C.G. range Landplane: For s/n 1001-1045, 1001C-1074C, 1079C, 1080C: (+15.0) to (+23.0) at 2100 lbs. (+11.0) to (+23.0) at 1400 lbs. or less For s/n 1075C, 1081C-1117C: (+16.0) to (+19.6) at 2300 lbs. (+15.0) to (+23.0) at 2100 lbs. (+11.0) to (+23.0) at 1400 lbs. or less NOTE: S/n 1001-1035 when modified per Maule SL#7 and SL#15 and s/n 1036- 1045, 1001C-1074C, 1079C, 1080C when modified per Maule SL#15 dated 11/12/68 are eligible for the above C.G. range at 2300 lbs. GW. Skiplane: Models M-4-210, M-4-210C with Fli-Lite 3000 MK IIIA Skis: (+13.0) to (+23.0) at 2100 lbs. (+10.6) to (+23.0) at 1550 lbs. or less Models M-4-210, M-4-210C with Federal A2000A Skis: (+15.0) to (+23.0) at 2100 lbs. (+11.0) to (+23.0) at 1400 lbs. or less Models M-4-210, M-4-210C, M-4-210S, M-4-210T with Federal C2200H or C3000H Skis: (+12.6) to (+18.4) at 2100 lbs. (+9.6) to (+18.4) at 1620 lbs. or less Floatplane: EDO 248A2440, 248B2440 or Fleet 2500 Floats: (+15.5) to (+20.5) at 2300 lbs. (+11.0) to (+20.5) at 1600 lbs. or less CAP 62-2000 Floats: 3A23 Page 4 of 48 (+15.6) to (+20.5) at 2220 lbs. (+12.0) to (+20.5) at 1700 lbs. or less Straight line variation between points given. Empty weight C.G. range None Maximum weight Landplane: 2300 lbs. or 2100 lbs. (Reference C.G. Range-landplane) Skiplane: 2100 lbs. Floatplane: Fleet 2500, EDO 248A2440 or 248B2440 Floats: 2300 lbs. CAP 62-2000 Floats: 2220 lbs. Number of seats 4 (2 at +18 to +21, 2 at +53)(M-4-210, M-4-210C, M-4-210S) 2 (+18 to +21)(M-4-210T) Maximum baggage 100 lbs. (+72)(M-4-210) 100 lbs. (+20), 350 lbs. (+42)(M-4-210C, M-4-210S, M-4-210T) 250 lbs. (+70)(M-4-210C, M-4-210S) Fuel capacity 43 gal. (40 gal. usable; two 21.5 gal. tanks in wings at +24) Optional wing auxiliary tanks - 23 gal. (23 gal. usable; two 11.5 gal. tanks in outerwings at +22.2) (Fuel in the optional auxiliary tanks not approved in combination with skis or floats.) (See NOTE 1 for data on system fuel.) Oil capacity 10 qt. (-37), 7 qt. Minimum (See NOTE 1 for data on system oil.) Control surface Wing flaps Down 1st Notch 15º +3º movement 2nd Notch 35º +3º Aileron Up 20º + 1º Down 20º +1º Elevator Up 25º + 2º Down 21º +1º Elevator tab Up 11º + 3º Down 25º +1º (M-4-210, s/n 1051 and up; all M-4-210C, -210S and -210T; and M-4-210 s/n 1001-1050 modified per Maule SL#9 dated 11/8/65) Up 8º +2º /-1º Down 25º +1º (M-4-210, s/n 1001-1050 unless modified per Maule SL#9 dated 11/8/65) Rudder Right 21º + 1º Left 21º +1º Rudder tab Right 48º + 4º Left 48º +4º Serial numbers Model M-4-210, 1001 and up eligible Model M-4-210C, 1001C and up Model M-4-210S, 1001S and up Model M-4-210T, 1001T and up Production basis (No longer in production) III. Model M-4-220, 4 PCLM (Normal Category), Approved October 18, 1966 Model M-4-220C, 4 PCLM (Normal Category), Approved October 18, 1966 Model M-4-220S, 4 PCLM (Normal Category), Approved October 18, 1966 Model M-4-220T, 2 PCLM (Normal Category), Approved October 18, 1966 (Same as M-4, M-4C, M-4S and M-4T except for the installation of a Franklin 6A-350-C1 engine.) Engine Franklin 6A-350-C1 Fuel 100/100LL minimum grade aviation gasoline Engine limits Takeoff (5 min.) 2800 rpm, F.T. (220 hp). For all other operations, 2800 rpm at 26.5 in. hg. (194 hp) (See NOTE 8) Propeller and McCauley constant speed model 2A31C21/84S-8 or -6 propeller limits Diameter: Not over 78 in.; not under 74 in. Pitch settings at 30 in. sta.: low 12.8º high 23.1º Spinner: Cessna 0552016-1 McCauley constant speed model 2A34C22-N/S84SF-6 or -8 Page 5 of 48 3A23 Diameter: Not over 78 in.; not under 74.5 in. Pitch settings at 30 in. sta.: low 11.5º high 22º Spinner: McCauley D4101 assembly NOTE: This installation also requires incorporation of Maule Drawings 5030F, rev. D, 5090B, rev. D, and 5043F, rev. G. Governor: Woodward 210453 or 210660 Airspeed limits (CAS) Landplane, Floatplane, and Skiplane: (See NOTE 11) C.G. range Landplane: (+15.6) to (+19.0) at 2300 lbs. (+14.5) to (+20.5) at 2100 lbs. (+11.1) to (+20.5) at 1500 lbs. or less Model M-4-220S, s/n 2001S only: (+15.0) to (+20.5) at 2100 lbs. (+11.0) to (+20.5) at 1400 lbs. or less NOTE: With fuel in optional wing auxiliary tanks, aft C.G. restricted to +18.0. Skiplane: Federal C2200H Skis: (+12.6) to (+18.4) at 2100 lbs. (+9.6) to (+18.4) at 1620 lbs. or less Model M-4-220C only: Federal A2000A Skis (+14.5) to (+20.5) at 2100 lbs. (+11.1) to (+20.5) at 1500 lbs. or less Fli-Lite 3000 MK IIIA Skis (+14.5) to (+20.5) at 2300 lbs. (+11.1) to (+20.5) at 1500 lbs. or less Floatplane: EDO 248A2440, 248B2440 or Fleet 2500 Floats: (+15.5) to (+20.5) at 2300 lbs. (+11.0) to (+20.5) at 1600 lbs. or less Straight line variation between points given. Empty weight C.G. range None Maximum weight Landplane: 2300 lbs. (M-4-220, M-4-220C, M-4-220S (s/n 2002S and up), M-4-220T) 2100 lbs. (s/n 2001S only) Skiplane: 2100 lbs. Floatplane: 2300 lbs. Number of seats 4 (2 at +18 to +21, 2 at +53) (M-4-220, M-4-220C, M-4-220S) 2 (+18 to +21) (M-4-220T) Maximum baggage 100 lbs. (+70) (M-4-220) 100 lbs. (+20), 350 lbs. (+42) (M-4-220C, M-4-220S, M-4-220T) 250 lbs. (+70) (M-4-220C, M-4-220S) Fuel capacity 43 gal. (40 gal. usable; two 21.5 gal. tanks in wings at +24) Optional wing auxiliary tanks 23 gal. (23 gal. usable; two 11.5 gal. tanks in wings at +22.2) (Fuel in the optional auxiliary tanks not approved in combination with skis or floats) (See NOTE 1 for data on system fuel.) Oil capacity 8.8 qt.(-37), 5.8 qt. Minimum (See NOTE 1 for data on system oil.) Control surface Wing flaps Down 1st Notch 15º +3º movements 2nd Notch 35º +3º Aileron Up 20º +1º Down 20º +1º Elevator Up 25º +2º Down 21º +1º Elevator tab Up 11º +3º Down 25º +1º Rudder Right 21º +1º Left 21º +1º Rudder tab Right 48º +4 Left 48º +4º 3A23 Page 6 of 48 Serial numbers eligible Model M-4-220, 2001 and up Model M-4-220C, 2001C and up Model M-4-220S, 2001S and up Model M-4-220T, 2001T and up Production basis (No longer in production) IV. Model M-4-180C, 4 PCLM (Normal Category), Approved October 20, 1970 Model M-4-180S, 4 PCLM (Normal Category), Approved October 20, 1970 Model M-4-180T, 2 PCLM (Normal Category), Approved October 20, 1970 (Same as M-4C, M-4S and M-4T except for the installation of Franklin 6A-335-B1A engine.) Engine Franklin 6A-335-B1A Fuel 80/87 minimum grade aviation gasoline Engine limits For all operations, 2800 rpm (180 hp) Propeller and McCauley constant speed model 2A34C22-N/S84SF-6 propeller limits Diameter: Not over 78 in.; not under 76.5 in. Pitch settings at 30 in. sta.: low 11.5º high 22º Spinner: McCauley D4180 with C4181 bulkhead assembly, B3243 front support, B3410-16 or -32 shim. Governor: Woodward 210453 or 210660 Airspeed limits (CAS) Landplane: (See NOTE 11) C.G. Range Landplane: (+15.6) to (+19.0) at 2300 lbs. (+14.5) to (+20.5) at 2100 lbs. (+11.1) to (+20.5) at 1500 lbs. or less Straight line variation between points given. NOTE: With fuel in optional wing auxiliary tanks, aft C.G. restricted to (+18.0). See Service Bulletin No. 18, AFMS No. 2 is required. Empty weight C.C. Range None Maximum weight 2300 lbs. Number of seats 4 (2 at +18 to +21, 2 at +53) (M-4-180C, M-4-180S) 2 (+18 to +21) (M-4-180T) Maximum baggage 100 lbs. (+20), 350 lbs. (+42) (M-4-180C, M-4-180S, M-4-180T) 250 lbs. (+70) (M-4-180C, M-4-180S) Fuel capacity 43 gal. (40 gal. usable; two 21.5 gal. tanks in wings at +24) (See NOTE 1 for data on system fuel.) Oil capacity 8.8 qt. (-37), 5.8 qt. Minimum (See NOTE 1 for data on system oil.) Control surface Wing flaps Down 1st Notch 15º +3º movements 2nd Notch 35º +3º Aileron Up 20º +1º Down 20º +1º Elevator Up 25º +2º Down 21º +1º Elevator tab Up 11º +3º Down 25º +1º Rudder Right 21º +1º Left 21º +1º Rudder tab Right 48º +4º Left 48º +4º Serial numbers eligible Model M-4-180C, 3001C and up Model M-4-180S, 3001S and up Model M-4-180T, 3001T and up Production basis (No longer in production) Page 7 of 48 3A23 V. Model M-5-210C, 4 PCLM (Normal Category), Approved December 28, 1973 (Same as M-4-210C except modified empennage, increased span flaps, smaller ailerons, modified C.G. range and other minor changes.) Engine Continental IO-360-D Fuel 100/100LL minimum grade aviation gasoline Engine limits 210 hp at 2800 rpm all operations Propeller and McCauley constant speed model D2A34C67N/S76C-2 propeller limits Diameter: 74 in., no further reduction permitted. Pitch settings at 30 in. sta.: low 12.5º high 23º Spinner: McCauley spinner assembly D-2771-1 Governor (hydraulic): Woodward B210680 or F210452 Airspeed limits (CAS) Landplane, Floatplane, and Skiplane: (See NOTE 11) C.G. range Landplane: (+16.0) to (+20.5) at 2300 lbs. (+15.0) to (+20.5) at 2100 lbs. (+12.0) to (+20.5) at 1600 lbs. or less All s/n modified per Maule SL#45 and SL#46: (+17.0) to (+20.5) at 2500 lbs. (+15.0) to (+20.5) at 2100 lbs. (+12.0) to (+20.5) at 1600 lbs. or less Floatplane: EDO 248A2440 or 248B2440 Floats: (+16.0) to (+18.0) at 2300 lbs. (+12.0) to (+18.0) at 1600 lbs. or less EDO 248B2400 Floats with modification per Maule Drawing 9173A: (+15.6) to (+19.0) at 2500 lbs. (+12.0) to (+19.0) at 1600 lbs. or less Pee Kay 2300 Floats: (+15.5) to (+20.0) at 2300 lbs. (+14.0) to (+20.0) at 1800 lbs. or less Note: M-5-210C s/n 6001C-6014C, 6039C, 6043C-6045C requires compliance to Maule SL#28 when equipped with EDO 248A2440/B2440 floats. Skiplane: Fluidyne C2200H Skis (+12.5) to (+20.0) at 2300 lbs. (+9.5) to (+20.0) at 1600 lbs. or less Fli-Lite 3000 MK IIIA Skis (+16.0) to (+20.0) at 2300 lbs. (+12.0) to (+20.0) at 1600 lbs. or less Straight line variation between points given. Empty weight C.G. range None Maximum weight Landplane, Skiplane and Floatplane: 2300 lbs. Landplane modified per SL#45 and SL#46: 2500 lbs. Floatplane modified per 9173A: 2500 lbs. Number of seats 4 (2 at +20, 2 at +48.8) Maximum baggage 100 lbs. (+20), 350 lbs. (+42), 250 lbs. (+70) Fuel capacity 43 gal. (40 gal. usable; two 21.5 gal. tanks in wings at +23.3) Optional wing auxiliary tanks 23 gal. (23 gal. usable; two 11.5 gal. tanks in wings at +22.2) See NOTE 16 if Modification Kit No. 15 is installed. (See NOTE 1 for data on system fuel.) 3A23 Page 8 of 48 Oil capacity 10 qt. (-37) 7 qt. Minimum (See NOTE 1 for data on system oil.) Control surface Wing flaps Down 1st Notch 15º +3º movements 2nd Notch 35º +3º Modified per Down 1st Notch 20º +3º Maule SL#46 2nd Notch 40º +3º Aileron Up 20º +1º Down 20º +1º Elevator Up 25º +2º Down 21º +1º Elevator tab Up 12º +4º Down 29º +2º Rudder Right 21º +1º Left 21º +1º Rudder tab Right 48º +4º Left 48º +4º Serial numbers eligible Model M-5-210C, 6001C and up (See NOTE 13 for float installation requirements.) Production basis (No longer in production) VI. Model M-5-220C, 4 PCLM (Normal Category), Approved December 28, 1973 (Same as M-4-220C except modified empennage, increased span flaps, smaller ailerons, and other minor changes.) Engine Franklin 6A-350-C1 Fuel 100/100LL minimum grade aviation gasoline Engine limits 220 hp at 2800 rpm, all operations Propeller and McCauley constant speed model 2A34C22-N/S84SF-6 or -8 propeller limits Diameter: Not over 78 in., not under 74.5 in. Pitch settings at 30 in. sta.: low 11.5º high 22º Spinner: McCauley D4180 with C4181 bulkhead assembly, B3243 front support, B3410-16 or -32 shim Governor: Woodward 210453 or 210660 Airspeed limits (CAS) Landplane, Floatplane, and Skiplane: (See NOTE 11) C.G. range Landplane: (+16.0) to (+20.5) at 2300 lbs. (+15.0) to (+20.5) at 2100 lbs. (+12.0) to (+20.5) at 1600 lbs. or less All s/n modified per Maule SL#48 and SL#51: (+17.0) to (+20.5) at 2500 lbs. (+15.0) to (+20.5) at 2100 lbs. (+12.0) to (+20.5) at 1600 lbs. or less Floatplane: EDO 248A2440 or 248B2440 Floats: (+16.0) to (+18.0) at 2300 lbs. (+12.0) to (+18.0) at 1600 lbs. or less EDO 248B2400 Floats with modification per Maule Drawing 9173A: (+15.6) to (+19.0) at 2500 lbs. (+12.0) to (+19.0) at 1600 lbs. or less Pee Kay 2300 Floats: (+15.5) to (+20.0) at 2300 lbs. (+14.0) to (+20.0) at 1800 lbs. or less NOTE: M-5-220C, s/n 5002C, 5019C, 5020C, 5022C-5024C requires compliance to Maule SL#28 when equipped with EDO 248A2440/B2440 floats. Skiplane: FluiDyne C2200H Skis (+12.5) to (+20.0) at 2300 lbs. ( +9.5) to (+20.0) at 1600 lbs. or less Straight line variation between points given. Empty weight C.G. range None Page 9 of 48 3A23 Maximum weight Landplane, Skiplane and Floatplane: 2300 lbs. Landplane modified per SL#48 and SL#51: 2500 lbs. Floatplane modified per 9173A: 2500 lbs. Number of seats 4 (2 at 15.1 to +18.1, 2 at 48.8) Maximum baggage 100 lbs. (+20), 350 lbs. (+42), 250 lbs. (+70) Fuel capacity 43 gal. (40 gal. usable; two 21.5 gal. tanks in wings at +23.3) Optional wing auxiliary tanks 23 gal. (23 gal. usable; two 11.5 gal. tanks in wings at +22.2) See NOTE 16 if Modification Kit No. 15 is installed. (See NOTE 1 for data on system fuel.) Oil capacity 8.8 qt. (-37) 5.8 qt. minimum (See NOTE 1 for data on system oil.) Control surface Wing flaps Down 1st Notch 15º +3º movements Modified per 2nd Notch 35º +3º Maule SL#48 Down 1st Notch 20º +3º 2nd Notch 40º +3º Aileron Up 20º +1º Down 20º +1º Elevator Up 25º +2º Down 21º +1º Elevator tab Up 12º +4º Down 29º +2º Rudder Right 21º +1º Left 21º +1º Rudder tab Right 48º +4º Left 48º +4º Serial numbers eligible Model M-5-220C, 5001C and up. (See NOTE 13 for float installation requirement.) Production basis (No longer in production) VII. Model M-5-235C, 4 PCLM (Normal Category), Approved April 6, 1976 (Same as M-5-220C except for nacelle, engine, propeller and electrical system.) Engine Lycoming O-540-J1A5D, O-540-J3A5, IO-540-W1A5D, IO-540-W1A5, or O-540-B4B5 Fuel 100/100LL minimum grade aviation gasoline Engine limits 235 hp at 2400 rpm, all operations (O-540-J/IO-540-W) 235 hp at 2575 rpm, all operations (O-540-B) Propeller and propeller limits (See NOTE 14) Airspeed limits (CAS) Landplane, Floatplane, and Skiplane: (See NOTE 11) C.G. range Landplane: S/n 7001C-7026C, 7028C, 7030C-7032C, 7037C (+16.0) to (+20.5) at 2300 lbs. (+12.0) to (+20.5) at 1600 lbs. or less or - S/n 7001C-7026C, 7028C, 7030C-7032C, 7037C with expanded C.G. limits per Maule SL#36 (+12.5) to (+20.5) at 2300 lbs. (+10.5) to (+20.5) at 1700 lbs. or less or -S/n 7001C-7320C, 7322C-7346C, 7348C,7349C modified per Maule SL#43 (+13.2) to (+20.5) at 2500 lbs. (+10.5) to (+20.5) at 1700 lbs. or less or -S/n 7001C-7320C, 7322C-7346C, 7348C, 7349Cmodified per Maule SL#44 (+12.5) to (+20.5) at 2300 lbs. (+11.7) to (+20.5) at 1700 lbs. or less or -S/n 7001C-7320C, 7322C-7346C, 7348C, 7349C modified per Maule SL#43 and SL#44 and s/n 7321C, 7347C, 7351C, 7363C, 7369C and up (+13.2) to (+20.5) at 2500 lbs. (+11.7) to (+20.5) at 1700 lbs. or less 3A23 Page 10 of 48 Floatplane: EDO 248A2440, 248B2440 or Aqua 2400 Floats: (+14.3) to (+20.0) at 2530 lbs. (+13.3) to (+20.0) at 2100 lbs. or less Pee Kay 2300 Floats: (+14.3) to (+20.0) at 2500 lbs. (+13.3) to (+20.0) at 2100 lbs. or less EDO 248B2440, Aqua 2400, or EDO 797-2500 amphibious Floats (Floatplanes modified per Maule drawing 9143A (B2440's), 9166A (2400’s) or 9057A (amphibs)): (+14.0) to (+19.0) at 2750 lbs. (+10.5) to (+19.0) at 1600 lbs. or less Skiplane: FluiDyne C2200H, C3000H, C3000M or Fli-Lite 3000 MK IIIA Skis: (+12.5) to (+20.0) at 2300 lbs. (+9.5) to (+20.0) at 1600 lbs. or less FluiDyne A2500A Skis: (+12.9) to (+20.5) at 2300 lbs. (+11.7) to (+20.5) at 1700 lbs. or less Fli-Lite MK IIIA Skis (Skiplanes modified per Maule drawing 9081A): (+13.2) to (+20.0) at 2500 lbs (+11.7) to (+20.0) at 1700 lbs. or less FluiDyne C3000M or C3000H Skis (Skiplanes modified per Maule drawing 9158A for C3000M or 9174A, Rev. C or later for C3000H): (+13.2) to (+20.0) at 2500 lbs. (+10.7) to (+20.0) at 1700 lbs. or less Straight line variation between points given. Empty weight C.G. range None Maximum weight Landplane: 2300 lbs. Floatplane: 2530 lbs. (EDO 2440 only), 2500 lbs. (PeeKay 2300) Skiplane: 2300 lbs. Landplanes modified per Maule SL#43 and s/n 7321C, 7347C, 7350C and up: 2500 lbs. Floatplanes modified per Maule drawing 9143A (EDO B2440), 9166A(Aqua 2400), or 9057A (EDO amphibs): 2750 lbs. Skiplanes modified per Maule drawing 9081A (Fli-Lites), 9158A (C3000M), or 9174A (C3000H): 2500 lbs. Number of seats 4 (2 at +20, 2 at +48.8) Maximum baggage 170 lbs. (+20), 350 lbs. (+42), 250 lbs. (+70) Fuel capacity 43 gal. (40. gal. usable; two 21.5 gal. tanks in wings at +24) Optional wing auxiliary tanks 23 gal. (23 gal. usable; two 11.5 gal. tanks in wings at +24) See NOTE 16 if Modification Kit No. 15 is installed. (See NOTE 1 for data on system fuel.) Oil capacity IO-540: 8 qt. (-34), 5 qt. minimum O-540: 12 qt. (-34), 9 qt. minimum (See NOTE 1 for data on system oil.) Control surface Wing flaps (s/n 7001C-7320C, 7322C-7346C, 7348C-7350C, 7352C-7362C, 7364C-7368C): movements Down 1st Notch 15º +3º 2nd Notch 35º +3º (s/n 7321C, 7347C, 7351C, 7363C, 7369C and up and airplanes modified per Maule SL#44): Down 1st Notch 20º +3º 2nd Notch 40º +3º Aileron Up 20º +1º Down 20º +1º Elevator Up 25º +2º Down 21º +1º Elevator tab Up 12º +4º Down 29º +2º Elevator tab w/piano hinge Up 12º +2º Down 38º +2º Rudder Right 21º +1º Left 21º +1º Page 11 of 48 3A23 Rudder tab Right 48º +4º Left 48º +4º Serial number eligible Model M-5-235C, 7001C and up (NOTE: Letter 'A' preceding serial number denotes installation of Lycoming IO-540-W1A5D fuel-injected engine and applies only to the following s/n A7354C, A7355C, A7358C, A7360C, A7361C, A7366C and A7367C.) ‘A’ was not used on later serial numbers with this engine. Production basis (No longer in production) VIII. Model M-5-180C, 4 PCLM (Normal Category), Approved April 19, 1979 (Same as M-5-235C except for nacelle, engine and propeller.) Engine Lycoming O-360-C1F Fuel 100/100LL minimum grade aviation gasoline Engine limits 180 hp at 2700 rpm, all operations Propeller and Hartzell constant speed model HC-C2YR-1BF/F7666A propeller limits Diameter: Not over 76 in; not under 72 in. Pitch settings at 30 in. sta.: low 12º high 27.8º to 29.8º Avoid continuous operation between 2000 and 2250 rpm. Spinner: Hartzell spinner assembly A2298-2 Governor: Woodward H210681 McCauley C290D3(X)/T29 or DC290D1(X)/T12 Airspeed limits (CAS) Landplane: (See NOTE 11) C.G. range Landplane: (+16.7) to (+20.5) at 2300 lbs. (+12.6) to (+20.5) at 1600 lbs. or less Straight line variation between points given. Empty weight C.G. range None Maximum weight Landplane: 2300 lbs. Number of seats 4 (2 at +20, 2 at +48.8) Maximum baggage 170 lbs. (+20), 350 lbs. (+42), 250 lbs. (+70) Fuel capacity 43 gal. (40 gal. usable; two 21.5 gal. tanks in wings at +24) Optional wing auxiliary tanks 23 gal. (23 gal. usable; two 11.5 gal. tanks in wings at +24) See NOTE 16 if Modification Kit No. 15 is installed. (See NOTE 1 for data on system fuel.) Oil capacity 8 qt. (-36.5), 2 qt. Minimum (See NOTE 1 for data on system oil.) Control surface Wing flaps (s/n 8001C-8022C): movements Down 1st Notch 15º +3º 2nd Notch 35º +3º (s/n 8023C and up and airplanes modified per Maule SL#49): Down 1st Notch 20º +3º 2nd Notch 40º +3º Aileron Up 20º +1º Down 20º +1º Elevator Up 25º +2º Down 21º +1º Elevator tab Up 12º +4º Down 29º +2º w/piano hinge Up 12º +2º Down 38º +2º Rudder Right 21º +1º Left 21º +1º Rudder tab Right 48º +4º Left 48º +4º Serial numbers eligible Model M-5-180C, 8001C-8014C, 8016C-8019C, 8021C, 8023C-8042C, 8044C-8064C, 8068C-8094C 3A23 Page 12 of 48 and up Production basis (No longer in production) IX. Model M-5-210TC, 4 PCLM (Normal Category), Approved February 4, 1980 (Same as M-5-180C except for nacelle, engine and propeller.) Engine Lycoming TO-360-F1A6D, Carburetor parts listing No. IO-5258 Fuel 100/100LL minimum grade aviation gasoline Engine limits 210 hp at 2575 rpm at 42.0 in. hg. MP, all operations Propeller and Hartzell constant speed model HC-E2YR-1BF/F8467-7R propeller limits Diameter: Not over 77 in.; not under 76.5 in. Pitch settings at 30 in. sta.: low 15º +0.1º high 30º to 33º Spinner: Hartzell spinner assembly A2298-2 Governor: Woodward C210681 Airspeed limits (CAS) Landplane and Skiplane: (See NOTE 11) C.G. range Landplane: (+15.0) to (+20.5) at 2300 lbs. (+12.0) to (+20.5) at 1700 lbs. or less Skiplane: Fli-Lite 3000 MK IIIA Skis: (+12.5) to (+20.0) at 2300 lbs. (+9.5) to (+20.0) at 1600 lbs. or less Straight line variation between points given. Empty weight C.G. range None Maximum weight Landplane and Skiplane: 2300 lbs. Number of seats 4 (2 at +20, 2 at +48.8) Maximum baggage 170 lbs. (+20), 350 lbs. (+42), 250 lbs. (+70) Fuel capacity 43 gal. (40 gal. usable; two 21.5 gal. tanks in wings at +24) Optional wing auxiliary tanks 23 gal. (23 gal. usable; two 11.5 gal. tanks in wings at +24) See NOTE 16 if Modification Kit No. 15 is installed. (See NOTE 1 for data on system fuel.) Oil capacity 8 qt. (-36.5), 2 qt. Minimum (See NOTE 1 for data on system oil.) Maximum operating altitude 20,000 feet Control surface Wing flaps (s/n 9001C-9010C): movements Down 1st Notch 15º +3º 2nd Notch 35º +3º (s/n 9011C and up and airplanes modified per Maule SL#47): Down 1st Notch 20º +3º 2nd Notch 40º +3º Aileron Up 20º +1º Down 20º +1º Elevator Up 25º +2º Down 21º +1º Elevator tab Up 12º +4º Down 29º +2º Rudder Right 21º +1º Left 21º +1º Rudder tab Right 48º +4º Left 48º +4º Serial numbers eligible Model M-5-210TC, 9001C and up Production basis (No longer in production) Page 13 of 48 3A23 X. Model M-6-235, 4*PCLM (Normal Category), Approved June 25, 1981 (Same as M-5-235C except for wings, flaps, ailerons and flap control mechanism.)(*Optional 5th seat s/n's 7474C and up.) Engine Lycomin g O-540-J1A5D, O-540-J3A5, IO-540-W1A5D, IO-540-W1A5 or O-540-B4B5 Fuel 100/100LL minimum grade aviation gasoline Engine limits 235 hp at 2400 rpm, all operations (O-540-J/O-540-W) 235 hp at 2575 rpm, all operations (O-540-B) Propeller and (See NOTE 14) propeller limits Airspeed limits (CAS) Landplane, Floatplane, and Skiplane: (See NOTE 11) C.G. range Landplane: (+15.0) to (+20.5) at 2500 lbs. (+11.0) to (+20.5) at 1700 lbs. or less Floatplane: EDO 797-2500 amphibious* or 248B2440 Floats (+14.0) to (+19.0) at 2750 lbs. (+10.5) to (+19.0) at 1600 lbs. or less Aqua 2400 Floats (+14.8) to (+19.0) at 2750 lbs. (+10.5) to (+19.0) at 1600 lbs. or less Wipline 3000 amphibious Floats (+14.0) to (+19.0) at 2750 lbs. (+12.0) to (+19.0) at 2100 lbs. or less Wipline 2350 amphibious Floats*** (+14.1) to (+19.0) at 2500 lbs. (+12.6) to (+19.0) at 2090 lbs. or less Skiplane: FluiDyne A2500A Skis* (+14.3) to (+20.5) at 2300 lbs. (+11.0) to (+20.5) at 1700 lbs. or less Fli-Lite 3000 MK IIIA Skis* (+15.0) to (+20.5) at 2500 lbs. (+11.0) to (+20.5) at 1700 lbs. or less FluiDyne C2200H, C3000H/AH/M wheel Skis** (+15.0) to (+20.0) at 2500 lbs. (+10.0) to (+20.0) at 1700 lbs. or less *Not applicable s/n 7474C and up **Not applicable s/n 7466C, 7468C-7473C ***Not applicable s/n 7249C, 7356C-7465C Straight line variation between points given. Empty weight C.G. range None Maximum weight Landplane: 2500 lbs. Floatplane: 2750 lbs. Skiplane: Fli-Lite 3000/C2200H/C3000H/AH/M: 2500 lbs. FluiDyne A2500A: 2300 lbs. Number of seats 4 (2 at +20, 2 at +56) S/n 7474C and up: Optional: 5 (2 at +20.0, 2 at +53, 1 at +78) Maximum baggage 170 lbs. (+20), 350 lbs. (+42), 250 lbs. (+70) Fuel capacity 43 gal. (40 gal. usable; two 21.5 gal. tanks in wings at +24) 3A23 Page 14 of 48 For S/n 7249C, 7356C-7472C w/ MK#27 and S/n 7473C and up: 47.6 gal. (43 gal. usable; two 23.8 gal. tanks in wings at +24) Optional wing auxiliary tanks 26 gal. (26 gal. usable; two 13 gal. tanks in wings at +24), S/n 7473C and up: Optional wing auxiliary tanks 30 gal. (30 gal. usable; two 15 gal. tanks in wings at +24), or With Modification Kit 33 installed: Optional wing auxiliary tanks 42 gal. (42 gal. usable; two 21 gal. tanks in wings at +24) (See NOTE 1 for data on system fuel.) Oil capacity IO-540: 8 qt. (-34), 5 qt. minimum O-540: 12 qt. (-34), 9 qt. Minimum (See NOTE 1 for data on system oil.) Control surface movements (See NOTE 12) Serial numbers eligible Model M-6-235, s/n 7249C, 7356C, 7379C-7444C, 7446C-7450C, 7452C-7459C, 7461C-7466C, 7468C, 7469C, 7471C-7475C, 7488C-7514C, 7516C-7519C and up Production basis Production Certificate No. 11S0 XI. Model M-6-180, 4 PCLM (Normal Category), Approved September 15, 1982 (Same as M-6-235, s/n 7249C-7472C, except for nacelle, engine and propeller.) Engine Lycoming O-360-C1F Fuel 100/100LL minimum grade aviation gasoline Engine limits 180 hp at 2700 rpm, all operations Propeller and Hartzell constant speed model HC-C2YR-1BF/F7666A propeller limits Diameter: Not over 76 in; not under 72 in. Pitch settings at 30 in. sta.: low 12º high 27.8º to 29.8º Avoid continuous operation between 2000 and 2250 rpm. Spinner: Hartzell spinner assembly A2298-2 Governor: Woodward H210681 McCauley DC290D1(X)T12 or C290D3(X)/T29 Airspeed limits (CAS) Landplane: (See NOTE 11) C.G. range Landplane: (+16.7) to (+20.5) at 2400 lbs. (+13.6) to (+20.5) at 1600 lbs. or less Straight line variation between points given. Empty weight C.G. range None Maximum weight Landplane: 2400 lbs. Number of seats 4 (2 at +20, 2 at +56) Maximum baggage 170 lbs. (+20), 350 lbs. (+42), 250 lbs. (+70) Fuel capacity 43 gal. (40 gal. usable; two 21.5 gal. tanks in wings at +24) Optional wing auxiliary tanks 26 gal. (26 gal. usable; two 13 gal. tanks in wings at +24) (See NOTE 1 for data on system fuel.) Oil capacity 8 qt. (-36.5), 2 qt. Minimum See NOTE 1 for data on system oil.) ( Control surface movements (See NOTE 12) Serial numbers eligible Model M-6-180, s/n 8020C, 8065C-8067C and up Production basis Production Certificate No. 11S0 Page 15 of 48 3A23 XII. Model M-5-200, 4 PCLM (Normal Category), Approved October 29, 1982 (Same as M-5-235C except for nacelle, engine and propeller.) Engine Lycoming I0-360-J1A6D Fuel 100/100LL minimum grade aviation gasoline Engine limits 200 hp at 2700 rpm, all operations Propeller and Hartzell constant speed model HC-E2YR-1BF/F8467-7R propeller limits Diameter: Not over 77 in.; not under 76.5 in. Pitch settings at 30 in. sta.: low 12º high 30º to 33º Do not exceed 24 in. manifold pressure below 2350 rpm. Spinner: Hartzell spinner assembly A2298-2P Governor: Woodward K210681 Airspeed limits (CAS) Landplane: (See NOTE 11) C.G. range Landplane: (+16.7) to (+20.5) at 2500 lbs. (+13.2) to (+20.5) at 1700 lbs. or less Straight line variation between points given. Empty weight C.G. range None Maximum weight 2500 lbs. Number of seats 4 (2 at +20, 2 at +56) Maximum baggage 170 lbs. (+20), 350 lbs. (+42), 250 lbs. (+70) Fuel capacity 43 gal. (40 gal. usable; two 21.5 gal. tanks in wings at +24) Optional wing auxiliary tanks 23 gal. (23 gal. usable; two 11.5 gal. tanks in wings at +24) See NOTE 16 if Modification Kit No. 15 is installed. (See NOTE 1 for data on system fuel.) Oil capacity 8 qt. (-36.5), 2 qt. Minimum (See NOTE 1 for data on system oil.) Control surface Wing flaps Down 1st Notch 20º +3º movements 2nd Notch 40º +3º Aileron Up 20º +1º Down 20º +1º Elevator Up 25º +2º Down 21º +1º Elevator tab Up 8º to 16º Down 29º +2º Rudder Right 21º +1º Left 21º +1º Rudder tab Right 48º +4º Left 48º +4º Serial numbers eligible Model M-5-200, s/n 8015C, 8022C Production basis (No longer in production.) XIII. Model M-7-235, 5 PCLM (Normal Category) Approved November 9, 1983 (Same as M-6-235 except for fuselage, wings, flaps, ailerons, and rudder.) Engine Lycoming O-540-J1A5D, O-540-J3A5, IO-540-W1A5D, IO-540-W1A5 or O-540-B4B5 Fuel 100/100LL minimum grade aviation gasoline Engine limits 235 hp at 2400 rpm, all operations (O-540-J/IO-540-W) 235 hp at 2575 rpm, all operations (O-540-B) Propeller and 3A23 Page 16 of 48 propeller limits (See NOTE 14) Airspeed limits (CAS) Landplane, Floatplane, and Skiplane: (See NOTE 11) C.G. range Landplane: (+15.0) to (+20.0) at 2500 lbs. (+12.5) to (+20.0) at 1700 lbs. or less Floatplane: EDO 797-2500 amphibious or 248B2440 Floats (+14.0) to (+19.0) at 2750 lbs. (+10.5) to (+19.0) at 1600 lbs. or less Aqua 2400 Floats (+15.0) to (+20.0) at 2750 lbs. (+12.5) to (+20.0) at 1600 lbs. or less Wipline 3000 amphibious Floats (+14.0) to (+19.0) at 2750 lbs. (+12.0) to (+19.0) at 2100 lbs. or less Skiplane: Fli-Lite 3000 MK IIIA Skis (+15.0) to (+20.0) at 2500 lbs. (+12.5) to (+20.0) at 1700 lbs. or less FluiDyne C3000H and C3000M Skis (+15.0) to (+20.0) at 2500 lbs. (+10.0) to (+20.0) at 1700 lbs. or less Straight line variation between points given. Maximum weight Landplane: 2500 lbs. Floatplane: 2750 lbs. Skiplane: 2500 lbs. Number of seats 5(2 at +20, 2 at +53, 1 at +83) Empty weight None C.G. range Maximum baggage 170 lbs. (+20), 350 lbs. (+42), 250 lbs. (+72) Fuel capacity 43 gal. (40 gal. usable; two 21.5 gal. tanks in wings at +24) or 47.6 gal. (43 gal. usable; two 23.8 gal. tanks in wings at +24) Optional wing auxiliary tanks 30 gal. (30 gal. usable; two 15 gal. tanks in wings at +24) or 42 gal. (42 gal. usable;two 21 gal. tanks in wings at +24) (See NOTE 1 for data on system fuel.) Oil capacity IO-540: 8 qt. (-34), 5 qt. minimum O-540: 12 qt. (-34), 9 qt. Minimum (See NOTE 1 for data on system oil.) Control surface movements (See NOTE 12) Serial numbers eligible Model M-7-235, s/n 4001C and up; With STC SA2661SO, s/n 12001C and up (also known as Model M-7-420) Production basis Production Certificate No. 11S0 XIV. Model MX-7-235, 4/5 PCLM (Normal Category), Approved October 18, 1984 (Same as M-6-235 except for wings, flaps, aileron and wing tip.) Engine Lycoming O-540-J1A5D, O-540-J3A5, IO-540-W1A5D, IO-540-W1A5 or O-540-B4B5 Fuel 100/100LL minimum grade aviation gasoline Engine limits 235 hp at 2400 rpm, all operations (O-540-J/IO-540-W) 235 hp at 2575 rpm, all operations (O-540-B) Page 17 of 48 3A23 Propeller and propeller limits (See NOTE 14) Airspeed limits (CAS) Landplane, Floatplane, and Skiplane: (See NOTE 11) C.G. range Landplane: (+15.0) to (+20.5) at 2500 lbs. (+12.0) to (+20.5) at 1700 lbs. or less Floatplane: EDO 797-2500 amphibious or 248B2440: (+14.3) to (+19.0) at 2750 lbs. (+12.3) to (+19.0) at 2100 lbs. or less Wipline 2350 amphibious Floats (+14.1) to (+19.0) at 2500 lbs. (+12.6) to (+19.0) at 2090 lbs. or less Wipline 3000 amphibious Floats (+14.0) to (+19.0) at 2750 lbs. (+12.0) to (+19.0) at 2100 lbs. or less Skiplane: FluiDyne C3000H: (+15.0) to (+19.0) at 2500 lbs. (+11.0) to (+19.0) at 1840 lbs. or less FliLite 3000 MK IIIA: (+15.0) to (+19.0) at 2500 lbs. (+11.0) to (+19.0) at 1700 lbs. or less Straight line variation between points given. Empty weight C.G. range None Maximum weight Landplane: 2500 lbs. Floatplane: 2750 lbs. Skiplane: 2500 lbs. Number of seats 4 (2 at +20, 2 at +56) Optional: 5 (2 at +20, 2 at +53, 1 at +78) Maximum baggage 170 lbs. (+20), 350 lbs. (+42), 250 lbs. (+70) Fuel capacity 43 gal. (40 gal. usable; two 21.5 gal. tanks in wings at +24) or 47.6 gal. (43 gal. usable; two 23.8 gal. tanks in wings at +24) Optional wing auxiliary tanks 30 gal. (30 gal. usable; two 15 gal. tanks in wings at +24) (See NOTE 1 for data on system fuel.) Oil capacity IO-540: 8 qt. (-34), 5 qt. minimum O-540: 12 qt. (-34), 9 qt. Minimum (See NOTE 1 for data on system oil.) Control surface movements (See NOTE 12) Serial numbers eligible Model MX-7-235, s/n 10001C and up Production basis Production Certificate No. 11S0 XV. Model MX-7-180, 4/5 PCLM (Normal Category), Approved December 18, 1984 (Same as MX-7-235 except for nacelle, engine and propeller.) Engine Lycoming 0-360-C1F Fuel 100/100LL minimum grade aviation gasoline Engine limits 180 hp at 2700 rpm, all operations Propeller and Hartzell constant speed model HC-C2YR-1BF/F7666A propeller limits Diameter: Not over 76 in., not under 72 in. 3A23 Page 18 of 48 Pitch settings at 30 in. sta.: low 12º high 27.8º to 29.8º Spinner: Hartzell spinner assembly A2298-2 Governor: Woodward H210681 McCauley C290D3(X)/T29 or DC290D1(X)/T12 Airspeed limits (IAS) Landplane and Floatplane: (See NOTE 11) C.G. range Landplane: (+16.7) to (+20.5) at 2500 lbs. (+13.6) to (+20.5) at 1600 lbs. or less Floatplane: Aqua 2200 Floats: (+13.9) to (+20.5) at 2500 lbs. (+10.5) to (+20.5) at 1600 lbs. or less Straight line variation between points given. Empty weight C.G. range None Maximum weight 2500 lbs. Number of seats 4 (2 at +20, 2 at +56) Optional: 5 (2 at +20, 2 at +53, 1 at +78) Maximum baggage 170 lbs. (+20), 350 lbs. (+42), 250 lbs. (+70) Fuel capacity 43 gal. (40 gal. usable; two 21.5 gal. tanks in wings at +24) or 47.6 gal. (43 gal. usable; two 23.8 gal. tanks in wings at +24) Optional wing auxiliary tanks 30 gal. (30 gal. usable; two 15 gal. tanks in wings at +24) (See NOTE 1 for data on system fuel.) Oil capacity 8 qt. (-36.5), 2 qt. Minimum (See NOTE 1 for data on system oil.) Control surface movements (See NOTE 12) Serial numbers eligible Model MX-7-180, s/n 11001C and up Production basis Production Certificate No. 11S0 XVI. Model MX-7-420, 4/5 PCLM (Normal Category) Approved June 1, 1989 (Same as MX-7-235 except for nacelle, engine, propeller and rudder.) Engine Rolls-Royce Corp. (Allison) Gas Turbine 250-B17C Fuel Primary: Mil-T-5624L, grade JP-4 and JP-5, Mil-T-83133A, grade JP-8, ASTM-D-1655, Jet A, A1 or B, JP-1 Fuel conforming to ASTM-D-1655, Jet A, Artic Diesel Fuel DF-A (VV0F800B) conforming to ASTM-D-1655, Jet A or A1 Diesel #1 fuel conforming to ASTM-D-1655, Jet A Emergency: Mil-G-5572, all grades (aircraft boost pump on; maximum of 6 hours operation per overhaul period of turbine through an engine operating range of idle to 90% maximum SHP) Cold Weather: To assure consistent starts below 4ºC (40ºF), the following fuels may be necessary: MIL-T-5624, grade JP-4 ASTM-D-1655, Jet B AVGAS/Jet A, Jet A1 or Jet JP-5 mixture. (Refer to Cold Weather Fuels, para 2-48, for mixing/use of cold weather fuel in Allison Manual 11W2.) Engine limits 369 hp - 90 psi torque, at 2030 rpm continuous Propeller and Hartzell, constant speed, full-feathering beta, model propeller limits HC-B3TF-7A/T10173F-21R or HC-B3TF-7A/T10173-21R Diameter: 80.5 - 78 inches Pitch settings at 30" sta.: Reverse pitch -15º +5º feather 81.1º +5º Spinner: Hartzell spinner assembly A3640P Page 19 of 48 3A23 Maximum operating altitude 20,000 feet Airspeed limits (CAS) Landplane and Floatplane: (See NOTE 11) C.G. range Landplane: (+15.0) to (+20.0) at 2500 lbs. (+12.0) to (+20.0) at 1700 lbs. or less Floatplane: Wipline 2350 Amphibious: (+14.1) to (+18.5) at 2500 lbs. (+12.6) to (+18.5) at 2090 lbs. or less Straight line variation between points given. Empty weight C.G. range None Maximum weight 2500 lbs. Number of seats 4 (2 at +20, 2 at +56) Optional: 5 (2 at +20, 2 at +53, 1 at +78) Maximum baggage 170 lbs. (+20), 350 lbs. (+42), 250 lbs. (+70) Fuel capacity 43 gal. (40.6 usable; two 21.5 gal. tanks in wings at +24-considered one tank) or 47.6 gal. (43 gal.usable, two 23.8 gal. tanks in wings at +24 - considered one tank) Optional wing auxiliary tanks, 30 gal. (30 usable; two 15 gal. tanks in wings at +24) (or 42 gal. 42 usable; two 21 gal. tanks in wings at + 24). (See NOTE 1 for data on system fuel.) Oil capacity 10 qt. (-22.5), 9 qts. Minimum (See NOTE 1 for data on system oil.) Control surface movements (See NOTE 12) Serial numbers eligible Model MX-7-420, s/n 13001C and up Production basis Production Certificate No. 11S0 XVII. Model MXT-7-180, 4/5 PCLM (Normal Category), Approved November 9, 1990 (Same as M-6-235, s/n 7474C and up, except for nacelle, engine, propeller, ailerons, flaps and landing gear (aluminum spring mains with nosewheel in lieu of tailwheel).) Engine Lycoming Lycoming 0-360-C1F Fuel 100/100LL minimum grade aviation gasoline Engine limits 180 hp at 2700 rpm, all operations Propeller and Hartzell constant speed model HC-C2YR-1BF/7666A propeller limits Diameter: Not over 76 in., not under 72 in. Pitch settings at 30 in. sta.: low 12º high 27.8º to 29.8º Avoid continuous operation between 2000 and 2250 rpm. McCauley constant speed 3-blade model B3D32C414-C/G-82NDA-8 Diameter: 74 in. Pitch settings at 30" sta: low 10.6º +0.2º high 27.5º +0.5º Avoid continuous operation below 10 inches HG between 1900 and 2300 rpm. Spinner: Hartzell spinner assembly A2298-2 (use with Hartzell propeller only) McCauley spinner assembly D-6240 (use with McCauley propeller only) Governor: Woodward H210681 McCauley C290D3(X)/T29 or DC290D1(X)/T12 Airspeed limits (IAS) Landplane and Floatplane: (See NOTE 11) 3A23 Page 20 of 48 C.G. range Landplane: (+15.9) to (+20.5) at 2500 lbs. (+12.4) to (+20.5) at 1740 lbs. or less Floatplane: Aqua 2200 Floats: (+13.9) to (+20.5) at 2500 lbs. (+10.5) to (+20.5) at 1600 lbs. or less Straight line variation between points given. Empty weight C.G. range None Maximum weight 2500 lbs. Number of seats 4 (2 at +20, 2 at +56) Optional: 5 (2 at +20, 2 at +53, 1 at +78) Maximum baggage 170 lbs. (+20), 350 lbs. (+42), 250 lbs. (+70) Fuel capacity 43 gal. (40 gal. usable; two 21.5 gal. tanks in wings at +24) or 47.6 gal. (43 gal. usable; two 23.8 gal. tanks in wings at +24) Optional wing auxiliary tanks 30 gal. (30 gal. usable; two 15 gal. tanks in wings at +24) or 42 (42 gal. usable; two 21 gal. tanks in wings at +24) (See NOTE 1 for data on system fuel.) Oil capacity 8 qt. (-36.5), 2 qt. Minimum (See NOTE 1 for data on system oil.) Control surface movements (See NOTE 12) Serial numbers eligible Model MXT-7-180, s/n 14000C and up Production basis Production Certificate No. 11S0 XVIII. Model MT-7-235, 5 PCLM (Normal Category), Approved March 20, 1992 (Same as MXT-7-180 except for nacelle, engine, propeller and M-7 fuselage.) Engine Lycoming IO-540-W1A5D, IO-540-W1A5 Fuel 100/100LL minimum grade aviation gasoline Engine limits 235 hp at 2400 rpm, full throttle continuous Propeller and Hartzell constant speed model HC-C2YR-1BF/8468A-6R or -3R propeller limits Diameter: -3R: Not over 81 in.; not under 77 in -6R: Not over 78 in.; not under 77 in. Pitch settings at 30" sta.: -3R: low 16º +1º high 30º +1º -6R: low 16.7º +1º high 30º +1º -6R: Do not exceed 23 in. M.P. below 2050 rpm. McCauley constant speed model B3D32C414-C/G-82NDA-4 or -2 McCauley constant speed model B2D37C-224-B/G-90RA-9 Pitch settings at 30" sta: -2 (80"): low 15.0º +0.2º high 30.0º +0.5º -4 (78"): low 15.7º +0.2º high 30.0º +0.5º -9 (81"): low 14.7º +0.2º high 24.6º +0.5º Spinner: Hartzell spinner assembly A2298-2 (use with Hartzell 2 blade propeller only) McCauley spinner assembly D-6240 (use with McCauley 3 blade propeller only) McCauley spinner assembly D-6195 (use with McCauley 2 blade propeller only) Governor: Woodward F210681 or B210761 McCauley C290D3(X)/T30 or DC290D1(X)/T14 Airspeed limits (IAS) Landplane, Floatplane, and Skiplane: (See NOTE 11) C.G. range Landplane: (+15.0) to (+20.5) at 2500 lbs. Page 21 of 48 3A23 (+12.0) to (+20.5) at 1800 lbs. or less Floatplane: Aqua 2400 Floats (+15.0) to (+20.0) at 2750 lbs. (+12.5) to (+20.0) at 1600 lbs. or less Wipline 3000 amphibious Floats (+14.0) to (+19.0) at 2750 lbs. (+12.0) to (+19.0) at 2100 lbs. or less Straight line variation between points given. Empty weight C.G. range None Maximum weight Landplane: 2500 lbs. Floatplane: 2750 lbs. Number of seats 5 (2 at +20, 2 at +53, 1 at +83) Maximum baggage 170 lbs. (+20), 350 lbs. (+42), 250 lbs. (+72) Fuel capacity 43 gal. (40 gal. usable; two 21.5 gal. tanks in wings at +24) or 47.6 gal. (43 gal. usable; two 23.8 gal. tanks in wings at +24) Optional wing auxiliary tanks 30 gal. (30 gal. usable; two 15 gal. tanks in wings at +24) or 42 gal. (42 gal. usable; two 21 gal. tanks in wings at +24) (See NOTE 1 for data on system fuel.) Oil capacity 8 qt. (-34), 5 qt. Minimum (See NOTE 1 for data on system oil Control surface movements (See NOTE 12) Serial numbers eligible Model MT-7-235, s/n 18001C and up Production basis Production Certificate No. 11S0 XIX. Model M-8-235, 4/5 PCLM (Normal Category), Approved August 10, 1992 (Same as M-6-235, s/n 7474C & up, except for flaps, ailerons and landing gear (aluminum spring mains.) Engine Lycoming O-540-J1A5D, O-540-J3A5, IO-540-W1A5D, IO-540-W1A5 or O-540-B4B5 Fuel 100/100LL minimum grade aviation gasoline Engine limits 235 hp at 2400 rpm, all operations (O-540-J/IO-540-W) 235 hp at 2575 rpm, all operations (O-540-B) Propeller and propeller limits (See NOTE 14) Airspeed limits (CAS) Landplane: (See NOTE 11) C.G. range Landplane: (+15.0) to (+20.5) at 2500 lbs. (+12.0) to (+20.5) at 1760 lbs. or less Straight line variation between points given. Empty weight C.G. range None Maximum weight Landplane: 2500 lbs. Number of seats 4 (2 at +20, 2 at +56) Optional: 5 (2 at +20, 2 at +53, 1 at +78) Maximum baggage 170 lbs. (+20), 350 lbs. (+42), 250 lbs. (+70) 3A23 Page 22 of 48 Fuel capacity 43 gal. (40 gal. usable; two 21.5 gal. tanks in wings at +24) or 47.6 gal. (43 gal. usable; two 23.8 gal. tanks in wings at +24) Optional wing auxiliary tanks 30 gal. (30 gal. usable; two 15 gal. tanks in wings at +24) or 42 gal. (42 gal. usable; two 21 gal. tanks in wings at +24) (See NOTE 1 for data on system fuel.) Oil capacity IO-540: 8 qt. (-34), 5 qt. minimum O-540: 12 qt. (-34), 9 qt. Minimum (See NOTE 1 for data on system oil.) Control surface movements (See NOTE 12) Serial numbers eligible Model M-8-235, s/n 15001C and up Production basis Production Certificate No. 11S0 XX. Model MX-7-160, 4 PCLM (Normal Category), Approved November 13, 1992 (Same as MXT-7-180, except for engine, propeller, and has conventional tailwheel landing gear.) Engine Lycoming Lycoming 0-320-B2D Fuel 100/100LL minimum grade aviation gasoline Engine limits 160 hp at 2700 rpm, full throttle continuous Propeller and Sensenich fixed pitch 74DM7S5-0-52 or -54 or -56 (74" Dia.) or propeller limits Sensenich fixed pitch 74DM7S8-0-52 or -54 or -56 (74" Dia.) Diameter: Not over 74 in., not under 72 in., no further reduction permitted. Static rpm at full throttle: Not over 2500 rpm, not under 2400 rpm (-54 or -56) Not over 2620 rpm, not under 2520 rpm (-52) Spinner: Sensenich spinner assembly S74DM Airspeed limits (IAS) Landplane: (See NOTE 11) C.G. range Landplane: (+15.4) to (+20.5) at 2200 lbs. (+12.5) to (+20.5) at 1600 lbs. or less Straight line variation between points given. Empty weight C.G. range None Maximum weight 2200 lbs. Number of seats 4 (2 at +20, 2 at +56) Maximum baggage 170 lbs. (+20), 350 lbs. (+42), 250 lbs. (+70) Fuel capacity 43 gal. (40 gal. usable; two 21.5 gal. tanks in wings at +24) or 47.6 gal. (43 gal. usable; two 23.8 gal. tanks in wings at +24) Optional wing auxiliary tanks 30 gal. (30 gal. usable; two 15 gal. tanks in wings at +24) or 42 gal. (42 gal. usable; two 21 gal. tanks in wings at +24) (See NOTE 1 for data on system fuel.) Oil capacity 8 qt. (-36.5), 2 qt. Minimum (See NOTE 1 for data on system oil.) Control surface movements (See NOTE 12) Serial numbers eligible Model MX-7-160, s/n 19001C and up Production basis Production Certificate No. 11S0 Page 23 of 48 3A23 XXI. Model MXT-7-160, 2/4 PCLM (Normal Category), Approved November 13, 1992 (Same as MXT-7-180, except for engine and propeller.) Engine Lycoming Lycoming 0-320-B2D Fuel 100/100LL minimum grade aviation gasoline Engine limits 160 hp at 2700 rpm, full throttle continuous Propeller and Sensenich fixed pitch 74DM7S5-0-52 or -54 or -56 (74" Dia.) or propeller limits Sensenich fixed pitch 74DM7S8-0-52 or -54 or -56 (74" Dia.) Diameter: Not over 74 in., not under 72 in., no further reduction permitted. Static rpm at full throttle: Not over 2500 rpm, not under 2400 rpm (-54 or -56) Not over 2620 rpm, not under 2520 rpm (-52) Spinner: Sensenich spinner assembly S74DM Airspeed limits (IAS) Landplane: (See NOTE 11) C.G. range Landplane: (+15.4) to (+20.5) at 2200 lbs. (+12.5) to (+20.5) at 1600 lbs. or less Floatplane: Aqua 2200 Floats: (+14.6) to (+20.5) at 2200 lbs. (+13.5) to (+20.5) at 1600 lbs. or less Straight line variation between points given. Empty weight C.G. range None Maximum weight 2200 lbs. Number of seats 4 (2 at +20, 2 at +56) Optional: 2 (2 at +20) Maximum baggage 170 lbs. (+20), 350 lbs. (+42), 250 lbs. (+70) Fuel capacity 43 gal. (40 gal. usable; two 21.5 gal. tanks in wings at +24) or 47.6 gal. (43 gal. usable; two 23.8 gal. tanks in wings at +24) Optional wing auxiliary tanks 30 gal. (30 gal. usable; two 15 gal. tanks in wings at +24) or 42 gal. (42 gal. usable; two 21 gal. tanks in wings at +24) (See NOTE 1 for data on system fuel.) Oil capacity 8 qt. (-36.5), 2 qt. Minimum (See NOTE 1 for data on system oil.) Control surface movements (See NOTE 12) Serial numbers eligible Model MXT-7-160, s/n 17001C and up Production basis Production Certificate No. 11S0 XXII. Model MX-7-180A, 4 PCLM (Normal Category), Approved June 3, 1993 (Same as MXT-7-180, except for engine, propeller, and has conventional tailwheel landing gear.) Engine Lycoming 0-360-C1F or 0-360-C4F Fuel 100/100LL minimum grade aviation gasoline Engine limits 180 hp at 2700 rpm, full throttle continuous Propeller and Sensenich fixed pitch 76EM8S5-0-56 (76" Dia.) or 76EM8S8-0-56 (76" Dia.) propeller limits Diameter: Not over 76 in., not under 76 in., no further reduction permitted. 3A23 Page 24 of 48 Static rpm at full throttle: Not over 2500 rpm, not under 2400 rpm. Spinner: Sensenich spinner assembly S76EM Airspeed limits (IAS) Landplane: (See NOTE 11) C.G. range Landplane: (+15.9) to (+20.5) at 2400 lbs. (+12.4) to (+20.5) at 1740 lbs. or less Straight line variation between points given. Empty weight C.G. range None Maximum weight 2400 lbs. Number of seats 4 (2 at +20, 2 at +56) Maximum baggage 170 lbs. at (+20), 350 lbs. (+42), 250 lbs. (+70) Fuel capacity 43 gal. (40 gal. usable; two 21.5 gal. tanks in wings at +24) or 47.6 gal. (43 gal. usable; two 23.8 gal. tanks in wings at +24) Optional wing auxiliary tanks 30 gal. (30 gal. usable; two 15 gal. tanks in wing at +24) or 42 gal. (42 gal. usable; two 21 gal. tanks in wings at +24) (See NOTE 1 for data on system fuel.) Oil capacity 8 qt. (-36.5), 2 qt. Minimum (See NOTE 1 for data on system oil.) Control surface movements (See NOTE 12) Serial numbers eligible Model MX-7-180A, s/n 20001C and up Production basis Production Certificate No. 11S0 XXIII. Model MXT-7-180A, 4 PCLM (Normal Category), Approved June 3, 1993 (Same as MXT-7-180, except for engine and propeller.) Engine Lycoming 0-360-C1F or 0-360-C4F Fuel 100/100LL minimum grade aviation gasoline Engine limits 180 hp at 2700 rpm, full throttle continuous Propeller and Sensenich fixed pitch 76EM8S5-0-56 (76" Dia.) or 76EM8S8-0-56 (76" Dia.) propeller limits Diameter: Not over 76 in., not under 76 in., no further reduction permitted. Static rpm at full throttle: Not over 2500 rpm, not under 2400 rpm. Spinner: Sensenich spinner assembly S76EM Airspeed limits (IAS) Landplane and Floatplane: (See NOTE 11) C.G. range Landplane: (+15.9) to (+20.5) at 2400 lbs. (+12.4) to (+20.5) at 1740 lbs. or less Floatplane: Aqua 2200 Floats: (+15.0) to (+20.5) at 2400 lbs. (+13.5) to (+20.5) at 1600 lbs. or less Straight line variation between points given. Empty weight C.G. range None Maximum weight 2400 lbs. Number of seats 4 (2 at +20, 2 at +56) Page 25 of 48 3A23 Maximum baggage 170 lbs. at (+20), 350 lbs. (+42), 250 lbs. (+70) Fuel capacity 43 gal. (40 gal. usable; two 21.5 gal. tanks in wings at +24) or 47.6 gal. (43 gal. usable; two 23.8 gal. tanks in wings at +24) Optional wing auxiliary tanks 30 gal. (30 gal. usable; two 15 gal. tanks in wing at +24) or 42 gal. (42 gal. usable; two 21 gal. tanks in wings at +24) (See NOTE 1 for data on system fuel.) Oil capacity 8 qt. (-36.5), 2 qt. Minimum (See NOTE 1 for data on system oil.) Control surface movements (See NOTE 12) Serial numbers eligible Model MXT-7-180A, s/n 21001C and up Production basis Production Certificate No. 11S0 XXIV. Model MX-7-180B, 4/5 PCLM (Normal Category), Approved July 12, 1993 (Same as MXT-7-180 except for conventional tailwheel landing gear.) Engine Lycoming Lycoming 0-360-C1F Fuel 100/100LL minimum grade aviation gasoline Engine limits 180 hp at 2700 rpm, all operations Propeller and Hartzell constant speed model HC-C2YR-1BF/7666A propeller limits Diameter: Not over 76 in., not under 72 in. no further reduction permitted. Pitch settings at 30 in. sta.: low 12º high 27.8º to 29.8º Avoid continuous operation between 2000 and 2250 rpm. Spinner: Hartzell spinner assembly A2298-2 Governor: Woodward H210681 McCauley C290D3(X)/T29 or DC290D1(X)/T12 Airspeed limits (IAS) Landplane and Floatplane: (See NOTE 11) C.G. range Landplane: (+15.9) to (+20.5) at 2500 lbs. (+12.4) to (+20.5) at 1740 lbs. or less Straight line variation between points given. Floatplane: See appropriate AFMS for C.G. range for different float installations. Empty weight C.G. range None Maximum weight 2500 lbs. Number of seats 4 (2 at +20, 2 at +56) Optional: 5 (2 at +20, 2 at +53, 1 at +78) Maximum baggage 170 lbs. (+20), 350 lbs. (+42), 250 lbs. (+70) Fuel capacity 43 gal. (40 gal. usable; two 21.5 gal. tanks in wings at +24) or 47.6 gal. (43 gal. usable; two 23.8 gal. tanks in wings at +24) Optional wing auxiliary tanks 30 gal. (30 gal. usable; two 15 gal. tanks in wings at +24) or 42 (42 gal. usable; two 21 gal. tanks in wings at +24) (See NOTE 1 for data on system fuel.) Oil capacity 8 qt. (-36.5), 2 qt. minimum (See NOTE 1 for data on system oil.) Control surface movements (See NOTE 12) 3A23 Page 26 of 48 Serial numbers eligible Model MX-7-180B, s/n 22001C and up Production basis Production Certificate No. 11S0 XXV. Model MXT-7-420, 4/5 PCLM (Normal Category), Approved July 12, 1993, Model deleted from TC January 7, 2003 Model MXT-7-420 removed from the type certificate per Maule Aerospace Technology’s request. One serial number airplane of this model was built and has now been dismantled. XXVI. Model M-7-235B, 5 PCLM (Normal Category), Approved October 14, 1993 (Same as MT-7-235 except has conventional tailwheel landing gear.) Engine Lycoming O-540-J1A5D, O-540-J3A5, IO-540-W1A5D, IO-540-W1A5 or O-540-B4B5 Fuel 100/100LL minimum grade aviation gasoline Engine limits 235 hp at 2400 rpm, all operations (O-540-J/IO-540-W) 235 hp at 2575 rpm, all operations (O-540-B) Propeller and propeller limits (See NOTE 14) Airspeed limits (CAS) Landplane, Floatplane, and Skiplane: (See NOTE 11) C.G. range Landplane: (+15.0) to (+20.0) at 2500 lbs. (+12.5) to (+20.0) at 1700 lbs. or less Floatplane: EDO 797-2500 amphibious or 248B2440: (+14.0) to (+19.0) at 2750 lbs. (+12.5) to (+19.0) at 2400 lbs. or less Aqua 2400 Floats (+15.0) to (+20.0) at 2750 lbs. (+12.5) to (+20.0) at 1600 lbs. or less Wipline 3000 amphibious Floats (+14.0) to (+19.0) at 2750 lbs. (+12.0) to (+19.0) at 2100 lbs. or less Skiplane: FliLite 3000 MK IIIA: (+15.0) to (+20.0) at 2500 lbs. (+12.5) to (+20.0) at 1700 lbs. or less FluiDyne C3000H: (+15.0) to (+19.5) at 2500 lbs. (+11.5) to (+19.5) at 1700 lbs. or less Straight line variation between points given. Empty weight C.G. range None Maximum weight Landplane: 2500 lbs. Floatplane: 2750 lbs. Skiplane: 2500 lbs. Number of seats 5 (2 at +20, 2 at +53, 1 at +83) Maximum baggage 170 lbs. (+20), 350 lbs. (+42), 250 lbs. (+72) Fuel capacity 43 gal. (40 gal. usable; two 21.5 gal. tanks in wings at +24) or 47.6 gal. (43 gal. usable; two 23.8 gal. tanks in wings at +24) Optional wing auxiliary tanks 30 gal. (30 gal. usable; two 15 gal. tanks in wings at +24) or 42 gal. (42 gal. usable; two 21 gal. tanks in wings at +24) (See NOTE 1 for data on system fuel.) Oil capacity IO-540: 8 qt. (-34), 5 qt. minimum Page 27 of 48 3A23 O-540: 12 qt. (-34), 9 qt. minimum (See NOTE 1 for data on system oil.) Control surface movements (See NOTE 12) Serial numbers eligible Model M-7-235B, s/n 23001C and up Production basis Production Certificate No. 11S0 XXVII. Model M-7-235A, 5 PCLM (Normal Category) Approved March 10, 1994 (Same as M-7-235 except for flaps and ailerons.) Engine Lycoming O-540-J1A5D, O-540-J3A5, IO-540-W1A5D, IO-540-W1A5 or O-540-B4B5 Fuel 100/100LL minimum grade aviation gasoline Engine limits 235 hp at 2400 rpm, all operations (O-540-J/IO-540-W) 235 hp at 2575 rpm, all operations (O-540-B) Propeller and propeller limits (See NOTE 14) Airspeed limits (CAS) Landplane, Floatplane, and Skiplane: (See NOTE 11) C.G. range Landplane: (+15.0) to (+20.0) at 2500 lbs. (+12.5) to (+20.0) at 1700 lbs. or less Floatplane: Aqua 2400 Floats (+15.0) to (+20.0) at 2750 lbs. (+12.5) to (+20.0) at 1600 lbs. or less Skiplane: FluiDyne C3000H: (+15.0) to (+19.5) at 2500 lbs. (+11.5) to (+19.5) at 1700 lbs. or less Straight line variation between points given. Empty weight C.G. range None Maximum weight Landplane: 2500 lbs. Floatplane: 2750 lbs. Skiplane: 2500 lbs. Number of seats 5 (2 at +20, 2 at +53, 1 at +83) Maximum baggage 170 lbs. (+20), 350 lbs. (+42), 250 lbs. (+72) Fuel capacity 43 gal. (40 gal. usable; two 21.5 gal. tanks in wings at +24) or 47.6 gal. (43 gal. usable; two 23.8 gal. tanks in wings at +24) Optional wing auxiliary tanks 30 gal. (30 gal. usable; two 15 gal. tanks in wings at +24) or 42 gal. (42 gal. usable; two 21 gal. tanks in wings at +24) (See NOTE 1 for data on system fuel.) Oil capacity IO-540: 8 qt. (-34), 5 qt. minimum O-540: 12 qt. (-34), 9 qt. minimum (See NOTE 1 for data on system oil.) Control surface movements (See NOTE 12) Serial numbers eligible Model M-7-235A, s/n 24001C and up Production basis Production Certificate No. 11S0 3A23 Page 28 of 48 XXVIII. Model M-7-235C, 5 PCLM (Normal Category) Approved October 10, 1995 (Same as M-7-235B except spring aluminum main landing gear.) Engine Lycoming O-540-J1A5D, O-540-J3A5, IO-540-W1A5D, IO-540-W1A5 or O-540-B4B5 Fuel 100/100LL minimum grade aviation gasoline Engine limits 235 hp at 2400 rpm, all operations (O-540-J/IO-540-W) 235 hp at 2575 rpm, all operations (O-540-B) Propeller and propeller limits (See NOTE 14) Airspeed limits (CAS) Landplane, Floatplane, and Skiplane: (See NOTE 11) C.G. range Landplane: (+15.0) to (+20.5) at 2500 lbs. (+12.0) to (+20.5) at 1760 lbs. or less Floatplane: EDO 797-2500 amphibious Floats (+14.0) to (+19.0) at 2750 lbs. (+12.5) to (+19.0) at 2400 lbs. or less Aqua 2400 Floats (+15.0) to (+20.0) at 2750 lbs. (+12.5) to (+20.0) at 1600 lbs. or less Wipline 3000 amphibious Floats (+14.0) to (+19.0) at 2750 lbs. (+12.0) to (+19.0) at 2100 lbs. or less Straight line variation between points given. Empty weight C.G. range None Maximum weight Landplane: 2500 lbs. Floatplane: 2750 lbs. Number of seats 5 (2 at +20, 2 at +53, 1 at +83) Maximum baggage 170 lbs. (+20), 350 lbs. (+42), 250 lbs. (+72) Fuel capacity 43 gal. (40 gal. usable; two 21.5 gal. tanks in wings at +24) or 47.6 gal. (43 gal. usable; two 23.8 gal. tanks in wings at +24) Optional wing auxiliary tanks 30 gal. (30 gal. usable; two 15 gal. tanks in wings at +24) or 42 gal. (42 gal. usable; two 21 gal. tanks in wings at +24) (See NOTE 1 for data on system fuel.) Oil capacity IO-540: 8 qt. (-34), 5 qt. minimum O-540: 12 qt. (-34), 9 qt. minimum (See NOTE 1 for data on system oil.) Control surface movements (See NOTE 12) Serial numbers eligible Model M-7-235C, s/n 25001C and up Production basis Production Certificate No. 11S0 XXIX. Model MX-7-180C, 4/5 PCLM (Normal Category) Approved August 27, 1996 (Same as MX-7-180B except for landing gear (aluminum spring mains) Engine Lycoming Lycoming 0-360-C1F Fuel 100/100LL minimum grade aviation gasoline Engine limits 180 hp at 2700 rpm, all operations Page 29 of 48 3A23 Propeller and Hartzell constant speed model HC-C2YR-1BF/7666A propeller limits Diameter: Not over 76 in., not under 72 in. no further reduction permitted. Pitch settings at 30 in. sta.: low 12º high 27.8º to 29.8º Avoid continuous operation between 2000 and 2250 rpm. Spinner: Hartzell spinner assembly A2298-2 Governor: Woodward H210681 McCauley C290D3(X)/T29 or DC290D1(X)/T12 Airspeed limits (IAS) Landplane and Floatplane: (See NOTE 11) C.G. range Landplane: (+15.9) to (+20.5) at 2500 lbs. (+12.4) to (+20.5) at 1740 lbs. or less Floatplane: Aqua 2200 Floats (+13.9) to (+20.5) at 2500 lbs. (+10.5) to (+20.5) at 1600 lbs. or less Wipline 2350 amphibious Floats (+15.0) to (+19.0) at 2500 lbs. (+13.5) to (+19.0) at 2090 lbs. or less Straight line variation between points given. Empty weight C.G. range None Maximum weight 2500 lbs. Number of seats 4 (2 at +20, 2 at +56) Optional: 5 (2 at +20, 2 at +53, 1 at +78) Maximum baggage 170 lbs. (+20), 350 lbs. (+42), 250 lbs. (+70) Fuel capacity 47.6 gal. (43 gal. usable; two 23.8 gal. tanks in wings at +24) or 43 gal. (40 gal. usable; two 21.5 gal. tanks in wings at +24) Optional wing auxiliary tanks 30 gal. (30 gal. usable; two 15 gal. tanks in wings at +24) or 42 (42 gal. usable; two 21 gal. tanks in wings at +24) (See NOTE 1 for data on system fuel.) Oil capacity 8 qt. (-36.5), 2 qt. minimum (See NOTE 1 for data on system oil.) Control surface movements (See NOTE 12) Serial numbers eligible Model MX-7-180C, s/n 28001C and up Production basis Production Certificate No. 11S0 XXX. Model M-7-260, 5 PCLM (Normal Category) Approved April 17, 1998 (Same as M-7-235B except engine and propeller.) Engine Lycoming IO-540-V4A5 Fuel 100/100LL minimum grade aviation gasoline Engine limits 260 hp at 2700 rpm, full throttle continuous Propeller and propeller limits (See NOTE 15) Airspeed limits (IAS) Landplane, Floatplane, and Skiplane: (See NOTE 11) C.G. range Landplane: (+15.0) to (+20.0) at 2500 lbs. 3A23 Page 30 of 48 (+12.5) to (+20.0) at 1700 lbs. or less Floatplane: Wipline 3000 amphibious Floats (+14.0) to (+19.0) at 2750 lbs. (+12.0) to (+19.0) at 2100 lbs. or less Aqua 2400 Floats (+15.0) to (+20.0) at 2750 lbs. (+12.5) to (+20.0) at 1600 lbs. or less Straight line variation between points given. Empty weight C.G. range None Maximum weight Landplane: 2500 lbs. Floatplane: 2750 lbs. Number of seats 5 (2 at +20, 2 at +53, 1 at +83) Maximum baggage 170 lbs. (+20), 350 lbs. (+42), 250 lbs. (+72) Fuel capacity 47.6 gal. (43 gal. usable; two 23.8 gal. tanks in wings at +24) Optional wing auxiliary tanks 30 gal. (30 gal. usable; two 15 gal. tanks in wings at +24) or 42 gal. (42 gal. usable; two 21 gal. tanks in wings at +24) (See NOTE 1 for data on fuel system.) Oil capacity 8 qt. (-34), 5 qt. minimum (See NOTE 1 for data on oil system.) Control surface movements (See NOTE 12) Serial numbers eligible Model M-7-260, s/n 26001C and up Production basis Production Certificate No. 11S0 XXXI. Model MT-7-260, 5 PCLM (Normal Category) Approved April 17, 1998 (Same as MT-7-235 except engine and propeller.) Engine Lycoming IO-540-V4A5 Fuel 100/100LL minimum grade aviation gasoline Engine limits 260 hp at 2700 rpm, full throttle continuous Propeller and propeller limits (See NOTE 15) Airspeed limits (IAS) Landplane, Floatplane, and Skiplane: (See NOTE 11) C.G. range Landplane: (+15.0) to (+20.0) at 2500 lbs. (+12.5) to (+20.0) at 1700 lbs. or less Floatplane: Wipline 3000 amphibious Floats (+14.0) to (+19.0) at 2750 lbs. (+12.0) to (+19.0) at 2100 lbs. or less Aqua 2400 Floats (+15.0) to (+20.0) at 2750 lbs. (+12.5) to (+20.0) at 1600 lbs. or less Straight line variation between points given. Empty weight C.G. range None Page 31 of 48 3A23 Maximum weight Landplane: 2500 lbs. Floatplane: 2750 lbs. Number of seats 5 (2 at +20, 2 at +53, 1 at +83) Maximum baggage 170 lbs. (+20), 350 lbs. (+42), 250 lbs. (+72) Fuel capacity 47.6 gal. (43 gal. usable; two 23.8 gal. tanks in wings at +24) Optional wing auxiliary tanks 30 gal. (30 gal. usable; two 15 gal. tanks in wings at +24) or 42 gal. (42 gal. usable; two 21 gal. tanks in wings at +24) (See NOTE 1 for data on fuel system.) Oil capacity 8 qt. (-34), 5 qt. minimum (See NOTE 1 for data on oil system.) Control surface movements (See NOTE 12) Serial numbers eligible Model MT-7-260, s/n 27001C and up Production basis Production Certificate No. 11S0 XXXII. Model M-7-260C, 5 PCLM (Normal Category) Approved October 19, 1998 (Same as M-7-235C except engine and propeller.) Engine Lycoming IO-540-V4A5 Fuel 100/100LL minimum grade aviation gasoline Engine limits 260 hp at 2700 rpm, full throttle continuous Propeller and propeller limits (See NOTE 15) Airspeed limits (IAS) Landplane, Floatplane, and Skiplane: (See NOTE 11) C.G. range Landplane: (+15.0) to (+20.0) at 2500 lbs. (+12.5) to (+20.0) at 1700 lbs. or less Floatplane: Wipline 3000 amphibious Floats (+14.0) to (+19.0) at 2750 lbs. (+12.0) to (+19.0) at 2100 lbs. or less Aqua 2400 Floats (+15.0) to (+20.0) at 2750 lbs. (+12.5) to (+20.0) at 1600 lbs. or less Straight line variation between points given. Empty weight C.G. range None Maximum weight Landplane: 2500 lbs. Floatplane: 2750 lbs. Number of seats 5 (2 at +20, 2 at +53, 1 at +83) Maximum baggage 170 lbs. (+20), 350 lbs. (+42), 250 lbs. (+72) Fuel capacity 47.6 gal. (43 gal. usable; two 23.8 gal. tanks in wings at +24) Optional wing auxiliary tanks 30 gal. (30 gal. usable; two 15 gal. tanks in wings at +24) or 42 gal. (42 gal. usable; two 21 gal. tanks in wings at +24) (See NOTE 1 for data on fuel system.) 3A23 Page 32 of 48 Oil capacity 8 qt. (-34), 5 qt. minimum (See NOTE 1 for data on oil system.) Control surface movements (See NOTE 12) Serial numbers eligible Model M-7-260, s/n 30001C and up Production basis Production Certificate No. 11S0 XXXIII. Model M-7-420AC, 5 PCLM (Normal Category) Approved December 17, 1998 (Same as M-7-235A except for main landing gear, flap ratchet, nacelle, engine, and propeller.) Engine Rolls-Royce Corp. (Allison) Gas Turbine 250-B17C Fuel Primary: Mil-T-5624L, grade JP-4 and JP-5, Mil-T-83133A, grade JP-8, ASTM-D-1655, Jet A, A1 or B, JP-1 Fuel conforming to ASTM-D-1655, Jet A, Artic Diesel Fuel DF-A (VV0F800B) conforming to ASTM-D-1655, Jet A or A1 Diesel #1 fuel conforming to ASTM-D-1655, Jet A Emergency: Mil-G-5572, all grades (aircraft boost pump on; maximum of 6 hours operation per overhaul period of turbine through an engine operating range of idle to 90% maximum SHP) Cold Weather: To assure consistent starts below 4ºC (40ºF), the following fuels may be necessary: MIL-T-5624, grade JP-4 ASTM-D-1655, Jet B AVGAS/Jet A, Jet A1 or Jet JP-5 mixture. (Refer to Cold Weather Fuels, para 2-48, for mixing/use of cold weather fuel in Allison Manual 11W2.) Engine limits 369 hp - 90 psi torque, at 2030 rpm continuous Propeller and Hartzell, constant speed, full-feathering beta, model propeller limits HC-B3TF-7A/T10173F-21R Diameter: 80.5 - 78 inches Pitch settings at 30" sta.: Reverse pitch -15º +5º feather 81.1º +5º Spinner: Hartzell spinner assembly A3640P Maximum operating altitude 20,000 feet Airspeed limits (CAS) Landplane and Floatplane: (See NOTE 11) C.G. range Landplane: (+15.0) to (+20.5) at 2500 lbs. (+13.1) to (+20.5) at 2090 lbs. or less Floatplane: Wipline 3000 Amphibious: (+14.0) to (+19.0) at 2750 lbs. (+12.0) to (+19.0) at 2100 lbs. or less Straight line variation between points given. Empty weight C.G. range None Maximum weight Landplane: 2500 lbs. Floatplane: 2750 lbs. Number of seats 5 (2 at +20, 2 at +53, 1 at +83) Maximum baggage 170 lbs. (+20), 350 lbs. (+42), 250 lbs. (+72) Fuel capacity 47.6 gal. (43 gal. usable, two 23.8 gal. tanks in wings at +24 - considered one tank) Optional wing auxiliary tanks, 42 gal. (42 usable; two 21 gal. tanks in wings at + 24). (See NOTE 1 for data on fuel system.) Oil capacity 10 qt. (-22.5), 9 qts. Minimum (See NOTE 1 for data on oil system.) Page 33 of 48 3A23 Control surface movements (See NOTE 12) Serial numbers eligible Model M-7-420AC, s/n 29001C and up Production basis Production Certificate No. 11S0 XXXIV. Model MX-7-160C, 4 PCLM (Normal Category), Approved March 12, 1999 (Same as MX-7-160, except for spring aluminum main landing gear.) Engine Lycoming 0-320-B2D Fuel 100/100LL minimum grade aviation gasoline Engine limits 160 hp at 2700 rpm, full throttle continuous Propeller and Sensenich fixed pitch 74DM7S5-0-52 or -54 or -56 (74" Dia.) or propeller limits Sensenich fixed pitch 74DM7S8-0-52 or -54 or -56 (74" Dia.) Diameter: Not over 74 in., not under 72 in., no further reduction permitted. Static rpm at full throttle: Not over 2500 rpm, not under 2400 rpm (-54 or -56) Not over 2620 rpm, not under 2520 rpm (-52) Spinner: Sensenich spinner assembly S74DM Airspeed limits (IAS) Landplane: (See NOTE 11) C.G. range Landplane: (+15.4) to (+20.5) at 2200 lbs. (+12.5) to (+20.5) at 1600 lbs. or less Floatplane: Aqua 2200 Floats (+14.6) to (+20.5) at 2200 lbs. (+13.5) to (+20.5) at 1600 lbs. or less Straight line variation between points given. Empty weight C.G. range None Maximum weight 2200 lbs. Number of seats 4 (2 at +20, 2 at +56) Maximum baggage 170 lbs. (+20), 350 lbs. (+42), 250 lbs. (+70) Fuel capacity 47.6 gal. (43 gal. usable; two 23.8 gal. tanks in wings at +24) Optional wing auxiliary tanks 30 gal. (30 gal. usable; two 15 gal. tanks in wings at +24) or 42 gal. (42 gal. usable; two 21 gal. tanks in wings at +24) (See NOTE 1 for data on fuel system.) Oil capacity 8 qt. (-36.5), 2 qt. minimum (See NOTE 1 for data on oil system.) Control surface movements (See NOTE 12) Serial numbers eligible Model MX-7-160C, s/n 34001C and up Production basis Production Certificate No. 11S0 XXXV. Model MX-7-180AC, 4/5 PCLM (Normal Category), Approved May 4, 2000 (Same as MX-7-180A, except for aluminum spring main landing gear.) Engine Lycoming 0-360-C1F or 0-360-C4F Fuel 100/100LL minimum grade aviation gasoline 3A23 Page 34 of 48 Engine limits 180 hp at 2700 rpm, full throttle continuous Propeller and Sensenich fixed pitch 76EM8S5-0-56 (76" Dia.) or 76EM8S8-0-56 (76" Dia.) propeller limits Diameter: Not over 76 in., not under 76 in., no further reduction permitted. Static rpm at full throttle: Not over 2500 rpm, not under 2400 rpm. Spinner: Sensenich spinner assembly S76EM Airspeed limits (IAS) Landplane and Floatplane: (See NOTE 11) C.G. range Landplane: (+15.9) to (+20.5) at 2400 lbs. (+12.4) to (+20.5) at 1740 lbs. or less Floatplane: Aqua 2200 Floats (+15.0) to (+20.5) at 2400 lbs. (+13.5) to (+20.5) at 1600 lbs. or less Straight line variation between points given. Empty weight C.G. range None Maximum weight 2400 lbs. Number of seats 4 (2 at +20, 2 at +56) Optional: 5(2 at +20, 2 at +53, 1 at +78) Maximum baggage 170 lbs. at (+20), 350 lbs. (+42), 250 lbs. (+70) Fuel capacity 47.6 gal. (43 gal. usable; two 23.8 gal. tanks in wings at +24) Optional wing auxiliary tanks 30 gal. (30 gal. usable; two 15 gal. tanks in wing at +24) or 42 gal. (42 gal. usable; two 21 gal. tanks in wings at +24) (See NOTE 1 for data on fuel system.) Oil capacity 8 qt. (-36.5), 2 qt. minimum (See NOTE 1 for data on oil system.) Control surface movements (See NOTE 12) Serial numbers eligible Model MX-7-180AC, s/n 33001C and up Production basis Production Certificate No. 11S0 XXXVI. Model M-7-420A, 5 PCLM (Normal Category) Approved November 20, 2000 (Same as M-7-420AC except conventional oleo main landing gear.) Engine Rolls-Royce Corp. (Allison) Gas Turbine 250-B17C Fuel Primary: Mil-T-5624L, grade JP-4 and JP-5, Mil-T-83133A, grade JP-8, ASTM-D-1655, Jet A, A1 or B, JP-1 Fuel conforming to ASTM-D-1655, Jet A, Artic Diesel Fuel DF-A (VV0F800B) conforming to ASTM-D-1655, Jet A or A1 Diesel #1 fuel conforming to ASTM-D-1655, Jet A Emergency: Mil-G-5572, all grades (aircraft boost pump on; maximum of 6 hours operation per overhaul period of turbine through an engine operating range of idle to 90% maximum SHP) Cold Weather: To assure consistent starts below 4ºC (40ºF), the following fuels may be necessary: MIL-T-5624, grade JP-4 ASTM-D-1655, Jet B AVGAS/Jet A, Jet A1 or Jet JP-5 mixture. (Refer to Cold Weather Fuels, para 2-48, for mixing/use of cold weather fuel in Allison Manual 11W2.) Engine limits 369 hp - 90 psi torque, at 2030 rpm continuous Propeller and Hartzell, constant speed, full-feathering beta, model HC-B3TF-7A/T10173F-21R propeller limits Or HC-B3TF-7A/T10173-21R Diameter: 80.5 - 78 inches Page 35 of 48 3A23 Pitch settings at 30" sta.: Reverse pitch -15º +5º feather 81.1º +5º Spinner: Hartzell spinner assembly A3640P Maximum operating altitude 20,000 feet Airspeed limits (CAS) Landplane and Floatplane: (See NOTE 11) C.G. range Landplane: (+15.0) to (+20.5) at 2500 lbs. (+13.1) to (+20.5) at 2090 lbs. or less Floatplane: Wipline 3000 Amphibious: (+14.0) to (+19.0) at 2750 lbs. (+12.0) to (+19.0) at 2100 lbs. or less Straight line variation between points given. Empty weight C.G. range None Maximum weight Landplane: 2500 lbs. Floatplane: 2750 lbs. Number of seats 5 (2 at +20, 2 at +53, 1 at +83) Maximum baggage 170 lbs. (+20), 350 lbs. (+42), 250 lbs. (+72) Fuel capacity 47.6 gal. (43 gal. usable, two 23.8 gal. tanks in wings at +24 - considered one tank) Optional wing auxiliary tanks, 42 gal. (42 usable; two 21 gal. tanks in wings at + 24). (See NOTE 1 for data on fuel system.) Oil capacity 10 qt. (-22.5), 9 qts. Minimum (See NOTE 1 for data on oil system.) Control surface movements (See NOTE 12) Serial numbers eligible Model M-7-420A, s/n 35001C and up Production basis Production Certificate No. 11S0 XXXVII. Model MT-7-420, 5 PCLM (Normal Category) Approved January 6, 2003 (Same as MT-7-260 except for nacelle, engine, propeller.) Engine Rolls-Royce Corp. (Allison) Gas Turbine 250-B17C Fuel Primary: Mil-T-5624L, grade JP-4 and JP-5, Mil-T-83133A, grade JP-8, ASTM-D-1655, Jet A, A1 or B, JP-1 Fuel conforming to ASTM-D-1655, Jet A, Artic Diesel Fuel DF-A (VV0F800B) conforming to ASTM-D-1655, Jet A or A1 Diesel #1 fuel conforming to ASTM-D-1655, Jet A Emergency: Mil-G-5572, all grades (aircraft boost pump on; maximum of 6 hours operation per overhaul period of turbine through an engine operating range of idle to 90% maximum SHP) Cold Weather: To assure consistent starts below 4ºC (40ºF), the following fuels may be necessary: MIL-T-5624, grade JP-4 ASTM-D-1655, Jet B AVGAS/Jet A, Jet A1 or Jet JP-5 mixture. (Refer to Cold Weather Fuels, para 2-48, for mixing/use of cold weather fuel in Allison Manual 11W2.) Engine limits 369 hp - 90 psi torque, at 2030 rpm continuous Propeller and Hartzell, constant speed, full-feathering beta, model HC-B3TF-7A/T10173F-21R propeller limits or HC-B3TF-7A/T10173-21R Diameter: 80.5 - 78 inches Pitch settings at 30" sta.: Reverse pitch -15º +5º feather 81.1º +5º 3A23 Page 36 of 48 Spinner: Hartzell spinner assembly A3640P Maximum operating altitude 20,000 feet Airspeed limits (CAS) Landplane and Floatplane: (See NOTE 11) C.G. range Landplane: (+16.0) to (+20.5) at 2500 lbs. (+13.0) to (+20.5) at 1700 lbs. or less Floatplane: Wipline 3000 Amphibious: (+14.0) to (+19.0) at 2750 lbs. (+12.0) to (+19.0) at 2100 lbs. or less Straight line variation between points given. Empty weight C.G. range None Maximum weight Landplane: 2500 lbs. Floatplane: 2750 lbs. Number of seats 5 (2 at +20, 2 at +53, 1 at +83) Maximum baggage 170 lbs. (+20), 350 lbs. (+42), 250 lbs. (+72) Fuel capacity 47.6 gal. (43 gal. usable, two 23.8 gal. tanks in wings at +24 - considered one tank) Optional wing auxiliary tanks, 42 gal. (42 usable; two 21 gal. tanks in wings at + 24). (See NOTE 1 for data on fuel system.) Oil capacity 10 qt. (-22.5), 9 qts. Minimum (See NOTE 1 for data on oil system.) Control surface movements (See NOTE 12) Serial numbers eligible Model MT-7-420, s/n 51001C and up Production basis Production Certificate No. 11S0 XXXVIII. Model M-4-180V, 2 PCLM (Normal Category) Approved September 6, 2005 (Same as MX-7-180 except for M-4 tail, M-4 maximum weight, seat capacity (2) and door quantity (2) Engine Lycoming 0-360-C1F or 0-360-C4F Fuel 100/100LL minimum grade aviation gasoline Engine limits 180 hp at 2700 rpm, full throttle continuous Propeller and Hartzell constant speed model HC-C2YR-1BF/F7666A (eligible on O-360-C1F only) propeller limits Diameter: Not over 76 in., not under 72 in. Pitch settings at 30 in. sta.: low 12º high 27.8º to 29.8º Avoid continuous operation between 2000 rpm and 2250 rpm Spinner: Hartzell spinner assembly A2298-2 Governor: Woodward H210681 McCauley C290D3(X)/T29 or DC290D1(X)/T12 Sensenich fixed pitch 76EM8S5-0-56 or 76EM8S8-0-56 Diameter: Not over 76 in., not under 76 in., no further reduction permitted. Static rpm at full throttle: Not over 2500 rpm, not under 2400 rpm. For O-360-C1F (modified) avoid continuous operation between 2150 rpm and 2350 rpm. Spinner: Sensenich spinner assembly S76EM Airspeed limits (IAS) Landplane: (See NOTE 11) C.G. range Landplane: (+15.6) to (+19.0) at 2300 lbs. (+11.0) to (+19.0) at 1500 lbs. or less Page 37 of 48 3A23 Straight line variation between points given. Empty weight C.G. range None Maximum weight 2300 lbs. Number of seats 2 at +20 Maximum baggage 170 lbs. at (+20), 200 lbs. (+54) Fuel capacity 47.6 gal. (43 gal. usable; two 23.8 gal. tanks in wings at +24) Optional wing auxiliary tanks, 30 gal. (30 gal. usable; two 15 gal. tanks in wing at +24) (See NOTE 1 for data on fuel system.) Oil capacity 8 qt. (-36.5), 2 qt. minimum (See NOTE 1 for data on oil system.) Control surface Wing flaps Handle full down -7º +1º movements First Notch 0º +1º Second Notch 20º +3º Third Notch 35º +3º Aileron Up 20º +1º Down 20º +1º Elevator Up 25º +2º Down 21º +1º Elevator tab Up 11º +3º Down 25º +1º Rudder Right 21º +1º Left 21º +1º Rudder tab Right 48º +4º Left 48º +4º Serial numbers eligible Model M-4-180V, s/n 47001C and up Production basis Production Certificate No. 11S0 DATA PERTINENT TO ALL MODELS: Datum Wing leading edge Leveling means Leveling lug and mark on bottom side of right wing root. Certification basis Part 3, Civil Air Regulations, effective May 15, 1956 as amended by 3-1 thru 3-5 and 3.705 as amended by 3-7; and 14 CFR part 36 amended thru 36-4* and part 23.955 in lieu of CAR 3.435 for the models M- 5-235C, M-5-180C, M-5-210TC, M-6-235, M-5-200, M-6-180, M-7-235, MX-7-235, MX-7-180, MXT- 7-180, MT-7-235, M-8-235, MX-7-160, MXT-7-160, MX-7-180A, MXT-7-180A, MX-7-180B, M-7- 235A, M-7-235B, M-7-235C, MX-7-180C, M-7-260, MT-7-260, M-7-260C, MX-7-160C, MX-7-180AC and M-4-180V. * Part 36 amendment shown is for the model M-5-235C. For the other models shown, the Part 36 amendment in effect on the certification date of each model was used. Special Certification Rules for the Model M-5-210TC: Part 21.101(b) Amendment 21-42 23.141 23-7 23.909 23-7 23.1041 23-7 23.1043 23-7 23.1047 23-7 23.1093 23-17 23.1143 23-17 23.1183 23-15 23.1305(p) 23-15 23.1527 23-7 23.1583(k) 23-7 Special Certification Rule for the Model MX-7-180: 3A23 Page 38 of 48 14 CFR part 23.1545 Amendment 23-23, October 30, 1978 in lieu of CAR 3.757 (Amendment 3-5, September 1, 1959) Special Certification Rules for the Model MX-7-420, M-7-420AC, M-7-420A and MT-7-420: Part 3, Civil Air Regulations, affective May 15, 1956, as amended through 3-7; and 14 CFR part 36 as amended through 36-14, SFAR 27 as amended through 27-2,* and the following Part 23 requirements for turbine engine installations: 23.45 (-21) 23.939 (-18) 23.1143 (-17) 23.49 (-21) 23.943 (-18) 23.1145 (-18) 23.65 (-21) 23.951 (-15) 23.1155 (-7) 23.75 (-21) 23.955 (-7) 23.1165 (-17) 23.77 (-21) 23.977 (-17) 23.1183 23.173 (-14) 23.991 (-26) 23.1303 (-17) 23.175 (-17) 23.997 (-15) 23.1305 (-26) 23.251 (-0) 23.1013 (-15) 23.1323 (-20) 23.253 (-7) 23.1015 (-15) 23.1337 (-18) 23.335 (-16) 23.1019 (-15) 23.1353 (-20) 23.361 (-26) 23.1027 (-14) 23.1505 (-7) & 3.187 or 23.333 23.371 (-7) 23.1041 (-7) 23.1521 (-21) 23.629 (-31) 23.1043 (-21) 23.1527 (-7) (to include whirl mode) 23.1045 (-7) 23.1529 (-26) 23.863 (-23) 23.1091 (-7) 23.1545 (-23) 23.901 (-18) 23.1093 (-18) 23.1549 (-12) 23.903 (-26) 23.1103 (-7) 23.1557 (-23) 23.905 (-26) 23.1105 (0) 23.1583 (-23) 23.929 (-14) 23.1111 (-17) 23.1587 (-23) 23.933 (-17) 23.1121 (-18) 23.937 (-7) 23.1141 (-18) *Part 36 and SFAR 27 amendments shown are for the model MX-7-420. For the other models shown, the amendments of Parts 36 and 34 in effect on the certification date of each model were used. Type Certificate No. 3A23 issued August 10, 1961 Application for Type Certificate dated November 1, 1957 Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see certification basis) must be installed in the aircraft for certification. In addition, the following items of equipment are required: (A) Stall Warning Indicator, Maule drawing 6016F (B) The following FAA Approved Airplane Flight Manuals are required (Original AFM or any later FAA approved revision is acceptable): 1. Model M-4: AFM dated 3/15/66 with rev. 2 dated 5/1/84 is in effect for all M-4, M-4C, M-4S and M-4T. 2. Model M-4-210, s/n 1001-1005 modified per Maule SL#6, 1001-1035 modified per Maule SL#7 (AD#65-28-04) and s/n 1036-1045, AFM dated 9/24/64 with rev. 1 dated 11/18/64 or AFM dated 3/15/66 with rev. 2 dated 3/15/66. When s/n 1001-1045 modified per Maule SL#15 for 2300# GW, AFM dated 3/15/66 with rev. 3 dated 10/15/68 must be incorporated. 3. Model M-4-210C, s/n 1001C-1074C, 1079C, 1080C, AFM dated 3/15/66 with rev. 2 dated 3/15/66; s/n 1001C-1074C, 1079C 1080C modified per Maule SL#15 for2300# GW and s/n 1075C-1078C, 1081C-1085C, AFM dated 3/15/66 with rev. 3 dated 10/15/68; s/n 1086C-1117C, AFM dated 3/15/66 with rev. 4 dated 6/20/73 Note: Models M-4-210S and T were never produced. 4. Model M-4-220/C, (includes M-4-220, M-4-220C), AFM dated 9/28/66 with rev. 5 dated 5/1/84 Note: Model M-4-220T was never produced. Page 39 of 48 3A23 5. Model M-4-220S, s/n 2001S, AFM dated 9/28/66 (2100# GW) Note: Rev. 1 to this AFM does not apply to this s/n. 6. Model M-4-180C, AFM dated 10/20/70 with rev. A dated 5/1/84 Note: Models M-4-180S and T were never produced. 7. Model M-5-220C, AFM dated 12/28/73 with rev. A dated 5/1/84 8. Model M-5-210C, AFM dated 12/28/73 with rev. B dated 5/1/84 9. Model M-5-235C, s/n 7001C-7026C, 7028C, 7030C-7032C, 7037C, AFM dated 4/6/76, with expanded C.G. limits per Maule SL#36, rev. B dated 11/6/80; s/n 7027C, 7029C, 7033C-7036C, 7038C-7248C, 7250C-7320C, 7322C-7346C, 7348C, 7349C, AFM dated 4/6/76 with rev. B dated 11/6/80; s/n 7350C, 7352C-7355C, 7357C-7362C, 7364C-7367C, AFM dated 4/6/76 with rev. C dated 4/22/81; s/n 7321C, 7347C, 7351C, 7363C, 7369C-7373C, 7375C, 7445C, 7451C, 7460C, 7467C, AFM dated 8/12/81 with rev. A dated 5/1/84. Note: AFMs dated 4/6/76 must have AFM Supplement #13 attached. AFM dated1/13/86 for s/n 7470C, 7478C-7480C, 7484C-7487C, 7515C. 10. Model M-5-180C, AFM dated 4/19/79 for s/n 8001C-8014C, 8016C-8019C, 8021C, 8023C- 8042C, 8044C-8064C, 8068C, 8069C with rev. D dated 4/12/84; AFM dated 6/12/85 for s/n 8070C-8094C 11. Model M-5-200, AFM dated 10/29/82, rev. B dated 6/10/94 12. Model M-5-210TC, AFM dated 2/4/80, rev. B dated 5/1/84 13. Model M-6-235, AFM dated 6/25/81, rev. I dated 6/10/94 for s/n 7249C, 7356C, 7379C-7465C; AFM dated 5/23/85, rev. B dated 6/10/94 for s/n 7466C, 7468C-7473C; AFM dated 2/19/87, rev. C dated 3/3/95 for s/n 7474C and up 14. Model M-6-180, AFM dated 9/15/82, rev. C dated 6/10/94 15. Model M-7-235, AFM dated 11/9/83, rev. F dated 10/17/94 16. Model MX-7-235, AFM dated 10/18/84, rev. F dated 10/28/94 17. Model MX-7-180, AFM dated 12/18/84, rev. E dated 10/28/94 18. Model MX-7-420, AFM dated 6/1/89, rev. E dated 10/26/98 19. Model MXT-7-180, AFM dated 11/9/90, rev. D dated 3/7/02 20. Model MT-7-235, AFM dated 3/20/92, rev. D dated 3/7/02 21. Model M-8-235, AFM dated 8/10/92, rev. D dated 1/26/96 22. Model MX-7-160, AFM dated 11/13/92, rev. G dated 5/24/02 23. Model MXT-7-160, AFM dated 11/13/92, rev. C dated 3/7/02 24. Model MX-7-180A, AFM dated 6/3/93, rev. D dated 3/7/02 25. Model MXT-7-180A, AFM dated 6/3/93, rev. E dated 3/7/02 26. Model MX-7-180B, AFM dated 7/12/93, rev. D dated 3/7/02 27. Model MXT-7-420 removed from TC January 7, 2003 28. Model M-7-235B, AFM dated 10/14/93, rev. E dated 5/24/02 29. Model M-7-235A, AFM dated 3/10/94, rev. C dated 3/7/02 3A23 Page 40 of 48 30. Model M-7-235C, AFM dated 10/10/95, rev C dated 5/20/02 31. Model MX-7-180C, AFM dated 8/26/96, rev. D dated 5/24/02 32. Model M-7-260, AFM dated 4/17/98, rev. F dated 5/24/02 33. Model MT-7-260, AFM dated 4/17/98, rev. E dated 3/7/02 34. Model M-7-260C, AFM dated 10/15/98, rev. E dated 5/24/02 35. Model M-7-420AC, AFM dated 12/17/98, rev. C dated 3/7/02 36. Model MX-7-160C, AFM dated 3/12/99, rev. E dated 3/7/02 37. Model MX-7-180AC, AFM dated 5/4/2000, rev. A dated 3/7/02 38. Model M-7-420A, AFM dated 11/20/2000, rev. C dated 3/7/02 39. Model MT-7-420, AFM dated 1/7/2003, rev.A dated 3/5/04 40. Model M-4-180V, AFM dated 9/6/2005 Note 1 Current weight and balance report including list of equipment included in certificated empty weight, and loading instructions when necessary, must be provided for each aircraft at the time of original certification. The certificated empty weight and corresponding center of gravity location must include unusable fuel and undrainable oil as follows: Fuel 18 lbs. (+24) (20 gal. main) M-4 series (except M-4-180V), M-4-210 series, M-4-220 series, M-4-180 series, M-5-210C, M-5-220C, M-5-210TC, M-5-235C, M-5-200, M-6-235, M-6-180, M-7-235, MX-7-235, MX-7-180, MXT-7-180, MT-7-235, M-8-235, MX-7-160, MXT-7-160, MX-7-180A, MXT- 7-180A, MX-7-180B, M-7-235B, M-7-235A, M-7-235C, MX-7-180C Fuel 27.6 lbs. (+24) (21.5 gal. main) M-7-235, MX-7-235, MX-7-180, MXT-7-180, MT-7-235, M-8-235, MX-7-160, MXT-7- 160, MX-7-180A, MXT-7-180A, MX-7-180B, M-7-235B, M-7-235A, M-7-235C, MX-7- 180C, M-7-260, MT-7-260, M-7-260C, MX-7-160C, M-6-235, MX-7-180AC, M-5-210C*, M-5-220C*, M-5-235C*, M-5-180C*, M-5-210TC*, M-5-200*, M-4-180V *with Modification Kit No. 15 installed. Fuel 16.2 lbs. (+24) (40.6 gal. main)* MX-7-420 (tank configuration A) Fuel 31 lbs. (+24) (43 gal. main)* MX-7-420 (tank configuation C), M-7-420AC, M-7-420A, MT-7-420 * Two main tanks considered one tank Oil 8 lbs. (-37) M-4 series Oil 6 lbs. (-37) M-4-220 series, M-4-180 series, M-4-210 series, M-5-220C, M-5-210C Oil 6 lbs. (-36.5) M-5-180, M-5-210TC, M-5-200, M-6-180, MX-7-180, MXT-7-180, MX-7-160, MXT-7- 160, MX-7-180A, MXT-7-180A, MX-7-180B, MX-7-180C, MX-7-160C, MX-7-180AC, M- 4-180V Oil 6 lbs. (-34) M-5-235C, M-6-235, M-7-235, MX-7-235, MT-7-235, M-7-235B, M-7-235A, M-7-235C, M-7-260, MT-7-260, M-7-260C Oil 20 lbs. (-22.5) MX-7-420, M-7-420AC, M-7-420A, MT-7-420 Note 2 The following placards shall be displayed: Page 41 of 48 3A23 (A) In front of and in clear view of the pilot: 1. For all M-4 models (except M-4-180V): THIS AIRPLANE MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS, AND MANUALS. For M-4-180V and M-5 and subsequent models: THIS AIRPLANE MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATION LIMITATIONS STATED IN THE FLIGHT MANUAL AND IN THE FORM OF PLACARDS AND MARKINGS. 2. NO ACROBATIC MANEUVERS, INCLUDING SPINS, APPROVED. or AEROBATIC MANEUVERS, INCLUDING SPINS, ARE NOT APPROVED. 3. For M-4 series (except M-4-180V), M-5 series, M-6 series, M-7-235, and MX-7-235: ROUGH AIR OR MANEUVERING SPEED 125 MPH. For M-4-180V: ROUGH AIR OR MANEUVERING SPEED 109K (125 MPH). For MX-7-180: ROUGH AIR OR MANEUVERING SPEED: 129 MPH (112K) For MX-7-420, M-7-420AC, M-7-420A, and MT-7-420: ROUGH AIR OR MANEUVERING SPEED IS 121 MPH (105K) For MXT-7-180, MT-7-235, M-8-235, MX-7-160, MXT-7-160, MX-7-180A, MXT-7-180A, MX-7-180B, M-7-235B, M-7-235A, M-7-235C, MX-7-180C, M-7-260, MT-7-260, M-7-260C, MX-7-160C, MX-7- 180AC: MANEUVERING SPEED: 125 MPH IAS (109K). (Knots and MPH may be interchanged) 4. One of the following placards must be installed in the M-4 and M-4-210: a. THIS AIRCRAFT APPROVED FOR DAY VFR FLIGHT ONLY. b. THIS AIRCRAFT APPROVED FOR DAY OR NIGHT VFR FLIGHT. (If equipment and instruments conforming to 14 CFR part 91.33(c) are installed.) c. THIS AIRCRAFT APPROVED FOR DAY OR NIGHT VFR OR IFR FLIGHT. (If equipment and instruments conforming to §91.33(d) and §91.170 are installed.) The following placard must be installed on all models except the M-4 and M-4-210: THIS AIRCRAFT APPROVED FOR DAY OR NIGHT IFR NON-ICING FLIGHT WHEN EQUIPPED IN ACCORDANCE WITH FAR 91 OR FAR 135. 5. SEE LOADING INSTRUCTIONS IN WEIGHT AND BALANCE SECTION OF AIRPLANE FLIGHT MANUAL. 6. FUEL REMAINING IN TANK WHEN INDICATOR READS ZERO CANNOT BE USED SAFELY IN FLIGHT. 7. For M-4-180V, M-5 and subsequent models except -420 series: DO NOT TURN OFF ALTERNATOR IN FLIGHT EXCEPT IN CASE OF EMERGENCY. 8. For -420 series: COMPASS UNRELIABLE WHEN HEATED INLET IS ON. 9. For -235 series (when using -6R propeller): 3A23 Page 42 of 48 DO NOT EXCEED 23 INCHES M.P. BELOW 2050 RPM. For M-5-200: FOR CONTINUOUS OPERATION DO NOT EXCEED 24 INCHES OF MANIFOLD PRESSURE BELOW 2350 RPM. For M-5-210TC: NOT MORE THAN 34" OF MANIFOLD PRESSURE AT PROPELLER SPEEDS LESS THAN 2350 RPM. and NOT LESS THAN 20" OF MANIFOLD PRESSURE AT PROPELLER SPEEDS BETWEEN 2250 AND 2450 RPM. For M-4-180V: With Hartzell HC-C2YR-1BF/F7666A: AVOID CONTINUOUS OPERATION 2000-2250 RPM With Sensenich fixed pitch propeller and O-360-C1F(modified): AVOID CONTINUOUS OPERATION 2150-2350 RPM 10. For MXT-7-180A: DEMONSTRATED CROSSWIND 15 MPH. For M-4-180V: DEMONSTRATED CROSSWIND 12K (14 MPH) and TAKEOFF WITH 20° FLAPS 11. In addition to the above placards, the following is required when Fli-Lite 3000 MK IIIA skis are installed: For M-4 series: SKIPLANE LIMITATIONS: MAXIMUM GROSS WEIGHT 1850 LBS. DO NOT EXCEED 160 MPH. SKI OPERATION PROCEDURES: SET SELECTOR TO POSITION DESIRED THEN OPERATE PUMP UNTIL MAXIMUM PRESSURE IS DEVELOPED. For M-4-210C series: SKIPLANE LIMITATIONS: MAXIMUM GROSS WEIGHT 2100 LBS. DO NOT EXCEED 160 MPH. SKI OPERATION PROCEDURES: SET SELECTER TO POSITION DESIRED THEN OPERATE PUMP UNTIL MAXIMUM PRESSURE IS DELVELOPED. Additional placards listed in the applicable AFM Supplement for skiplane operation must be installed. 12. For M-4, s/n 3-91, M-4-210, s/n 1001-1043, M-4-210C, s/n 1001C-1010C, or if no ashtray installed per Maule drawing 6007B: At the top of the instrument panel, to the right of the radio group: NO SMOKING 13. On the instrument panel or wing root panel at the auxiliary fuel tank transfer switches, (if installed): FUEL TRANSFER PUMPS PUSH FOR PUSH FOR AUX. QUANT. AUX. QUANT. LEFT RIGHT FUEL CAPACITY: MAIN TANKS (*) GAL. USABLE EACH, AUX. TANKS (**) GAL. USABLE EACH TANK. * 20 gal. except M-7/MX-7/MXT-7/MT-7/M-8 series may have either 20 gal. or 21.5 gal. and M-4-180V has 21.5 gal. ** For M-4 (except M-4-180V) and M-5 series: 11.5 gal. For M-6-180: 13.0 gal. For M-6-235, s/n 7249C-7473C: 13.0 gal. For M-6-235, s/n 7474C and up, M-4-180V: 15.0 gal. For M-7/MXT-7/MT-7/M-8 series Page 43 of 48 3A23 and MX-7 series except those listed below: 15.0 or 21.0 gal. For MX-7-420/MX-7-180/MX-7-235: 15.0 gal. (B) Located on the flap handle: 1. For M-4 series (all except M-4-180V) and M-5-235C, s/n 7001C-7248C, 7250C- 7320C, 7322C-7346C, 7348C-7350C, 7352C-7362C, 7364C-7368C, M-5-180, s/n 8001C-8022C, M-5-210C (all), M-5-220C (all), M-5-210TC (all): FLAPS - PULL ON/ 15º TAKEOFF/ 35º LANDING or for M-5-235C, s/n 7321C, 7347C, 7351C, 7363C, 7369C and up, M-5-200, s/n 8015C and up, M-5-180C, s/n 8023C and up, and for M-5-235C, s/n 7001C-7248C, 7250C-7320C, 7322C-7346C, 7348C-7350C, 7352C-7362C, 7364C-7368C with Maule SL#44 c/w, M-5-180C, s/n 8001C-8022C with Maule SL#49 c/w, all M-5-210C with Maule SL#46 c/w, all M-5-220C with Maule SL#48 c/w, all M-5-210TC with Maule SL#47 c/w: FLAPS - PULL ON/ 20º TAKEOFF/ 40º LANDING 2. For M-6-180/-235, M-7-235/-235A/-235B*/-235C/-260/-260C, MX-7-180/-180A*/-180B*/-180C/-180AC/- 235/-160*/-160C, M-8-235*: FLAPS/PULL ON/ 2ND NOTCH/ TAKEOFF/ 4TH NOTCH/ LANDING * 4TH NOTCH" is replaced by "3RD NOTCH" for M-7-235B S/N's 23001C thru 23003C, 23005C thru 23010C, and 23012C, MX-7-180A S/N's 20001C thru 20026C, 20028C, 20029C, and 20031C thru 20035C, MX-7-180B S/N's 22003C, 22006C, and 22007C, MX-7-160 S/N's 19001C thru 19034C and 19041C M-8- 235 S/N’s 15001C thru 15005C unless Mod Kit #11 is complied with. 3. For MX-7-420, MXT-7-180/-180A/-160/-420, MT-7-235/-260/-420, M-8-235, M-7-420AC, M-7-420A, M- 4-180V: FLAPS/PULL ON/2ND NOTCH/TAKEOFF/3RD NOTCH/LANDING (C) Located at the main fuel tank selector valve on left kick panel: 1. For M-4, s/n 23, 25-45: TAKE + LANDING LEFT ONLY 21 GAL. RIGHT 21 GAL. OFF 2. For M-4, s/n 24, 46-94, 1C-11C, 1S-3S, 1T-3T: TAKEOFF + LANDING BOTH TANKS LEFT 21 GAL. RIGHT 21 GAL. OFF 3. For M-4-220C, (s/n 2125C, 2127C, 2128C, 2137C, 2138C, 2140C and up), M-5-220C, M-5-200, M- 5-210TC, M-5-235C/-180C, M-6-235C/-180C, MX-7-235/-180, M-7-235/-235A/-235B, MXT-7- 180, MT-7-235, M-8-235, MX-7-160, MXT-7-160, MX-7-180A, MXT-7-180A, MX-7-180B, M-7- 235C, MX-7-180C, M-7-260, MT-7-260, M-7-260C, MX-7-180AC: FUEL SELECTOR VALVE LEFT: 20* GAL. OFF BOTH RIGHT: 20* GAL. *or 21.5 gal. for M-7/MXT-7/MT-7/M-8 series and MX-7-160/-180/-180A/-180B/-180C/-180AC and M-4-180V or for M-4-220C and early M-5-235C with SP2321-B3 Fuel Selector Valve: (Not applicable to M-5- 235C s/n 7321C, 7347C, 7351C, 7363C, 7369C and up.): LEFT 20 GAL. RIGHT 20 GAL. OFF 3A23 Page 44 of 48 4. For M-4-210(C,S) and M-5-210C: LEFT LEFT 20 GAL. 20 GAL. RIGHT or BOTH (Use with 10049E-7 Valve) 20 GAL. RIGHT (Use with SP-2263-B3 or10049E-6 Valve) 20 GAL. 5. For -420 series: FUEL SELECTOR VALVE BOTH ON OFF (D) In rear cabin area: 1. For M-4 (except M-4-180V) and M-5 series: BAGGAGE 250 LBS. MAXIMUM. FOR LOADING INSTRUCTIONS SEE WEIGHT AND BALANCE INFORMATION. 2. For M-5 and subsequent models (except M-4-180V): CARGO OR BAGGAGE LIMITATIONS MAX. LOAD AREA "A" 170 LBS. MAX. LOAD AREA "B" 350 LBS. MAX. LOAD AREA "C" 250 LBS. 3. For models with optional 5th seat installed and M-7/MT-7 series: CHECK WEIGHT AND BALANCE CAREFULLY WHEN USING 5TH SEAT OR LOADING REAR/CARGO/BAGGAGE. MAXIMUM REAR SEAT LOADING 170 LBS. 4. For M-7-235, s/n 4001C-4061C: (Unless Maule SK#15 is c/w) BALLAST IN AFT FUSELAGE SHOULD BE REMOVED FOR LARGE AFT CABIN LOADS. THIS BALLAST SHOULD BE IN PLACE IN THE AFT FUSELAGE STORAGE FOR LIGHT/FORWARD LOADING. 5. For M-4-180V: CHECK WEIGHT AND BALANCE CAREFULLY WHEN LOADING REAR/CARGO/BAGGAGE. CARGO OR BAGGAGE LIMITATION MAX. LOAD AREA “A” 170 LBS. MAX. LOAD AREA “B” 200 LBS. Note 3 The models Bee Dee M-4 and M-4, s/n 3-23, 25-45 fuel systems do not comply with CAR 3.433 and 3.434 for horsepower greater than 125 at the best angle of climb speed, which is the most critical flight attitude, unless optional Modification Kit No. 36 is installed. Note 4 The following aircraft were manufactured at Jackson, Michigan: Models Serial numbers M-4 3-94 M-4C 1C-11C M-4S 1S-3S M-4T 1T-3T M-4-210 1001-1045 M-4-210C 1001C-1074C, 1079C, 1080C Page 45 of 48 3A23 M-4-220C 2001C-2018C M-4-220S 2001S Note 5 Optional wing tips (ref. Maule drawing 9041F) have been approved for all M-4 series models except Bee Dee M-4 s/n 3-14. Note 6 Equipment approved for all models is listed on the Required and Optional Equipment Lists. Note 7 The following aircraft are eligible for manufacture under Production Certificate No. 11S0: Models Serial numbers M-4 Series (Spare parts) M-5-220C (Spare parts) M-5-210C (Spare parts) M-5-235C (Spare parts) M-5-180C (Spare parts) M-5-200 (Spare parts) M-5-210TC (Spare parts) M-6-235 7249C, 7356C, 7379C and up M-7-235 4001C and up, and 12001C with STC SA2661SO (known as M-7-420) M-6-180 8020C, 8065C-8067C and up MX-7-235 10001C and up MX-7-180 11001C and up MX-7-420 13001C and up MXT-7-180 14000C and up MT-7-235 18001C and up M-8-235 15001C and up MX-7-180A 20001C and up MXT-7-180A 21001C and up MX-7-160 19001C and up MXT-7-160 17001C and up MX-7-180B 22001C and up M-7-235B 23001C and up M-7-235A 24001C and up M-7-235C 25001C and up MX-7-180C 28001C and up M-7-260 26001C and up MT-7-260 27001C and up M-7-260C 30001C and up M-7-420AC 29001C and up MX-7-160C 34001C and up MX-7-180AC 33001C and up M-7- 420A 35001C and up MT-7-420 51001C and up M-4-180V 47001T and up Note 8 For M-4-220C, s/n 2178C and up, and all other M-4-220 airplanes which have complied with Maule SL#27, the maximum continuous throttle operation restriction may be removed and replaced by 220 hp - 2800 rpm all operations. Airplane Flight Manual Supplement No. 3 must be attached to

All MAULE M-6 type certificate