MAULE M-7-235C Technical specifications

FAA APPROVED
FOR
MAULE M-7-235C
Airplane Serial No.__________________
Registration No.____________________
THIS DOCUMENT MUST BE KEPT IN THE AIRPLANE AT ALL TIMES.
FAA APPROVED:
Manager, Aircraft Certification Office
Federal Aviation Administration
Atlanta, Georgia USA
DATE: October 10, 1995
Performance That Counts!
2099 Georgia Highway 133 South •Moultrie, GA 31788 •
[phone] •Fax: [phone] •www.mauleairinc.com

MAULE AEROSPACE TECHNOLOGY, INC.
AIRPLANE FLIGHT MANUAL
MAULE M-7-235C
Page i
LOG OF REVISIONS
REV. TO
PAGES
DESCRIPTION APPROVAL AND DATE
A 13 Clarified noise data.
B 3, 5,
11-16
Changed primary airspeed units to knots.
C 11 In 3.3.B. RECOMMENDED FLAP SETTINGS,
corrected landing flap setting to read: - Normally
Fourth Notch (48°/full flaps).
D 6,
9,
10,
11,
24
Described placard notation and removal of aux.
quantity buttons if JPI EDM-930 units are in-
stalled. In rear cabin area revised cargo weight
limitation placard and added loading caution
placard for 4-seater. Added limit placard for op-
tional swing out windows. Added to Operating
Check Lists for Parking Brake when in OFF po-
sition to PUSH KNOB COMPLETELY AGAINST
INSTRUMENT PANEL. Revised Section VI re
Owner Alert system, the availability of data
downloads and Maule Parts Catalog DVD.
___________________
Manager, Atlanta Aircraft
Certification Office, FAA
Atlanta, GA
Date:______________
E 6 Added JPI EDM-900/930. ___________________
Manager, Southeast
Flight Test Section, AIR-
712, FAA
Atlanta, GA
Date:________________

MAULE AEROSPACE TECHNOLOGY, INC.
AIRPLANE FLIGHT MANUAL
MAULE M-7-235C Page ii
LOG OF SUPPLEMENTS
SUP.
NO. NO. OF PAGES DESCRIPTION
APPROVAL
DATE
1 2 Installation of McCauley B3D32C414-[ ]/[ ]-82NDA-2 (80") or –4 (78") Propeller with Lycoming
O-540-B4B5 Engine per Maule Dwg 5490E. 04/26/96
2 2 Inst. of McCauley B3D32C414-[ ]/[ ]-82NDA-4 Propeller and Lycoming O-540-B4B5 Engine in
Switzerland per Maule Dwg 5490E. Rev. B 01/29/97
4 9 Inst. of EDO 797-2500 Amphibious Floats per Maule Dwg 9139A. (09/22/97) Rev. A 08/19/02
5 8 Inst. of Aqua 2400 Floats per Dwg 9135A, rev. Dor later. Rev. B 08/19/02
6 21 Inst. of Wipline 3000 Amphibious Floats per Maule Dwg 9188A. (05/17/99) Rev. A 08/19/02
7 2 Installation of Hartzell HC-C2YR-1BF/8477D-6 or HC-C3YR-1RF/F-7693(F)-( ) Propeller per
Maule Drawing 5279F. Rev. B 01/28/04
8 6 English to Metric Conversion Charts - required in aircraft when registered in Canada. 09/03/99
9 9 Inst. of S-TEC System 50 Two Axis Autopilot ST-418-50 (14v) - Maule Dwg 9193A. 01/05/00
10 9 Inst. of S-TEC System 30 Two Axis Autopilot ST-810-30 (14v) - Maule Dwg 9197A. (Land) 01/21/00
11 9 Inst. of S-TEC System 30 Two Axis Autopilot ST-810-30 (14v) - Maule Dwg 9197A. (Sea) 01/21/00
12 9 Inst. of S-TEC System 50 Two Axis Autopilot ST-609-50 (28v) - Maule Dwg 9200A. 02/14/00
13 6 Inst. of S-TEC System 55 Two Axis Autopilot ST-620 (14v) - Maule Dwg 9196A. (Land) 04/04/00
14 6 Inst. of S-TEC System 55 Two Axis Autopilot ST-620 (14v) - Maule Dwg 9196A. (Sea) 04/04/00
15 8 Inst. of S-TEC System 20 Single Axis Autopilot ST-810-20 (14v) - Maule Dwg 9197A. (Land) 03/20/00
16 8 Inst. of S-TEC System 20 Single Axis Autopilot ST-810-20 (14v) - Maule Dwg 9197A. (Sea) 03/20/00
17 8 Inst. of S-TEC System 20 Single Axis Autopilot ST-820-20 (28v) - Maule Dwg 9201A. 03/20/00
18 7 Inst. of S-TEC System 40 Single Axis Autopilot ST-418-40 (14v) - Maule Dwg 9193A. 10/29/01
19 7 Inst. of S-TEC System 40 Single Axis Autopilot ST-609-40 (28v) - Maule Dwg 9200A. 10/29/01
- 4 Inst. of S-TEC System 20 Single Axis Autopilot ST-872-20 (28v) - Maule Dwg 9211A. (Land) 06/25/01
- 5 Inst. of S-TEC System 30 Two Axis Autopilot ST-872-30 (28v) - Maule Dwg 9211A. (Land) 06/25/01
- 5 Inst. of S-TEC System 20 Single Axis Autopilot ST-872-20 (28v) - Maule Dwg 9211A. (Sea) 06/25/01
- 5 Inst. of S-TEC System 30 Two Axis Autopilot ST-872-30 (28v) - Maule Dwg 9211A. (Sea) 06/25/01
- 6 Inst. of EDO 628-2960 Non-Amphib. or 597-2790 Amphib. Floats - STC No. SA01695AT. 09/24/01
- 5 Inst. of S-TEC System 20 Single Axis Autopilot ST-873-20 (14/28v) - Maule Dwg 9212A. 10/15/01
- 5 Inst. of S-TEC System 30 Two Axis Autopilot ST-873-30 (14/28v) - Maule Dwg 9212A. 10/15/01
- 5 Installation of Apollo MX20 Multi-Function Display - Maule Drawing 7265A. 08/15/02
- 3 Installation of GARMIN GNS-430 (GPS/NAV/COMM) System - Maule Dwg 7205A. 01/03/01
- 3 Installation of GARMIN GNC-300XL (GPS/COMM) System - Maule Drawing 7207A. 01/03/01
- 3 Installation of GARMIN GNC-250XL (GPS/COMM) System - Maule Drawing 7209A. 01/03/01
- 3 Installation of Bendix-King KLX-135A (GPS/COMM) System - Maule Drawing 7219A. 01/03/01
- 8 Installation of GARMIN GNC-420 (GPS/COMM) System - Maule Drawing 7251A. 06/30/03
- 9 Installation of GARMIN GNS-530 (GPS/NAV/COMM) System - Maule Drawing 7253A. 06/30/03
- 4 Installation of GARMIN GTX-330 Mode S Transponder Traffic Information System (TIS) -
Maule Drawing 7255A. 06/30/03
- 3 Operation of aircraft when Micro AeroDynamics Vortex Generator System is installed in ac-
cordance with Maule Drawing 9177A. 12/16/05
- 2 Installation of McCauley B2D37C224/90RA-4 (86") Prop with Lyc. O-540-J/IO-540-W Engine. 04/03/12

MAULE AEROSPACE TECHNOLOGY, INC.
AIRPLANE FLIGHT MANUAL
MAULE M-7-235C Page iii
TABLE OF CONTENTS
ITEM
COVER PAGE
LOG OF REVISIONS…………………………………………………….. i
LOG OF SUPPLEMENTS……………………………………………..… ii
TABLE OF CONTENTS………………………………………………..... iii & iiii
SECTION I GENERAL
Plan View…………………..………………………………………..
1
1.1 Maximum Weight….………………………………………. 2
1.2 Center of Gravity Limits..…………………………………. 2
1.3 Maneuvers……………….………………………………… 2
1.4 Fuel Capacity…………….………………………………... 2
SECTION II LIMITATIONS
2.1 Airspeed Limits……………..………………………………
3
2.2 Power Plant Limits…………..…………………………….. 4
2.3 Flight Load Factors…………..……………………………. 5
2.4 Placards………………………..…………………………… 5
SECTION III NORMAL PROCEDURES
3.1 Preflight Inspection……………..………………………….
7
3.2 Operating Check Lists…………..………………………… 8
3.3 Normal Flight Operations………..
………………………...
11
3.4 Door-Off Operation………………..………………………. 13
3.5 Noise Levels..………………………..…………………….. 13
3.6 Anti-Collision Light…………………..…………………….. 13
SECTION IV EMERGENCY PROCEDURES
4.1 Emergency Basic Rules……………..…………………….
14
4.2 Engine Emergency Shut Down………..…………………. 14
4.3 Engine Fire During Starting……………..………………... 14
4.4 Engine Fire After Starting………………..……………….. 14
4.5 Emergency Exit on the Ground…………..
……………….
14
4.6 Takeoff Abort……………………………….……………… 14
4.7 Engine Failure After T.O. or Forced Landing….……….. 14
4.8 Partial Power Failure During Flight of After T.0..………. 15
4.9 Complete Power Failure During Flight………….………. 15
4.10 Engine Airstart……………………………………..………. 15
4.11 Electrical Fire……………………………………….………
15
4.12 Engine Fire During Flight………………………….……… 16
4.13 Smoke and Fume Elimination…………………….……… 16
4.14 Structural Damage………………………………….…….. 16
4.15 Recovery From Inadvertent Spins………………….…… 16
4.16 Alternator Failure…………………………………….……. 16

MAULE AEROSPACE TECHNOLOGY, INC.
AIRPLANE FLIGHT MANUAL
MAULE M-7-235C Page iiii
TABLE OF CONTENTS
SECTION V WEIGHT AND BALANCE AND EQUIPMENT LIST
5.1 Weight and Balance Data………………………………....
17
Equipment Change Sheet………………………………… 23
Required Equipment List ………Provided for each Airplane
SECTION VI AIRCRAFT SERVICING, HANDLING AND MAINTENANCE
6.1 Introduction…………………………………………………
24
6.2 Airplane Inspection Period…………………………….…. 24
6.3 Preventive Maintenance that may be Accomplished by
a Certified Pilot…………………………………………..… 24
6.4 Alterations or Repairs to Airplane…………………….…. 24
SECTION VII MANUFACTURER'S DATA
Optional Equipment List………..Provided for each Airplane

MAULE AEROSPACE TECHNOLOGY, INC.
AIRPLANE FLIGHT MANUAL
MAULE M-7-235C
SECTION I
GENERAL
PAGE 1

MAULE AEROSPACE TECHNOLOGY, INC.
AIRPLANE FLIGHT MANUAL
MAULE M-7-235C
SECTION I
GENERAL
SECTION I
GENERAL: NORMAL CATEGORY OPERATION
1.1 MAXIMUM WEIGHT: 2500 Pounds
1.2 CENTER OF GRAVITY LIMITS: +15.0 to +20.5 @ 2500 lbs.
+12.0 to +20.5 @ 1760 lbs. or less
Straight line variation between points given
Datum: Wing Leading Edge
NOTE: It is the responsibility of the pilot to assure that the airplane is property loaded. Re-
fer to the Weight and Balance Data for baggage/cargo loading recommendations
and loading graphs.
////////////////////////
////CAUTION////
////////////////////////
CHECK WEIGHT AND BALANCE CAREFULLY, ESPECIALLY WHEN USING
THE 5TH SEAT, IF INSTALLED, OR WHEN CARGO OR BAGGAGE IS CAR-
RIED IN THE REAR CABIN AREA. ALSO, FLIGHT PLANNING SHOULD IN-
CLUDE ALLOWANCE FOR FORWARD C.G. SHIFT WITH FUEL BURN.
1.3 MANEUVERS: Only Normal Category Maneuvers including Stalls, Lazy Eights, Chandelles
and steep turns involving bank angles not greater than 60°are approved in
this airplane.
////////////////////////
////CAUTION////
//////////////////////// AEROBATICS AND INTENTIONAL SPINS PROHIBITED.
1.4 FUEL CAPACITY: Usable and Unusable Fuel: See Table Below
Fuel Capacity - See Instrument Panel Placard for Tank configuration installed
in this aircraft
Tank
Config. Tank Location Usable Fuel (Gal) Unusable Fuel (Gal)
A Main
Aux. 20.0 15.0 1.5 0.0
B Main
Aux. 20.0 21.0 1.5 0.0
C Main
Aux. 21.5 15.0 2.3 0.0
D Main
Aux. 21.5 21.0 2.3 0.0
////////////////////////
////CAUTION////
////////////////////////
FUEL REMAINING IN TANK WHEN INDICATOR READS EMPTY
CANNOT BE USED SAFELY IN FLIGHT.
FAA APPROVED
DATE: 10/10/95 PAGE 2

MAULE AEROSPACE TECHNOLOGY, INC.
AIRPLANE FLIGHT MANUAL
MAULE M-7-235C
SECTION II
LIMITATIONS
SECTION II
LIMITATIONS
2.1 AIRSPEED LIMITS: All airspeeds are Indicated Airspeeds (IAS).
A. AIRSPEED INDICATOR MARKINGS:
Red Radial, (VNE) - 158K (182 mph)
Yellow Arc, Caution Range - 128 – 158K (147 – 182 mph)
Green Arc, Normal Operating Range – 54 - 128K (62 - 147 mph)
White Arc, Flap Operating Range – 43 - 83K (50 - 95 mph)
B. EXPLANATION OF AIRSPEED INDICATOR MARKINGS:
Red Radial Line - Never Exceed Speed (VNE) 158K (182 mph): Maximum safe
airspeed in smooth air.
Yellow Arc - Caution Range, 128 – 158K (147 – 182 mph): Operation in this
speed range should be conducted only in smooth air and con-
trol movements should not be large or abrupt.
Green Arc - Normal Operating Range, 54 - 128K (62 - 147 mph): Extends
from flaps up, power off stall speed at 2500 lbs. (VS1) to design
cruise speed (VC).
White Arc - Flap Operating Range, 43 - 83K (50 - 95 mph): Extends from
full flap, power off minimum stall speed at 2500 lbs. (VSO) to the
Maximum flaps extended speed (VFE).
FAA APPROVED: 10/10/95
Rev. B dated: 03/07/02 PAGE 3

MAULE AEROSPACE TECHNOLOGY, INC.
AIRPLANE FLIGHT MANUAL
MAULE M-7-235C
SECTION II
LIMITATIONS
2.2 POWER PLANT LIMITS:
Engine: Lycoming O-540-J1A5D, IO-540-W1A5D, O-540-J3A5,
IO-540-W1A5, or O-540-B4B5
Engine Limits: 235 hp @ 2400 rpm, Full Throttle Continuous
2575 rpm for B4B5
Propeller:
Constant Speed Hartzell: HC-C2YR-1BF/F8468A-6R (78") or -3R (81")
(Use -3R with 7:00 tires or larger/26 psi minimum air
pressure)
McCauley:
B3D32C414-C/G-82NDA-4 (78") or -2 (80")
(use with J or W engines only) or
B2D37C224-B/G-90RA-9 (81")
(Use -9 with 7:00 tires or larger/26 psi minimum air
pressure; use –2 with 7:00 tires or larger)
Fuel: 100/100LL Minimum Grade Aviation Gasoline
Engine Instrument Markings:
Cylinder Head Temperature: Green Arc - Normal Operating Range,
200°F - 435°F
Red Radial - Operating Limit, 500°F
Oil Temperature: Green Arc - Normal Operating Range,
140°F - 245°F
Red Radial - Operating Limit, 245°F
Oil Pressure: Green Arc - Normal Operating Range, 55
to 95 PSI
Yellow Arc - Caution Range, 25 to 55 PSI
and 95 to 115 PSI
Red Radial - Minimum Operating Pressure,
25 PSI
Red Radial - Maximum Operating Pressure,
115 PSI
Manifold Pressure Green Arc - Normal Operating Range,
14.5 to 29 ins. of Mercury
Fuel Pressure
(O-540 only) Green Arc - Normal Operating Range, 0.5 to 8 PSI
Red Radial - Minimum Pressure, 0.5 PSI,
Maximum Pressure, 8.0 PSI
FAA APPROVED
DATE: 10/10/95 PAGE 4

MAULE AEROSPACE TECHNOLOGY, INC.
AIRPLANE FLIGHT MANUAL
MAULE M-7-235C
SECTION II
LIMITATIONS
2.2 POWER PLANT LIMITS: (Cont’d)
Fuel Flow (IO-540 only) Red Radial - Maximum, 8.9 psi or 26.9 gph
Tachometer:
(J and W only) Green Arc - Normal Operating Range, 2050 - 2400 RPM
Red Radial - Maximum RPM, 2400 RPM
Tachometer:
(O-540-B4B5 only) Green Arc - Normal Operating Range, 2200 - 2575 RPM
Red Radial - Maximum RPM, 2575 RPM
/////////////////////////
////CAUTION////
/////////////////////////
DO NOT EXCEED 23 INCHES M.P. BELOW 2050 RPM. WHEN EQUIPPED
WITH THE HARTZELL –6R (78") PROP. THIS IS A VIBRATORY STRESS
LIMITATION WHICH APPLIES ONLY TO THIS MODEL PROPELLER.
2.3 FLIGHT LOAD FACTORS: Flaps Fully Retracted: 3.8g Positive to 1.5g Negative
Flaps Extended: 1.9g Positive to 0g Negative
NOTE: DESIGN MANEUVERING SPEED: The maximum safe airspeed at which full
aerodynamic controls can be applied (VA) is 109K (125 mph). This airspeed is
not marked on the airspeed indicator.
2.4 PLACARDS:
The following placards are in the cockpit in clear view of the pilot:
FAA APPROVED: 10/10/95
Rev. B dated: 03/07/02 PAGE 5
THIS AIRPLANE MUST BE OPERATED AS A NORMAL CATEGORY AIR-
PLANE IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN
THE FLIGHT MANUAL AND IN THE FORM OF PLACARDS AND MARKINGS.
NO AEROBATIC MANEUVERS INCLUDING SPINS, APPROVED.
MANEUVERING SPEED 109K (125 MPH) IAS.
SEE LOADING INSTRUCTIONS IN WEIGHT AND BALANCE SECTION
OF AIRPLANE FLIGHT MANUAL.
THIS AIRPLANE APPROVED FOR DAY OR NIGHT IFR NON-ICING FLIGHT WHEN
EQUIPPED IN ACCORDANCE WITH FAR 91 OR FAR 135.
DO NOT TURN OFF ALTERNATOR IN FLIGHT EXCEPT IN CASE OF EMERGENCY.
FUEL REMAINING IN TANK WHEN INDICATOR READS ZERO CANNOT BE USED
SAFELY IN FLIGHT.

MAULE AEROSPACE TECHNOLOGY, INC.
AIRPLANE FLIGHT MANUAL
MAULE M-7-235C
SECTION II
LIMITATIONS
When equipped with Hartzell –6R (78”) 2 blade propeller:
DO NOT EXCEED 23 INCHES M.P. BELOW 2050 RPM.
At the main fuel tank selector valve on the left kick panel:
FUEL SELECTOR VALVE
LEFT: * GAL.
OFF BOTH
RIGHT: * GAL.
On the instrument panel at the auxiliary tank transfer switches:
FUEL TRANSFER PUMPS
PUSH FOR
AUX. QUANT. PUSH FOR AUX. QUANT.
LEFT RIGHT
NOTE: If JPI EDM-900/930 units are installed, the PUSH FOR AUX. QUANT. buttons and placards are not installed.
However, FUEL TRANSFER PUMPS and LEFT and RIGHT placards are used as below:
FUEL TRANSFER PUMPS
LEFT RIGHT
FUEL CAPACITY: MAIN TANKS * GAL. USABLE EACH, AUX. TANKS
*GAL. USABLE EACH. (TANK CONFIGURATION ____)
*Instrument Panel Placard will show capacity of the tanks installed in this aircraft. See Table on Page 2 for capacity of
available tank configurations.
On flap control handle:
FLAPS / PULL ON / 2ND NOTCH / TAKEOFF / 4TH NOTCH / LANDING.
In rear cabin area:
In rear cabin area when 5
th
seat is installed: Or when 5
th
seat is not installed:
CHECK WEIGHT AND BALANCE CAREFULLY WHEN
USING 5
TH
SEAT OR LOADING REAR/ CARGO/ BAG-
GAGE. MAXIMUM REAR SEAT LOADING IS 170 LBS.
CHECK WEIGHT AND BALANCE CA-
REFULLY WHEN LOADING
REAR/CARGO/BAGGAGE.
On the lower window frame near the latch when optional swing out windows are installed:
WINDOW MUST BE CLOSED ABOVE 120 MPH
CARGO OR BAGGAGE LIMITATIONS
MAX. LOAD AREA "A" 100 LBS.
MAX. LOAD AREA "B" 175 LBS.
MAX. LOAD AREA "C" 125 LBS.
FAA APPROVED:10/10/95
Rev. D dated: 2/21/2014
Rev. E dated: PAGE 6

SECTION III
NORMAL PROCEDURES:
3.1 PREFLIGHT INSPECTION:
A. INTERIOR:
1. BAT Switch…………………………………..... ON
2. Fuel Gauges…………………………………... CHECK INDICATIONS
3. Auxiliary Fuel Pumps………………………....
ON, THEN OFF (LISTEN TO VERIFY
OPERATION)
4. All Electrical Switches………………………... OFF
5. BAT Switch……………………………………. OFF
6. Flaps………………………………………….... FULL DOWN (4TH NOTCH)*
EXTERIOR: Begin at the left front door, proceed around the left wing to the nose area, then
around the right wing and back to the fuselage, then around the tail section.
1. Fuel drains behind step…………………….... DRAIN (2)
2. Left Flap……………………………………….. CHECK HINGES & CONTROL
ATTACHMENTS
3. Aileron…………………………………………. CHECK HINGES & CONTROL
ATTACHMENTS
4. Left Wing Top……………………………….... CHECK FOR WRINKLES AS INDICA-
TION OF INTERNAL DAMAGE
5. Left Wing Main & Aux Fuel Tank Drain…….. DRAIN (2)
6. Left Wing Tip & Nav Light…………………....
CHECK FOR DAMAGE
7. Auxiliary Fuel Tank....................................... VISUALLY CHECK QUANTITY
8. Landing Light………………………………….. CHECK FOR DAMAGE
9. Left Wing Tiedown………………………….... REMOVE
10. Pitot Tube……………………………………... REMOVE COVER
11. Stall Warning Switch………………………..... CHECK FOR FREEDOM OF MOVE-
MENT
12. Main Fuel Tank…………………………….…. VISUALLY CHECK QUANTITY
13. Left Landing Gear……………………………. CHECK TIRE INFLATION AND
BRAKE LINE SECURITY
14. Bottom left side of Cowl……………………... DRAIN GASCOLATOR (1)
15. Top Cowl, Oil Access Door…………………. CHECK OIL QUANTITY
16. Propeller……………………………………..... CHECK LEADING EDGE FOR DAM-
AGE.
17. Air Inlets……………………………………….. CHECK FOR FOREIGN OBJECTS,
INSPECT VISIBLE CONNECTIONS
AND COMPONENTS
18. Right Landing Gear…………………………... CHECK TIRE INFLATION & BRAKE
LINE SECURITY
19. Right Wing & Controls………………………..
INSPECT SAME AS LEFT WING
FAA APPROVED
DATE: 10/10/95 PAGE 7
MAULE AEROSPACE TECHNOLOGY, INC.
AIRPLANE FLIGHT MANUAL
MAULE M-7-235C
SECTION III
NORMAL
PROCEDURES

MAULE AEROSPACE TECHNOLOGY, INC.
AIRPLANE FLIGHT MANUAL
MAULE M-7-235C
SECTION III
NORMAL
PROCEDURES
3.1 PREFLIGHT INSPECTION: (Cont'd)
20. Wing Main & Aux Fuel Tank Drain…….……
DRAIN (2)
21.Right Fuselage, Side, Top & Bottom….…… INSPECT FOR WRINKLES AS INDI-
CATION OF INTERNAL DAMAGE
22. Right Side Static Port…………………….….. CLEAR
23. Right Stabilizer…………………………….….
CHECK ATTACHMENT POINTS &
STRUT
24. Right Elevator……………………………….... CHECK HINGE POINTS
25. Rudder……………………………………….... CHECK HINGE POINTS, CONTROL
ATTACHMENT & NAV LIGHT
26. Tailwheel…………………………………….... CHECK FOR INFLATION, ATTACH-
MENTS, REMOVE TIEDOWN
27. Left Elevator…………………………………... CHECK TAB CONTROLS & ALL
HINGE POINTS
28. Left Stabilizer…………………………………. CHECK ATTACHMENT POINTS &
STRUT
29. Left Fuselage, Top, Side & Bottom……….... CHECK FOR WRINKLES AS INDICA-
TION OF INTERNAL DAMAGE
30. Left Side Static Port………………………….. CLEAR
3.2 OPERATING CHECK LISTS:
A. BEFORE STARTING:
1. Seat Belts & Shoulder Harnesses………….. FASTENED
2. Flaps………………………………………..….
RETRACTED
3. Circuit Breakers…………………………….... CHECK
B. STARTING:
1. Parking or Toe Brakes…………………….…. ON
2. Fuel Selector Valve…………………………... ON FULLEST TANK, OR BOTH IF
SAME QUANTITY
3. Throttle……………………………………….... OPEN 1/4 INCH
4. Propeller Control……………………………... FULL INCREASE RPM
5. Mixture Control……………………………….
..
RICH (SEE NOTE NEXT PAGE FOR
HOT START)
6. Anti-Collision Light………………………….... ON
7. BAT and ALT Switch……………………….... ON
8. Primer (O-540). ………………………………. AS REQUIRED
Primer (IO-540). ……………………………...
.
AS REQUIRED USING BOOST PUMP
(SEE NOTE NEXT PAGE)
9. Mixture Control (IO-540 only)……………….. FULL LEAN
10. Starter Switch…………………………………. TWIST FULL RIGHT TO ENGAGE
11. Mixture Control (IO-540 only)……………….. FULL RICH WHEN ENGINE STARTS
TO FIRE
FAA APPROVED
DATE: 10/10/95 PAGE 8

MAULE AEROSPACE TECHNOLOGY, INC.
AIRPLANE FLIGHT MANUAL
MAULE M-7-235C
SECTION III
NORMAL
PROCEDURES
3.2 OPERATING CHECK LISTS: (Cont'd)
NOTE:
FOR A HOT START, DO NOT PRIME. A HOT ENGINE MAY FLOOD ON A
START ATTEMPT. TO CLEAR A FLOODED ENGINE, PULL MIXTURE FULL
LEAN AND OPEN THROTTLE, CRANK WITH STARTER. WHEN ENGINE
STARTS, PULL THROTTLE TO IDLE AND EASE MIXTURE TO FULL RICH.
NOTE:
(IO-540)
FOR A COLD ENGINE (FIRST START OF THE DAY), PLACE MIXTURE TO
FULL RICH, THROTTLE ¼" OPEN. PRIME WITH BOOST PUMP FOR 3 TO 5
SECONDS. IF ENGINE DOES NOT START, PRIME FOR ANOTHER 3 TO 5
SECONDS. OVER- PRIME CAN BE NOTED BY FUEL COMING FROM DRAIN
IN CENTER OF BOTTOM COWL.
////////////////////////
////CAUTION////
////////////////////////
IN EVENT OF ENGINE FIRE, CONTINUE CRANKING. PULL MIXTURE TO
FULL LEAN. IF ENGINE FAILS TO START AFTER SEVERAL REVOLU-
TIONS, AND FIRE CONTINUES, SECURE IGNITION, BAT. AND ALT.
SWITCHES, TURN FUEL VALVE OFF AND EXIT AIRCRAFT.
12. After Starting……………………………….….
CHECK OIL PRESSURE
////////////////////////
////CAUTION////
////////////////////////
IF OIL PRESSURE DOES NOT EXCEED 25 PSI WITHIN 30 SECONDS,
SHUT DOWN ENGINE.
13. Alternator……………………………………....
CHECK CHARGING
14. Radios & other electrical switches…………..
AS REQUIRED
15. Parking Brake……………………………….... OFF (PUSH KNOB COMPLETELY
AGAINST INSTRUMENT PANEL)
C. ENGINE CHECK:
1. Parking Brake………………………………....
ON, IF DESIRED
2. Engine Instruments…………………………... CHECK, IN GREEN ARCS
3. Throttle……………………………………….... INCREASE TO 2000 RPM
4. Magnetos…………………………………….... SWITCH TO RIGHT, LEFT, BOTH,
CHECKING RPM DROPS
5. Propeller Control……………………………...
RETARD SLOWLY UNTIL MAXIMUM
OF 500 RPM DROP IS NOTED. RE-
TURN TO FULL INCREASE RPM.
REPEAT. SET FULL INCREASE RPM
////////////////////////
////CAUTION////
////////////////////////
A RPM DROP OF MORE THAN 175 RPM OR A DIFFERENCE BETWEEN
LEFT AND RIGHT OF MORE THAN 50 RPM IS UNACCEPTABLE.
FAA APPROVED: 10/10/95
Rev. D dated: 2/21/2014 PAGE 9

MAULE AEROSPACE TECHNOLOGY, INC.
AIRPLANE FLIGHT MANUAL
MAULE M-7-235C
SECTION III
NORMAL
PROCEDURES
3.2 OPERATING CHECK LISTS: (Cont'd)
6. Carburetor Air Control (O-540)………...……
PULL HOT, NORMAL DROP WITH
CARBURETOR AIR HOT IS 150 ±50
RPM
Alternate Air Control (IO-540)…………….…. TURN LEFT TO UNLOCK AND PULL.
NORMAL RPM DROP WITH ALTER-
NATE AIR IS APPROXIMATELY 50
RPM
7. Carburetor Air Control (O-540)………….…..
PUSH COLD
Alternate Air Control (IO-540) …………...…. PUSH IN AND TURN RIGHT TO LOCK
8. Vacuum Gauge……………………………..… CHECK IN GREEN
9. Alternator…………………………………….... CHARGING: LIGHT OUT ABOVE 900
RPM
10. Throttle………………………………………... RETARD TO IDLE
D. BEFORE TAKEOFF:
1. Fuel Selector………………………………….. ON FULLEST TANK OR BOTH
2. Flaps…………………………………………...
AS DESIRED FOR T.O. (MAX. 24°)
3. Trim Controls………………………………..... SET FOR TAKEOFF
4. Flight Controls………………………………... CHECK FOR FREEDOM AND PROP-
ER TRAVEL
5. Mixture Control…………………………….…. FULL RICH
6. Propeller Control……………………………… FULL INCREASE RPM
7. Carburetor Air Control (O-540)....…….…….. PUSH COLD
Alternate Air Control (IO-540)…………….....
PUSH IN AND LOCK
8. Engine Instruments…………………………... RECHECK IN NORMAL RANGE
9. Radios…………………………………………. AS DESIRED
10. Altimeter……………………………………….. SET
11. Attitude Indicator……………………………... CHECK ERECT
12. Directional Indicator………………………….. SET
13. Seat Belts & Shoulder Harnesses………….. RECHECK FASTENED
14. Doors…………………………………………... CLOSED & LATCHED
15. Passengers……………………………….…... BELTS & HARNESSES SECURED.
BRIEFED ON OPENING DOORS.
16. Parking Brake…………………………….…... OFF (PUSH KNOB COMPLETELY
AGAINST INSTRUMENT PANEL)
E. BEFORE LANDING:
1. Seat Belts & Shoulder Harnesses……….…. FASTENED
2. Fuel Selector Valve……………………….….. ON FULLEST TANK OR BOTH
3. Mixture Control…………………………….…. FULL RICH
4. Propeller Control……………………………... FULL INCREASE RPM
5. Flaps…………………………………………... AS REQUIRED
6. Carburetor Air Control (O-540)……………... PULL HOT (AS REQUIRED)
Alternate Air Control (IO-540)..……………...
IN AND LOCKED
FAA APPROVED: 10/10/95
Rev. D dated: 2/21/2014 PAGE 10

MAULE AEROSPACE TECHNOLOGY, INC.
AIRPLANE FLIGHT MANUAL
MAULE M-7-235C
SECTION III
NORMAL
PROCEDURES
3.2 OPERATING CHECK LISTS: (Cont'd)
F. ENGINE SHUT DOWN:
1. Parking Brakes…………………………..…....
ON, IF DESIRED
2. Radios……………………………………..…... OFF
3. All other electrical switches………………..... AS DESIRED
4. Flaps………………………………………….... AS DESIRED
5. Magneto Grounding Check…………………..
PERFORM BELOW 1000 RPM
6. Mixture Control………………………….……
..
FULL LEAN
7. Magneto Switch……….……………………… OFF
8. Anti-Collision Light……..…………………….. OFF
9. BAT & ALT Switch………..………………….. OFF
10. Parking Brake……………..………………….. OFF (AS DESIRED) (FOR OFF, PUSH
KNOB COMPLETELY AGAINST
INSTRUMENT PANEL)
3.3 NORMAL FLIGHT OPERATIONS:
A. NOTE: FLAP SETTINGS:
The following Flap Settings are available:
Flap Configuration Flap Handle Position Flap Position
Cruise Handle Full Down -7°
Flaps Up First Notch 0°
Takeoff Second Notch 24°
Landing Third Notch (optional) 40°
Landing Fourth Notch 48°
B.
RECOMMENDED FLAP SETTINGS:
Flap settings are given in number of notches above the fully retracted position, which is
handle full down (Normal -7°).
NOTE: The airplane meets CAR 3 takeoff climb requirements at 78K (90 mph) IAS
with the flaps selected in any of the following three positions: (a) Fully Re-
tracted, Handle full down (-7°), (b) First Notch (0°) and (c) Second Notch (24°).
Normal Takeoff - Second Notch (24°)
Normal Climb - First Notch (0°)
Best Angle of Climb - Second Notch (24°)
Cruise - Fully retracted (-7°/no notches or 0°/1st notch)
Landing - Normally Fourth Notch (48°/full flaps) - other positions optional
FAA APPROVED: 10/10/95
Rev. B dated: 03/07/02
Rev. C dated: 05/20/02
Rev. D dated: 02/21/2014 PAGE 11

3.3 NORMAL FLIGHT OPERATIONS: (Cont'd)
C. CLIMBING:
Best Rate of Climb – 78K (90 mph) IAS, flaps @ First Notch (0°)
Best Angle of Climb – 65K (75 mph) IAS with flaps set @ Second Notch (24°)
////////////////////////
////CAUTION////
////////////////////////
FOR TAKEOFF OR LANDING UNDER GUSTY CROSSWIND CONDI-
TIONS, FLAP SETTING OF 0°(one notch) IS RECOMMENDED. -7°
OPTIONAL.
////////////////////////
////CAUTION////
////////////////////////
USE CLIMB AIRSPEED BELOW 78K (90 MPH) ONLY AS NECESSARY
AND CHECK CYLINDER HEAD TEMPERATURE FREQUENTLY WHEN
DOING SO.
D. RUDDER TRIM:
NOTE: To assure full effectiveness of the Right Rudder Trim:
Unlock "T" handle (½ turn left), depress right rudder as you pull "T" handle full out.
Lock "T" handle ½ turn right before releasing right rudder pressure. If too much trim,
move handle in until trim is correct and then lock.
E. STALLS:
Stalls are preceded by mild buffet that can be felt through the rudder pedals. The red
stall warning light on the instrument panel will illuminate at 4 to 9K (5 to 10 mph) above
the stall speed. Loss of altitude prior to recovery from a stall may be as much as 300
feet.
F. CROSSWIND LANDINGS & TAKEOFFS:
Maximum demonstrated crosswind component is 12K (14 mph) and flap extension
should be limited to 0°(first notch) with such crosswind or higher. 12K (14 mph) is the
maximum demonstrated for certification of the airplane and is not considered limiting
with flaps at 0°.
MAULE AEROSPACE TECHNOLOGY, INC.
AIRPLANE FLIGHT MANUAL
MAULE M-7-235C
SECTION III
NORMAL
PROCEDURES
////////////////////////
////CAUTION////
////////////////////////
THE STALL WARNING LIGHT IS INOPERATIVE WHEN THE BAT
TERY
SWITCH IS OFF
FAA APPROVED: 10/10/95
Rev. B dated: 03/07/02 PAGE 12

3.3 NORMAL FLIGHT OPERATIONS: (Cont'd)
G.
FUEL SYSTEM MANAGEMENT:
Fuel is fed to the engine from the main (inboard) tanks and is controlled by the selector valve
on the left kick panel. Auxiliary (outboard) tanks feed their respective main tanks via transfer
pumps that are controlled by switches on the instrument panel. These transfer pumps trans-
fer fuel at a rate of 0.4 gallons per minute or approximately 45 minutes for a full auxiliary
tank. Since overfilling a main tank from an auxiliary tank will force excess fuel overboard, it
is recommended that the transfer pumps not be activated until their respective main tanks
are slightly more than one quarter full. If the tank being transferred to is feeding the engine,
however, transfer can be initiated when the main tank is down to approximately one half.
Confirm fuel transfer by illumination of the transfer pump switch, an increase in the respec-
tive main tank fuel gauge indicator, and a decrease on the respective auxiliary tank indicator.
3.4 DOOR-OFF OPERATION:
This aircraft may be operated with either one (not both) of the front doors removed, or when
both front doors are installed, with the rear passenger door or rear passenger and baggage
doors off. When doing so, observe the following additional limitations:
1. Maximum airspeed – 109K (125 mph)
2. Maximum bank angle - 30°
3. Maximum yaw angle - 10°
4. No Smoking permitted
5. Limit flight to VFR conditions
3.5 NOISE LEVEL:
The noise levels obtained during certification per FAR 36, were:
with J/W engine with B engine
with Hartzell -6R (78") 2 blade 67.6 dBA 73.9 dBA
with Hartzell -3R (81") 2 blade 71.3 dBA 73.9 dBA
The noise levels obtained during certification per FAR 36, Appendix G were:
with McCauley -4 (78") 3 blade 68.0 dBA 76.5 dBA
with McCauley -2 (80") 3 blade 73.6 dBA 78.1 dBA
with McCauley -9 (81") 2 blade 73.3 dBA 77.8 dBA
No determination has been made by the Federal Aviation Administration that the noise
level of this airplane is or should be acceptable for operation at, into, or out of any airport.
3.6 ANTI-COLLISION LIGHT:
//////////////////////////
////WARNING////
/////////////////////////
ANTI-COLLISION LIGHT MAY CAUSE ADVERSE EFFECT ON PILOT
WHEN FLYING IN VISIBLE MOISTURE, OVERCAST OR HAZE. IT IS
RECOMMENDED THAT IT BE TURNED OFF UNDER THESE CONDI-
TIONS.
MAULE AEROSPACE TECHNOLOGY, INC.
AIRPLANE FLIGHT MANUAL
MAULE M-7-235C
SECTION III
NORMAL
PROCEDURES
FAA APPROVED: 10/10/95
Rev. B dated: 03/07/02 PAGE 13

MAULE AEROSPACE TECHNOLOGY, INC.
AIRPLANE FLIGHT MANUAL
MAULE M-7-235C
SECTION IV
EMERGENCY
PROCEDURES
SECTION IV
EMERGENCY PROCEDURES
4.1 EMERGENCY BASIC RULES:
To assist the pilot when an emergency occurs, three basic rules are established which apply
to most emergencies occurring while airborne. They should be remembered by each crew
member.
1. Maintain aircraft control
2. Analyze the situation and take proper action
3. Land as soon as conditions permit
4.2 ENGINE EMERGENCY SHUT DOWN:
1. Mixture - Full lean
2. Fuel Selector - OFF
3. Ignition Switch - OFF
4.3 ENGINE FIRE DURING STARTING:
1. Mixture - Full lean
2. Throttle - Open
3. Continue cranking for several revolutions. Attempt to draw fire inside engine.
4. Accomplish ENGINE EMERGENCY SHUT DOWN if fire continues.
4.4 ENGINE FIRE AFTER STARTING:
1. Accomplish ENGINE EMERGENCY SHUT DOWN
2. Master Switch - OFF
4.5 EMERGENCY EXIT ON THE GROUND:
1. Accomplish ENGINE EMERGENCY SHUT DOWN
2. Master Switch - OFF
3. Leave aircraft by either door or kick out side window panels or baggage door.
4.6 TAKEOFF ABORT: (BEFORE LIFT-OFF)
1. Throttle - Closed
2. Brakes - As Required
4.7 ENGINE FAILURE AFTER TAKEOFF OR FORCED LANDING:
1. Glide - Establish 69K (80 mph) IAS with flaps at 0°
FAA APPROVED: 10/10/95
Rev. B dated: 03/07/02 PAGE 14

MAULE AEROSPACE TECHNOLOGY, INC.
AIRPLANE FLIGHT MANUAL
MAULE M-7-235C
SECTION IV
EMERGENCY
PROCEDURES
4.7 ENGINE FAILURE AFTER TAKEOFF OR FORCED LANDING: (Cont’d)
2. Switch Fuel Selector to fullest tank
3. Electric Fuel Pump - ON
4. Mixture Rich, Ignition ON
5. Carburetor Air Control (O-540) – Pull HOT
Alternate Air Control – (IO-540) - Pull ON
6. If engine does not restart, accomplish EMERGENCY SHUT DOWN
7. Wing Flaps - As Required
8. Master Switch - OFF
4.8 PARTIAL POWER FAILURE DURING FLIGHT OR AFTER TAKEOFF:
1. Mixture - RICH
2. Carburetor Air Control (O-540) – Pull HOT
Alternate Air Control – (IO-540) - Pull ON
3. Airspeed - Glide at 69K (80 mph) IAS if unable to maintain level flight
4. Fuel Selector - BOTH
5. Electric Fuel Pump - ON
6. Ignition Switch - BOTH
7. Master Switch - ON
4.9 COMPLETE POWER FAILURE DURING FLIGHT:
1. Glide - Establish 69K (80 mph) (IAS)
2. Attempt engine airstart if warranted
4.10 ENGINE AIRSTART:
1. Fuel Selector – BOTH
2. Electric Fuel Pump - ON
3. Mixture – RICH
4. Ignition Switch - BOTH (start if propeller is not turning)
5. Auxiliary fuel tank pump switch – ON for tank feeding engine if auxiliary tank has
fuel.
6. If engine does not start, try flooded engine clearing procedure with throttle wide
open and mixture FULL LEAN.
7. If no start, make forced landing
NOTE: PROPELLER WILL NOT WINDMILL BELOW 61K (70 MPH).
NOTE: AT ALTITUDES OVER 8000 FEET, A LEANER MIXTURE MAY BE REQUIRED.
4.11 ELECTRICAL FIRE:
1. Master Switch - OFF
FAA APPROVED: 10/10/95
Rev. B dated: 03/07/02 PAGE 15