As with most certificated aircraft manufactured after
March 1979, FAA-certificated gyroplanes are required
to have an approved flight manual. The flight manual
describes procedures and limitations that must be
adhered to when operating the aircraft. Specification
for Pilot’ s Operating Handbook , published by the
General Aviation Manufacturers Association (GAMA),
provides a recommended format that more recent gyro-
plane flight manuals follow. [Figure 19-1]
This format is the same as that used by helicopters,
which is explained in depth in Chapter 6—Rotorcraft
Flight Manual (Helicopter).
Amateur-built gyroplanes may have operating limita-
tions but are not normally required to have an approved
flight manual. One exception is an exemption granted
by the FAA that allows the commercial use of
two-place, amateur-built gyroplanes for instructional
purposes. One of the conditions of this exemption is to
have an approved flight manual for the aircraft. This
manual is to be used for training purposes, and must be
carried in the gyroplane at all times.
USING THE FLIGHT MANUAL
The flight manual is required to be on board the aircraft
to guarantee that the information contained therein is
readily available. For the information to be of value,
you must be thoroughly familiar with the manual and
be able to read and properly interpret the various charts
and tables.
WEIGHT AND BALANCE SECTION
The weight and balance section of the flight manual
contains information essential to the safe operation of
the gyroplane. Careful consideration must be given to
the weight of the passengers, baggage, and fuel prior to
each flight. In conducting weight and balance compu-
tations, many of the terms and procedures are similar to
those used in helicopters. These are further explained
in Chapter 7—Weight and Balance. In any aircraft,
failure to adhere to the weight and balance limita-
tions prescribed by the manufacturer can be
extremely hazardous.
SAMPLE PROBLEM
As an example of a weight and balance computation,
assume a sightseeing flight in a two-seat, tandem-con-
figured gyroplane with two people aboard. The pilot,
seated in the front, weighs 175 pounds while the rear
seat passenger weighs 160 pounds. For the purposes of
this example, there will be no baggage carried. The
basic empty weight of the aircraft is 1,315 pounds with
a moment, divided by 1,000, of 153.9 pound-inches.
ROTORCRAFT FLIGHT MANUAL□
GENERAL—Presents basic information, such as loading,
handling, and preflight of the gyroplane. Also includes
definitions, abbreviations, symbology, and terminology
explanations.□□
LIMITATIONS—Includes operating limitations, instrument
markings, color coding, and basic placards necessary for the
safe operation of the gyroplane.□□
EMERGENCY PROCEDURES—Provides checklists followed
by amplified procedures for coping with various types of
emergencies or critical situations. Related recommended
airspeeds are also included. At the manufacturer's option, a
section of abnormal procedures may be included to describe
recommendations for handling equipment malfunctions or other
abnormalities that are not of an emergency nature.□□
NORMAL PROCEDURES—Includes checklists followed by
amplified procedures for conducting normal operations.
Related recommended airspeeds are also provided.□□
PERFORMANCE—Gives performance information
appropriate to the gyroplane, plus optional information
presented in the most likely order for use in flight.□□
WEIGHT AND BALANCE—Includes weighing procedures,
weight and balance records, computation instructions, and
the equipment list.□□
AIRCRAFT AND SYSTEMS DESCRIPTION—Describes the
gyroplane and its systems in a format considered by the
manufacturer to be most informative.□□
HANDLING, SERVICE, AND MAINTENANCE—Includes
information on gyroplane inspection periods, preventative
maintenance that can be performed by the pilot, ground
handling procedures, servicing, cleaning, and care instructions.□□
SUPPLEMENTS—Contains information necessary to safely
and efficiently operate the gyroplane's various optional
systems and equipment.□□
SAFETY AND OPERATIONAL TIPS—Includes optional
information from the manufacturer of a general nature
addressing safety practices and procedures.□
□Figure 19-1. The FAA-approved flight manual may contain as
many as ten sections, as well as an optional alphabetical
index.
Using the loading graph [Figure 19-2], the
moment/1000 of the pilot is found to be 9.1 pound-
inches, and the passenger has a moment/1000 of 13.4
pound-inches.
Adding these figures, the total weight of the aircraft for
this flight (without fuel) is determined to be 1,650
pounds with a moment/1000 of 176.4 pound-inches.
[Figure 19-3]
The maximum gross weight for the sample aircraft is
1,800 pounds, which allows up to 150 pounds to be car-
ried in fuel. For this flight, 18 gallons of fuel is deemed
sufficient. Allowing six pounds per gallon of fuel, the
fuel weight on the aircraft totals 108 pounds. Referring
again to the loading graph [Figure 19-2], 108 pounds of
fuel would have a moment/1000 of 11.9 pound-inches.
This is added to the previous totals to obtain the total
aircraft weight of 1,758 pounds and a moment/1000 of
188.3. Locating this point on the center of gravity enve-
lope chart [Figure 19-4], shows that the loading is
within the prescribed weight and balance limits.
PERFORMANCE SECTION
The performance section of the flight manual contains
data derived from actual flight testing of the aircraft.
Because the actual performance may differ, it is pru-
dent to maintain a margin of safety when planning
operations using this data.
SAMPLE PROBLEM
For this example, a gyroplane at its maximum gross
weight (1,800 lbs.) needs to perform a short field take-
off due to obstructions in the takeoff path. Present
weather conditions are standard temperature at a pres-
sure altitude of 2,000 feet, and the wind is calm.
Referring to the appropriate performance chart [Figure
19-5], the takeoff distance to clear a 50-foot obstacle is
determined by entering the chart from the left at the
pressure altitude of 2,000 feet. You then proceed hori-
zontally to the right until intersecting the appropriate
temperature reference line, which in this case is the
dashed standard temperature line. From this point,
descend vertically to find the total takeoff distance to
clear a 50-foot obstacle. For the conditions given, this
particular gyroplane would require a distance of 940
feet for ground roll and the distance needed to climb 50
feet above the surface. Notice that the data presented in
this chart is predicated on certain conditions, such as a
running takeoff to 30 m.p.h., a 50 m.p.h. climb speed, a
Weight Moment□
(pounds) (lb.-in./1,000)
Basic Empty Weight□
Pilot□
Passenger□
Baggage□
Total Aircraft (Less Fuel)
1,315□
175□
160□
1,650
153.9□
9.1□
13.4□
176.4
Max Gross Weight = 1,800 lbs.
Figure 19-3. Loading of the sample aircraft, less fuel.
CENTER OF GRAVITY ENVELOPE
Gross Moment in Thousands of LBS-IN.
Gross Weight in Pounds (x100)
160 180 190 200170
1. Total Aircraft Weight□
(Less Fuel) ...............................□
□
3. Fuel...........................................
TOTALS
□
Weight□
(lbs.)
Moment□
(lb.-ins.□
/1,000)
176.41,650
11.9108
188.31,758
AftForward
Figure 19-4. Center of gravity envelope chart.
0 2 4 6 8 10 12 14 16 18 20
Load Weight in Pounds (x100)
Load Moment in Thousands of LBS - IN
LOADING GRAPH
A = Pilot
B = Passenger
C = Fuel
D = Baggage
Figure 19-2. A loading graph is used to determine the load
moment for weights at various stations.
rotor prerotation speed of 370 r.p.m., and no wind.
Variations from these conditions alter performance,
possibly to the point of jeopardizing the successful out-
come of the maneuver.
HEIGHT/VELOCITY DIAGRAM
Like helicopters, gyroplanes have a height/velocity
diagram that defines what speed and altitude combina-
tions allow for a safe landing in the event of an engine
failure. [Figure 19-6]
During an engine-out landing, the cyclic flare is used to
arrest the vertical velocity of the aircraft and most of the
forward velocity. On gyroplanes with a manual collec-
tive control, increasing blade pitch just prior to touch-
down can further reduce ground roll. Typically, a
gyroplane has a lower rotor disc loading than a helicop-
ter, which provides a slower rate of descent in autorota-
tion. The power required to turn the main transmission,
tail rotor transmission, and tail rotor also add to the
higher descent rate of a helicopter in autorotation as
compared with that of a gyroplane.
EMERGENCY SECTION
Because in-flight emergencies may not allow enough
time to reference the flight manual, the emergency sec-
tion should be reviewed periodically to maintain
familiarity with these procedures. Many aircraft also
use placards and instrument markings in the cockpit,
which provide important information that may not be
committed to memory.
Running Takeoff to 30 MPH & Climb out at 50 MPH CAS□
□Weight 1800 LBS Rotor Prerotated to 370 RPM
2 4 6 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36
Total Takeoff Distance to Clear 50 FT Obstacle in Feet (x 100)
Pressure Altitude in Feet (x 1000)
TOTAL TAKEOFF DISTANCE□
TO CLEAR 50 FT. OBSTACLE
Zero Wind
0ϒ F
20ϒ F
Std. Temp. 40ϒ F
60ϒ F
80ϒ F
100ϒ F
Figure 19-5. Takeoff performance chart.
HEIGHT vs. VELOCITY□
FOR SAFE LANDING
Avoid Continuous Operation In□
Shaded Area.
0 20 40 60 80 100
Indicated Airspeed In MPH
Height Above Runway In Feet
Figure 19-6. Operations within the shaded area of a
height/velocity diagram may not allow for a safe landing and
are to be avoided.
HANG TEST
The proper weight and balance of a gyroplane without
a flight manual is normally determined by conducting
a hang test of the aircraft. This is achieved by remov-
ing the rotor blades and suspending the aircraft by its
teeter bolt, free from contact with the ground. A meas-
urement is then taken, either at the keel or the rotor
mast, to determine how many degrees from level the
gyroplane hangs. This number must be within the
range specified by the manufacturer. For the test to
reflect the true balance of the aircraft, it is important
that it be conducted using the actual weight of the pilot
and all gear normally carried in flight. Additionally,
the measurement should be taken both with the fuel
tank full and with it empty to ensure that fuel burn
does not affect the loading.