Nardi FN-333 Riviera Checklist:
PRE
FLIGHT CONTROL CHECK
Before flight verify you have full control authority. Perform while sitting
on the ground with the engine off.
Elevator Up 25.0
Elevator Down 20.0
Aileron Up 25.0
Aileron Down 18.0
Rudder 25.0
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STARTUP
Mixture : 100%
Fuel Pump: ON
Fuel Valve: OPEN
Fuel Selector: BOTH
Magnetos: START
Throttle: 0%
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TAKEOFF
Elevator Trim Set to 0.0 deg
Flaps AS NEEDED (0.0 or 10.0 deg)
Throttle 100% (or derated if possible)
Brakes RELEASE
V1 50 KIAS
V2 60 KIAS - ROTATE
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NORMAL CLIMB
Throttle 70%
Airspeed 110 KIAS
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CRUISE (FAST)
Throttle 90%
Airspeed 140 KIAS
CRUISE
(BEST RANGE)
Throttle 70%
Airspeed 130 KIAS
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LANDING
Airspeed - Pattern 70 KIAS
Flaps DOWN
Gear DOWN
Floats UP
Water
Rudder UP
Airspeed - Over the Fence 60 KIAS
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WATER LANDING
Airspeed - Pattern 70 KIAS
Flaps DOWN
Gear UP
Floats DOWN
Water
Rudder AS DESIRED
Airspeed - Over the Fence 60 KIAS
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FEDERAL AVIATION AGENCY
| 7A5 Revision 2 NARDI FN-333 April 18, 1963 |
||
TYPE CERTIFICATE DATA SHEET NO. 7A5
This data sheet which is a part of type certificate No. 7A5 prescribes conditions
and limitations under which the product for which the type certificate was issued
meets the airworthiness requirements of the Civil Air Regulations.
| Type Certificate Holder | NARDI S. A. |
| Milan, Italy |
I - Model FN-333, 4 PCAmM (Normal Category), approved December 15,
1958
| Engine | Continental IO-470-P | |||
| Fuel * | 91/96 Minimum grade aviation gasoline | |||
| Engine limits * | For all operations, 2600 r.p.m. (250 hp.) | |||
| Propeller and | 1. Hartzell HC82X20-5L/L8433-H | |||
| propeller limits | 2 blades, metal, constant speed with reversible pitch | |||
| Maximum diameter 84 in. | ||||
| Maximum diameter 81 in. (No further reduction permitted) | ||||
| Pitch settings at 30 in. sta.: | ||||
| Low 13°, high 27°30', reversed -14° | ||||
| 2. Hartzell HCA3X20-5L/L8433-6B | ||||
| 3 blades, metal, constant speed with reversible pitch | ||||
| Maximum diameter 78 in. | ||||
| Maximum diameter 76 in. (No further reduction permitted) | ||||
| Pitch settings at 30 in. sta.: | ||||
| Low 12°30", high 28°30', reversed -14°30' | ||||
| Airspeed limits | *Vne (never exceed) | 206 m.p.h. (178 knots) | |
| *Vno (max. structural cruising) | 162 m.p.h. (140 knots) | ||
| #Vp (maneuvering speed) | 146.5 m.p.h. (127 knots) | ||
| *Vfe (flaps extended in all positions) | 125 m.p.h. (109 knots) | ||
| *Vle (landing gear extended) | 125 m.p.h. (109 knots) | ||
| *Vfle (wing floats extended) | 125 m.p.h. (109 knots) | ||
| *Vwre (water rudder extended) | 206 m.p.h. (178 knots) |
| C.G. range | *(+110) to (+117) | |
| (landing gear extended) | ||
| Empty weight C.G. range | None | |
| Datum | Nose of aircraft | |
| Leveling means | Datum pads on left door frame | |
| Maximum weight | *3270 lb. | |
| No. seats | 4 (2 at +52.1, 2 at +95.3) | |
| Maximum baggage | *300 lb. (+95.3) | |
| Fuel capacity | 65.8 U.S. gal. (two wing tanks, 32.9 U.S. gal. ea.) (+107.5) | |
| Oil capacity | 3.5 U.S. gal. (+141.6). See NOTE 1 for data on system oil. |
| Control surface movements | Wing flaps | Down 45° | ||||
| Aileron | Up 25° | Down 18° | ||||
| Elevator Tab | Up 23° | Down 23° | ||||
| Elevator | Up 25° | Down 20° | ||||
| Rudder | Right 25° | Left 25° | ||||
| Stabilizer | Fixed |
| Serial Nos. eligible | The Registro Aeronautico Italiano (RAI) Certificate of
Airworthiness endorsed as noted below under "Certification basis"
must be submitted for each individual aircraft for which application for
certification is made. |
|
| Certification basis | CAR 10. Type Certificate No. 7A5 issued December 25, 1958. Date of Application for Type Certificate December 3, 1957. Each aircraft and any replacement parts manufactured in Italy must be clearly identified as imported. |
|
| A U.S. airworthiness certificate may be issued on the basis of a Certificate
of Airworthiness for Export signed by a representative of the Registro Aeronautico
Italiano (RAI) containing the following statement: "The airplane covered
by this certificate has been examined and found to comply with U.S. Civil
Air Regulations Part 3, dated May 15, 1956, including Amendments 3-1, 3-2,
3-3, 3-4 and 3-5, and conforms to TC 7A5." |
||
| 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 item of equipment is required: |
|
| (a) Pre-stall warning indicator, Safe Flight Instrument Corp. 164.S |
| NOTE 1. | Current weight and balance report including list of equipment in certificated
empty weight, and loading instructions, must be provided for each aircraft
at the time of original certification. The certificated empty weight and
corresponding center of gravity locations must include system oil of 1 lb.
at (+141.6). |
|||||||||
| NOTE 2. | The following placards must be displayed on the instrument panel in full
view of the pilot:
|
NOTE 3. This aircraft is approved for night flying when the prescribed equipment
is installed.
.....END.....
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