← Sec. 5 Index Sec. 7 → Italiano
× Enlarged image

SECTION 6 - WEIGHT AND BALANCE / EQUIPMENT LIST

Introduction

This section describes the procedure for establishing basic empty weight and moment of the aircraft. Information on loading procedures is also provided.

DATUM: Propeller support flange without spacer
MAC (Mean Aerodynamic Chord): 1400 mm

Aircraft Weighing Procedures

Preparation

  1. Perform the weighing procedure inside a closed hangar
  2. Remove from the cabin any items left unintentionally
  3. Ensure the following are on board:
    • Flight manual
    • Certificate of airworthiness
    • Navigation charts, etc.
  4. Align the nose wheel
  5. Drain the fuel through the specific drain valve
  6. Oil, hydraulic fluid and coolant at operational levels
  7. Move the sliding seats to the most forward position
  8. Set the flaps to fully retracted position (0°)
  9. Position the control surfaces in neutral position
  10. Position the scales (min. capacity 150 kg) under each wheel

Leveling

  1. Level the aircraft using the cabin floor as reference
  2. Center the spirit level bubble by deflating the nose tire

Weighing

  1. Record the weight shown on each scale
  2. Repeat the weighing procedure three times
  3. Calculate the empty weight

Determination of C.G. Position

  1. Drop a plumb line tangent to the leading edge (in the non-tapered wing area, about one meter from the root) and mark a reference point on the floor
  2. Repeat the operation for the other wing half
  3. Stretch a string between the two marks
  4. Measure the distance between the reference line and the main wheel axis
  5. Using the recorded data it is possible to determine the C.G. position and the aircraft moment (see following table)

Weighing Report

Model P92-JS     S/N: __________     Weighing no.: __________

Date: __________

Datum: Propeller support flange without spacer     Equipment list, date: __________

MAC: 1400 mm

Weighing Diagram
Weighing diagram with scale positions (dimensions 1405mm and distance D from datum)
Weights (Kg)
Nose wheel weightW1 =
LH wheel weightWL =
RH wheel weightWR =
W2 = WL + WR=
Distances (meters)
Plumb line distance LH wheelAL =
Plumb line distance RH wheelAR =
Average distance (AL+ AR)/2A =
Plumb line distance from nose wheelB =

Empty weight(1): We = W1 + W2 = __________ kg

D = (W2 · A - W1 · B) / We = __________ m

D% = (D / 1.4) · 100 = __________%

Empty weight moment: M = [(D + 1.405) · We] = __________ Kg·m

WT = 550 kg WT = 600 kg Signature:
Maximum takeoff weight WT = 550 kg WT = 600 kg
Empty weight We = We =
Max useful load WT - We Wu = Wu =
NOTE (1): Includes unusable fuel (2.3 kg).

Weight and Balance

To determine the aircraft C.G. position and verify that the C.G. falls within the predetermined allowable range, it is necessary to use the graph on the following page. The graph shows the C.G. position as a function of the empty weight moment with respect to the datum as resulting from the weighing report.

Using the "Weight and Balance" Graph (page 6-6)

To use the graph it is necessary to know the value of the moment arm with respect to the datum. Once this value is found on the abscissa, draw a line parallel to the oblique lines until it intersects the ordinate relative to pilot and passenger weight. From this point, draw a horizontal line to the limit value of 180 kg and, from there, draw a line parallel to the oblique lines until it intersects the abscissa relative to the fuel loaded. Then draw a horizontal line through this point to the limit value of 70 liters and a new line parallel to the oblique lines until it intersects the abscissa relative to the baggage loaded behind the seats.

Draw another horizontal line and it is thus possible to verify that the intersection of this segment with the vertical abscissa relative to the total takeoff weight of the aircraft falls within the shaded area representing the allowable C.G. range as a function of total weight.

Pages 6-6 and 6-7 show the C.G. range graphs as a function of aircraft weight, the distances in meters of pilots and baggage from the datum (propeller support flange).

Example (see page 6-6)

Weight and Balance Graph
Fig. 6-1. Weight and Balance Graph
C.G. Range Graph
Fig. 6-2. C.G. Range Graph
C.G. Range:
Forward limit: 1.727 m from datum (23% MAC)
Aft limit: 1.769 m from datum (26% MAC)

Loading

The baggage compartment is designed for a maximum load of 20 kg. Baggage dimensions must avoid excessive loading of the service shelf (maximum pressure 12.5 kg/dm2). Maximum baggage dimensions: 80 x 45 x 32 cm. Baggage must be secured with a tie-down net to prevent any movement during maneuvers.

Cabin Dimensions
Fig. 6-4. Cabin Dimensions

Load Positions from Datum

Load Positions from Datum
Fig. 6-3. Load Positions from Datum
Fuel
1.66 m
Pilot (average value)
1.76 m
Baggage
2.21 m

Equipment List

Below is a complete list of all equipment supplied by TECNAM for the P92-JS. The list is composed of the following groups:

The following information describes each item in the list:

NOTE: Items marked with an asterisk (*) are part of the basic installation. Additionally, further equipment marked with X in the Inst. column is installed on the subject S/N aircraft.
A - ENGINE AND ACCESSORIES
Ref.Description and P/NInst.Weight kgDatum m
A1Engine Rotax 912S2 - p/n 309.120.133*59.00.32
A2Propeller HOFFMANN p/n HO17GHM A 174 177C*4.50-0.08
A3Exhaust and manifolds - p/n SSB-978-480-CC*4.500.55
A4Heat exchanger - p/n 92-11-830*2.000.55
A5Oil tank (full) - p/n 956.137 or 656.865*4.000.61
A6Oil radiator - p/n 886 025 or 886.033*0.400.07
A7Coolant radiator - p/n 995.697 or 997.083*0.900.33
A8Air filter K&N - p/n 33-2544*0.400.60
A9Vacuum instruments system - RA215CC Rapco3.000.25
A10Vacuum valve RA2H3-120.1000.71
A11Fuel pump p/n 21-11-342-000*0.2000.71
A12Fuel tank 45 Lt. P/N 21-1-340-001/2*////
B - LANDING GEAR AND ACCESSORIES
Ref.Description and P/NInst.Weight kgDatum m
B1Main gear leaf springs - p/n 92-8-300-1*5.7001.930
B2Main wheel rims - CLEVELAND 40-78B or 199-102*2.0501.930
B3Main tires - AIR TRAC 5.00-5*2.5801.930
B4Disc brakes - Cleveland 30-9 or 160-17*0.8001.930
B5Nose wheel rim p/n 92-8-880-1 or 92-8-700-000*1.3000.310
B6Nose tire - 4.00-6N1.2000.460
B7Nose tire - AIR TRACK 5.00-51.5000.460
B8Nose wheel fairing p/n 92-8-410-1/2N1.5000.460
B9Nose wheel fairing p/n 27-8-420-11.5000.460
B10Main wheel fairing p/n 92-8-420-1/2x1.5001.930
B11Nose shock absorber p/n 92-8-200-000*1.4500.465
C - ELECTRICAL SYSTEM
Ref.Description and P/NInst.Weight kgDatum m
C1Battery FIAMM 6H4P 12V 18Ah6.004.24
C2Regulator, rectifier - p/n 945.345*0.200.82
C3Battery relay - p/n 111-226-5*0.304.19
C4Flap actuator - SIR Mod. AO-01/M*2.202.57
C5Flap actuator switch - FEME MS35059-34*0.081.20
C6Trim actuator control Ray Allen C. T2-10A*0.405.75
C7Overvoltage sensor OS75-140.300.80
C8Overvoltage sensor B00289-2*0.300.80
C9Strobe light - p/n 2005N0.155.52
C10Navigation lights - AS W1285N0.152.30
C11Nav-Strobe light - AVE-WPTSG-54G0.252.30
C12Stall warning AS 164R or TECNAM 21-9-420-000*0.101.95
C13Landing light - AS GE 45090.501.50
C14Landing light - Pled1L0.601.50
C15BATTERY SPARK 5004.94.24
D - INSTRUMENTS
Ref.Description and P/NInst.Weight kgDatum m
D1Altimeter - MIKROTECHINA p/n 1128.12B60.391.20
D2Altimeter - United Instruments p/n 5934PM-30.391.20
D3Airspeed indicator - MIKROTECHINA 116.B0B2*0.301.20
D4Compass - Airpath C2400 L4P*0.291.20
D5Clock - DAVTRON mod. M 800*0.151.20
D6Variometer - MIKROTECHINA UL 30-42.20.351.20
D7Variometer - Wultrad Inc. p/n BC-2A0.351.20
D8Turn and slip indicator - FALCON GAUGER TC02F-3-20.561.20
D9Turn and slip indicator - Mid. Continent p/n 1394T100-TZ0.561.20
D10Attitude indicator - FALCON G. GH02V-31.101.20
D11Attitude indicator - RCA ALLEN INSTR. RCA 22-71.101.20
D12Directional gyro - RCA ALLEN INSTR. RCA 11A-81.101.20
D13Directional gyro - FALCON G. DG02V-31.101.20
D14OAT indicator - 397035001G VDO*0.051.20
D15CHT indicator - 641-011-7047/-7048 VDON0.101.20
D16CHT indicator - Ind. SOR 53 or SOR 59*0.101.20
D17Oil temp indicator - VDO 644-001-7030N0.101.20
D18Oil temp indicator - SOR 54*0.101.20
D19Vacuum instruments - UMA Inc. 3-200-12*0.101.20
D20Prop RPM indicator - D1-112-5040 Aircraft MitchellN1.101.20
D21Prop RPM indicator - Sorlini (SOR52)*1.101.20
D22Fuel level indicator - Road XID4.0008.00*0.561.20
D23Oil pressure indicator - Sorlini (SOR50, SOR50V)0.101.20
E - AVIONICS AND OTHER
Ref.Description and P/NInst.Weight kgDatum m
E1Nav/Comm Trans. - Bendix/King KX1552.241.20
E2Nav indicator - Bendix/King KI2080.461.20
E3R/T VHF COMM Garmin SL401.201.20
E4Transponder - Bendix/King KT76A1.361.20
E5GPS/NAV receiver and COM r/t GNS 430W2.311.20
E6R/T VHF COMM IC-A200 ICOM1.201.20
E7ELT ARTEX ME 4061.102.70
E8Transponder - Garmin GTX328 or GTX3351.001.20
E9Audio panel - Garmin GMA 340 or 3450.501.20
E10VOR/Loc indicator - Garmin GI106( )0.641.20
E11Antenna KA 92 GPS0.271.07
E12Transponder antenna - Bendix/King KA600.351.50
E13GPS antenna - Garmin 10120.171.07
E14Microphone - Telex TRA 1000.171.90
E15Antenna Garmin GA350.271.08
E16Comm antenna CI 291 or CI 121*0.343.30
E17VOR/ILS antenna CI 138C or CI 158C0.265.60
E18ELT antenna0.212.70
E19Fire extinguisher Fire Fighting Enterprises Ltd BA51015-32.202.16
E20Fire extinguisher - HALON H3G 1301 or AMEREX A3441.002.16
E21First aid kit*0.282.60
E22Altitude encoder - Amery King A300.561.00
E23ADF receiver - Bendix King KR871.381.20
E24ADF indicator - Bendix King KI2270.391.20
E25ADF antenna - Bendix King KA44B1.892.05
E26GTN 6503.201.20
E27GTR225A1.071.20
E28GNC 255 or 255A1.361.20
E29ELT ACK E04 or Kannad Compact / Integra1.002.70
E30Transponder antenna CI 1050.111.50
E31Marker antenna CI1020.272.70

P92-JS FLIGHT MANUAL - SECTION 6: WEIGHT AND BALANCE

Edition 3 - Revision 5 - July 12, 2022

English translation for educational purposes - Always refer to the original document

← Section 5: Performance Manual Index Section 7: Aircraft Description →