SECTION 5 - PERFORMANCE

Introduction

This section provides all data necessary for accurate and complete flight activity planning, from takeoff to landing.

The data shown in graphs and/or tables have been determined using:

"Flight test data" with conditions prescribed by JAR-VLA
Aircraft and engine in good condition
Average piloting techniques

Each graph or table was determined according to ICAO Standard Atmosphere (ISA - m.s.l.); performance impact evaluations were made with theoretical methods for:

Speed
Outside temperature
Altitude
Weight
Runway type and condition

NOTE: Sections approved by EASA are highlighted with "Approved Data" immediately after the paragraph title.

Using Performance Charts

Performance data are presented in tabular or graphical form to illustrate the effect of different variables such as altitude, temperature and weight. The information provided is sufficient to plan the flight with required accuracy and safety. Additional information is provided for each table or chart.

Airspeed Indicator System Calibration Approved Data

The chart shows calibrated airspeed V_CAS as a function of indicated airspeed V_IAS.

Example:

Given

V_IAS = 78 Kts

Find

V_CAS = 75 Kts

NOTE: Indicated airspeed assumes instrument error equal to zero.

ICAO Chart

Example:

Given

Temperature = 20degC

Pressure altitude = 1600 ft

Find

Ts = 12deg

Stall Speeds Approved Data

Conditions: Weight 550 kg

Weight 550 kg
Engine at idle
Out of ground effect

Stall Speeds - MTOW 550 kg
FLAPS	BANK ANGLE
FLAPS	0deg		30deg		45deg		60deg
	KIAS	KCAS	KIAS	KCAS	KIAS	KCAS	KIAS	KCAS
0deg	44	43	47	46	52	51	63	61
15deg	42	41	45	44	50	49	60	58
38deg	40	39	42	41	47	46	56	55

Conditions: Weight 600 kg

Weight 600 kg
Engine at idle
Out of ground effect

Stall Speeds - MTOW 600 kg
FLAPS	BANK ANGLE
FLAPS	0deg		30deg		45deg		60deg
	KIAS	KCAS	KIAS	KCAS	KIAS	KCAS	KIAS	KCAS
0deg	46	45	49	48	54	53	66	64
15deg	44	43	47	46	52	51	63	61
38deg	41	40	44	43	49	48	58	56

NOTE: Altitude loss during recovery from conventional stall demonstrated during flight tests is approximately 100 ft with bank angle less than 30deg.

Crosswind

Maximum demonstrated crosswind component is 15 Kts.

Example:

Given

Wind direction = 30deg

Wind speed = 20 Kts

Find

Headwind = 17.5 Kts

Crosswind = 10 Kts

Takeoff Performance Approved Data

Takeoff Distance

Conditions:

Flaps: 15deg
Engine: full power (see Sec. 4)
Runway: dry, compact, grass
Slope: 0deg - Wind: zero
R/C >= 200 ft/min

Takeoff Speeds
Speed	MTOW = 550 kg	MTOW = 600 kg
V_R (Rotation)	47 KIAS	48 KIAS
V_obs (Obstacle clearance)	56 KIAS	58 KIAS
V_LO (Lift-off)	49 KIAS	51 KIAS

NOTES:

Reduce distances by 10% for each 10 Kts of headwind. Increase distances by 20% for each 10 Kts of tailwind.
For operations on dry asphalt runway, reduce takeoff roll by 6%.

Example:

Given

O.A.T. = 15degC

Pressure altitude = 2900 ft

MTOW = 600 kg

Weight = 450 kg

Find

TOD = 253 m

TOR = 117 m

Climb Performance

Rate of Climb in Takeoff Configuration Approved Data

Conditions	550 kg MTOW	600 kg MTOW
Flaps	15deg	15deg
Engine	Full power	Full power
V_obs	56 KIAS	58 KIAS

Demonstrated rate of climb in ISA conditions at sea level is 850 ft/min at maximum takeoff weight of 550 kg and 750 ft/min at maximum takeoff weight of 600 kg.

Rate of Climb in Clean Configuration

Conditions:

Flaps: 0deg
Engine: full power
V_Y = 70 KIAS for 550 kg MTOW
V_X = 63 KIAS for 550 kg MTOW
V_Y = 73 KIAS for 600 kg MTOW
V_X = 66 KIAS for 600 kg MTOW
Residual R/C 100 ft/min

Example:

Given

O.A.T. = 17degC

Pressure altitude = 5600 ft

Weight = 550 kg

Find

Rate of climb = 700 ft/min

Cruise

Conditions:

ISA
Maximum takeoff weight = for both MTOWs
(1) Fuel tanks 2x35 liters (less unusable fuel)
(2) Fuel tanks 2x45 liters (less unusable fuel)

Pressure Altitude H_P: 0 ft - OAT: +15degC
Prop %	RPM	KTAS	l/h	End (1)	End (2)	N.m. (1)	N.m. (2)
55%	1900	96	15	4.5	5.8	431	599
65%	2050	102	18	3.7	4.9	382	495
75%	2150	108	20	3.4	4.4	364	472

Pressure Altitude H_P: 2000 ft - OAT: +11degC
Prop %	RPM	KTAS	l/h	End (1)	End (2)	N.m. (1)	N.m. (2)
55%	1950	98	15	4.5	5.8	440	571
65%	2070	106	18	3.7	4.9	397	515
73%	2150	109	19	3.5	4.6	387	501

Pressure Altitude H_P: 4000 ft - OAT: +7degC
Prop %	RPM	KTAS	l/h	End (1)	End (2)	N.m. (1)	N.m. (2)
55%	2020	101	15	4.5	5.8	454	588
60%	2080	105	17	4.0	5.1	416	540
70%	2150	110	18.5	3.6	4.7	401	520

Pressure Altitude H_P: 6000 ft - OAT: +3degC
Prop %	RPM	KTAS	l/h	End (1)	End (2)	N.m. (1)	N.m. (2)
55%	2060	104	15	4.5	5.8	467	606
60%	2150	108	17	4.0	5.1	429	556

Pressure Altitude H_P: 8000 ft - OAT: -0.8degC
Prop %	RPM	KTAS	l/h	End (1)	End (2)	N.m. (1)	N.m. (2)
55%	2120	99	15	4.5	5.8	445	578
58%	2150	102	16	4.2	5.4	428	556

Pressure Altitude H_P: 10000 ft - OAT: -5degC
Prop %	RPM	KTAS	l/h	End (1)	End (2)	N.m. (1)	N.m. (2)
55%	2150	100	15	4.5	5.8	450	585

Pressure Altitude H_P: 12000 ft - OAT: -9degC
Prop %	RPM	KTAS	l/h	End (1)	End (2)	N.m. (1)	N.m. (2)
50%	2150	98	14	4.8	6.2	475	617

NOTE: Range and endurance are intended as approximate and refer to "zero" wind conditions.

Go-Around (Balked Landing)

Rate of Climb: Go-Around

Conditions:

Maximum weight = 550 kg | 600 kg
V_obs = 48 KIAS | 50 KIAS
Flaps: 38deg
Engine: full power max 5'

NOTE: During go-around maneuver, flaps must be retracted immediately after applying full power.

Example:

Given

Pressure altitude = 7000 ft

Conditions: ISA

Find

Rate of climb = 230 ft/min

NOTE: If maximum takeoff weight is 600 kg, rate of climb decreases by approximately 10%.

Landing Distance Approved Data

Conditions: Maximum Weight 550 kg

Maximum weight = 550 kg
Brakes: maximum braking
Slope: 0deg
Conditions: ISA
Engine: at idle
Runway: dry, compact, grass
Wind: zero
Flaps: 38deg

Landing Distance - 550 kg
H_P (ft)	0	1000	2000	3000	4000	5000	6000	7000
GR (m)	100	103	106	109	112	116	119	123
LD (m)	252	256	260	264	268	273	279	282

Conditions: Maximum Weight 600 kg

Maximum weight = 600 kg
Brakes: maximum braking
Slope: 0deg
Conditions: ISA
Engine: at idle
Runway: dry, compact, grass
Wind: zero
Flaps: 38deg

Landing Distance - 600 kg
H_P (ft)	0	1000	2000	3000	4000	5000	6000	7000
GR (m)	120	124	127	131	134	139	143	148
LD (m)	302	307	312	317	322	328	335	338

GR = Ground Roll
LD = Landing Distance

NOTES:

Reduce distances by 10% for each 10 Kts of headwind. Increase distances by 20% for each 10 Kts of tailwind.
For operations on dry asphalt runway, reduce ground roll by 10%.
If it becomes necessary to land without flap extension (flap malfunction), increase approach speed by 10 Kts, increase by 40% the distance relative to flap 38deg setting and increase V_obs to 58 KIAS (61 KIAS) for 550 kg MTOW (600 kg).
V_obs (obstacle clearance speed) is 48 KIAS (50 KIAS) for 550 kg MTOW (600 kg).

Consequences of Rain and Insects

Flight tests demonstrated that neither rain impact nor insect accumulation on the leading edge caused substantial variations to aircraft flight qualities. Such variations fall within JAR-VLA tolerance limits as they do not exceed: 5 Kts for stalls, 100 ft/min for climb rates and 50 m for takeoff runs.

Noise Data

Noise level was determined according to JAR-36 Sub.C Ed. May 23, 1997 ICAO/Annex 16 Cap.10 Edition 1993, and results are shown in the following table:

	550 kg MTOW	600 kg MTOW
Noise Level (dB)	63.6	65.0

P92-JS FLIGHT MANUAL - SECTION 5: PERFORMANCE

Edition 3 - Revision 5 - July 12, 2022

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

Section 4: Normal Procedures Manual Index Section 6: Weight & Balance