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NOTES made by Capt. Salil Sharma for DA42 self-study for Tech. Specific Exam Questions, explanations and answers and reference of page number in POH in which answer is given. Most answers are in POH but for Autopilot related questions refer to KAP140 supplement: -
Page 29 of DA42 POH PDF FILE vS: Stalling Speed, or the minimum continuous speed at which the airplane is still controllable in the given configuration. vS0: Stalling Speed, or the minimum continuous speed at which the airplane is still controllable in the landing configuration. vS1: Stalling Speed, or the minimum continuous speed at which the airplane is still controllable with flaps and landing gear retracted. vSSE: Minimum Control Speed for Schooling. Minimum speed spe ed necessary in case of one engine intentionally inoperative / idle (training purposes).
PAGE 32 FULL AUTHORITY DIGITAL ENGINE CONTROL
. Refer page 26 of POH pdf. Overall Dimensions Span : 13.42 m/ 44.0 ft Length : 8.56 m / 28 ft 1 in Height : 2.49 m / 8 ft 2 in
13.55 m / 44.5 ft including ACL
Wing Airfoil : Wortmann FX 63-137/20 - W4 Wing area : 16.29 m² 175.3 sq.ft. Mean aerodynamic chord : 1.271 m Aspect ratio : 11.06 Dihedral : 5° Leading edge sweep : 1°
4 ft 2 in
Aileron Area (total, left + right) : 0.66 m²
PAGE 49 OF POH PDF
7.1 sq.ft.
2.3 AIRSPEED INDICATOR MARKINGS Marking
KIAS
White arc Green arc Yellow arc Blue radial Red radial
Significance Operating range with flaps fully extended. Normal operating range. ‘Caution range’ - “Only in smooth air”. Best rate of climb speed, single engine. Minimum control speed, single engine.
Maximum speed for all operations – vNE
PAGE 50 OF POH POWERPLANT LIMITATIONS d) RPM limitations (shown as propeller RPM) Maximum : 2300 RPM Maximum overspeed : 2500 RPM (max. 20 sec)
PAGE 50 OF POH POWERPLANT LIMITATIONS AND PAGE 53 ENGINE INSTRUMENT MARKINGS g) Oil pressure (indicated values are corrected for pressure altitude) Minimum : 1.0 bar Maximum : 6.5 bar
Center of Gravity Limitations The center of gravity (CG position) for flight conditions must be between the following limits: Most forward flight CG: 2.35 m (92.52 in) aft of Datum Plane at 1250 kg (2756 lb) 2.35 m (92.52 in) aft of Datum Plane at 1468 kg (3236 lb) 2.40 m (94.49 in) aft of Datum Plane at max. take-off mass (see Section 2.7) linear variation in between
Most rearward flight CG: 2.42 m (95.28 in) aft of Datum Plane at 1250 kg (2756 lb) 2.49 m (98.03 in) aft of Datum Plane at 1600 kg (3527 lb) 2.49 m (98.03 in) aft of Datum Plane at max. take-off mass (see Section 2.7) linear variation in between
QUESTION 14 PAGE 63
QUESTION 15 PAGE 63 Clearly mentioned that powerplant load must not be
exceeded but only implied on (b). Still BOTH are correct in qb, so mark C (BOTH).
QUESTION 16 PAGE 64…..The answer in QB is wrong….Remember 18000
feet(5486 meters)
useable fuel each tank PAGE 53 Fuel qty. 0 US gal -- 0 to 25 US gal
And Page 260 shows that : Unusable fuel in main fuel tanks (2 x 1.0 US gal = 2 x 3.8 liter)
