Zlin Z 242 L weight & balance

Data source

AFM Fig. 1-5, 1-6; Section 2.15.1 Fig. 2-8; Fig. 2-16; Section 6, Fig. 6-1, 6-2, 6-3, 6-5, 6-7, 6-9 and sample problem p. 6-10/6-11 (pages 22-132 of z242l__afm__zlin-003-012-1.pdf) · version type

• Envelope read from Fig. 2-8 in % MAC and converted to arm with the manual's formula arm = 0.368 + %MAC/100 x 1.504 m (MAC 1.504 m, LEMAC 0.368 m aft of datum).
• Max takeoff weights: Normal 1090 kg (2400 lb), Utility 1020 kg (2250 lb), Acrobatic 970 kg (2140 lb). Max landing weight Normal 1050 kg (2315 lb), Utility and Acrobatic equal to takeoff (Fig. 1-6, 2-7). The lowest envelope line 820 kg is printed as the FAR 23.25 minimum weight in Fig. 2-8 and Fig. 6-9, so the zero fuel weight must be at least 820 kg too.
• Forward limit 19% MAC up to 900 kg, then a straight line to 22% MAC at 1090 kg (20.1% at 970 kg and 20.9% at 1020 kg on that line). Aft limits: Normal 23% at 820 kg to 26% at 1000 kg, 26% above; Utility 24.5% from 970 to 1020 kg; Acrobatic 22% at 820 kg to 24.5% at 970 kg.
• The moment check diagram Fig. 6-9, read back to arm, matches Fig. 2-8 within 0.05% MAC at every corner.
• Seat arms depend on seat position: L 242 seats front 0.856 / middle 0.906 / rear 0.956 m; E 242 seats positions 1 to 5: 0.856, 0.881, 0.906, 0.931, 0.956 m. Stations default to the front position, adjust for actual seat position.
• Max 100 kg per seat (applicable for L 242 and E 242 seats; air crew weight includes parachute). Record form shows 220 lb left and 250 lb right (100 kg is 220 lb); the lb values are inconsistent, verify.
• Auxiliary tank fuel and baggage are permitted in Normal category only.
• Fuel capacities (Fig. 2-16): main tanks 2 x 60 L (116 L usable), auxiliary tanks 2 x 55 L (108 L usable, Normal category only). Fuel is drained from the auxiliary tanks first. Fuel density 0.72 kg/L per the sample problem.
• Basic empty weight 730 kg at 0.653 m (476.7 kgm) is the Fig. 6-3 example; sample problem uses 760 kg / 447 kgm. Use the actual aircraft's weighing record.
• Sample problem p. 6-10/6-11 (760 kg at 447 kgm empty, 73 kg front seat, 96 kg rear seat, 120 L main, 40 L auxiliary, 20 kg baggage) reproduces at 1064.2 kg and 728.7 kgm, 21.06% MAC, as printed. The book calls it acceptable, but the forward limit of Fig. 2-8 at 1064 kg is 21.6% MAC, and Fig. 6-9 plots the point at about 1040 kg instead of 1064 kg. The envelope was kept as printed.
• Default load is two 80 kg occupants in the front seat position with full main tanks: with one 80 kg pilot the Fig. 6-3 empty airplane is only 810 kg, below the 820 kg minimum weight.
• Arms in front of the datum are negative (oil -0.434 m).
• Read from the POH by ZuluCheck and checked by a second reading; verify against your own manual.

For reference only. The aircraft’s approved flight manual and weighing report are the final authority.