Federal Aviation Administration, DOT Pt. 121, App. C 33. Carriage of cargo in passenger compartments. Section 121.285 is not applicable to nontransport category C-46 cargo airplanes. 34. Carriage of cargo in cargo compartments. A standard cargo loading and tiedown arrangement set forth in the operator-s manual and found acceptable to the Administrator must be used in complying with Section 121.287. 35. Performance data. Performance data on Curtiss model C-46 airplane certificated for maximum weight of 45,000 and 48,000 pounds for cargo-only operations. 1. The following performance limitation data, applicable to the Curtiss model C-46 airplane for cargo-only operation, must be used in determining compliance with SectionSection 121.199 through 121.205. These data are presented in the tables and figures of this appendix. (b) Curtiss C-46 certificated for maximum weight 48,000 pounds. (1) Effective length of runway required when effective length is determined in accordance with Section 121.171 (distance to accelerate to 93 knots TIAS and stop, with zero wind and zero gradient). (Factor = 1.00) TABLE 1 - TAKEOFF LIMITATIONS 1 Ref. Fig. 1(b)(1) for weight and distance for altitudes above 6,000-. (a) Curtiss C-46 certificated for maximum weight of 45,000 pounds. (1) Effective length of runway required when effective length is determined in accordance with Section 121.171 (distance to accelerate to 93 knots TIAS and stop, with zero wind and zero gradient). (Factor = 1.00) [Distance in feet] Standard altitude in feet S.L ..................... 1,000 .................. 2,000 .................. 3,000 .................. 4,000 .................. 5,000 .................. 6,000 .................. 7,000 .................. 8,000 .................. Airplane weight in pounds 39,000 4,110 4,250 4,400 4,650 4,910 5,160 5,420 5,680 5,940 S.L ....................................... 1,000 .................................... 2,000 .................................... 3,000 .................................... 4,000 .................................... 5,000 .................................... 6,000 .................................... 7,000 .................................... 8,000 .................................... 4,110 4,250 4,400 4,650 4,910 5,160 5,420 5,680 5,940 42,000 Standard altitude in feet 4,290 4,440 4,600 4,880 5,170 5,450 5,730 6,000 6,280 45,000 1 4,570 4,720 4,880 5,190 5,500 5,810 6,120 6,440 (1) 1 Ref. Fig. 1(a)(1) for weight and distance for altitudes above 7,000-. (2) Actual length of runway required when effective length, considering obstacles, is not determined (distance to accelerate to 93 knots TIAS and stop, divided by the factor 0.85). S.L ..................... 1,000 .................. 2,000 .................. 3,000 .................. 4,000 .................. 5,000 .................. 6,000 .................. 7,000 .................. 8,000 .................. S.L ....................................... 1,000 .................................... 2,000 .................................... 3,000 .................................... 4,000 .................................... 5,000 .................................... 6,000 .................................... 7,000 .................................... 8,000 .................................... 4,830 5,000 5,170 5,470 5,770 6,070 6,380 6,680 6,990 Airplane weight in pounds 39,000 4,830 5,000 5,170 5,470 5,770 6,070 6,380 6,680 6,990 42,000 5,050 5,230 5,410 5,740 6,080 6,410 6,740 7,070 7,410 42,000 5,050 5,230 5,410 5,740 6,080 6,410 6,740 7,070 7,410 45,000 1 5,370 5,550 5,740 6,100 6,470 6,830 7,200 7,570 (1) 1 Ref. Fig. 1(a)(2) for weight and distance for altitudes above 7,000-. 5,370 5,550 5,740 6,100 6,470 6,830 7,200 7,570 7,940 08:20 May 17, 2019 Jkt 247048 PO 00000 Frm 00271 Fmt 8010 5,830 6,030 6,230 6,670 7,120 7,560 8,010 (1) (1) TABLE 2 - EN ROUTE LIMITATIONS 45,000 44,000 43,000 42,200 41,000 40,000 39,000 ............................................ ............................................ ............................................ ............................................ ............................................ ............................................ ............................................ Terrain clearance (feet) 1 6,450 7,000 7,500 8,000 9,600 11,000 12,300 Blower setting Low. Do. Do. High. Do. Do. Do. 1 Highest altitude of terrain over which airplanes may be operated in compliance with Section 121.201. Ref. Fig. 2(a). (b) Curtiss model C-46 certificated for maximum weight of 48,000 pounds or with engine installation approved for 2,550 revolutions 261 VerDate Sep<11>2014 48,000 1 45,000 (a) Curtiss model C-46 certificated for maximum weight of 45,000 pounds (based on a climb speed of 113 knots (TIAS)). Weight (pounds) Airplane weight in pounds 39,000 4,950 5,130 5,300 5,670 6,050 6,420 6,800 (1) (1) 1 Ref. Fig. 1(b)(2) for weight and distance for altitudes above 6,000-. [Distance in feet] Standard altitude in feet 4,570 4,720 4,880 5,190 5,500 5,810 6,120 6,440 6,750 [Distance in feet] Standard altitude in feet 39,000 4,290 4,440 4,600 4,880 5,170 5,450 5,730 6,000 6,280 48,000 1 45,000 (2) Actual length of runway required when effective length, considering obstacles, is not determined (distance to accelerate to 93 knots TIAS and stop, divided by the factor 0.85). [Distance in feet] Airplane weight in pounds 42,000 Sfmt 8002 Y:\SGML\247048.XXX 247048