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[[preprinted]] [[underlined]] CH-53A WEIGHT AND BALANCE [[/underlined]] ^[[NATOPS]] EVENT NUMBER ^[[???]] A/C SIDE NUMBER CJ- DAT ^[[WX/P4-11]] PA ^[[WX]] DA ^[[WX]] a. MAXIMUM TORQUE AVAILABLE - ^[[p 4-16]] b. MAXIMUM GROSS WEIGHT (HIGE 40' - ^[[9 4-23]] c. BASIC WEIGHT OF AIRCRAFT - ^[[23,000]] d. CREW WEIGHT (Number X 170#) - ^[[500]] } [[total]] ^[[1000]] e. OIL, TOOLS & EQUIPMENT - ^[[500]] } f. OPERATING WEIGHT (Add c,d,&e) - ^[[24,000]] g. FUEL LOAD - ^[[4,000]] h. TOTAL WEIGHT (Add f & g) - ^[[28,000]] i. MAXIMUM PAYLOD (With full fuel)(b minus h) - ^[[b-h]] j. INITIAL TAKE-OFF WEIGHT - ^[[normally h]] k. TORQUE REQUIRED (HIGE 40') - ^[[p 4-23]] [[underlined]] EMERGENCY OPERATIONS [[/underlined]] A. MAXIMUM SINGLE AIRSPEED - ^[[p 4-60]] B. MINIMUM SINGLE ENGINE AIRSPEED - ^[[p 4-60]] NOTE- Anytime a 40 foot hover can be accomplished with less than 10 knots headwind, single engine level flight capability is available. MAX ENDURANCE SINGLE ENGINE ^[[p 4-66]] Wf ^[[p 4-66]]Q ^[[4-66]]KTS MAX ENDURANCE TWO ENGINES ^[[p 4-63]] Wf ^[[p 4-63]]Q ^[[4-63]]KTS