§3.85 Climb—(a) Normal climb condition.

The steady rate of climb at sea level shall be at least 300 feet per minute, and the steady angle of climb at least 1:12 for landplanes or 1:15 for seaplanes with: (1) Not more than maximum continuous power on all engines, (2) Landing gear fully retracted, (3) Wing flaps in take-off position, (4) Cowl flaps in the position used in cooling tests specified in §§ 3.581-3.596, (b) Climb with inoperative engine. All multiengine airplanes having a stalling speed V;, greater than 70 miles per hour or a maximum weight greater than 6,000 poutids shall have a steady rate of climb of at least 0.02 Vs,” in feet per minute at an altitude of 5,000 feet with the critical engine inoperative and: (1) The remaining engines operating at not more than maximum continuous power, . (2) The inoperative propeller in the minimum drag position, (3) Landing gear retracted, (4) Wing flaps in the most favorable position, (5) Cowl flaps in the position used in cooling tests specified in §§ 3.581-3.596. (c) Balked landing conditions. The steady angle of climb at sea level shall be at least 1:30 with: (1) Take-off power on all engines, (2) Landing gear extended, (3) Wing flaps in landing position. If rapid retraction is possible with safety without loss of altitude and without requiring sudden changes of angle of attack or exceptional skill on the part of the pilot, wing flaps may be retracted. §3.85a Climb requirements; airplanes of 6,000 lbs. or less. Airplanes having a maximum certificated take-off weight of 6,000 lbs. or less shall comply with the requirements of this section. (a) Climb; take-off climb condition. The steady rate of climb at sea level shal] not be less than 10 Vs, or 300 feet per minute, whichever is the greater, with: (1) Take-off power, (2) Landing gear extended, (3) Wing flaps in take-off position, (4) Cowl flaps in the position used in cooling tests specified in §§ 3.581 through 3.596. (b) Climb with inoperative engine. All multiengine airplanes having a stalling speed Vs, greater than 70 miles per hour shall have a steady rate of climb of at least 0.02 Vs,’ in feet per minute at an altitude of 5,000 feet with the critical engine inoperative and: (1) The remaining engines operating at not more than maximum continuous power, (2) The inoperative propeller in the minimum drag position, (3) Landing gear retracted, (4) Wing flaps in the most favorable position, (5) Cowl.flaps in the position used in cooling tests specified in $§ 3.581 through 3.596, (ce) Climb; balked landing conditions, The steady rate of climb at sea level shall not be less than 5 Vs, or 200 feet per minute, whichever is the greater, with: (1) Take-off power, (2) Landing gear extended, (3) Wing flaps in the landing position. If rapid retraction is possible with safety, without loss of altitude and without requiring sudden changes of angle of attack or exceptional skill on the part of the pilot, wing flaps may be retracted. LANDING