Resumão - Portal do Piloto Edição 07 | Page 16

PÁG 16

AERONAVEGABILIDADE

Nas semanas anteriores falamos sobre o conceito de aeronavegabilidade, o processo de certificação e a manutenção da aeronave. Nesta semana em que tivemos um acidente aéreo em que dezenas de vidas de jovens atletas e profissionais da mídia conhecidos e adorados pela população, vamos interromper a sequência didática para falar rapidamente sobre alguns assuntos que vieram à tona devido ao acidente.

Um dos assuntos que mais chamou a atenção foi a possibilidade de ter havido ou não o alijamento do combustível pela aeronave ARJ-85. O requisito de alijamento de combustível está no FAR 25:

Sec. 25.1001 - Fuel jettisoning system.

(a) A fuel jettisoning system must be installed on each airplane unless it is shown that the airplane meets the climb requirements of Secs. 25.119 and 25.121(d) at maximum takeoff weight, less the actual or computed weight of fuel necessary for a 15-minute flight comprised of a takeoff, go-around, and landing at the airport of departure with the airplane configuration, speed, power, and thrust the same as that used in meeting the applicable takeoff, approach, and landing climb performance requirements of this Part.

(…)

Sec. 25.119 - Landing climb: All-engines-operating.

In the landing configuration, the steady gradient of climb may not be less than 3.2 percent, with the engines at the power or thrust that is available 8 seconds after initiation of movement of the power or thrust controls from the minimum flight idle to the go-around power or thrust setting--

(a) In non-icing conditions, with a climb speed of VREF determined in accordance with Sec. 25.125(b)(2)(i); and

(b) In icing conditions with the most critical of the landing ice accretion(s) defined in Appendices C and O of this part, as applicable, in accordance with § 25.21(g), and with a climb speed of V REF determined in accordance with § 25.125(b)(2)(ii).

Sec. 25.121 - Climb: One-engine inoperative

(…)

(d) Approach. In a configuration corresponding to the normal all- engines-operating procedure in which VSR for this configuration does not exceed 110 percent of the VSR for the related all-engines-operating landing configuration: configuration:

(1) The steady gradient of climb may not be less than 2.1 percent for two-engine airplanes, 2.4 percent for three-engine airplanes, and 2.7 percent for four-engine airplanes, with:

(i) The critical engine inoperative, the remaining engines at the go-around power or thrust setting;

(ii) The maximum landing weight;

(iii) A climb speed established in connection with normal landing procedures, but not exceeding 1.4 VSR; and

(iv) Landing gear retracted.

(2) The requirements of paragraph (d)(1) of this section must be met:

(i) In non-icing conditions; and

(1) The steady gradient of climb may not be less than 2.1 percent for two-engine airplanes, 2.4 percent for three-engine airplanes, and 2.7 percent for four-engine airplanes, with:

(i) The critical engine inoperative, the remaining engines at the go-around power or thrust setting;

(ii) The maximum landing weight;

(iii) A climb speed established in connection with normal landing procedures, but not exceeding 1.4 VSR; and

(iv) Landing gear retracted.

(2) The requirements of paragraph (d)(1) of this section must be met:

(i) In non-icing conditions; and

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