Badan Kebijakan Transportasi, Kementerian Perhubungan
Publishing Year
2017
Publishing Place
Collation
Abstract/Notes
Pesawat dengan kategori Short Take-Off Landing pada umumnya adalah pesawat ringan yang mempunyai berat take-off antara 20.000 lb (9.072 kg) hingga 50.000 lb (22.680 kg) dengan kemampuan melewat irintangan setinggi 50 ft (15 m) untuk jarak take-off dan landing sejauh 1.500 ft (450 m). Pengembangan pesawat dengan kategori tersebut perlu memperhatikan tiga persyaratan umum yaitu kemampuan aerodinamika yang tinggi, tenaga mesin yang besar, dan teknik pilot yang baik yang disertai dengan kekuatan struktur yang mampu menahan beban berat. Pada studi kasus ini, penulis menggunakan data prestasi terbang Short Field Landing pesawat CN235-100 (serial N-16) dengan menggunakan flap 230 pada saat pengujian performance trade-off di PT Dirgantara Indonesia pada tahun 1996. Pengujian tersebut juga termasuk uji rejected take-off atau accelerate stop distance dengan menggunakan flap 100 pada tenaga penuh dimana kemudian salah satu mesin dimatikan untuk mencapai kondisi kritis dan pilot mengurangi daya propulsi mesin lainnya untuk dapat berhenti di ujung landasan. Beberapa rekomendasi pilot diberikan pada bagian kesimpulan.
[The Short Takeoff Landing Method (CN235 Turbo Prop Field Performance Test Case Study)] The aircraft category of Short Take-Off Landing, in general, including lightweight aircrafts with take-off weight between 20.000 lb (9.072 kg) and 50.000 lb (22.680 kg) and capable in exceeding 50 ft (15 m) obstacle height with only 1.500 ft (450 m) of take-off and landing distance. Thera are, at least, three general requirements that have to be considered in order to develop this category of aircraft; high aerodynamic performance, powerful engine, qualified skill of pilot, and also the strength of aircraft structure that can sustain heavy load.As for the study case, the author used the flight performance data of CN235-100 (serial N-16) Short Field Landing with 230 flap that was tested in Indonesian Aerospace Industry in 1996 for its trade-off performance. There was also rejected take-off or accelerate stop distance test with 100 flap and full throttle where one of the engine, then suddenly, shut down in order to achieve critical condition and later the power of the another engine being reduced by the pilot so that the aircraft can stop at the end of the runway. Several pilot recommendations are given in the conclusion chapter.
