無法與 7 個以上設備互連者；
N. B. SEE ALSO 2B226
propellants', used in rocket systems capable of delivering at least a 500 kg payload to a range of at least 300 km.
or gel propellants', used in rocket systems capable of delivering at least a 500 kg payload to a range of at least 300 km.
少500 kg、射程至少300 km之火箭系統。
217 217
9B001 Equipment, tooling or fixtures, specially designed for manufacturing gas turbine blades, vanes or "tip shroud" castings, as follows:
9B001 Equipment, tooling or fixtures, specially designed for manufacturing gas turbine engine blades, vanes or "tip shrouds", as follows:
b. A gas supply total pressure equal to or greater than 3 MPa.
Technical Notes:
1. 'Aerothermodynamic test facilities' include plasma arc jet facilities and plasma wind tunnels for the study of thermal and mechanical effects of airflow on objects.
2. In 9B107 'missile' means complete rocket systems and unmanned aerial vehicle systems capable of a range exceeding 300 km.
設施與電漿風洞，用於研究氣流對物件的熱和機 械影響。
2. 9B107
所述之‵飛彈′係指射程或航程超過
300 km
之完整火箭系統及無人飛行載具系統。
221-222
無 Note: 9D105 includes "software" specially
designed for a manned "aircraft" converted to operate as "unmanned aerial vehicle", as follows:
a. "Software" specially designed or modified to integrate the conversion equipment with the
"aircraft" system functions; and
b. "Software" specially designed or modified to operate the "aircraft" as an "unmanned aerial vehicle".
說明：
9D105包括特別設計用於將載人〝航空
器〞轉換為〝無人飛行載具〞操作之〝軟體〞，
如下：
a.
特別設計或改裝之〝軟體〞，用於整合轉換 設備與〝航空器〞系統功能；及
b.
特別設計或改裝之〝軟體〞，用於如同〝無 人飛行載具〞般操作〝航空器〞。
222
無 Technical Note:
For the purposes of 9E003.a.1., stress-rupture life testing is typically conducted on a test specimen.
技術註解：
就
9E003.a.1.而言，應力斷裂試驗通常在一測試
樣本上進行。
221 222 a. Thermally decoupled liners designed to operate at 'combustor exit temperature' exceeding 1 883K
a. 'Thermally decoupled liners' designed to operate at 'combustor exit temperature'
a. 設計為在操作‵燃燒室出口溫度′超過1,883 K(1,610 °C)操作之‵熱解偶襯墊′；
(1 610°C); exceeding 1 883 K (1 610 °C);
222 222-223
Technical Note:
'Combustor exit temperature' is the bulk average gas path total (stagnation) temperature between the combustor exit plane and the leading edge of the turbine inlet guide vane (i.e., measured at engine station T40 as defined in SAE ARP 755A) when the engine is running in a 'steady state mode' of operation at the certificated maximum continuous operating temperature.
Technical Notes:
1. 'Thermally decoupled liners' are liners that feature at least a support structure designed to carry mechanical loads and a combustion facing structure designed to protect the support structure from the heat of combustion. The combustion facing structure and support structure have independent thermal displacement (mechanical displacement due to thermal load) with respect to one another, i.e. they are thermally decoupled.
2. 'Combustor exit temperature' is the bulk average gas path total (stagnation) temperature between the combustor exit plane and the leading edge of the turbine inlet guide vane (i.e., measured at engine station T40 as defined in SAE ARP 755A) when the engine is running in a 'steady state mode' of operation at the certificated maximum continuous operating temperature.
技術註解：
1.
‵熱解偶襯墊′為一襯墊至少具備一個支撐 結構設計以承載機械負載，以及一個燃燒覆蓋層 結構設計用於在燃燒產生熱時保護支撐結構。燃 燒覆蓋層結構與支撐結構在相互之間具有獨立 熱置換
(基於熱負載的機械置換
)，即其為熱解偶。
2.
‵燃燒室出口溫度′為，當發動機在‵穩定 狀態模式′下運轉至認證之最大連續操作溫度 時，燃燒室出口平面與渦輪機進氣導向葉片尖端
(即依照
SAE APR 755A所定義之
T40發動機站量 測
)兩者間之主體平均氣流總
(停滯
)溫度。
225 226
Note: 9E003.i. does not control "development" or
"production" "technology" for any of the following:
a. Inlet guide vanes;
b. Variable pitch fans or prop-fans;
Note: 9E003.i. does not control "technology" for any of the following:
a. Inlet guide vanes;
b. Variable pitch fans or prop-fans;
c. Variable compressor vanes;
說明：
9E003.i.不管制下列任一〝技術〞：
a.
進氣導片；
b.
可變節距風扇或螺旋槳風扇；
c.
可變壓縮機葉片；
d.
壓縮機排氣閥；或
c. Variable compressor vanes;
d. Compressor bleed valves; or
e. Adjustable flow path geometry for reverse thrust
d. Compressor bleed valves; or
e. Adjustable flow path geometry for reverse thrust.
e.