Main Landing Gear Clause Samples
The 'Main Landing Gear' clause defines the requirements and specifications for the primary landing gear system of an aircraft. It typically outlines the design standards, materials, and performance criteria that the main landing gear must meet, such as load-bearing capacity, retraction mechanisms, and compliance with aviation regulations. This clause ensures that the main landing gear is safe, reliable, and suitable for the intended aircraft operations, thereby addressing safety concerns and regulatory compliance in aircraft design and manufacturing.
Main Landing Gear. (i) Outer cylinder.
(ii) Inner cylinder, including axles.
(iii) Upper and lower side struts, including spindles, universals and reaction links.
(iv) Drag strut.
(v) Orifice support tube.
(vi) Downlock links including spindles and universals.
(vii) Torsion links.
(viii) ▇▇▇▇ crank.
(ix) Trunnion link.
(x) Actuator beam, support link and beam arm.
Main Landing Gear. (a) Outer cylinder.
(b) Inner cylinder.
Main Landing Gear. (a) Outer cylinder.
(b) Inner cylinder.
(c) Upper and lower side struts, including spindles and universals.
(d) Drag strut.
(e) Side strut reaction link.
(f) Side strut support link.
(g) Downlock links including spindles and universals.
(h) Orifice plate.
(i) Trunnion link.
(j) Truck beam.
Main Landing Gear. (xxxviii) Outer cylinder.
Main Landing Gear. (i) Outer cylinder.
(ii) Inner cylinder.
(iii) Upper and lower side brace, including spindles
(iv) Upper and lower drag brace, including spindles and shackle. “[***]” This information is subject to confidential treatment and has been omitted and filed separately with the commission ▇▇▇▇ Terms Updates LA Page 44
(v) Downlock links including spindles.
(vi) Torsion links.
(vii) Truck beam.
(viii) Axles.