Quote from C152 ops manual
"FLIGHT LOAD FACTOR LIMITS
Flight Load Factors:
*Flaps Up: +4.4g, -1.76g
*Flaps Down: +3.5g _
"The design load factors are 150% of the above, and in all cases, the structure meets or exceeds design loads."
Note the negative 1.76G......
How can Cessna authorize that without a full inverted system? Perhaps Lycoming has a prohibitation with less than positive G in their engine manual?
Interesting combining the innocent questions of youth and the legal answers of the real world. I have to admit, that I am quite surprised by Cessna's apparent lack of warnings here.
"FLIGHT LOAD FACTOR LIMITS
Flight Load Factors:
*Flaps Up: +4.4g, -1.76g
*Flaps Down: +3.5g _
"The design load factors are 150% of the above, and in all cases, the structure meets or exceeds design loads."
Note the negative 1.76G......
How can Cessna authorize that without a full inverted system? Perhaps Lycoming has a prohibitation with less than positive G in their engine manual?
Interesting combining the innocent questions of youth and the legal answers of the real world. I have to admit, that I am quite surprised by Cessna's apparent lack of warnings here.
