(d)
For an engine that incorporates a protection device, compliance with this section need not be demonstrated with respect to foreign objects to be ingested under the conditionsprescribedinparagraph(e) of this sectionifitis shownthat–

′
Elodie Roux. Septembre 2003
SubpartE :Design andConstruction;TurbineAircraftEngines
Engine Inlet Throat Area (A)– Square-meters (square-inches)  Bird quantity  Bird weight kg. (lb.) 
0.05 (77.5) . A  none 
.05 (77.5) ≤ A . 0.10 (155)  1  0.35 (0.77) 
0.10 (155) ≤ A . 0.20 (310)  1  0.45 (0.99) 
0.20 (310) ≤ A . 0.40 (620)  2  0.45 (0.99) 
0.40 (620) ≤ A . 0.60 (930)  2  0.70 (1.54) 
0.60 (930) ≤ A . 1.00 (1,550)  3  0.70 (1.54) 
1.00 (1,550) ≤ A . 1.35 (2,092)  4  0.70 (1.54) 
1.35 (2,092) ≤ A . 1.70 (2,635)  1  1.15 (2.53) 
plus 3  0.70 (1.54) 
1.70 (2,635) ≤ A .2.10 (3,255)  1  1.15 (2,53) 
plus 4  0.70 (1.54) 
2.10 (3,255) ≤ A . 2.50 (3,875)  1  1.15 (2.53) 
plus 5  0.70 (1.54) 
2.50 (3,875) ≤ A . 3.90 (6045)  1  1.15 (2.53) 
plus 6  0.70 (1.54) 
3.90 (6045) ≤ A .4.50 (6975)  3  1.15 (2.53) 
4.50 (6975) ≤ A  4  1.15 (2.53) 

Tab. 92.2–(Tableofr33.76):MediumFlockingBirdWeightandQuantityRequirements
Engine Inlet Throat Area (A)–square-meters (square-inches)  Bird quantity  Bird weight kg.(lb.) 
1.35 (2,092). A  None 
1.35 (2,092) . A . 2.90 (4,495)  1  1.15 (2.53) 
2.90 (4,495) . A . 3.90 (6,045).  2  1.15 (2.53) 
3.90 (6,045) . A  1  1.15 (2.53) 
plus 6  0.70 (1.54) 

Tab. 92.3 –(Table of r33.76) : Additional Integrity Assessment
(1)
Such foreign objects are of a size that will not pass through the protective device;

(2)
The protective device will withstand the impact of the foreign objects and

(3)
The foreign object, or objects, stopped by the protective device will not obs-truct the .ow of induction air into the engine with a resultant sustained re-duction in power or thrust greater than those values required by paragraph (c)of this section.

(e) Compliance withparagraph(c) of this section mustbe shownby enginetest under the following ingestion conditions :
(1) Ice quantity will be the maximum accumulation on a typical inlet cowl and engineface resultingfrom a2-minutedelayin actuating the anti-icing system; or a slab ofice whichis comparablein weight or thicknessfor that size engine.
(2)
The ingestion velocity will simulate ice being sucked into the engine inlet.

(3)
Engine operation will be Maximum Cruise power or thrust.

(4)
The ingestion will simulate a continuous maximum icing encounter at 25 de-grees Fahrenheit.]

Amdt. 33-20, E.. 12/13/2000
FAR33.78 :[Rain andhailingestion.]
(a)
[Allengines.

(1)
Theingestion oflargehailstones(0.8to0.9 speci.cgravity) atthe maximum true air speed, up to15,000feet(4,500 meters), associated with a representa-tive aircraft operating in rough air, with the engine at maximum continuous power, may not cause unacceptable mechanical damage or unacceptable po-wer or thrust loss after the ingestion, or require the engine to be shut down. One-half the number of hailstones shall be aimed randomly over the inlet face area and the other half aimed at the critical inlet face area. The hailstones shall be ingested in a rapid sequence to simulate a hailstone encounter and the number and size of the hailstones shall be determined as follows :
　
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本文鏈接地址：FAA規(guī)章 美國聯(lián)邦航空規(guī)章 Federal Aviation Regulations 5(140)