(3)
The impact to the front of the engine from the single large bird and the single largest medium bird which can enter the inlet must be evaluated. It must be shown that the associated components when struck under the conditions prescribed in paragraphs (b) or (c) of this section, as applicable, will not a.ect the engine to the extent that it cannot comply with the requirements ofparagraphs(b)(3) and(c)(6) of this section.

(4)
For an enginethatincorporates aninletprotectiondevice, compliance withthis section shall be established with the device functioning. The engine approval will be endorsed to show that compliance with the requirements has been established with the device functioning.

(5)
Objects that are accepted by the Administrator may be substituted for birds when conducting thebirdingestiontests requiredbyparagraphs(b) and(c) of this section.

(6)
Ifcompliance withthe requirements ofthis sectionis not established,the engine type certi.cation documentation will show that the engine shall be limited to aircraft installations in which it is shown that a bird cannot strike the engine, or be ingested into the engine, or adversely restrict air.ow into the engine.

(b) Large birds. Compliance with the large bird ingestion requirements shall be in ac-cordance with the following :
(1)
The large bird ingestion test shall be conducted using one bird of a weight determined from (Table 92.1, p. 1154) aimed at the most critical exposed loca-tion on the .rst stage rotor blades and ingested at a bird speed of 200-knots for engines to be installed on airplanes, or the maximum airspeed for normal rotorcraft .ight operations for engines to be installed on rotorcraft.

(2)
Power lever movement is not permitted within 15 seconds following ingestion of the large bird.

(3)
Ingestion of a single large bird tested under the conditions prescribed in this section may not cause the engine to :

(i)
Catch .re;

(ii)
Release hazardous fragments through the engine casing;

(iii) Generateloadsgreaterthanthose ultimateloads speci.edunder r33.23(a); or
(iv) Lose the ability to be shut down.

(4)
Compliance with the large bird ingestion requirements of this paragraph may be shown by demonstrating that the requirements of r33.94(a) constitute a more severe demonstration of blade containment and rotor unbalance than the requirements of this paragraph.

′
Elodie Roux. Septembre 2003
SubpartE :Design andConstruction;TurbineAircraftEngines
Engine Inlet Throat Area (A) Square-meters (square-inches)  Bird Weight kg. (lb.) 
1.35 (2,092). A  1.85 (4.07) minimum, unless a smaller bird is determined to be a more severe demonstra-tion. 
1.35 (2,092) ≤ A. 3.90 (6,045)  2.75 (6.05) 
3.90 (6,045) ≤ A  3.65 (8.03) 

Tab. 92.1 –(Table of r33.76) : Large Bird Weight Requirements
(c) Small and medium birds. Compliance with the small and medium bird ingestion requirements shall be in accordance with the following :
(1)
Analysisorcomponenttest,orboth, acceptabletotheAdministrator,shallbe conducted to determine the critical ingestion parameters a.ecting power loss anddamage.Criticalingestionparameters shallinclude,but are notlimitedto, the a.ects of bird speed, critical target location, and .rst stage rotor speed. The critical bird ingestion speed should re.ect the most critical condition within the range of airspeeds used for normal .ight operations up to 1,500 feet above ground level, but not less than V1 minimum for airplanes.

(2)
Mediumbirdenginetestsshallbeconducted soastosimulatea .ock encounter, and will use the bird weights and quantities speci.ed in (Table 92.2, p. 1156). When only one bird is speci.ed, that bird will be aimed at the engine core primary.owpath;theothercriticallocationsontheenginefaceareamustbe addressed, as necessary, by appropriate tests or analysis, or both. When two or more birds are speci.ed in (Table 92.2, p. 1156), the largest of those birds mustbeaimed attheenginecoreprimary .owpath,and asecondbird must be aimed at the most critical exposed location on the .rst stage rotor blades. Any remaining birds must be evenly distributed over the engine face area.
　
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 5(138)