An aircraft engine cowling (102) comprises a first cowling portion (104) and a second cowling portion (106) moveable relative to each other. A cowling latch (114) secures the first cowling portion (104) and the second cowling portion (106) in a closed position. The aircraft engine cowling (102) further comprises a deflection limiter band (122) and a deflection limiter latch (124) moveable between an engaged state and a disengaged state for the deflection limiter band (122). An interlock mechanism (240) prevents disengagement of the cowling latch (114) while the deflection limiter latch (124) is in the engaged state. The interlock mechanism (240) includes a lock element (124, 126) moveable between a first position that prevents disengagement of the cowling latch (114) and a second position (222) that enables disengagement of the cowling latch (114). The interlock mechanism (240) also includes an indicator paddle (242) movable to contact the deflection limiter latch (124). A linkage assembly (510) coordinates movement of the lock element (124, 126) with movement of the indicator paddle (242).


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    Title :

    COWLING LATCH INTERLOCK MECHANISM


    Additional title:

    VERRIEGELUNGSMECHANISMUS FÜR EINE VERKLEIDUNGSVERRIEGELUNG
    MÉCANISME DE VERROUILLAGE DE VERROU DE CAPOT



    Publication date :

    2024-11-06


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02K JET-PROPULSION PLANTS , Strahltriebwerke



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