Airworthiness Directive · Amendment 39-22902 · Power lever
Cirrus Design Corporation Airplanes
This AD applies to Cirrus Design Corporation Model SR20, SR22, and SR22T airplanes, certificated in any category, that are equipped with upper power lever part number (P/N) 19181-001, 19181-002, or 46505-001.
The FAA is adopting a new airworthiness directive (AD) for certain Cirrus Design Corporation (Cirrus) Model SR20, SR22, and SR22T airplanes. This AD was prompted by a report of failure of the upper power lever. This AD requires repetitively inspecting (visual) the upper power lever for any crack(s) and depending on the results of any visual inspection, either inspecting (fluorescent penetrant) or replacing the upper power lever. This AD also requires reporting all inspection results to the FAA. The FAA is issuing this AD to address the unsafe condition on these products.
(1) Initially, at whichever time occurs latest in paragraphs (g)(1)(i) through (iii) of this AD and thereafter at intervals not to exceed 110 hours time-in-service (TIS), visually inspect the upper power lever in accordance with paragraphs A. through F. of the Accomplishment Instructions in Cirrus SR2X Service Bulletin SB2X-76-05, dated October 29, 2024 (Cirrus SB2X-76-05).
(i) Before any upper power lever identified in paragraph (c) of this AD accumulates 1,200 hours TIS,
Note 1 to paragraph (g)(1)(i): These parts are not serialized. If by checking the logbook, you cannot determine how many hours the upper power lever has since installation, then you may use the hours TIS of the airplane.
(ii) Within 10 hours TIS on the upper power lever after the effective date of this AD; or
(iii) Within 15 days after the effective date of this AD.
(2) If any crack(s) are found during any inspection required by paragraph (g)(1) of this AD, before further flight, replace the upper power lever with a new (zero hours TIS) upper power lever and do the actions in accordance with paragraphs L. through N. of the Accomplishment Instructions in Cirrus SB2X-76-05, as applicable.
(3) If no crack(s) are found during any inspection required by (g)(1) of this AD, before further flight, perform a fluorescent penetrant inspection in accordance with paragraphs G. through J. of the Accomplishment Instructions in Cirrus SB2X-76-05.
(i) If any crack(s) are found during any inspection required by paragraph (g)(3) of this AD, before further flight, replace the upper power lever with a new (zero hours TIS) upper power lever and do the actions in accordance with paragraphs L. through N. of the Accomplishment Instructions in Cirrus SB2X-76-05, as applicable.
(ii) If no crack(s) are found during any inspection required by paragraph (g)(3) of this AD, reinstall the existing upper power lever and do the actions in accordance with paragraphs L. through N. of the Accomplishment Instructions in Cirrus SB2X-76-05, as applicable.
(4) Cirrus SB2X-76-05 specifies to return cracked (damaged) upper power levers to Cirrus, this AD does not require that action but requires removing any cracked (damaged) upper power lever from service.
Within 5 days after the inspections required by paragraphs (g)(1) and (3) of this AD or within 5 days after the effective date of this AD, whichever occurs later, report all inspection results to the FAA at the address specified in paragraph (j) of this AD. The report must include the airplane registration and serial number, results of each inspection, the airplane's hours TIS, and any additional operator/mechanic comments.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
