AD 2006-24-07

You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done.

(f) For propellers listed by SN in Table 1 or Table 2 overhauled or repaired by CSE after November 2003, or overhauled by an FAA-approved propeller repair facility after October 2003, no further action is required.

Before further flight, perform a document search of airplane and propeller records to determine if the propeller was involved in a ground strike.

(h) If the propeller was involved in a ground strike, perform the requirements specified in paragraph (j) or paragraph (k) of this AD within 10 flight hours (FH) time-in-service (TIS) after the effective date of this AD, or 2 years after the effective date of this AD, whichever is earlier.

(i) For all propellers listed by SN in Table 1 or Table 2 of this AD, not involved in a ground strike, use the compliance schedule in the following Table 3 to perform the requirements specified in paragraph (j) or paragraph (k) of this AD as applicable.

For Hartzell propellers listed by SN in Table 1 of this AD, do the following:

(1) Disassemble the propeller.

(2) Clean all disassembled propeller parts.

(3) Perform a visual inspection for the following conditions:

(i) Wear or damage such as cracks, corrosion, scratches, or nicks.

(ii) Except for blades installed new at the last CSE maintenance action, examine for:

(A) Bent or damaged pitch change knobs.

(B) Damage in the bore area of the blade shank.

(C) Damage in the blade balance hole.

(iii) Damage that indicates a previous ground strike (if applicable).

(iv) Unacceptable wear or damage in areas where shot peening is required. It is not necessary to strip the paint and corrosion protective coatings from the external surface of the blade. It is also not necessary to perform dimensional measurements on the external surface of the blade unless there is evidence of damage that has occurred since CSE returned the propeller to service.

(v) Confirm that CSE Aviation correctly performed the repairs listed in the manufacturers maintenance manuals. An example of a maintenance manual repair is chamfering of the hub grease fitting hole on Hartzell “Y” shank series propellers.

(4) Perform all Eddy Current inspections applicable.

(5) Repair and replace with serviceable parts, as necessary.

(6) Assemble and test.

(7) Confirm that hubs affected by AD 2001-23-08 are returned to service only on aircraft affected by that AD.

For McCauley propellers listed by SN in Table 2 of this AD, do the following:

(1) Disassemble the propeller.

(2) Clean all disassembled propeller parts.

(3) Perform a visual inspection for the following conditions:

(i) Wear or damage such as cracks, corrosion, scratches or nicks.

(ii) Damage that indicates a previous ground strike (if applicable).

(iii) Unacceptable wear or damage in areas where shot peening is required, paying particular attention to hub internal shot peened surfaces and blade shank peening. It is not necessary to strip the paint and corrosion protective coatings from the external surface of the blade. It is also not necessary to perform dimensional measurements on the external surface of the blade unless there is evidence of damage that has occurred since CSE returned the propeller to service.

(4) Inspect threaded surfaces of threaded blade shanks with a 10X magnifying glass for scratches parallel to retention threads in the thread root of the first four outboard blade threads. If the retention threads are scratched, repair is not allowed.

(5) Confirm that CSE Aviation correctly performed repairs or modifications listed in the manufacturer's maintenance instructions.

(6) Repair and replace with serviceable parts, as necessary.

(7) Assemble and test.

For the purposes of this AD:

(1) Overhauling a propeller is not necessary to comply with the requirements specified in paragraph (j) or paragraph (k) of this AD. If you do not overhaul the propeller, the TSO does not change.

(2) Unacceptable wear is wear or damage that can penetrate the shotpeen compressive layer.