AD 2015-07-03

At the compliance times specified in paragraphs (g)(1) through (g)(4) of this AD, inspect each engine mount beam using radiographic (x-ray), eddy current, and visual methods following the Accomplishment Instructions in Cessna Aircraft Company Multi-engine Service Letter No. MEL-54-01, dated March 20, 2015. If total hours time-in-service (TIS) on an engine mount beam is unknown, use the airplane's total hours TIS.

(1) For each engine mount beam that has accumulated less than 20,000 hours TIS, initially inspect at whichever of the following that occurs later and repetitively thereafter at intervals not to exceed 200 hours TIS as long as no cracks are found:

(i) At or before the accumulation of 15,000 hours TIS on each engine beam; or

(ii) Within the next 100 hours TIS after the effective date of this AD or within the next 90 days after the effective date of this AD, whichever occurs first.

(2) For each engine mount beam that has accumulated 20,000 hours TIS but no more than 24,999 hours TIS, initially inspect at whichever of the following that occurs first and repetitively thereafter at intervals not to exceed 200 hours TIS as long as no cracks are found:

(i) Within the next 75 hours TIS after the effective date of this AD; or

(ii) Within the next 60 days after the effective date of this AD.

(3) For each engine mount beam that has accumulated 25,000 hours TIS but no more than 30,000 hours TIS, initially inspect at whichever of the following that occurs first and repetitively thereafter at intervals not to exceed 200 hours TIS as long as no cracks are found:

(i) Within the next 50 hours TIS after the effective date of this AD; or

(ii) Within the next 45 days after the effective date of this AD.

(4) For each engine mount beam that has accumulated more than 30,000 hours TIS, initially inspect at whichever of the following that occurs first and repetitively thereafter at intervals not to exceed 200 hours TIS as long as no cracks are found:

(i) Within the next 25 hours TIS after the effective date of this AD; or

(ii) Within the next 30 days after the effective date of this AD.

If any cracks are found during any inspection required in paragraphs (g)(1) through (g)(4) of this AD, before further flight, contact Cessna Aircraft Company at the address specified in paragraph (m)(3) of this AD for an FAA-approved corrective action developed specifically for this AD.

Within 10 days after each inspection required in paragraphs (g)(1) through (g)(4) of this AD or within 10 days after the effective date of this AD, whichever occurs later, using the undated Attachment, “Inspection Results Form,” to Cessna Aircraft Company Multi-engine Service Letter No. MEL-54-01, dated March 20, 2015, report the results to the FAA, Wichita Aircraft Certification Office (ACO) at the address specified in paragraph (l) of this AD. Report the result of each inspection to the FAA, Wichita ACO, for one year after the date of the initial inspection required in paragraphs (g)(1) through (g)(4) of this AD. Also report the results of the initial inspection to Cessna at the address specified in paragraph (m)(3) of this AD.

A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120-0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES-200.