AD 2018-03-03

Within the next 25 hours TIS after February 28, 2018 (the effective date of this AD), do a detailed visual inspection of the left and right forward lower carry through spar cap for cracks. Using a 10X magnifier visually inspect the bottom surface of the carry through spar cap in the areas around the fasteners located just inboard of the left-hand and right-hand forward lower wing fittings. If a crack is not positively identified during the detailed visual inspection but is suspected or the area is questionable, before further flight, do a surface eddy current inspection of the suspected area. Do these inspections using the Accomplishment Instructions in Textron Aviation Multi-engine Mandatory Service Letter MEL-57-01 and Textron Aviation Conquest Mandatory Service Letter CQL-57-01, both dated December 18, 2017, as applicable.

Using the compliance times listed in paragraphs (h)(1) through (3) of this AD, do a detailed visual inspection of the left and right forward lower carry through spar cap for cracks. Using a 10X magnifier visually inspect the bottom surface of the carry through spar cap in the areas around the fasteners located just inboard of the left-hand and right-hand forward lower wing fittings. If a crack is not positively identified during the detailed visual inspection but is suspected or the area is questionable, before further flight, do a surface eddy current inspection of the suspected area. Do these inspections using the Accomplishment Instructions in Textron Aviation Multi-engine Mandatory Service Letter MEL-57-01 and Textron Aviation Conquest Mandatory Service Letter CQL-57-01, both dated December 18, 2017, as applicable.

(1) For Models 401, 401A, 401B, 402, 402A, 402B, 402C, 411, 411A, 414, 414A, 421, and 421A airplanes: Before the accumulation of 15,000 TIS on the carry through spars or within the next 50 hours TIS after February 28, 2018 (the effective date of this AD), whichever occurs later.

(2) For Models 421B and 421C airplanes: Before the accumulation of 12,000 hours TIS on the carry through spars or within the next 50 hours TIS after February 28, 2018 (the effective date of this AD), whichever occurs later.

(3) For Model 425 airplanes: Before the accumulation of 11,000 TIS on the carry through spars or within the next 50 hours TIS after February 28, 2018 (the effective date of this AD), whichever occurs later.

If no cracks are found during the detailed visual inspections or the surface eddy current inspections required in paragraphs (g) and (h) of this AD, repetitively thereafter inspect at intervals not to exceed 50 hours TIS. Inspect as specified in paragraphs (g) and (h) of this AD using the service information specified in each paragraph as applicable.

If cracks are found during any inspection required in paragraphs (g) through (i) and paragraph (k) of this AD, before further flight, replace the carry through spar.

At the compliance times in paragraphs (k)(1) through (3) of this AD, do a detailed visual inspection of the left and right forward lower carry through spar cap for cracks. Using a 10X magnifier visually inspect the bottom surface of the carry through spar cap in the areas around the fasteners located just inboard of the left-hand and right-hand forward lower wing fittings. If a crack is not positively identified during the detailed visual inspection but is suspected or the area is questionable, before further flight, do a surface eddy current inspection of the suspected area. Do these inspections using the Accomplishment Instructions in Textron Aviation Multi-engine Mandatory Service Letter MEL-57-01 and Textron Aviation Conquest Mandatory Service Letter CQL-57-01, both dated December 18, 2017, as applicable.

(1) For Models 401, 401A, 401B, 402, 402A, 402B, 402C, 411, 411A, 414, 414A, 421, and 421A airplanes: Before the accumulation of 15,000 hours TIS on the newly installed carry through spar. If no cracks are found, repetitively thereafter inspect at intervals not to exceed 50 hours TIS.

(2) For Models 421B and 421C airplanes: Before the accumulation of 12,000 hours TIS on the newly installed carry through spar. If no cracks are found, repetitively thereafter inspect at intervals not to exceed 50 hours TIS.

(3) For Model 425 airplanes: Before the accumulation of 11,000 hours TIS on the newly installed carry through spar. If no cracks are found, repetitively thereafter inspect at intervals not to exceed 50 hours TIS.

Within 30 days after each inspection required by paragraphs (g) through (i) and paragraph (k) of this AD, report the results of the inspection to the FAA representative identified in paragraph (q) of this AD using the undated Attachment (titled Spar Cap Inspection Results Form and Spar Cap Inspection Results Form Continued) to Textron Aviation Multi-engine Mandatory Service Letter MEL-57-01 and Textron Aviation Conquest Mandatory Service Letter CQL-57-01, both dated December 18, 2017, as applicable. Please identify AD 2018-03-03 in the subject line if submitted through email.

Textron Aviation Conquest Service Bulletin CQB-57-01, Textron Aviation Multi-engine Service Bulletin MEB-57-01, and Textron Multi-engine Service Bulletin MEB-57-02, all dated December 20, 2017, provide the manufacturer's optional procedures for installing access panels for easier access to the forward carry through spars. This AD does not require installing the access panels, but does not restrict the owner/operator from doing so.

This AD allows credit for the initial inspection of the forward lower carry through spar cap required in paragraphs (g) and (h) of this AD if done before February 28, 2018 (the effective date of this AD) using the following documents:

(1) Models 401, 401A, 401B, 402, 402A, 402B airplanes: Cessna Aircraft Company Model 401/402 Supplemental Inspection Document, Supplemental Inspection Number 57-10-10, dated June 3, 2002.

(2) Model 402C airplanes: Cessna Aircraft Company Model 402C Maintenance Manual, Supplemental Inspection Number 57-10-14, dated June 3, 2002.

(3) Models 411 and 411A airplanes: Cessna Aircraft Company Model 411, Supplemental Inspection Document, Supplemental Inspection Number 57-10-10, dated January 6, 2003.

(4) Model 414 airplanes: Cessna Aircraft Company Model 414 Supplemental Inspection Document, Supplemental Inspection Number 57-10-10, dated August 1, 2002.

(5) Model 414A airplanes: Cessna Aircraft Company Model 414A Supplemental Inspection Document, Supplemental Inspection Number 57-10-14, dated August 1, 2002.

(6) Models 421, 421A, and 421B airplanes: Cessna Aircraft Company Model 421 Supplemental Inspection Document, Supplemental Inspection Number 57-10-10, dated March 3, 2003.

(7) Model 421C airplanes: Cessna Aircraft Company Model 421C Supplemental Inspection Document, Supplemental Inspection Number 57-10-14, dated January 6, 2003.

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 15 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.