Airworthiness Directive · Amendment 39-21222 · Fuselage
Textron Aviation Inc. Airplanes
This AD applies to the following Textron Aviation Inc. (type certificate previously held by Cessna Aircraft Company) model airplanes, certificated in any category:
The FAA is adopting a new airworthiness directive (AD) for certain Textron Aviation Inc. (Textron) Model 172N, 172P, 172Q, 172RG, F172N, F172P, FR172K, R172K, 182E, 182F, 182G, 182H, 182J, 182K, 182L, 182M, 182N, 182P, 182Q, 182R, T182, F182P, F182Q, FR182, R182, TR182, 206, P206, P206A, P206B, P206C, P206D, P206E, TP206A, TP206B, TP206C, TP206D, TP206E, U206, U206A, U206B, U206C, U206D, U206E, U206F, U206G, TU206A, TU206B, TU206C, TU206D, TU206E, TU206F, TU206G, 207, 207A, T207, T207A, 210-5 (205), 210-5A (205A), 210B, 210C, 210D, 210E, 210F, and T210F airplanes. This AD was prompted by cracks found in the lower area of the forward cabin doorpost bulkhead. This AD requires repetitively inspecting the lower area of the forward cabin doorposts at the strut attach fitting for cracks and repairing any cracks. The FAA is issuing this AD to address the unsafe condition on these products.
(1) For airplanes without a lower forward doorpost bulkhead and wing strut fitting reinforcement service kit (service kit) installed in accordance with Cessna Single Engine Service Bulletin SEB95-19, dated December 29, 1995 (SEB95-19), or Cessna Single Engine Service Bulletin SEB93-5, Revision 2, dated May 29, 2019 (SEB93-5R2): At the applicable compliance time specified in paragraph (g)(1)(i) or (ii) of this AD, do a visual inspection of the lower forward doorpost at the strut attach fitting for cracks in accordance with steps 1.A., 1.B., 1.C., and 1.B. (the step following step 1.C.) of the Accomplishment Instructions in SEB95-19; or steps 1.A. and 1.B. of the Accomplishment Instructions in SEB93-5R2; as applicable to your model airplane.
(i) For airplanes that have accumulated less than 4,000 hours time-in-service (TIS) as of the effective date of this AD: Initially inspect prior to the accumulation of 4,000 hours TIS or within the next 200 hours TIS after the effective date of this AD, whichever occurs later.
(ii) For airplanes that have accumulated 4,000 or more hours TIS as of the effective date of this AD: Initially inspect within 200 hours TIS after the effective date of this AD or within 12 calendar months after the effective date of this AD, whichever occurs first.
(2) For airplanes with a service kit installed in accordance with SEB95-19 or SEB93-5R2: At the later of the times specified in paragraphs (g)(2)(i) and (ii) of this AD, do a visual inspection of the lower forward doorpost at the strut attach fitting for cracks in accordance with steps 1.A., 1.B., 1.C., and 1.B. (the step following step 1.C.) of the Accomplishment Instructions in SEB95-19; or steps 1.A. and 1.B. of the Accomplishment Instructions in SEB93-5R2; as applicable to your model airplane. Do not remove the installed service kit; instead, inspect for cracking that extends beyond the modified parts.
(i) At the applicable time specified in paragraph (g)(1)(i) or (ii) of this AD.
(ii) Within 1,000 hours TIS or 36 calendar months, whichever occurs first, since installing the service kit.
(1) If no cracks are found during the initial inspection required by paragraph (g)(1) or (2) of this AD, thereafter repeat the inspection at intervals not to exceed 36 calendar months or 1,000 hours TIS, whichever occurs first from the last inspection, as long as no cracks are found.
(2) If cracks are found during any inspection required by paragraph (g)(1) or (h)(1) of this AD, do the inspection specified in paragraph (g)(2) of this AD within 36 calendar months or 1,000 hours TIS, whichever occurs first after installing the service kit required by paragraph (i)(1) of this AD. Thereafter, repeat the inspection at intervals not to exceed 36 calendar months or 1,000 hours TIS, whichever occurs first from the last inspection, as long as no additional cracks are found.
(1) If cracks are found during any inspection required by paragraph (g)(1) or paragraph (h)(1) of this AD, before further flight, install a service kit in accordance with step 1.D. of the Accomplishment Instructions in SEB95-19; or step 1.C. of the Accomplishment Instructions in SEB93-5R2; as applicable to your model airplane.
(2) If cracks are found during any inspection required by paragraph (g)(2) or (h)(2) of this AD, before further flight, repair the area using a method approved by the Manager, Wichita ACO Branch, FAA. For a repair method to be approved by the Manager, Wichita ACO Branch as required by this paragraph, the Manager's approval letter must specifically refer to this AD. You may use the contact information in paragraph (n)(1) of this AD to obtain FAA approval of your repair method.
Within 30 days after the effective date of this AD, or within 30 days after completing the initial inspection required by paragraph (g) of this AD, whichever occurs later, report the findings of the initial inspection (regardless if cracks were found or not) to the FAA at Wichita-COS@faa.gov. Thereafter, within 30 days after completing each repetitive inspection required by paragraph (h) of this AD, if any crack was found, report the crack findings to the FAA at Wichita-COS@faa.gov. Include in your reports the following information:
(1) Name and address of the owner;
(2) Date of the inspection;
(3) Name, address, telephone number, and email address of the person submitting the report;
(4) Airplane serial number and total hours TIS on the airplane at the time of the inspection; and
(5) If any crack was found during the inspection, provide detailed crack information as specified below:
(i) A sketch or picture detailing the crack location;
(ii) Measured length of the crack(s) found;
(iii) Installation of a Cessna service kit or any other kit or repair before the inspection; and
(iv) Installation of any supplemental type certificates (STCs), alterations, repairs, or field approvals affecting the area of concern or affecting gross weight.
