Airworthiness Directive · Amendment 39-15895 · Cessna Aircraft Company (Type Certificate Previously Held by Columbia Aircraft Manufacturing (Previously The Lancair Company)) Models LC40-550FG, LC41-550FG, and LC42-550FG Airplanes
Cessna Aircraft Company (Type Certificate Previously Held by Columbia Aircraft Manufacturing (Previously The Lancair Company)) Models LC40-550FG, LC41-550FG, and LC42-550FG Airplanes
Superseded. A later AD replaced this one: AD 2011-03-04. Comply with the one in force.
This AD applies to the following airplane models and serial numbers that are certificated in any category:
| Model | Serial Nos. |
|---|---|
| LC40-550FG | 40001 through 40079. |
| LC41-550FG | 41001 through 41800, 411001 and subsequent. |
| LC42-550FG | 42001 through 42569, 421001 and subsequent. |
We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company (Type Certificate previously held by Columbia Aircraft Manufacturing (previously The Lancair Company)) Models LC40- 550FG, LC41-550FG, and LC42-550FG airplanes. This AD requires you to repetitively inspect the rudder hinges and the rudder hinge brackets for damage, i.e., cracking, deformation, and discoloration. If damage is found during any inspection, this AD also requires you to replace the damaged rudder hinge and/or rudder hinge bracket. This AD results from reports that cracked lower rudder hinge brackets were found on two of the affected airplanes. We are issuing this AD to detect and correct damage in the rudder hinges and the rudder hinge brackets, which could result in failure of the rudder. This failure could lead to loss of control.
To address this problem, you must do the following per Cessna Aircraft Company Single Engine Service Bulletin SB09-27-01, dated April 13, 2009, unless already done:
| Condition | Initial inspection | Repetitive inspection |
|---|---|---|
| (1) For airplanes with 25 hours time-in-service (TIS) or more as of May 11, 2009 (the effective date of this AD): | With the rudder removed and using 10X visual magnification, inspect all three rudder hinges and rudder hinge brackets for damage, i.e., cracking, deformation, and discoloration, at whichever of the following occurs first: (i) Within the next 10 hours TIS after May 11, 2009 (the effective date of this AD); or (ii) Within the next 30 days after May 11, 2009 (the effective date of this AD). | Thereafter inspect as follows: (A) Every 25 hours TIS or 3 months, whichever occurs first, without removing the rudder, visually inspect all three rudder hinges and rudder hinge brackets for damage; and (B) Every 50 hours TIS or 6 months, whichever occurs first, with the rudder removed and using 10X visual magnification, inspect all three rudder hinges and rudder hinge brackets for damage. |
| (2) For airplanes with less than 25 hours TIS as of May 11, 2009 (the effective date of this AD): | Without removing the rudder, visually inspect all three rudder hinges and rudder hinge brackets for damage, at whichever of the following occurs later: (i) Upon accumulating 25 hours TIS; or (ii) Within the next 10 hours TIS after May 11, 2009 (the effective date of this AD). | Thereafter inspect as follows: (A) Every 25 hours TIS or 3 months, whichever occurs first, without removing the rudder, visually inspect all three rudder hinges and rudder hinge brackets for damage. (B) Every 50 hours TIS or 6 months, whichever occurs first, with the rudder removed and using 10X visual magnification, inspect all three rudder hinges and rudder hinge brackets for damage. |
(3) If damage is found on any of the rudder hinges and/or rudder hinge brackets during any inspection required in paragraphs (e)(1) or (e)(2), before further flight, replace the damaged rudder hinges and/or rudder hinge brackets with new parts and inspect following the Repetitive Inspection procedures specified in paragraphs (e)(1) or (e)(2) of this AD.
(4) If the repetitive inspections required in paragraphs (e)(1) and (e)(2) of this AD become due at the same time, credit for both inspections will be given by doing the rudder removal and 10X visual inspection.
(5) Use the form (Figure 1 of this AD) to report the results of the following inspections required in this AD to the FAA at the address specified in paragraph (f) of this AD:
(i) Initial inspections required in paragraphs (e)(1) and (e)(2) of this AD, report within 10 days after the inspection or within 10 days of May 11, 2009 (after the effective date of this AD), whichever occurs later.
(ii) Repetitive inspections required in paragraphs (e)(1) and (e)(2) of this AD ONLY if cracks are found, report within 10 days after the inspection.
(iii) The Office of Management and Budget (OMB) approved the information collection requirements contained in this regulation under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and assigned OMB Control Number 2120-0056.
| AD 2009-09-09 Inspection Report | ||
| Airplane Model | ||
| Airplane Serial Number | ||
| Airplane Tach Hours at Time of Inspection | ||
| Is Upper Rudder Bracket Damaged? | No | Yes, describe extent of damage |
| Is Middle Rudder Bracket Damaged? | No | Yes, describe extent of damage |
| Is the Lower Rudder Bracket Damaged? (Models LC40-550FG & LC42-550FG only) | No | Yes, describe extent of damage |
| Is Lower Rudder Hinge Damaged? (Model LC40-550FG) | No | Yes, describe extend of damage |
| Were any other discrepancies noticed during the inspection? | ||
| Name: | ||
| Telephone and/or e-mail address: | ||
| Date: | ||
| Send report to: Gary Park, Aerospace Engineer, ACE-118W, Wichita | ||
| Aircraft Certification Office (ACO), 1801 Airport Road, Room 100, | ||
| Wichita, Kansas 67209; fax: (316) 946-4107; e-mail: gary.park@faa.gov. | ||
| Figure 1 |
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.
