Airworthiness Directive · Amendment 39-16588 · Stabilizers
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 applies to the following Cessna Aircraft Company (type certificate previously held by Columbia Aircraft Manufacturing (previously The Lancair Company)) airplane models and serial numbers that are certificated in any category:
| Model | Serial Nos. |
|---|---|
| LC40-550FG (300) | 40001, 40002, and 40004 through 40079. |
| LC41-550FG (400) | 41001 through 41569, 41571 through 41800, 411001 through 411087, 411089 through 411110, 411112 through 411138, 411140, 411142, and 411147. |
| LC42-550FG (350) | 42001 through 42009, 42011 through 42558, 42560 through 42569, 421001 through 421013, 421015 through 421017, and 421019. |
| Model | Serial Nos. |
|---|---|
| LC41-550FG (400) | 41570, 411088, 411111, 411139, 411141, 411143 through 411146, and 411148 through 411153. |
| LC42-550FG (350) | 42010, 42559, 421014, 421018, and 421020. |
We are superseding an existing airworthiness directive (AD) for the products listed above. AD 2009-09-09 currently requires repetitive inspections of the rudder hinges and the rudder hinge brackets for damage, i.e., cracking, deformation, and discoloration. If damage is found during any inspection, AD 2009-09-09 also requires replacing the damaged rudder hinge and/or rudder hinge bracket. This new AD retains the inspection requirements of AD 2009-09-09, adds airplanes to the Applicability section, and adds a terminating action for the repetitive inspection requirements. This AD resulted from the manufacturer developing a modification that terminates the repetitive inspections and from the manufacture adding airplane serial numbers into the Applicability section. 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, unless already done:
(1) For Group 1 airplanes specified in paragraph (c) of this AD: Using the compliance times specified in table 1 of this AD, inspect the rudder hinges and rudder hinge brackets for damage, i.e., cracking, deformation, and discoloration. Do the inspections following Cessna Single Engine Service Bulletin SB09-27-01, dated April 13, 2009; Cessna Single Engine Service Bulletin SB09-27-01, Revision 2, dated November 23, 2009; or Cessna Single Engine Service Bulletin SB09-27-01, Revision 3, dated July 20, 2010.
| Condition | Initially inspect... | Repetitively inspect... |
|---|---|---|
| (i) For airplanes with 25 hours time-in-service (TIS) or more as of May 11, 2009 (the effective date of AD 2009-09-09). | With the rudder removed and using 10X visual magnification, inspect all three rudder hinges and rudder hinge brackets at whichever of the following occurs first (A) Within the next 10 hours TIS after May 11, 2009 (the effective date of AD 2009-09-09); or (B) Within the next 30 days after May 11, 2009 (the effective date of AD 009-09-09) | Thereafter inspect as follows until the modification required in paragraph (f)(5) of this AD is done: (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; 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. |
| (ii) For airplanes with less than 25 hours TIS as of May 11, 2009 (the effective date of AD 2009-09-09). | Without removing the rudder, visually inspect all three rudder hinges and rudder hinge brackets, at whichever of the following occurs later (A) Upon accumulating 25 hours TIS; or (B) Within the next 10 hours TIS after May 11, 2009 (the effective date of AD 2009-09-09) | Thereafter inspect as follows until the modification required in paragraph (f)(5) of this AD is done: (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; 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. |
(2) For Group 1 airplanes specified in paragraph (c) of this AD: Before further flight after any inspection required in paragraphs (f)(1)(i) or (f)(1)(ii) of this AD in which damage is found on any of the rudder hinges and/or rudder hinge brackets, incorporate Cessna Single Engine Modification Kit MK400-27-01, dated November 23, 2009; or Cessna Single Engine Modification Kit MK400-27-01A dated July 20, 2010, as specified in Cessna Single Engine Service Bulletin SB09-27-01, Revision 2, dated November 23, 2009; and Cessna Single Engine Service Bulletin SB09-27-01, Revision 3, dated July 20, 2010. Incorporating either Modification Kit MK400-27-01 or Modification Kit MK400-27-01A, terminates the repetitive inspections required in paragraphs (f)(1)(i) and (f)(1)(ii) of this AD.
(3) For Group 1 airplanes specified in paragraph (c) of this AD: If the repetitive inspections required in paragraphs (f)(1)(i) and (f)(1)(ii) 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.
(4) For Group 1 airplanes specified in paragraph (c) of this AD: Within the next 24 months after March 14, 2011 (the effective date of this AD), incorporate Cessna Single Engine Modification Kit MK400-27-01, dated November 23, 2009; or Cessna Single Engine Modification Kit MK400-27-01A, dated July 20, 2010, as specified in Cessna Single Engine Service Bulletin SB09-27-01, Revision 2, dated November 23, 2009; and Cessna Single Engine Service Bulletin SB09-27-01, Revision 3, dated July 20, 2010, unless already done as specified in paragraph (f)(2) of this AD. Incorporating either Modification Kit MK400-27-01 or Modification Kit MK400-27-01A, terminates the repetitive inspections required in paragraphs (f)(1)(i) and (f)(1)(ii) of this AD.
(5) For Group 1 airplanes specified in paragraph (c) of this AD: At any time after the initial inspections required in paragraphs (f)(1)(i) and (f)(1)(ii) of this AD, as long as no damage is found, and no later than the compliance time specified in paragraph (f)(4) of this AD, you may incorporate Cessna Single Engine Modification Kit MK400-27-01, dated November 23, 2009; or Cessna Single Engine Modification Kit MK400-27-01A, dated July 20, 2010, as specified in Cessna Single Engine Service Bulletin SB09-27-01, Revision 2, dated November 23, 2009; and Cessna Single Engine Service Bulletin SB09-27-01, Revision 3, dated July 20, 2010, to terminate the repetitive inspections required in paragraphs (f)(1)(i) and (f)(1)(ii) of this AD.
(6) For any Group 1 airplane with Cessna Single Engine Service Bulletin SB09-27-01, Revision 1, dated August 31, 2009, already incorporated and for all Group 2 airplanes: Within the next 30 days after March 14, 2011 (the effective date of this AD), inspect for proper rudder hinge and rudder bracket hardware thread engagement and inspect the rudder travel. Do these inspections following the Accomplishment Instructions in Cessna Single Engine Modification Kit MK400-27-01, dated November 23, 2009; or the Accomplishment Instructions in Cessna Single Engine Modification Kit MK400-27-01A, dated July 20, 2010.
(i) Before further flight after the inspection required in paragraph (f)(6) of this AD, if any discrepancies are found in the rudder hinge or rudder bracket hardware, replace the affected hardware. Do the replacements following the Accomplishment Instructions in Cessna Single Engine Modification Kit MK400-27-01, dated November 23, 2009; or the Accomplishment Instructions in Cessna Single Engine Modification Kit MK400-27-01A, dated July 20, 2010.
(ii) Before further flight after the inspection required in paragraph (f)(6) of this AD, if the rudder travel is outside the limits specified in the Accomplishment Instructions in Cessna Single Engine Modification Kit MK400-27-01, dated November 23, 2009; or the Accomplishment Instructions in Cessna Single Engine Modification Kit MK400-27-01A, dated July 20, 2010, reinstall the rudder following the Accomplishment Instructions in either Cessna Single Engine Modification Kit MK400-27-01, dated November 23, 2009; or Cessna Single Engine Modification Kit MK400-27-01A, dated July 20, 2010.
(iii) After the inspection and any necessary corrective actions required in paragraphs (f)(6), (f)(6)(i), and (f)(6)(ii) of this AD, no further action is required.
For all airplanes specified in paragraph (c) of this AD: As of March 14, 2011 (the effective date of this AD), if Cessna Single Engine Service Bulletin SB09-27-01, Revision 2, dated November 23, 2009, has already been incorporated, no further action is required.
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.
