Airworthiness Directive · Amendment 39-11885 · Fairchild Aircraft, Inc., SA226 Series and SA227 Series Airplanes
Fairchild Aircraft, Inc., SA226 Series and SA227 Series Airplanes
Models SA226-T, SA226-AT, SA226-T(B), SA226-TC, SA227-AT, SA227-TT, and SA227-AC (C-26A) airplanes, all serial numbers, certificated in any category, that incorporate one of the following:
(1) For SA226 series airplanes: Ozone Industries, Inc., part number (P/N) OAS5453-1 (Revision “H”, “J”, “K”, or “N”), or Ozone Industries, Inc., P/N OAS5453-5. These assemblies incorporate an Ozone Industries, Inc., P/N OAS5501-1 main landing gear (MLG) drag brace assembly (consisting of both a drag brace and drag links); or
(2) For SA227 series airplanes: Ozone Industries, Inc., 14,500 LB MGTOW, P/N OAS5453-5. These assemblies incorporate an Ozone Industries, Inc., P/N OAS5501-1 MLG drag brace assembly (consisting of both a drag brace and drag links).
This amendment adopts a new airworthiness directive (AD) that applies to certain Fairchild Aircraft, Inc. (Fairchild) SA226 and SA227 series airplanes equipped with certain Ozone Industries, Inc., main landing gear (MLG) assemblies. This AD requires you to repetitively inspect the MLG drag brace assembly (consists of both brace and links) for cracks, and requires you to replace or rework any cracked MLG drag brace assembly. This AD is the result of several reports of cracks in the MLG drag brace assemblies on the affected airplanes. The actions specified by this AD are intended to detect and correct cracks in MLG drag brace assembly. Continued airplane operation with such cracks could lead to MLG failure and result in loss of control of the airplane during takeoff or landing operations.
To address this problem, you must accomplish the following actions:
| Action | Compliance time | Procedures |
|---|---|---|
| (1) Inspect, using dye penetrant methods, the main landing gear drag brace assemblies for cracks | Accomplish this inspection within the next 50 hours time-in-service (TIS) after September 22, 2000 (the effective date of this AD) | Accomplish this inspection in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of whichever of the following that is applicable: (i) Fairchild Service Bulletin 226-32-068, Issued: June 23, 2000; or (i) Fairchild Service Bulletin 227-32-043, Issued: June 23, 2000. |
| (2) If no cracks are found during the initial inspection, repetitively reinspect the MLG drag brace assemblies | Begin the repetitive inspections within 1,000 hours TIS after the initial inspection, and continue thereafter at intervals not to exceed 1,000 hours TIS provided no cracks are found | Accomplish in accordance with the previously referenced service bulletins. |
| (3) If cracks are found during any inspection that are over 0.080 inches in combined length or any cracks are found on an already reworked assembly, replace the Ozone Industries, Inc., P/N OAS5501-1 MLG Drag Brace Assembly with a new or serviceable assembly, and repetitively reinspect these assemblies | (i) Replacement: Prior to further flight after the inspection where the cracks(s) is found; and (ii) Repetitive Inspections: (A) For new assemblies: Upon accumulating 15,000 hours TIS on the assembly, and thereafter at intervals not to exceed 1,000 hours TIS provided no crack(s) is found; and | Accomplish the replacement in accordance with the applicable maintenance manual and accomplish the repetitive with the previously referenced service bulletins. |
| (B) For serviceable assemblies: Within 1,000 hours TIS after installation, and thereafter at intervals not to exceed 1,000 hours TIS provided no crack(s) is found | ||
| (4) If cracks are found during any inspection that are equal to or less than 0.080 inches in total combined length, you may rework the MLG drag brace assembly (i) Only one rework of the MLG drag brace assembly is allowed. If any crack is found after rework, the assembly must be replaced (ii) After rework, repetitively inspect the MLG drag brace assembly provided no additional cracking is found at which time replacement is required | Accomplish the rework prior to further flight after the inspection where the crack(s) is found, and then reinspect at intervals not to exceed 400 hours TIS, unless further cracking is found at which time replacement is required prior to further flight | Accomplish in accordance with the previously referenced service bulletins. |
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.
