Airworthiness Directive · Amendment 39-14023 · Fairchild Aircraft, Inc. SA226 and SA227 Series Airplanes
Fairchild Aircraft, Inc. SA226 and SA227 Series Airplanes
This AD affects the following airplane models and serial numbers that are certificated in any category:
| Model | Serial Nos. |
|---|---|
| (1) SA226-AT | AT001 through AT074. |
| (2) SA226-TC | TC201 through TC419. |
| (3) SA226-T | T201 through T291. |
| (4) SA226-T(B) | T(B)276 and T(B)292 through T(B)417. |
| (5) SA227-TT | TT421 through TT541. |
| (6) SA227-TT(300) | TT(300)447, TT(300)465, TT(300)471, TT(300)483, TT(300)512, TT(300)518, TT(300)521, TT(300)527, TT(300)529, and TT(300)536. |
| (7) SA227-AC | AC406, AC415, AC416, and AC420 through AC785. |
| (8) SA227-AT | AT423 through AT631 and AT695. |
| (9) SA227-BC | BC762, BC764, BC766, and BC770 through BC789. |
| (10) SA227-CC/DC | CC/DC784, and CC/DC790 through CC/DC896. |
The FAA is adopting a new Airworthiness Directive (AD) to supersede AD 99-06-02, which currently applies to certain Fairchild Aircraft (Fairchild) SA226 and SA227 series airplanes. AD 99-06-02 requires you to repetitively inspect the wing spar center web cutout on both wings for cracks between Wing Station (WS) 8 and WS 17.5. That AD also requires you to repair any area found cracked before further flight. The repair will eliminate the need for the repetitive inspections on that particular wing spar. Since that AD became effective, we have determined that we inadvertently omitted certain Model SA227-CC/DC airplane serial numbers from the applicability. This AD retains the actions of AD 99-06-02 and adds additional Model SA227- CC/DC airplanes to the Applicability section. The actions specified in this AD are intended to detect and correct fatigue cracking of the wing spar center web cutout area, which could result in structural failure of the wing spar. This could lead to loss of control of the airplane.
To address this problem, you must do the following:
| Actions | Compliance | Procedures |
|---|---|---|
| (1) Inspect each wing spar center web cutout for cracks between Wing Station (WS) 8 and WS 17.5 | Initially inspect upon accumulating 6,500 hours time-in-service (TIS) on each wing spar; within the next 2,000 hours TIS after the last inspection done following the applicable Airworthiness Limitations Manual (the last inspection done following AD 99-06-02); or within the next 500 hours TIS after May 2, 2005 the effective date of this AD, whichever occurs later. Repetitively inspect thereafter at intervals not to exceed 2,000 hours TIS | For Models SA227-TT, SA227-AT, SAA227-AC, and SA227-BC airplanes: Follow Fairchild Airframe Airworthiness Limitations Manual ST-UN-M001, Rev. No. C-6, dated April 7, 1998; or Fairchild Airframe Airworthiness Limitations Manual ST-UN-M001, SA227 Series, Reissue C dated January 18, 1991, at the revision levels stated on page iii and page iv (page iii dated August 16, 1995, and page iv dated March 8, 2004); For Models SA226-T, SA226-T(B), SA226-AT, and SA226-TC airplanes; Follow Fairchild Airframe Inspection Manual ST-UN-M002, Rev. No. A-6, dated December 8, 1997; or Fairchild Airframe Inspection Manual ST-Un-M002, Reissue A, SA226 Series, dated December 9, 1986, at the revision levels stated on page iii and page iv (page iii dated April 7, 1998 and page iv dated March 8, 2004); and For Models SA227-CC and SA227-DC airplanes: Follow Fairchild Airframe Airworthiness Limitations Manual ST-UN-M003, Rev. No. 5, dated April 7, 1998; or Fairchild Airframe Airworthiness Limitations Manual ST-UN-M003, SA227 Commuter Category, Initial issue dated December 6, 1991, at the revision levels stated on page iii and page iv (page iii dated July 29, 2003, and page iv dated March 8, 2004). |
| (2) If any crack(s) is/are found during any inspection required by paragraph (e)(1) of this AD, repair the crack(s). This repair eliminates the repetitive inspections required in paragraph (e)(1) of this AD for that particular wing spar | Before further flight | For Models SA226-T, SA226-T(B), SA226-AT, SA226-TC, SA227-TT, SA227-AT, SA227-AC, and SA227-BC airplanes: Follow Fairchild SA226/227 Series Structural Repair Manual, part number (P/N) 27-10054-079, pages 57 through 90; Initial Issue: March 1, 1983; Revision 28, dated June 24, 1998; and For Models SA227-CC and SA227-DC airplanes: Follow Fairchild SA227 Series Structural Repair Manual, P/N 27-10054-127, pages 47 through 60; Initial Issue: December 1, 1991; Revision 7, dated June 24, 1998. |
| (3) The repetitive inspections required in paragraph (e)(1) of this AD may be terminated if the wing spar center web repair specified in paragraph (e)(2) of this AD has been done on both the left and right wing spar. If one wing spar center web has been repaired, then repetitive inspections are still required on the other one until the repair is done | Not applicable | Not applicable. |
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.
