AD/SWSA226/86 Amdt 1 Wing Spar Centre Web Cutout (Cth)

AIRWORTHINESS DIRECTIVE

On the effective date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/SWSA226/86 and issues the following AD under subregulation 39.001(1) of CASR 1998.  The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

Fairchild (Swearingen) SA226 and SA227 Series Aeroplanes

AD/SWSA226/86 Amdt 1 Wing Spar Centre Web Cutout 6/2005

Applicability:

Model   Serial Number

SA226-AT   AT001 through AT074

SA226-TC   TC201 through TC419

SA226-T   T201 through T291

SA226-T(B)   T(B)276 and T(B)292 through T(B)417

SA227-TT   TT421 through TT541

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.

SA227-AC   AC406, AC415, AC416, and AC420 through AC785

SA227-AT   AT423 through AT631 and AT695

SA227-BC   BC762, BC764, BC766, and BC770 through BC789

SA227-CC/DC   CC/DC784 and CC/DC790 through CC/DC896

Requirement:

1.    Inspect each wing spar centre web cutout for cracks between Wing Station (WS) 8 and WS 17.5.  Accomplish this inspection in accordance with one of the following:

a.     For Models SA227-TT, SA227-AT, SA227-AC, and SA227-BC aircraft: In accordance with Fairchild Airframe Airworthiness Limitations Manual ST-UN-M001, Revision C-6, dated April 7 1998;

b.    For Models SA226-T, SA226-T(B), SA226-AT, and SA226-TC aircraft: In accordance with Fairchild Airframe Inspection Manual ST-UN-M002, Revision A6, dated December 8 1997; or,

c.     For Models SA227-CC and SA227-DC aircraft: In accordance with Fairchild Airframe Airworthiness Limitations Manual ST-UN-M003, Revision 5, dated April 7 1998.

2.    If any crack(s) is/are found during the above required inspection, repair the crack(s) in accordance with one of the following, as applicable.  This repair eliminates the repetitive inspections (2,000 hours time in service intervals) specified in Requirement 1 of this Directive for that particular wing spar.

a.     For Models SA226-T, SA226-T(B), SA226-AT, SA226-TC, SA227-TT, SA-227-AT, SA227-AC, and SA-227-BC aircraft: In accordance with 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 241998; or,

b.    For Models SA227-CC and SA227-DC aircraft: In accordance with 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.

The repetitive inspections required by Requirement 1 of this Directive may be terminated if the wing spar centre web repair specified in Requirement 2 of this Directive has been accomplished on both the left and right wing spar.  If one wing spar centre web has been repaired, then repetitive inspections are still required on the other one if the repair has not been incorporated.

Note:  FAA AD 2005-06-13 Amdt 39-14023 refers.

Compliance:

1.    Upon accumulating 6,500 hours time in service on each wing spar; within the next 2,000 hours time in service after the last inspection accomplished per the applicable Airworthiness Limitations Manual; or within the next 500 hours time in service after 17 June 1999, whichever occurs later, unless already accomplished; and thereafter at intervals not to exceed 2,000 hours time in service.

2.    Before further flight.

The compliance times remain unchanged by this issue.

This Amendment becomes effective on 9 June 2005.

Background:

The FAA received reports of cracks in the wing spar centre web cutout of affected aircraft.  The cracks were caused by fatigue, due to aircraft manoeuvring and wing gusts, and if not detected and corrected, could result in structural failure of the wing spar with consequent loss of control of the aircraft.

Amendment 1 is issued to align this Directive with the latest FAA AD, with no change to technical content.

David Villiers
Delegate of the Civil Aviation Safety Authority

29 April 2005