AD/Swsa226/96 Inboard Wing Leading Edge Electrical Wires (Cth)

AIRWORTHINESS DIRECTIVE

For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (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/SWSA226/96 Inboard Wing Leading Edge
Electrical Wires 9/2008

Applicability:	This Directive is applicable to all serial numbers of the following aeroplane models:
Group 1 Group 2 Group 3 Group 4 Group 5 Group 6 Group 7		Model SA226-AT Model SA226-TA Model SA226-TC Model SA227-AC Model SA227-AT Model SA227-CC Model SA227-DC
Requirement:	1.    For Group 1, Group 2 and Group 3 aeroplanes carry out the following actions in accordance with the service bulletins (SB) listed in Table 1:
a.     Inspect electrical wires/components, hydraulic and bleed air tube assemblies at left-hand (LH)/right-hand (RH) inboard wing leading edge/battery box areas, LH/RH wing stations 51.167 to 81.174 and at all feed-through locations into the LH/RH inboard keelson for any evidence of chafing/arcing.  Clear, repair and/or replace all chafed electrical wires and components, hydraulic and bleed air tube assemblies and all feed-through locations, as required.
b.    Reposition battery lead cables, protect the battery power cable, and cover four-gauge wires leaving battery box with firesleeving and secure with clamp.
Table 1
Manufacturer	SB Number		Date
M7 Aerospace Swearingen Aviation Corporation Fairchild Aircraft Corporation Fairchild Aircraft Corporation	226-24-036 SB 24-001 SB 24-019 SB 24-020		Issued - 19 September 2007 Issued - 18 May 1971 Revised - 16 September 1975 Issued - 2 June 1982 Revised - 17 May 1983 Issued - 18 January 1983 Revised - 15 February 1984

2.    For Group 4 and Group 5 aeroplanes carry out the following actions in accordance with the SBs listed in Table 2:
a.     Inspect electrical wires/components, hydraulic and bleed air tube assemblies at LH/RH inboard wing leading edge/battery box areas, LH/RH wing stations 51.167 to 81.174 and at all feed-through locations into the LH/RH inboard keelson for any evidence of chafing/arcing.  Clear, repair and/or replace all chafed electrical wires and components, hydraulic and bleed air tube assemblies and all feed-through locations, as required.
b.    Protect the battery power cable and cover four-gauge wires leaving battery box with firesleeving and secure with clamp.
Table 2
Manufacturer	SB Number	Date
M7 Aerospace Fairchild Aircraft Corporation Fairchild Aircraft Corporation	227-24-019 SB24-001 SB24-002	Issued - 19 September 2007 Issued - 2 June 1982 Revised - 17 May 1983 Issued - 18 January 1983 Revised - 15 February 1984
3.    For Group 6 and Group 7 Aeroplanes - Inspect electrical wires/components, hydraulic and bleed air tube assemblies at LH/RH inboard wing leading edge/battery box areas, LH/RH wing stations 51.167 to 81.174 and at all feed-through locations into the LH/RH inboard keelson for any evidence of chafing/arcing.  Clear, repair and/or replace all chafed electrical wires and components, hydraulic and bleed air tube assemblies and all feed-through locations, as required.  These actions are to be accomplished in accordance with M7 Aerospace SB CC7-24-010, issued 19 September 2007.
Note 1:  Although not a requirement of this Directive, Swearingen Aviation Corporation SA226 SB. 57-010, Revised - 5 December 1975, may be incorporated on those aeroplanes that have not installed the access panel.  Installation of the access panel will simplify the incorporation of the service bulletins referenced in this Directive and future inspections of the areas of concern.
Later revisions of the above SB(s), approved by the United States Federal Aviation Administration (FAA) as an Alternate Method of Compliance (AMOC) to FAA AD 2008-12-16, are considered acceptable for compliance with the equivalent Requirements of this Directive.
Note 2:  FAA AD 2008-12-16 Amdt 39-15560.

Compliance:	For Requirements 1.a., 2.a. and 3 - Within 250 hours time-in-service (TIS) after 28 August 2008 (the effective date of this Directive) and thereafter inspect at intervals not to exceed 12 months.
For Requirements 1.b. and 2.b. - Within 250 hours TIS after 28 August 2008.
This Airworthiness Directive becomes effective on 28 August 2008.
Background:	The United States Federal Aviation Administration (FAA) has advised of five reports of chafing between the bleed air tube and the electrical starter cables with one incident resulting in a fire.  This condition could result in arcing of the exposed wires and burn a hole in the bleed air line or the nearby hydraulic line and lead to a possible hydraulic fluid leak and fire in the engine nacelle compartment.
This Directive is issued to detect and correct chafing/arcing of electrical wires, components and bleed air lines.

James Coyne
Delegate of the Civil Aviation Safety Authority

16 July 2008