AD/EMB-110/54 Amdt 1 Corrosion of Wing and Vertical Stabiliser to Fuselage Attachments, Rib 1 Half-Wing and Cabin Seat Tracks (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/EMB-110/54 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.

Embraer EMB-110 (Bandeirante) Series Aeroplanes

AD/EMB-110/54 Amdt 1 Corrosion of Wing and Vertical Stabiliser to Fuselage Attachments, Rib 1 Half-Wing and Cabin Seat Tracks 11/2007

Applicability:

All Model EMB-110 aircraft.

Requirement:

1.    Carry out a general visual inspection for corrosion in the area of the wing to fuselage attachments, vertical stabiliser to fuselage attachment, and Rib 1 half-wing and passenger seat tracks, in accordance with Parts I, II, and III of Embraer Service Bulletin (SB) No. 110-00-0007 original issue, or later ANAC approved revision.

All structure found corroded or cracked as a result of the inspections must be addressed in accordance with detailed instructions and procedures described in SB No. 110-00-0007 original issue, or later ANAC approved revision.

Note 1:  Previous accomplishment of Embraer Alert Service Bulletin (ASB) No.
110-00-A007 original issue, or later ANAC approved revision; or the implementation of the Requirement 1 inspections, as required by Section VI of Maintenance Planning Guides TP 110P2/145, PM 110/652, or PM 110/165, are considered acceptable means of compliance with Requirement 1 of this Directive.

2.    Accomplish Part IV of SB No. 110-00-0007 original issue, or later ANAC approved revision.

All structure found corroded or cracked as a result of the inspections must be addressed in accordance with detailed instructions and procedures described in SB No. 110-00-0007 original issue, or later ANAC approved revision.

3.    Accomplish Part V of SB No. 110-00-0007 original issue, or later ANAC approved revision.

All structure found corroded or cracked as a result of the inspections must be addressed in accordance with detailed instructions and procedures described in SB No. 110-00-0007 original issue, or later ANAC approved revision.

4.    Accomplish the detailed instructions and procedures described in Embraer Service Bulletin (SB) No. 110-57-0026 Revision 03, or later ANAC approved revision, as follows:

a.     Accomplish a general visual inspection on external and internal auxiliary fittings, forward and rear fittings, located on external areas of the wing (refer to CPM 110/1413 - Corrosion Prevention Manual - Section 57 - Wings - Task 57-F - Rib Assembly No. 1 - Inspection and Repair).  Repeat this inspection every 6 months;

b.    Accomplish a detailed visual inspection on regions of main fittings eyelets of wing-to-fuselage attachments (refer to CPM 110/1413 - Corrosion Prevention Manual - Section 53 - Wings - Task 53-F - Attachment Points of the Spar Cap and Spar Web, and Auxiliary Fitting Assembly of Bulkheads 16 and 18 - Inspection and Repair and Task 53-G - Wing-to Fuselage Attachment Fitting (Bulkheads 16 and 18) - Inspection and Repair).  Repeat this inspection every 6 months; and,

c.     Accomplish a general visual inspection on internal auxiliary fittings located within the fuel tanks (refer to CPM 110/1413 - Corrosion Prevention Manual - Section 57 - Wings - Task 57-F - Rib Assembly No. 1 - Inspection and Repair).  Repeat this inspection every 12 months.

5.    Corrosion or cracks detected during any inspection required by this Directive must be reported to CASA at [email protected].

Note 2:  Brazil ANAC AD 2006-10-01R1 Amdt 39-1204 refers.

Compliance:

1.    Within 30 calendar days or 100 flight hours after 21 December 2006, whichever occurs first.

2.    Before 31 January 2007.

3.    Before 31 December 2007.

4.    Before 31 December 2009, with the initial application within 30 days after
25 October 2007.  However, if the aircraft is in compliance with CPCP Implementation Tasks 53-F, 53-G, and 57-F, the Requirement 4 inspections do not need to start within 30 days after 25 October 2007.  Nevertheless, all Requirement 4 repeat actions must be begun before 31 December 2009.

5.    Within 7 days of detection.

The compliance times for Requirements 1, 2, 3, and 5 remain unchanged by this issue of the Directive.

This Amendment becomes effective on 25 October 2007.

Background:

The ANAC received reports of corrosion in the area of the wing to fuselage attachments, vertical stabiliser to fuselage attachments, Rib 1 half-wing and passenger seat tracks.  Such corrosion, unless detected and corrected, could lead to fatigue cracking of primary structure with consequent reduced aircraft structural integrity, which could result in structural failure.

Amendment 1 is issued in response to a revision of the related ANAC AD, which introduces new requirements in accordance with SB No. 110-57-0026 Rev. 03.

David Villiers
Delegate of the Civil Aviation Safety Authority

13 September 2007