Document ID: chunk:federal_register_of_legislation:F2008L00249:body:0:p1
Version: federal_register_of_legislation:F2008L00249
Segment Type: other
Provision Reference: 
Character Range: 0–3182

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/F22/1 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.

General Avia F22 Series Aeroplanes
AD/F22/1 Amdt 1  Engine to Firewall Attachment  3/2008 DM

Applicability:  Models F22A, F22B, F22C, and F22R aircraft, all serial numbers.
Requirement:       1. Perform a visual inspection for cracking of the structure surrounding the four bolts on the engine mount attachment at the firewall.  Gain access from the cabin below the instrument panel, and if access is restricted, it is possible to remove the upper panels of the firewall bulkhead (the right side totally and left side partially), so that the area to be inspected can be accessed via the engine bay.

                   Aircraft that have been inspected in accordance with the original issue of this Directive and no cracking or damage was detected, re-inspect as follows:

                     a. If, on the effective date of this Directive, the aircraft has accumulated 100 or more flight hours since accomplishment of the inspection required by the original issue of this Directive, carry out the Requirement 1 inspection.

                     b. If, on the effective date of this Directive, the aircraft has accumulated less than 100 flight hours since accomplishment of the inspection required by the original issue of this Directive, carry out the Requirement 1 inspection.

                   2. Repeat the Requirement 1 inspection.

                   3. If cracking or damage is detected during any inspection required by this Directive, accomplish one of the following actions:

                     a. Repair the aircraft in accordance with Gomolzig Modification 15328,  EASA approved under ref. EASA.A.R.01624; or,

                     b. Repair the aircraft in accordance with other EASA-approved repair method; or,

                     c. Ground the aircraft and contact EASA.

                After repair of the aircraft as specified in Requirement 3.a., the Requirement 2 repeat inspection interval can be extended to 500 flight hours.

                After repair of the aircraft as specified in Requirement 3.b., refer to the approved repair documents to establish the Requirement 2 repeat inspection interval.

             Note 1:  Enquiries regarding this Directive should be referred to AD Focal Point-Certification Directorate, EASA, at ADs@easa.europa.eu

             Note 2:  Enquiries regarding the technical content of this Directive should be referred to ENAC, Direzione Prodotti Aeronautici, at