Document ID: chunk:federal_register_of_legislation:F2007L00094:body:0:p1
Version: federal_register_of_legislation:F2007L00094
Segment Type: other
Provision Reference: 
Character Range: 0–3110

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/LYC/102 Amdt 2 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.

Lycoming Piston Engines
AD/LYC/102 Amdt 3  Crankshaft Internal Inspection  2/2007

Applicability:  Lycoming O-320 and O-360 series engines as detailed in Lycoming Mandatory Service Bulletin (MSB) No. 505B; and not incorporating a front bore protective coating as detailed in Lycoming Service Bulletin No. 530 at any revision status.

                Note 1:  Engines applicable are engines fitted with hollow front bore crankshafts and installed in aircraft propelled by fixed pitch propellers.
Requirement:       1. Carry out an internal inspection of the crankshaft front bore for evidence of corrosion in accordance with Lycoming MSB No. 505B or later FAA approved revisions.

                   If there is no evidence of pitting corrosion in the front bore, no further action is required until the next inspection as detailed in the compliance requirements of this Directive.

                   2. If in carrying out the internal inspection in accordance with Requirement 1 of this Directive there is evidence of pitting corrosion in the front bore:

                     a. Carry out a Fluorescent Penetrant Inspection (FPI) in accordance with the FPI procedures detailed in Lycoming MSB No. 505B or later FAA approved revisions.

                     b. Remove any evidence of pitting corrosion in accordance with approved data (procedures approved by CAR 35 authorised persons are considered acceptable for the purpose of this AD) or remove the crankshaft from service.

                     c. If in carrying out the FPI, a crankshaft is found to be cracked, remove the crankshaft from service.

                   3. Spare crankshafts: Carry out an internal inspection of the crankshaft front bore for evidence of corrosion in accordance with MSB No. 505B or later FAA approved revisions; and

                  a. Remove any evidence of pitting corrosion in accordance with approved data (procedures approved by CAR 35 authorised persons are considered acceptable for the purpose of this AD); and

                  b. Carry out a Magnetic Particle Inspection of the crankshaft front bore in accordance with approved data; and

                  c. Apply a protective coating in accordance with Lycoming MSB No. 530 dated 1 December 1997 or later FAA approved revisions.

             Note 2:  The application of Urethabond 104 to the