AD/MSR/26 - Wing Structural Fatigue Life Limitation
1AD/MSR/26 - Wing Structural Fatigue Life Limitation
Start here
Get a plain-English read of 1
Turn the raw legal text into a practical explanation grounded in AD/MSR/26 - Wing Structural Fatigue Life Limitation.
meta-content-style-type: text/css meta-content-type: application/xhtml+xml; charset=utf-8 meta-generator: Aspose.Words for .NET 22.10.0
?xml version="1.0" encoding="utf-8" standalone="no"?>
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Image unavailable in extracted text Aerospatiale Rallye Series Aeroplanes
AD/MSR/26 Wing Structural Fatigue Life Limitation 3/80
Applicability: All series 235E aircraft.
Requirement: Retire the wing main spar and the centre section splice plates from service.
Note: This fatigue life limitation will be reviewed upon receipt of future substantiation data from the manufacturer.
Compliance: Upon or prior to achieving 2800 hours component time in service.
Background: Based on information provided by the manufacturer, a safe fatigue life has been determined for the wing structure.