AD/VIPER/9 - Engine Centre Section
1AD/VIPER/9 - Engine Centre Section
Start here
Get a plain-English read of 1
Turn the raw legal text into a practical explanation grounded in AD/VIPER/9 - Engine Centre Section.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 106 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Image unavailable in extracted text
Rolls Royce Turbine Engines - Viper Series
AD/VIPER/9 Engine Centre Section 9/90
Applicability: Viper Mk 601-22 and Viper Mk 520, 521 and 522 engines.
Requirement: Inspect engine compressor casing/centre section joint flange in accordance with and as applicable:
Rolls Royce Viper Mk 601-22 Service Bulletin No 72-A173; or
Rolls Royce Viper Mk 520, 521, and 522 Service Bulletin No 72-A388.
Compliance: (1) Engines in service - Prior to 6 August 1990.
(2) Uninstalled engines - Prior to installation in an aircraft.
Background: Investigation of an engine established that the compressor casing/centre section joint had parted at the top, causing heavy bending loads on the turbine mainshaft causing spline failure. Parting of the compressor casing/centre section has been attributed to thermal stress pulling fastener inserts from the centre section.