1AD/F27/103 Amdt 7 - Structural Limitations

COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY

SCHEDULE OF AIRWORTHINESS DIRECTIVES

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Fokker F27 Series Aeroplanes

AD/F27/103

Amdt 7

Structural Limitations 6/95

Applicability: All F27 Aircraft, all Models. Requirement: 1. Inspect, modify or retire:

(a) Airframe parts as specified in Fokker Structural Integrity Program (SIP) Document 27438 Revision 11,

(b) Main landing gear components as specified in Dowty Rotol Service Bulletin No 32-152B, Revision 7,

(c) Nose landing gear components as specified in Dowty Rotol Service Bulletin No 32-154B Revision 4.

2. Retire the airframe from service before exceeding 90 000 flights.

Note 1: Load variability factors derived from Fatigue Meter and operational records may not be used in connection with the times specified in the SIP Document without the specific approval of the Authority.

Note 2: In spite of the allowable crack lengths and crack propagation data which may be provided by the manufacturer, an aircraft shall not be returned to service with known unrepaired cracks without the approval of the Authority or of the operator’s authorised structures design signatory.

Compliance: This amendment is effective from 25 May 1995.

Background: Amendment 6 references the latest revisions of the reference documents.

Amendment 7 removes reference to ‘subsequent amendment’ documentation, and reformats the text of the AD.