SCHEDULE OF AIRWORTHINESS DIRECTIVES
Piper PA-30 Twin Comanche · Airworthiness Directives
Overview
This document is a schedule of airworthiness directives issued by the Civil Aviation Safety Authority of Australia, specifically for the Piper PA-30 and PA-39 Twin Comanche series aeroplanes. It outlines mandatory inspection requirements to ensure the safety and airworthiness of these aircraft models. The directive focuses on the inspection of the fin forward spar attachment, which is critical for the structural integrity of the aircraft. Compliance with these directives is essential for maintaining airworthiness and safety standards in aviation operations involving these aircraft.
- Inspect the fin forward spar attachment for cracks using at least a 5X magnifying glass.
- Applicable to all PA-30 and PA-39 models with S/Nos. 30-1 to 30-2000 and 39-1 to 39-155.
- Initial inspection required within 50 hours after September 22, 1976.
- Subsequent inspections must be done at intervals not exceeding 100 hours.
- Refer to Piper SL No. 777 for modification instructions to gain visual access.
Document
Source
Originally published by services.casa.gov.au. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Airworthiness Directives
- Year
- 1976
- Pages
- 1
- File size
- 11 KB
- Publisher
- services.casa.gov.au
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- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins
- Type Certificate (TCDS)
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In this document
Applicability
The airworthiness directive applies to all Piper PA-30 and PA-39 models with serial numbers ranging from 30-1 to 30-2000 and 39-1 to 39-155.
Inspection Requirement
Operators are required to visually inspect the fin forward spar to fuselage attachment for any cracks, specifically in the bend relief cutout radius of channel part number 22903-00. A magnifying glass with at least 5X magnification should be used during this inspection.
Compliance Timeline
The initial inspection must be completed within 50 hours of time in service after September 22, 1976. Following the initial inspection, subsequent inspections must occur at intervals not exceeding 100 hours of time in service.
Notes on Inspection
It is noted that the part number mentioned may not be listed in the Parts Catalogue, as it is part of a complete assembly. Additionally, Piper Service Letter No. 777 provides guidance on modifying the fin assembly to facilitate visual access to the channel relief holes.
FAA Reference
This inspection requirement is also referenced in FAA Airworthiness Directive 76-18-05, indicating its importance in the regulatory framework.
Safety notes
- Failure to comply with inspection requirements may compromise aircraft safety.
- Cracks in the fin forward spar attachment can lead to structural failure.
Full document text
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Piper PA-30 & 39 (Twin Comanche) Series Aeroplanes AD/PA-30/28 Fin Forward Spar Attachment - Inspection 9/76 Applicability: All models PA-30 and PA-39 with S/Nos. 30-1 to 30-2000 and 39-1 to 39-155. Requirement: Visually inspect, with the aid of at least a 5X glass, the fin forward spar to fuselage attachment for cracks in the bend relief cutout radius of channel P/N 22903-00. Note 1: The part number quoted may not appear in the Parts Catalogue as it is a component of the fin front spar which is listed as a complete assembly under a separate part number. Note 2: Piper SL No. 777 provides instructions for modifying the Fin Assembly to gain Visual access to the channel relief holes. Note 3: This inspection is the subject of FAA AD 76-18-05. Compliance: Within 50 hours time in service after 22 September 1976 and there- after at intervals not exceeding 100 hours time in service.