COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Piper PA-38 (Tomahawk) Series Aeroplanes
AD/PA-38/7
Amdt 5
Fin Forward Spar Attachment - Inspection, Modification and Life Limit
10/83
Applicability: All model PA-38-112 with S/Nos. 38-78A0001 to 38-80A0198.
Requirement: 1. Gain access to vertical fin forward spar attachment plate P/n 77553-05 by removing lower fin fairing. Visually inspect for signs of movement, cracking and/or clamping witness marks in vicinity of fin forward spar attachment to fuselage.
2. Remove vertical fin and using a dye penetrant method inspect for cracks in:
(a) Fin forward spar in vicinity of attachment plate P/N 77553-05.
(b) Bend radius of attachment plate P/N 77553-05. Piper SB 628A refers.
(c) Front and rear faces of bulkhead P/N 77553-02 in vicinity of rivets that attach plate P/N 77553-05 and adjacent flange radius.
3. Fin spar attachment plate Piper P/N 77553-05 - Replacement.
Note: Piper SB 745 Parts 1, 2 and 3 and FAA AD 81-04-07 R1 refer.
Compliance: 1, 2(a) and 2(b). For aircraft which have achieved 300 hours TTIS and have not been modified by Piper forward fin spar modification, Kit P/N 764427 or D of A approved repair scheme Drg. 01-B-422 and AV-157-02 inspect within 100 hours time in service after 21 August 1982 and thereafter at intervals not exceeding 100 hours time in service until modified by Piper Kit P/N 764427 or D of A approved repair scheme Drg. 01-B-422 and AV-157-02.
2 (c). For aircraft which have achieved 300 hours TTIS and have not incorporated D of A approved repair scheme Drg. 01-B-422 and AV-157-02, within 5 hours time in service after 21 August 1982 and thereafter at intervals not exceeding 300 hours time in service.
3. Fin spar attachment plates with 3000 hours time in service, replace within 100 hours time in service after 31 March 1983 and thereafter at intervals not exceeding 3000 hours time in service; or
For aircraft which have incorporated D of A approved repair scheme Drg. 01-B-422 and AV-151-02 and have Fin spar attachment plates with 3000 hours time in service, replace within 100 hours time in service after 31 March 1983 and thereafter at intervals not exceeding 5000 hours time in service.
Background: Service experience indicates that modification of the fin forward spar attachment has been effective in reducing the incidence of cracking in this area. Amdt. 5 relieves some of the repetitive inspections in this area and for aircraft with the D. of A. approved reinforcement, repeat replacement of the fin spar attachment plate is extended to 5000 hours reflecting similarity with SB 710.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Overview
The Civil Aviation Regulations 1998, enacted by the Commonwealth of Australia, aim to ensure the safety of civil aviation through comprehensive regulation. This legislative framework includes specific directives to address safety concerns and ensure compliance with airworthiness standards. One such directive, F2006B05972, pertains to the Piper PA-38 (Tomahawk) Series Aeroplanes, specifically targeting issues related to the fin forward spar attachment. This amendment, introduced to address identified problems of cracking and movement in the fin forward spar attachment, provides detailed requirements for inspection, modification, and life limits of the affected components. The policy objective is to enhance aircraft safety by mitigating the risk of structural failure in this critical area, thereby ensuring the continued airworthiness of the aircraft within the Australian civil aviation sector.
Scope and Application
The Civil Aviation Safety Authority (CASA) Schedule of Airworthiness Directives under the Civil Aviation Regulations 1998 specifically targets Piper PA-38 (Tomahawk) Series aeroplanes, particularly model PA-38-112 with serial numbers ranging from 38-78A0001 to 38-80A0198. This legislation mandates a series of inspections and modifications for the vertical fin forward spar attachment to ensure continued airworthiness and safety. The directive applies to all relevant aircraft and requires regular inspections for signs of movement, cracking, and clamping witness marks around the fin forward spar attachment to the fuselage. Additionally, the directive stipulates the removal and replacement of specific fin spar attachment plates under certain conditions based on the aircraft's time in service. Compliance with these directives is essential to mitigate the risk of structural failure, ensuring the ongoing safety of the aircraft in question. The directive also provides for modifications to inspection and replacement intervals based on specific repair schemes and service hours, reflecting an adjustment to maintenance practices to enhance safety and reliability.
Key Provisions
The Civil Aviation Regulations 1998, under Part 39 and specifically within the Civil Aviation Safety Authority Schedule of Airworthiness Directives, contain provisions for the inspection, modification, and life limit of the fin forward spar attachment for Piper PA-38 (Tomahawk) series aeroplanes. The directive, identified as AD/PA-38/7 Amendment 5, targets all model PA-38-112 aeroplanes with serial numbers ranging from 38-78A0001 to 38-80A0198. The directive mandates that the vertical fin forward spar attachment plate, part number 77553-05, be inspected visually for any signs of movement, cracking, or clamping witness marks near the fin forward spar attachment to the fuselage (Section 1). It also requires a more thorough inspection using a dye penetrant method to check for cracks in the fin forward spar near the attachment plate, the bend radius of the attachment plate, and the front and rear faces of the bulkhead part number 77553-02 in the vicinity of the rivets attaching plate P/N 77553-05 and the adjacent flange radius (Section 2).
The directive imposes specific obligations on the operators and maintainers of these aircraft. For aircraft that have achieved 300 hours of time in service (TTIS) and have not undergone the forward fin spar modification using Piper Kit P/N 764427 or a Department of Aviation (D of A) approved repair scheme as per drawings 01-B-422 and AV-157-02, inspections must be conducted within 100 hours TTIS after 21 August 1982 and subsequently at intervals not exceeding 100 hours TTIS until the modification is performed (Section 2(a) and 2(b)). For those aircraft that have achieved 300 hours TTIS and have not incorporated the D of A approved repair scheme, inspections must be performed within 5 hours TTIS after 21 August 1982 and thereafter at intervals not exceeding 300 hours TTIS (Section 2(c)). Additionally, the fin spar attachment plates must be replaced at certain intervals based on the aircraft's TTIS and whether the D of A approved repair scheme has been implemented (Section 3).
Failure to comply with the requirements of this directive may result in legal consequences. The exact nature of these consequences is not specified in the directive; however, under the broader Civil Aviation Act 1988 and Civil Aviation Regulations 1988, non-compliance with airworthiness directives can lead to civil penalties and criminal charges. The penalties for non-compliance can include substantial fines and, in severe cases, imprisonment. The exact penalties would depend on the specific circumstances of the breach and the jurisdiction's legal framework. Operators and maintainers must adhere to these directives to ensure the continued airworthiness and safety of the aircraft.