COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Fokker F27 Series Aeroplanes
AD/F27/136 Outer Flap Centre Hinge 9/94
Applicability: Fokker Model F27 aircraft, serial numbers 10102 and 10105 to 10240 inclusive.
Requirement: Conduct a High Frequency Eddy Current (HFEC) inspection of the outer flap centre hinge bearing bore, on both wings, in accordance with Part 1 of Fokker Service Bulletin (SB) F27/57-66. Repair flap centre hinge fittings whether cracked or not.
Note: RLD AD 91-129 refers.
Compliance: 1. Hinge fittings not modified in accordance with Fokker SB F27/57-22.
- Inspect per Fokker SB F27/57-66 part 1
(i) If the aircraft has exceeded 72000 flights, then inspect within 1000 flights from 18 August 1994 or before 1 February 1995, whichever occurs first.
b. Repair per Fokker SB F27/57-66 part 2
(i) Within 300 flights if the crack length inside the bore is less than 5mm and no cracking exists on the faces of the bore,
(ii) Before further flight if cracking exceeds either of the limitations of para
1.b. (i).
(iii) Within 2800 flights or two years if no cracks are found.
2. Hinge fittings modified in accordance with Fokker SB F27/57-22.
- Inspect per Fokker SB F27/57-66 part 1
(i) If the aircraft has exceeded 55000 flights, then inspect within 1000 flights from 18 August 1994 or before 1 February 1995, whichever occurs first.
b. Repair per Fokker SB F27/57-66 part 2
(i) Within 300 flights if the crack length inside the bore is less than 5mm and no cracking exists on the faces of the bore,
(ii) Before further flight if cracking exceeds either of the limitations of para 2.b.(i), or if a crack inside the bore is located near the grease nipple bore.
(iii) Within 2800 flights or two years if no cracks are found.
Note: Outer flap centre hinges which have not yet reached the newly established retirement lives of 72000 or 55000 flights are covered by the F27 Structural Integrity Program, Part 1, Item 57-50-02 (AD/F27/103 refers).
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Background: Analysis of the service loads spectrum has shown that the loads on the outer flap centre hinge are higher than originally expected. This has resulted in a reduction in the fatigue life for the early style hinge fittings. This Directive requires inspection and repair to maintain airworthiness integrity on affected aircraft which now find themselves in excess of the new hinge fitting retirement lives.
Overview
The Civil Aviation Regulations 1998, enacted by the Parliament of Australia, serve to regulate the airworthiness of aircraft within the country. One specific legislative instrument, F2006B09703, targets the Fokker F27 Series Aeroplanes and addresses issues related to the outer flap centre hinge bearing bore through Airworthiness Directive AD/F27/136. This directive was introduced to address the problem of reduced fatigue life in the outer flap centre hinge fittings of Fokker Model F27 aircraft, specifically those with serial numbers ranging from 10102 to 10240 inclusive. The policy objective is to ensure continued airworthiness by mandating inspections and necessary repairs of the hinge fittings to prevent potential structural failures, thereby enhancing aviation safety. Compliance with these directives is critical for maintaining the operational integrity of the affected aircraft.
Scope and Application
The Civil Aviation Safety Authority's Airworthiness Directives under the Civil Aviation Regulations 1998 specifically target Fokker Model F27 aircraft, serial numbers ranging from 10102 to 10240 inclusive. These regulations mandate a High Frequency Eddy Current (HFEC) inspection of the outer flap centre hinge bearing bore on both wings, in accordance with Fokker Service Bulletin F27/57-66. The directive is designed to ensure that the outer flap centre hinge fittings are repaired irrespective of whether they are cracked or not, following the guidelines set out in Fokker SB F27/57-66. Compliance with this directive is critical for maintaining the airworthiness of the specified Fokker F27 aircraft, with detailed inspection and repair schedules provided depending on the number of flights the aircraft has completed and whether the hinge fittings have been modified in line with Fokker SB F27/57-22. The directive applies within the Commonwealth of Australia and adheres to the jurisdictional reach of the Civil Aviation Safety Authority, ensuring that the safety standards are uniformly enforced across all relevant aircraft within the specified serial number range.
Key Provisions
The Civil Aviation Regulations 1998, specifically within Part 39 - 105, mandate the Civil Aviation Safety Authority's (CASA) Schedule of Airworthiness Directives (AD) for various aircraft, including the Fokker F27 Series Aeroplanes. AD/F27/136 focuses on the outer flap centre hinge of Fokker F27 aircraft with serial numbers ranging from 10102 to 10240 inclusive (Section 1). The directive necessitates conducting a High Frequency Eddy Current (HFEC) inspection of the outer flap centre hinge bearing bore on both wings, adhering to Part 1 of Fokker Service Bulletin (SB) F27/57-66. Furthermore, it mandates the repair of the flap centre hinge fittings, irrespective of whether they are cracked or not.
The AD imposes several obligations on the parties involved. Aircraft operators must ensure that the specified inspections and repairs are conducted in accordance with Fokker's service bulletins. For aircraft that have not modified their hinge fittings as per Fokker SB F27/57-22, inspections must occur within 1000 flights from 18 August 1994 or before 1 February 1995, whichever comes first, if the aircraft has exceeded 72,000 flights (Section 2a). Repairs must be performed within 300 flights if the crack length inside the bore is less than 5mm and there is no cracking on the faces of the bore; otherwise, before further flight if the cracks exceed these limitations (Section 2b). If no cracks are found, the repairs must occur within 2800 flights or two years.
For aircraft with hinge fittings modified according to Fokker SB F27/57-22, inspections must occur within 1000 flights from 18 August 1994 or before 1 February 1995 if the aircraft has exceeded 55,000 flights (Section 2a). Repairs must be performed within 300 flights if the crack length inside the bore is less than 5mm and there is no cracking on the faces of the bore; before further flight if the cracks exceed these limitations or if a crack inside the bore is located near the grease nipple bore (Section 2b). If no cracks are found, repairs must be completed within 2800 flights or two years.
Failure to comply with these AD provisions can result in serious consequences. The AD references RLD AD 91-129, indicating that non-compliance may lead to aircraft being deemed unairworthy. In the event of a breach, the Civil Aviation Safety Authority has the authority to enforce penalties, which may include fines and other sanctions. The exact penalties can vary but are intended to ensure strict adherence to safety standards to prevent accidents and maintain the highest level of aviation safety.