Cessna 205 (210-5) Series Aeroplanes
AD/CESSNA 205/20
Amdt 1
Applicability: Model
205, 205A
Requirement: Part 1:
Seat Adjustment Mechanism 9/88
Serial Number
205-0001 to 205-0577
(a) Measure each hole in the seat track(s) for excessive wear. If the wear dimension across any hole exceeds 10.67mm (0.42") to a maximum depth of 3.81mm (0.15"), replace the seat track prior to further flight.
SECTION OF SEAT TRACK SHOWING HOLE WEAR
(b) Visually inspect the seat rail holes for dirt and any debris which may preclude engagement of the seat pin(s). Remove any such material prior to further flight.
(c) Lift up on the forward edge of each seat to eliminate all vertical play. With the seat in this position, measure the depth of engagement of each seat pin. If the engagement of any pin is less than 3.81mm (0.15") (see Figure 2), replace or repair necessary components to achieve a seat pin engagement of 3.81mm (0.15") or greater prior to further flight.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
FIGURE 2
(d) Visually inspect seat rollers for flat spots. Ensure all rollers and washers turn freely on their axle bolts (or bushings if installed) and move freely on the seat rails. Replace rollers having flat spots and any worn washers prior to further flight. If there is any binding between the bores of the rollers, washers, and axle bolts (or bushings if installed), remove, clean, and reinstall these parts prior to further flight.
Note: Do not lubricate rollers, washers, axle bolts or bushings as the lubrication will attract dust and other particles which can cause binding. (e) Measure the wall thickness of the roller housing and the tang (see Figure 2). If the tang thickness has worn to less than 1/2 the housing thickness, replace the roller housing prior to further flight.
(f) Check the spring(s) that keep the lock pin(s) in position in the track holes for positive engagement action. Replace any spring which does not provide positive engagement prior to further flight.
(g) Visually inspect the seat tracks for cracks in accordance with Cessna SIL SE83-6, dated 11 March 1983. Any limitation imposed as a result of seat track cracking shall be endorsed on the Maintenance Release. Replace any seat rail exceeding the crack criteria as specified in SE83-6 with a serviceable rail prior to further flight.
Part 2:
In accordance with temporary schemes approved by the Secretary, modify seat adjustment mechanisms to permanently limit seat travel to 255mm (10") or to 153mm (6") as applicable, aft of the forward stop.
Note: FAA AD 87-20-03 R1 refers.
Compliance: A. i. For aircraft with less than 1000 hours time in service as at 28 January 1988, prior to attaining 1100 hours time in service; or
ii. For aircraft with more than 1000 hours time in service as at 28 January 1988,at the next inspection for Maintenance Release issue after 28 January 1988; and
iii. Thereafter at each inspection for Maintenance Release issue. B. Pending any component replacement necessary to fully comply with Requirement: Part 1, compliance with Requirement: Part 2 is an acceptable alternative until 30 June 1989.
Background: There has been a history of seat adjustment mechanism failure that has resulted in accidents. As there will probably be a high demand for replacement items, Part 2 of the Requirement enables continued flight. Schemes acceptable to the Secretary are available from Regional Offices.
Overview
The Civil Aviation Regulations 1998, enacted by the Commonwealth of Australia, were designed to address the safety concerns associated with the seat adjustment mechanisms in the Cessna 205 (210-5) series aeroplanes. These regulations, administered by the Civil Aviation Safety Authority, aim to ensure the airworthiness of aircraft by setting forth specific directives to rectify known issues with the seat adjustment mechanisms, which have historically led to accidents. The primary objective of these directives is to prevent seat adjustment failures by mandating inspections and repairs to various components such as seat tracks, rollers, springs, and pins, ensuring that they meet specified tolerances and operational standards. Compliance with these directives is mandatory and must be achieved at designated intervals, with certain provisions allowing for temporary modifications until permanent repairs can be made.
Scope and Application
The AD/CESSNA 205/20 Amendment 1 applies specifically to the Cessna 205 (210-5) Series aeroplanes, covering model 205 and 205A within the specified serial number range of 205-0001 to 205-0577. This legislative instrument is issued under the authority of the Civil Aviation Regulations 1998, ensuring compliance with the regulations concerning airworthiness directives in Australia. The directive is applicable to all aircraft operators within the Commonwealth of Australia and aims to address critical safety issues associated with the seat adjustment mechanisms in these aircraft models. The regulations mandate specific inspections and maintenance actions to prevent accidents related to seat adjustment failures. The compliance schedule is tied to the aircraft's time in service, requiring inspections and actions either before reaching 1100 hours or at the next inspection after a specified date, depending on the aircraft's prior service hours. Additionally, there are temporary modifications available to continue flight operations until the necessary components are replaced, subject to approval by the Secretary.
Key Provisions
The primary operative sections of this legislation, AD/CESSNA 205/20 Amendment 1, focus on the inspection and repair of seat adjustment mechanisms in Cessna 205 (210-5) series aeroplanes. Specifically, Section 1 requires detailed inspections of the seat tracks and associated components to ensure they meet certain wear and engagement criteria before further flight. This includes measuring seat track holes for excessive wear, cleaning seat rail holes, ensuring the correct depth of engagement of seat pins, inspecting seat rollers, and checking the wall thickness of roller housings (sections 1(a)-(g)). Section 2 mandates that the seat adjustment mechanisms be modified to limit seat travel to either 255mm (10 inches) or 153mm (6 inches) aft of the forward stop, depending on the aircraft's service hours.
The Act imposes several obligations on the parties it governs. Aircraft operators and maintenance personnel must adhere to the outlined inspection and repair procedures, ensuring that all specified components are examined and either repaired or replaced as necessary before the aircraft is allowed to fly again. This includes ensuring that the seat pin engagement depth is at least 3.81mm (0.15"), rollers and washers are free from flat spots and binding, and the tang thickness of roller housings is not less than half the housing thickness. Furthermore, operators must comply with the seat travel limitation requirements specified in Part 2, either by modifying the seat adjustment mechanisms or by adhering to temporary schemes approved by the Secretary until a permanent modification can be made.
Failure to comply with the requirements set forth in this legislation can lead to severe consequences. While the specific penalties are not detailed in the provided text, non-compliance with Civil Aviation Safety Authority directives can typically result in enforcement actions, including fines, suspension or revocation of aircraft certificates, and potential criminal charges for operators or maintenance personnel found negligent. The severity of these consequences underscores the importance of strict adherence to the Act's provisions to ensure the continued airworthiness and safety of the aircraft in question.