AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/CESSNA 180/72 Amdt 1 and issues the following AD under subregulation 39.1 (1) of CASR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.
Cessna 180, 182 and Wren 460 Series Aeroplanes
AD/CESSNA 180/72
Amdt 2
Seat Adjustment Mechanism 2/2004
Applicability:
Model Serial Number
180, 180A 30000 to 32999
180A, 180B, 180C 50000 to 50911
180D, 180E, 180F, 180G, 180H, 180J, 180K 18050912 to 18053203
182, 182A, 182B, 182C, 182D, 182E, 182F, 182G,
182H, 182J, 182K, 182L, 182M, 182N, 182P, 182Q,
182R, R182, TR182, F182P, F182Q T182
Requirement: Part 1:
All
182267716 to 18268586
(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.
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 1: 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 Authority, modify seat adjustment mechanisms to permanently limit seat travel to 255mm (10") or to 153mm (6") as applicable, aft of the forward stop.
Note 2: FAA AD 87-20-03 R2 Amdt 39-6669 and FAA Special Airworthiness Information Bulletin (SAIB) No. CE-04-01, dated 2 October 2003, refer.
Compliance: a. (i) For aircraft with less than 1,000 hours time in service as at 28 January 1988, prior to attaining 1,100 hours time in service; or
(ii) For aircraft with more than 1,000 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.
The compliance times remain unchanged by this issue. This Amendment becomes effective on 19 February 2004.
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 Authority are available from Regional Offices.
Amendment 2 is issued in response to FAA SAIB No. CE-04-01, which clarifies applicability of Cessna Model T182 series aircraft.
David Villiers
Delegate of the Civil Aviation Safety Authority 7 January 2004
The above AD is notified in the Commonwealth of Australia Gazette on 28 January 2004.