AIRWORTHINESS DIRECTIVE
On the effective date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/CESSNA 210/69 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 210 Series Aeroplanes
AD/CESSNA 210/69
Amdt 2
Horizontal Stabilizer Front Spar 9/2004
Applicability: All models of Cessna 210 aircraft except 210R/T210R serial numbers 21064898 and subsequent.
Requirement: Visually inspect the front and rear faces of horizontal stabilizer front spar assembly centre section for cracks around the cut-out in the front spar web. Refer to Figure 1 below.
It should be noted that for models manufactured from 1969 onwards the horizontal stabiliser front spar will be of a three-layer design. This means that the centre laminate will effectively be hidden by the two outer laminates, making inspection of the centre laminate almost impossible. The centre laminate should be inspected as far as practicable without disassembly of the spar.
Any cracks in the front spar web must be repaired before further flight, and a defect report must be submitted.
Note 1: Access can be achieved by the removal of the fillet fairing. The front face of the front spar is easily seen. The rear face may be seen via a hole in the upper surface of the horizontal stabilizer using an inspection mirror and torch.
Note 2: This inspection may require some experimenting with lights and mirrors to obtain some certainty in the results of the inspection. The inspection would be much easier to conduct with the use of a borescope.
Compliance: a. For aircraft with less than 10000 hours time in service, inspect before exceeding 10000 hours total time in service, and thereafter at intervals not exceeding 110 hours time in service.
b. For aircraft with 10000 or more hours time in service, inspect before18 March 2002, and thereafter at intervals not exceeding 110 hours time in service.
This Amendment becomes effective on 2 September 2004.
Background: Reports have been received of cracking of the horizontal stabilizer front spar on Australian registered Cessna 210s. Both front and rear spars must be serviceable for the horizontal stabilizer to carry ultimate load. The front spar forms part of the horizontal stabilizer’s primary load path, and loss of strength in this area could be catastrophic.
It should be noted that this Airworthiness Directive mandates an inspection requirement already stated in the manufacturer’s maintenance data.
Amendment 1 of this Airworthiness Directive is issued to highlight that later models have been manufactured with horizontal stabiliser spars containing three layers, making the centre laminate almost impossible to inspect. This amendment provides guidance on inspection of the three layer configuration. Compliance times remain unchanged.
Amendment 2 of this Airworthiness Directive is issued to increase the recurrent compliance interval from 100 hours to 110 hours time in service to allow the inspections required by this Airworthiness Directive to be aligned with scheduled maintenance.
The original issue of this Airworthiness Directive became effective on 6 March 2002.
David Villiers
Delegate of the Civil Aviation Safety Authority 23 July 2004
The above AD is notified in the Commonwealth of Australia Gazette on 11 August 2004.
Overview
The Civil Aviation Safety Authority Act 1998 was enacted to ensure the safety of civil aviation within Australia, addressing the need for stringent oversight and regulation of aircraft and aeronautical products. One of the key legislative instruments under this Act is the Airworthiness Directive (AD) concerning the Cessna 210 Series Aeroplanes, specifically AD/CESSNA 210/69 Amdt 2, which was issued to address the identified unsafe condition related to the horizontal stabilizer front spar. This AD, effective from 2 September 2004, was introduced by the Civil Aviation Safety Authority (CASA) as a delegate under subregulation 39.1(1) of the Civil Aviation Safety Regulations 1998 (CASR). The directive mandates visual inspections of the front and rear faces of the horizontal stabilizer front spar assembly centre section for cracks, a requirement necessitated by reports of such cracks in Australian-registered Cessna 210s. Ensuring these inspections are carried out aims to prevent catastrophic failure of the front spar, which forms part of the horizontal stabilizer’s primary load path.
Scope and Application
The Airworthiness Directive AD/CESSNA 210/69 Amdt 2 applies to all models of Cessna 210 aircraft, excluding 210R/T210R serial numbers 21064898 and subsequent. It mandates a visual inspection of the front and rear faces of the horizontal stabilizer front spar assembly centre section for cracks around the cut-out in the front spar web. This requirement applies specifically to aircraft manufactured from 1969 onwards where the centre laminate of the front spar is hidden by the outer laminates, making inspection challenging. The directive specifies that any detected cracks must be repaired before further flight, and a defect report must be submitted. Compliance intervals vary based on the total time in service of the aircraft; for aircraft with less than 10,000 hours, inspections must occur before exceeding 10,000 hours and thereafter at intervals not exceeding 110 hours. For aircraft with 10,000 or more hours, inspections must be completed before 18 March 2002 and then at intervals not exceeding 110 hours. This directive was issued to address reports of cracking in the horizontal stabilizer front spar on Australian-registered Cessna 210s and became effective on 2 September 2004.
Key Provisions
The key operative sections of this Airworthiness Directive (AD) focus on the inspection and maintenance requirements for the horizontal stabilizer front spar assembly in certain models of Cessna 210 aircraft. Section (a) of the applicability section specifies that all models of Cessna 210 aircraft, except for 210R/T210R serial numbers 21064898 and subsequent, are subject to the inspection requirements outlined in the AD. Section (b) of the requirement section mandates a visual inspection of the front and rear faces of the horizontal stabilizer front spar assembly centre section for cracks around the cut-out in the front spar web. This inspection is necessary to ensure the airworthiness of the aircraft and must be conducted in accordance with the instructions provided in the requirement section. Section (c) of the compliance section details the inspection intervals: for aircraft with less than 10,000 hours of total time in service, an inspection must be performed before exceeding 10,000 hours and thereafter at intervals not exceeding 110 hours; for aircraft with 10,000 or more hours of total time in service, an inspection must be performed before 18 March 2002 and thereafter at intervals not exceeding 110 hours.
The AD imposes specific obligations on the owners and operators of the affected aircraft. They are required to visually inspect the horizontal stabilizer front spar assembly as per the outlined requirements and intervals. This includes inspecting the front and rear faces of the spar assembly for cracks, which may necessitate repairs and the submission of a defect report. The AD also provides guidance on how to access the inspection area, such as removing the fillet fairing and using inspection mirrors and torches. For models manufactured from 1969 onwards, the AD advises that the centre laminate should be inspected as far as practicable without disassembly of the spar. Operators must ensure these inspections are conducted to maintain the airworthiness of the aircraft and to prevent any unsafe conditions.
Failure to comply with the requirements set out in the AD may result in serious consequences. Non-compliance with the inspection and maintenance requirements could lead to the discovery of unsafe conditions, which could potentially compromise the structural integrity of the aircraft. This could result in the aircraft being grounded until the necessary repairs and inspections are completed. The AD does not explicitly outline specific penalties or legal consequences for non-compliance, but it is important to note that non-compliance with airworthiness directives can lead to enforcement actions by the Civil Aviation Safety Authority (CASA), which may include fines, penalties, or other regulatory actions. The severity of these actions would depend on the specific circumstances and the degree of non-compliance.