AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/EMB- 110/16 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.
Embraer EMB-110 (Bandeirante) Series Aeroplanes
AD/EMB-110/16
Amdt 2
Control Column P/N 4A-500-10-01-20 - Inspection
12/2003
DM
Applicability: All models of EMB-110.
Requirement: To prevent failure of the control column assembly in flight, perform the following:
- With the aid of a 4X-6X magnifying glass, visually inspect the control column walls, and the region adjacent to the two sharp corner of the aileron control chain access trim cover.
(a) If any cracks less than 10mm in length are detected, they shall be stop drilled using a 2 (two) mm diameter drill bit.
(b) If any cracks greater than 10mm in length are detected, repair them by manufacturing and installing a reinforcement plate in accordance with the instructions contained in Embraer Alert S/B 110-27-A59.
| 2. | If a permanent repair (reinforcement patch) has been performed in accordance with Embraer Alert S/B 110-27-A59, inspect the condition of the repair for cracks in the weld, reinforcement patch or control column walls. |
Compliance: | 1. | Before further flight and thereafter at 250 hour intervals (if no cracks were found in the initial inspection), until the permanent repair (reinforcement patch) is incorporated per Embraer Alert S/B 110-27-A59. Installation of the reinforcement patch is terminating action for Requirement 1 of this AD. |
| | (a) The crack shall be stop drilled before further flight in accordance with requirement 1a of this AD, and then permanently repaired in accordance with requirement 1b of this AD, within 50 hours time in service after stop drilling the crack. The inspection per Requirement 1 shall be carried out daily/overnight until the permanent repair is carried out. If, during the daily inspection, the crack is found to extend beyond the stop drill, perform the permanent repair in accordance with requirement 1(b), before further flight. |
| | (b) The crack shall be permanently repaired in accordance with requirement 1(b) of this AD, before further flight. |
Embraer EMB-110 (Bandeirante) Series Aeroplanes
AD/EMB-110/16 Amdt 2 (continued)
2. Perform repeat inspections at 250 hour intervals. The daily/overnight inspection is no longer required.
This Amendment becomes effective on 15 October 2003.
Background: The manufacturer has received a report of failure of a control column. The previous amendment clarified and simplified the requirements and compliance. There was no change to the technical requirement or compliance times.
This amendment is issued to clarify the compliance for requirement 1. No addition requirements are imposed.
Amendment 1 of this AD became effective on 7 August 2003.
The original issue of this AD became effective on the 15 December 1981.
David Villiers
Delegate of the Civil Aviation Safety Authority 9 October 2003
The above AD is notified in the Commonwealth of Australia Gazette on 15 October 2003.
Overview
The Civil Aviation Safety Authority (CASA) issued Airworthiness Directive (AD) AD/EMB-110/16 Amdt 2 in 2003 to address safety concerns associated with potential failures of the control column assembly in Embraer EMB-110 (Bandeirante) Series Aeroplanes. This directive was introduced to prevent in-flight failures of the control column, which could potentially result in hazardous situations. By revoking the previous amendment, AD/EMB-110/16 Amdt 1, CASA aimed to clarify the compliance requirements for the inspection and repair of the control column. The policy objective behind this AD is to ensure the continued airworthiness and safety of the Embraer EMB-110 aircraft by mandating specific actions to detect and rectify potential structural issues in the control column assembly. This legislative instrument was enacted under the authority of the Civil Aviation Safety Regulations 1998, ensuring that the directive aligns with the overarching goals of maintaining safe aviation practices in Australia.
Scope and Application
This Airworthiness Directive (AD) issued under the Civil Aviation Safety Regulations 1998 applies to all models of the Embraer EMB-110 (Bandeirante) series aeroplanes. The directive aims to prevent failure of the control column assembly in flight by requiring specific inspections and repairs to the control column walls and adjacent regions. The geographic and jurisdictional reach of this AD is limited to the Commonwealth of Australia, where it applies to aircraft and aeronautical products within the regulatory purview of the Civil Aviation Safety Authority (CASA). The AD does not specify any exclusions, exemptions, or thresholds for its application. Compliance with the AD is mandatory for all operators of the affected aircraft within Australia. The AD can be extended or restricted through subordinate instruments, but in this case, the primary focus is on ensuring the safety of the control column assembly in Embraer EMB-110 series aeroplanes through precise and timely inspections and repairs.
Key Provisions
This Airworthiness Directive (AD) applies to all models of the Embraer EMB-110 aircraft. The AD is concerned with the inspection and repair of the control column assembly to prevent failure in flight. The directive specifies that a visual inspection must be performed using a magnifying glass to check the control column walls and the area near the sharp corners of the aileron control chain access trim cover. If any cracks are found, they must be addressed based on their length: cracks less than 10mm must be stop drilled with a 2mm diameter drill bit, and cracks greater than 10mm must be repaired by installing a reinforcement plate as detailed in Embraer Alert S/B 110-27-A59. If a permanent repair has been performed, the condition of the repair must also be inspected for cracks in the weld, reinforcement patch, or control column walls.
The obligations imposed by this AD require that the inspection and repair actions be carried out before further flight and at specified intervals. The initial inspection must be performed before further flight, and if no cracks are found, the inspection must be repeated at 250-hour intervals until the permanent repair is incorporated. If cracks are found, they must be stop drilled before further flight and then permanently repaired within 50 hours in service after the stop drilling. The AD also mandates daily or overnight inspections until the permanent repair is completed. If the crack extends beyond the stop drill during inspection, the permanent repair must be performed before further flight. Once the permanent repair is completed, the daily inspections are no longer required, and inspections must continue at 250-hour intervals.
Breaches of this AD can result in serious consequences. Aircraft operators who fail to comply with the AD's requirements risk compromising the safety of the aircraft and its occupants. Non-compliance can lead to enforcement actions by the Civil Aviation Safety Authority (CASA). Potential penalties can include fines, orders to cease operations, and in severe cases, the suspension or revocation of an operator's licence. The specific penalties depend on the nature and severity of the breach, and CASA has the authority to impose fines that can reach up to several hundred thousand Australian dollars for serious violations. Additionally, failure to comply with the AD could lead to criminal charges if the non-compliance results in an accident or incident, potentially leading to imprisonment for the responsible parties.