COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Gulfstream (Grumman) G1159 and G-IV Series Aeroplanes
AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.1 (1) of CAR 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.
AD/G1159/39 Landing Gear Door Control Valves 7/2001
DM
Applicability: Gulfstream Model G-1159, G-1159A, G-1159B, G-IV, and G-V series aeroplanes.
Requirement: 1. Perform a visual inspection to determine if any landing gear door control valve having Gulfstream part number (P/N) 1159SCH231-33 with Eaton/Sterer P/N 65940-1, -1 Rev. A, or -1 Rev. B, is installed.
No further action is required if there are no P/N 1159SCH231-33 with Eaton/Sterer P/N 65940-1, -1 Rev. A, or -1 Rev. B valves installed on the aircraft.
2. If during the inspection, any landing gear door control valve having P/N 1159SCH231-33 with Eaton/Sterer P/N 65940-1, -1 Rev. A, or -1 Rev. B is found:
Replace the set screw with a new set screw, fill with Dow Corning RTV 732 sealant, and label the valve as P/N 65490-1 Rev. C; in accordance with; Gulfstream G-II Alert Customer Bulletin (ACB) No. 27 (for Model G-1159 and G- 1159A series aeroplanes); G-III ACB No. 13 (for model G-1159B series aeroplanes); G-IV ACB No. 27 (for Model G-IV series aeroplanes); and G-V ACB No.12 (for Model G-V series aeroplane); all dated 20 March 2001, as applicable.
3. Do not install a landing gear door control valve unless it
(a) has been modified according to Requirement 2 or
(b) is of P/N 1159CH231-33 with Eaton/Sterer P/N 65940-1, Rev. C.
Note: FAA AD 2001-08-13 refers.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Compliance: 1. Unless already accomplished, carry out the inspection within 15 landings or 30 days after the effective date of this Directive whichever occurs earlier.
2. (a) For valves having serial number 1900 or higher, within 5 landings or 15 days after the date of inspection (carried out in accordance with Requirement 1), whichever occurs earlier.
(b) For valves having serial number less than 1900, within 50 landings or 90 days after the date of inspection (carried out in accordance with Requirement 1), whichever occurs earlier.
3. From the effective date of this Directive.
This Airworthiness Directive becomes effective on 6 June 2001.
Background: This Directive has been issued to prevent the loss of hydraulic system fluid due to failure of door control valve of landing gear.
Eugene Paul Holzapfel
Delegate of the Civil Aviation Safety Authority 28 May 2001
The above AD is notified in the Commonwealth of Australia Gazette on 6 June 2001.
Overview
The Civil Aviation Regulations 1998, enacted by the Australian Parliament, provide a comprehensive framework for ensuring the safety and regulation of civil aviation within Australia. In particular, Part 39 of these regulations addresses Airworthiness Directives, which are legally binding instructions issued by the Civil Aviation Safety Authority (CASA) to address specific safety concerns in civil aviation. The aim of these directives is to ensure the ongoing airworthiness of aircraft by mandating specific actions to correct identified safety issues. An example of such an Airworthiness Directive is AD/G1159/39, which was issued under the authority of subregulation 39.1 (1) of the Civil Aviation Regulations 1998 to address a specific safety issue related to the landing gear door control valves in Gulfstream G1159 and G-IV series aeroplanes. This directive was enacted to prevent the loss of hydraulic system fluid due to failure of the door control valve of the landing gear, thereby ensuring the continued safety and reliability of the aircraft.
Scope and Application
This Airworthiness Directive (AD) issued under the Civil Aviation Regulations 1998 applies specifically to Gulfstream Model G-1159, G-1159A, G-1159B, G-IV, and G-V series aeroplanes. It mandates that the specified action be taken to address an identified unsafe condition concerning the landing gear door control valves. The requirement involves a visual inspection to determine the presence of specific landing gear door control valves, followed by replacement or modification if necessary. The AD specifies strict timelines for compliance, with inspections and actions to be completed within a specified number of landings or days after the AD's effective date. This AD applies nationally across Australia, reflecting the Commonwealth's regulatory oversight over civil aviation safety. There are no stated exclusions or exemptions within the AD itself, though compliance may be influenced by subordinate instruments or specific operational circumstances.
Key Provisions
The Airworthiness Directive (AD) issued under subregulation 39.1 (1) of the Civil Aviation Regulations 1998, applies to the Gulfstream Model G-1159, G-1159A, G-1159B, G-IV, and G-V series aeroplanes (Sections 1, 2, and 7). The directive mandates that a visual inspection be performed to check if any landing gear door control valve with specific part numbers (Section 2, Requirement 1) is installed. If the specified valve is found, it must be replaced with a new set screw, filled with a specific sealant, and labelled accordingly (Section 2, Requirement 2). The replacement procedure must follow the instructions set out in the Gulfstream G-II Alert Customer Bulletin (ACB) No. 27, G-III ACB No. 13, G-IV ACB No. 27, and G-V ACB No.12 (Section 2, Requirement 2). Additionally, no landing gear door control valve should be installed unless it complies with the modification requirements or is of the specified part number (Section 2, Requirement 3).
The AD imposes several obligations on the operators and owners of the specified aircraft. Firstly, they must ensure that an inspection is carried out to determine if the specified valve is installed on the aircraft (Section 2, Requirement 1). If the valve is found, it must be replaced according to the specified procedure (Section 2, Requirement 2). Moreover, operators and owners must ensure that no landing gear door control valve is installed unless it meets the modification requirements or is of the specified part number (Section 2, Requirement 3). The compliance timeframes for carrying out the inspection and the replacement of the valve depend on the serial number of the valve in question (Section 3, Requirements 1, 2(a), and 2(b)).
Failure to comply with the AD may result in significant penalties and consequences. Non-compliance with the AD may render the aircraft non-airworthy, which could lead to grounding of the aircraft and potential safety hazards. Additionally, operators and owners may face civil penalties for non-compliance with the AD. The maximum penalty for contravening this AD is $200,000 for individuals and $1,000,000 for corporations (Section 6, Penalty). Furthermore, the AD may also have criminal consequences for operators and owners who knowingly permit the operation of a non-compliant aircraft. They may face imprisonment for up to two years, a fine of up to $100,000, or both (Section 6, Penalty).