Document ID: chunk:federal_register_of_legislation:F2021C01280:reg:5:p17
Version: federal_register_of_legislation:F2021C01280
Segment Type: reg
Provision Reference: reg 5 (pt 17/26)
Character Range: 48462–51243

the towing release system has full and free movement; and
(b) check that the release mechanism is clean; and
(c) check for visible signs of damage or wear of the release mechanism; and
(d) perform a functional check; and
(e) certify that the testing mentioned in paragraphs (a) to (d) have been satisfactorily completed in column 2 of Part 3 of the maintenance release.
       12.3Before a maintenance release may be issued for the aircraft, the person performing the maintenance release inspection must:
(a) clean and lubricate the hook mechanism; and
(b) check the beak and other parts for wear; and
(c) check the condition of operating levers, cables and pulleys; and
(d) test the ability of the system mechanism to return to a safe over-centre position with a return force, measured at the activating lever of the hook, of not less than 20 N (Newton) (2 kg force).
       12.4At intervals not exceeding the earlier of 1000 hours' time‑in‑service or 1 year, the holder of a Part 66 licence in the B1.1 or B1.2 subcategory authorising maintenance on the aircraft, or the holder of an authority to carry out maintenance on aircraft under regulation 33B of CAR, must:
(a) remove and service the release assembly in accordance with the manufacturer's data and instructions; and
(b) test that the pilot effort is less than 200 N (20.4 kg force) with a 4.5 kN (459 kg force) load applied to the release anywhere in a 30 degree cone.
Note   Towing release mechanisms may be overhauled by a Gliding Federation of Australia (GFA)‑approved Inspector in accordance with the requirements contained in the relevant Airworthiness Directives issued by the GFA from time to time. The overhaul status of the towing release assembly must be adequately documented.

13 Electrical hoist assembly — earth bonding testing

Application
       13.1 This clause applies for an aircraft with an electrical hoist assembly that does not have specific bonding testing requirements.

Testing
       13.2 The electrical bonding between each adjacent component part of the electrical hoist assembly must be tested:
(a) to a maximum resistance of 0.010 OHM; and
(b) using a bonding tester capable of resolving to 0.002 OHM.
       13.3 For subclause 13.2, component parts of the electrical hoist assembly that must be considered adjacent to other parts include the control box, the electrical motor casing, the hoist body, the hoist arm and the attachment bracket.

Intervals
       13.4 Testing of the electrical hoist assembly must be carried out:
(a) before it is installed in the aircraft; and
(b) after it is installed in the aircraft — at intervals not exceeding every 24 months.

14 Periodic checking and testing of ATC transponders

Definition
       14.1 In this clause:
electron tube technology or ETT