Document ID: chunk:federal_register_of_legislation:F2019L01376:body:0:p1
Version: federal_register_of_legislation:F2019L01376
Segment Type: other
Provision Reference: 
Character Range: 0–3077

AIRWORTHINESS DIRECTIVE
On the commencement date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below repeals Airworthiness Directive (AD) AD/UH-1/20 Amdt 1 and issues the following AD under subregulation 39.001 (1) of CASR and subsection 33 (3) of the Acts Interpretation Act 1901. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct an 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.

Bell Helicopter Textron UH-1 (All Variants) Series Helicopters
AD/UH-1/20 Amdt 2  Tail Boom and Fin - Fretting and Cracking  22/2019

Applicability:  All models of Bell Helicopter Textron Inc UH-1 (All Variants) Series Helicopters.
Requirement:       1. Visually inspect the tail boom skin joint at tail boom Station 194 for fretting or cracking (inspect 10 inches forward and 10 inches aft of Station 194 as per Figures 1. and 2 below) .
                   2. Visually inspect the vertical fin front spar cap at its intersection with the tail rotor gear box support fitting for cracks as per Figure 1.
                   3. Conduct a radiographic inspection using a CASA approved procedure, or approved alternative procedure, of the tail boom skin at Station 194 splice joint. (inspect 10 inches forward and 10 inches aft of Station 194 as per Figures 1. and 2 below).
                   4. Replace any cracked skin panels found while performing Requirement 1 or Requirement 3 inspections, with serviceable panels.
                   5. Replace any cracked fin spar caps found while performing Requirement 2 inspection, with serviceable parts.
Compliance:             1.and 2 a. Within 100 hours' time in service after the commencement date of this AD.
                        b. At intervals no greater than 100 hours' time in service thereafter.
                        3. a. Within 90 days of the commencement date of this AD.
                        b. At intervals no greater than 500 hours' time in service thereafter.
                     4. and 5. Before further flight.
                        This AD commences on 25 October 2019.
                Note 1:  Federal Aviation Administration of the United States of America (FAA) Airworthiness Directive (AD) 83-03-03 Amdt 39-4556 (FAA AD) has been referenced as a source document for Figure 1.
                Note 2:  National Transportation Safety Board of the United States of America (NTSB) Safety Recommendation(s) A-82-52 has been referenced as a source document for Figure 2.

             Note 3:  CASA may approve a radiographic inspection procedure designed by an  NDT Level 3 from ASTM Standards and recommended by the National Aerospace Non-Destructive Testing Board for accomplishing Requirement 2 for