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 repeals Airworthiness Directive (AD) AD/PZL/5 and issues the following AD under subregulation 39.001 (1) of CASR 1998 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.
PZL M18 Dromader Series Aeroplanes
AD/PZL/5 Amdt 1
Centre Wing to Outboard
Wing Attachment Joints
24/2013
 
Applicability:
All Models PZL M18, M18A, and M18B aircraft.

Requirement:
1.    For aircraft with centre wing to outboard wing attachment joints with a corrected Time Since New (TSN) of less than 2500 hours:
(a)   Inspect the wing attachment joints, including the fore and aft faces of each lug, in accordance with Section 5.4.3 Verifying inspection, verifying inspection scope item 1 of the PZL Mielec Airplane Description and Service Manual (pages 5-14).
(i)    For item 1.e/ of Section 5.4.3 Verifying inspection, verifying inspection of the PZL Mielec Airplane Description and Service Manual (pages 5‑14), the non-destructive inspection method used must be the magnetic particle inspection method detailed in Section 2.7 of the PZL Mielec Airplane Description and Service Manual.
(ii)   Perform the following after each inspection:
(1)     Repair any corrosion damage found to the extent allowed in the PZL Service Bulletin E/02.170/2000 dated 3 August 2000 and apply anti-corrosion protection;
(2)     Replace the wing attachment joints if found cracked or if the corrosion damage is more than is specified using PZL Service Bulletin No. E/02.170/2000 dated 3 August 2000;
(3)   Eliminate any ovalisation of the wing attachment joint main holes using PZL Service Bulletin No. E/02.170/2000 dated 3 August 2000.
(b)   Inspect the wing attachment joints in accordance with the task at Section 5.5 Periodic Work, Wing item 4 of the PZL Mielec Airplane Description and Service Manual (pages 5-18).

 
2.    For aircraft with centre wing to outboard wing attachment joints with a corrected TSN at or above 2500 hours:
(a)   Inspect the wing attachment joints, including the fore and aft faces of each lug, in accordance with Section 5.4.3 Verifying inspection, verifying inspection scope item 1 of the PZL Mielec Airplane Description and Service Manual (pages 5-14).
(i)       For item 1.e/ of Section 5.4.3 Verifying inspection, verifying inspection of the PZL Mielec Airplane Description and Service Manual (pages 5‑14) the non-destructive inspection method used must be the magnetic particle inspection method detailed in Section 2.7 of the PZL Mielec Airplane Description and Service Manual.
(ii)     Perform the following after each inspection:
(1)     Repair any corrosion damage found to the extent allowed in the PZL Service Bulletin E/02.170/2000 dated 3 August 2000 and apply anti-corrosion protection;
(2)     Replace the wing attachment joints if found cracked or if the corrosion damage is more than is specified using PZL Service Bulletin No. E/02.170/2000 dated 3 August 2000;
(3)   Eliminate any ovalisation of the wing attachment joint main holes using PZL Service Bulletin No. E/02.170/2000 dated 3 August 2000.
(b)   Inspect the wing attachment joints in accordance with the task at Section 5.5 Periodic Work, Wing item 4 of the PZL Mielec Airplane Description and Service Manual (pages 5-18).
(c)   Inspect, using magnetic particle method detailed in Section 2.7 of PZL Mielec Airplane Description and Service Manual, the centre wing to outboard wing attachment joints for cracks in the lugs, corrosion in the main holes, and ovalisation of the main holes in accordance with PZL Service Bulletin No. E/02.170/2000 dated 3 August 2000 and perform the following after each inspection:
(i)       Repair any corrosion damage found to the extent allowed in the Requirement document and apply anti-corrosion protection;
(ii)     Replace the wing attachment joints if found cracked or if the corrosion damage is more than is specified using PZL Service Bulletin No. E/02.170/2000 dated 3 August 2000;
(iii)   Eliminate any ovalisation of the wing attachment joint main holes using PZL Service Bulletin No. E/02.170/2000 dated 3 August 2000.

 
 
Note 1:  FAA AD 2000-18-12 Amdt 39-11897 refers.
Note 2:  The approval by CASA of Aviation NDT Services Pty Ltd procedure titled Eddy Current Testing Procedure for Dromader M18 Centre Section Attachment Joints, Procedure No. QP.00.36(E), Issue 2, dated 8 September 2000 as an alternative inspection procedure to use in lieu of the non-destructive magnetic particle inspection procedure, has been revoked.

Compliance:
For requirement 1(a) -  Before next flight.
For requirement 1(b) -  Every of 100 corrected flight hours after carrying out requirement 1.(a).
For requirement 2(a)
A)   For attachment joints with a corrected total time in service of 2500 hours or more: Before next flight and then every 2500 corrected flight hours thereafter.
B)   For attachment joints that have complied with 1(a): Upon accumulating 2500 hours corrected total time in service on the attachment joint, and thereafter at intervals not to exceed 2500 corrected flight hours.
For requirement 2(b) -  Before next flight and then every 100 corrected flight hours.
For requirement 2(c) -  Every 500 corrected flight hours or 12 calendar months, whichever occurs first, after carrying out requirement 2(b).
Note 3:  Corrected flight hours is the total of the flight time that is calculated from each flight’s flying time multiplied by the appropriate factor that relates to the aircraft maximum take-off weight for that flight. (Refer to PZL M 18 “Dromader” Aircraft Repair Manual Model: M18, M18A, M18AS, M18B, Edition 3, dated
May 1981, Section 7.)

 
This Airworthiness Directive becomes effective on 15 November 2013.

Background:
This Directive is issued because of local reports of cracking of the bore in the joint and the issue of an Airworthiness Directive by the FAA following 2 instances of in‑flight wing separations, where severe corrosion and pitting led to high stress concentrations on the wing attachment joints. The FAA AD and PZL Service Bulletin call for the initial inspection at 3000 hours TIS. However, cracks were found in an Australian registered M-18A at only 2776 hours TIS.

 
This Amendment 1 was issued after review of Aviation NDT Services QP.00.36(E), Issue 2, dated 8 September 2000 eddy current inspection procedure that had previously been approved as an alternative to the magnetic particle procedure required by this airworthiness directive. It also includes a visual inspection required 100 hourly periodic inspection and to require the centre wing and outboard wings to be moved to allow better access for inspection of the wing attachment joints every 2500 hours. The repeat inspection of the attachment joints every 500 hours remains but the wings do not need to be removed from the fuselage.

 
[Signed N. Ward]
 
Nicholas Ward
Delegate of the Civil Aviation Safety Authority
15 November 2013