Airworthiness Directive Schedule Aeroplanes Beechcraft 200 Series (Super King Air)

Compliance: Before issue of a New Zealand Certificate of Airworthiness or at the next ARA inspection after the effective date of this AD, whichever is the sooner. Effective Date: DCA/B200/3 - 26 March 2009 DCA/B200/3A - 29 October 2009 DCA/B200/4 Cancelled – DCA/B200/9 refers Effective Date: 29 October 2009 DCA/B200/5 Cancelled FAA AD 89-19-04R1 refers Effective Date: 30 November 2023 DCA/B200/6 Engine Controls Cross Shaft & Pedestal – Inspection and Modification Applicability: Model 200 and B200 aircraft, S/N BB–6 through to BB–185, BB–187 through to BB– 202, BB–204 through to BB–269, BB–271 through to BB–407, BB–409 through to BB–468, BB–470 through to BB–488, BB–490 through to BB–509, BB–511 through to BB–529, BB–531 through to BB–550, BB–552 through to BB–562, BB–564 through to BB–572, BB–574 through to BB–590, BB–592 through to BB–608, BB–610 through to BB–626, BB–628 through to BB–646, BB–648 through to BB–664, BB–666 through to BB–694, BB–696 through to BB–797, BB–799 through to BB–822, BB–824 through to BB–870, BB–872 through to BB–894, BB–896 through to BB–990, BB–992 through to BB–1051, BB–1053 through to BB–1092, BB–1094, BB–1095, BB–1099 through to BB–1104, BB–1106 through to BB–1116, BB–1118 through to BB–1184, BB–1186 through to BB–1263, BB–1265 through to BB–1288, BB–1290 through to BB–1300, BB–1302 through to BB–1313, BB–1315 through to BB–1384, BB–1389 through to BB–1425, BB–1427 through to BB–1447, BB–1449, BB–1450, BB–1452, BB–1453, BB–1455, BB–1456, BB–1458 through to BB–1683, BB–1685 through to BB–1716, BB–1718 through to BB–1720, BB–1722, BB–1723, BB–1725, BB–1726, BB–1728 through to BB–1826. Model 200C and B200C aircraft, S/N BL–1 through to BL–23, BL–25 through to BL– 57, BL–61 through to BL–72, and BL–124 through to BL–147. Requirement: To detect and correct loose pedestal cross shaft bolts, which could result in limited effectiveness of the control levers, accomplish the following: 1. Inspect the engine controls/cross shaft/pedestal for proper installation and the torque of the cross attach bolt per the instructions in part I of Raytheon Aircraft Aeroplanes Beechcraft 200 Series (Super King Air) Issued 30 October 2025 Page 4 of 9 CAA of NZ Company MSB No. SB 73–3634, dated September 2003 and the applicable aircraft maintenance manual. If the installation or torque is found incorrect, accomplish the corrective actions per the instructions in part I of MSB No. SB 73–3634 and the applicable aircraft maintenance manual before further flight. 2. Modify the pedestal and replace the engine controls cross shaft hardware per the instructions in part II of MSB No. SB 73–3634 and the applicable aircraft maintenance manual. Note: The accomplishment of requirement 2 of this AD is a terminating action for the repetitive inspection and retorque of requirement 1. (FAA AD 2004-17-02 refers) Compliance: 1. Within the next 50 hours TIS unless previously accomplished and thereafter at intervals not to exceed 100 hours TIS until accomplishment of requirement 2 of this AD. 2. At the next scheduled maintenance inspection or by 26 March 2010 whichever occurs later, unless previously accomplished. Effective Date: 26 March 2009 DCA/B200/7 Nose Landing Gear Fork – Inspection and Modification Applicability: Model 200 and B200 aircraft, S/N BB–2 and BB–6 through to BB–1314. Model 200C and B200C aircraft, S/N BL–1 through to BL–72, and BL–124 through to BL–131. Model B200C (C–12F) aircraft, S/N BL–73 through to BL–112, BL–118 through to BL–123, and BP–64 through to BP–71. Model B200C (UC–12F) aircraft, S/N BU–1 through to BU–10. Model B200C (UC–12M) aircraft, S/N BV–1 through to BV–10. Note 1: This AD is not applicable to aircraft embodied with Kit No. 101–8030–1S or Kit No. 114–8015–1S, as applicable. Requirement: To prevent failure of the nose landing gear (NLG) fork due to possible cracks which could result in reduced structural integrity and inability of the NLG fork to carry design limit and ultimate loads, accomplish the following: Inspect the NLG fork assembly for cracks using a fluorescent liquid penetrant or magnetic particle method per the instructions in part II of Raytheon Aircraft Company MSB SB 32–2102 revision 7 dated July 2003. If any cracks are found embody Kit No. 101–8030–1S or Kit No. 114–8015–1S as applicable per part II of MSB SB 32–2102 before further flight. Note 2: Embodying Kit No. 101–8030–1S or Kit No. 114–8015–1S as applicable, is the terminating action for the repetitive inspection requirements of this AD. (FAA AD 2004-23-02 refers) Compliance: Within the next 200 hours TIS unless previously accomplished, and thereafter at intervals not to exceed 200 hours TIS until Kit No. 101–8030–1 S or Kit No. 114– 8015–1 S as applicable, is embodied. Effective Date: 26 March 2009 Beechcraft 200 Series (Super King Air) Issued 30 October 2025 Page 5 of 9 CAA of NZ DCA/B200/8 Aft Fuselage Stringers – Inspection and Modification Applicability: Model 200 and B200 aircraft, S/N BB–2 and BB–6 through to BB–1462 Model 200C and B200C aircraft, S/N BL–1 through to BL–72 and BL–124 through to BL–138 Model B200C (C–12F) aircraft, S/N BL–73 through to BL–112 and BL–118 through to BL–123 Model B200C (C–12F) aircraft, S/N BP–64 through to BP–71 Model B200C (UC–12F) aircraft, S/N BU–1 through to BU–10 Model B200C (UC–12M) aircraft, S/N BV–1 through to BV–12 Note 1: This AD introduces the mandatory modification/repair of aircraft with known cracks in the aft fuselage stringer locations No. 5 through to No. 11. These cracks would have been detected through previous compliance with FAA AD 93–25–07 and/or Raytheon MSB SB 53–2472. Requirement: To prevent failure of the primary structure of the fuselage which could result in loss of the aircraft control, accomplish the following: 1. For aircraft with known cracks in the aft fuselage stringer locations No. 5 through to No. 11 on both the left-hand and right-hand sides of the aircraft: Embody the applicable modification kit or kits per Raytheon MSB SB 53–2472 revision 4, dated June 1993, revised July 2003, or Fit external doubler repairs on all the aft fuselage stringer locations No. 5 through to No. 11 on both the left-hand and right-hand sides of the aircraft per the procedures in the aircraft maintenance manual. 2. For aircraft without the applicable modification kit or kits embodied and aircraft without external doubler repairs accomplished in the aft fuselage stringer locations No. 5 through to No. 11 on both the left-hand and right-hand sides of the aircraft: Inspect the aft fuselage stringers for cracks per Raytheon MSB SB 53–2472. If sealant covers the stringers, remove the sealant to accomplish the required inspections. If no cracks are found, reapply the sealant before further flight. If any cracks are found, embody the applicable modification kit or kits per Raytheon MSB SB 53–2472 before further flight, or Fit external doubler repairs on all the aft fuselage stringer locations No. 5 through to No. 11 on both the left-hand and right-hand sides of the aircraft per the procedures in the aircraft maintenance manual before further flight. Note 2: Embodying the applicable modification kit or kits per Raytheon MSB SB 53–2472 to all aft fuselage stringer locations No. 5 through to No. 11 on both the left-hand and righthand sides of the aircraft is a terminating action to requirement 2 of this AD. (FAA AD 2005-01-18 refers) Compliance: 1. For aircraft with less than five known cracked stringers: Within the next 25 cycles, unless previously accomplished. For aircraft with five or more known cracked stringers: Before further flight, unless previously accomplished. 2. At 2500 cycles or within the next 25 cycles whichever occurs later, unless previously accomplished, and thereafter at intervals not to exceed 500 cycles. Note 3: For aircraft with unknown cycles, divide the hours TIS by 0.75 (eg. 18.75 hours TIS divided by 0.75 = 25 cycles). Effective Date: 26 March 2009 Beechcraft 200 Series (Super King Air) Issued 30 October 2025 Page 6 of 9 CAA of NZ DCA/B200/9 Wing Attachment Bolts & Nuts – Inspection and Replacement Applicability: Model 200, 200C, B200 and B200C aircraft listed in the following table: Aircraft Models: Aircraft S/N: Joints: Instructions: 200 BB344 through to BB-983 LF, UF P/N 98-39006 B200 BB-985 thru BB-1038 LF,UF P/N 98-39006 B200 BB-1040 thru BB-1045 BB-1047 thru BB-1049 BB-1053 thru BB-1078 & BB- 1080 LF,UF LF,UF LF,UF LF,UF P/N 98-39006 P/N 98-39006 P/N 98-39006 P/N 98-39006 200C and B200C BL-1 thru BL-51 LF,UF P/N 98-39006 Note 1: This AD supersedes DCA/B200/4 and includes Beech 200 aircraft in the applicablity. Note 2: This AD is not applicable to aircraft fitted with wing attachment bolts and nuts made of Inconel. Note 3: Wing attachments on the left and right sides of the aircraft are abbreviated as: LF=lower forward and UF=upper forward. Requirement: To ensure the structural integrity of outer wing panels to the wing center section attachments, use the Structural Inspection and Repair Manual No. 98-39006 to accomplish the following requirements at each wing attachment specified in the table of this AD: 1. Outer Wing Panel to Wing Center Section Attachment Inspection: Remove each steel nut and each steel tension bolt and accomplish a visual inspection and a magnetic particle inspection of the bolt and nut for cracks and corrosion in the parent steel. Replace bolts and nuts which are cracked or corroded. With the reassembly of each joint, coat the bolt, nut and adjacent parts with MIL- C- 16173 Grade 2 corrosion preventative compound. 2. Joint Tightness Inspection: Inspect each joint for tightness and tighten bolts/nuts as required, and inject MIL-C- 16173 Grade 2 corrosion preventative compound into a lubrication fitting on each barrel nut, (wherever a barrel nut is used). (FAA AD 1985-22-05 refers) Compliance: 1. Within 60 months after the issue of the original airworthiness certificate or by 29 December 2009 whichever is the later, and thereafter at intervals not to exceed 60 months. 2. Within the next 150 hours TIS after accomplishment of requirement 1 of this AD and thereafter at intervals not to exceed 12 months inject MIL-C-16173 Grade 2 corrosion preventative compound into a lubrication fitting on each barrel nut, (wherever a barrel nut is used). Effective Date: 29 October 2009 Beechcraft 200 Series (Super King Air) Issued 30 October 2025 Page 7 of 9 CAA of NZ DCA/B200/10 Cabin Door – Inspection and Rework Applicability: Model 200 aircraft, S/N BB-2 through to BB-111 Requirement: To prevent the cabin door from opening in flight, accomplish the following: 1. Inspect the cabin door for correct operation and rigging in accordance with the applicable Beech Shop/Maintenance Manual. When all the items specified in Paragraph II have been complied with the requirements of this paragraph (I) are no longer applicable. 2. Accomplish the following instruction in accordance with Beechcraft Service Instruction 0818-016 or later FAA approved revisions: Install Beech P/N 101-430124-1 and fix step door decals Beech P/N 101-430124-3 or -5 on the existing cabin door instruction plate. Check the operation of the cabin door. Inspect the cabin door latching mechanism and warning system for proper operation and rigging in accordance with the applicable Beech Shop/Maintenance Manual. Amend the AFM and include FAA approved Beech P/N 101-590010-3A4 AFM supplement revision dated 14 November 1975 or later FAA approved revisions. (FAA AD 1976-10-10 refers) Compliance: 1. Within the next 50 hours TIS and thereafter at intervals not to exceed 50 hours TIS until requirement 2 of this AD is accomplished. 2. By 29 December 2010 unless previously accomplished. Effective Date: 29 October 2009 DCA/B200/11 Pneumatic Deicing System – Placard and Tube Replacement Applicability: Model B200 aircraft, S/N BB-1926, BB-1978 and BB-1988 through to BB-2000 Model B200GT aircraft, S/N BY-1 through to BY-26 Note 1: This AD retains the requirements in superseded DCA/B200/2 and introduces Hawker Beechcraft MSB SB 30-3889 revision 1, dated October 2010 which requires additional actions. Requirement: To prevent the collapse of the tail deice boots pneumatic supply tubes possibly resulting in the tail deice boots failing to operate which could result in loss of aircraft control in icing conditions, accomplish the following: 1. Fabricate a placard (using at least 1/8-inch letters) with the following text and install the placard on the instrument panel within the pilot's clear view: “THIS AIRCRAFT IS PROHIBITED FROM FLIGHT IN KNOWN OR FORECAST ICING.” Note 2: Requirement 1 of this AD may be performed and certified under the provision in Part 43 Appendix A.1 (7) by the holder of a current pilot licence, if that person is rated on the aircraft, appropriately trained and authorised (Part 43, Subpart B refers), and the maintenance is recorded and certified as required by Part 43. 2. Replace the tail deice boots pneumatic supply tubing from the rear spar at Fuselage Station (FS) 227.00 to the aft pressure bulkhead at FS 347.750 with Hytrel tubing part number P/N 131823VH10D-1210 and remove the placard on the instrument panel. Accomplish these actions per the instructions in Hawker Beechcraft MSB SB 30-3889 revision 1, dated October 2010. If Hawker Beechcraft MSB no. SB 30-3889 issued March 2008 has already been accomplished, then a new piece of Hytrel tubing may be spliced on the existing Hytrel tubing in the aft evaporator bay area. (FAA AD 2010-26-03 refers) Beechcraft 200 Series (Super King Air) Issued 30 October 2025 Page 8 of 9 CAA of NZ Compliance: 1. Before further flight in known or forecast icing conditions, or by 27 February 2011 whichever occurs sooner, unless previously accomplished. 2. Before further flight in known or forecast icing conditions, or within the next 25 hours TIS, or by 24 May 2011 whichever occurs sooner. Effective Date: 24 February 2011 Beechcraft 200 Series (Super King Air) Issued 30 October 2025 Page 9 of 9 CAA of NZ The State of Design ADs listed below are available directly from the National Airworthiness Authority (NAA) websites. Links to NAA websites are available on the CAA website at: Links to state of design airworthiness directives | aviation.govt.nz If additional NZ ADs need to be issued when an unsafe condition is found to exist in an aircraft or aeronautical product in NZ, they will be added to the list below. FAA AD 89-19-04R1 Wing Fuel Bay Skin Panels – Inspection Applicability: Beech 200 and B200 aircraft, S/N BB-2 through to BB-1362); and Beech 200C and B200C aircraft, S/N BL-1 through to BL-135); and Beech 200CT and B200CT aircraft, S/N BN-1 through to BN-4); and Beech 200T and B200T aircraft, S/N BT-1 through to BT-33); and Fitted with wing fuel bay upper skin panels made with bonded (aluminum honeycomb sandwich) construction. Note 1: Beech B200 aircraft with S/N above BB-1238, and Beech B200C aircraft with S/N above BL-127, and Beech B200CT aircraft with S/N above BN-4, and Beech B200T with S/N above BT-30 were manufactured with bonded skin panels without rivets. Note 2: Approved partial replacement skin panels are defined by Kit Nos. 101-4045-3S (LH) and 101-4045-4S (RH). Compliance with this AD is no longer required for any skin panel modified by one of these kits. These panels are bonded with Nomex honeycomb core and do not have rivets. Effective Date: 30 November 2023 * FAA AD 2025-20-11 Rudder Control Pushrod – Inspection Applicability: B200GT, S/N BY-335, BY-356, BY-443, BY-453, BY-454, and B200CGT, S/N BZ-4 through to BZ-9. Effective Date: 30 October 2025