Aeroplanes - De Havilland DH82 Series (Tiger Moth)

when an unsafe condition is found to exist in an aircraft or aeronautical product in NZ, they will be added to the list below. .................................................................................................................................................. 9 UK CAA AD G-2014-0001-E Lower Fuselage Tie Rods – Inspection and Replacement ................................ 9 UK CAA AD 007-03-99 Cockpit Safety Harness Installation – Inspection and Life Limitation ......................... 9 * DCA/DH82/129B Croydon Manufactured Wing and Aileron Spars – Flight Limitation ................................ 10 Aeroplanes De Havilland DH82 Series (Tiger Moth) Issued 26 April 2018 Page 3 of 12 CAA of NZ DCA/DH82/101 Control Column - Modification Applicability: All model DH 82 Requirement: To prevent flange at base of hand grip fouling and withdrawing safety harness release pin during aerobatic manoeuvres, all control column hand grip flanges must be completely removed leaving only a rounded collar approximately 1/8 inch Compliance: By 1 July 1955 DCA/DH82/102 Mainplane Leading Edges - Modification Applicability: All model DH 82 Requirement: 1. To prevent collapse of the top and bottom mainplane leading edges, caused by failure of the glued joints the following is required: (a) Replace gimp pins attaching riblets to leading edge with No. 3 brass countersunk x ½ inch or No. 3 x 3/8 inch wood screws. (b) On top riblet mark off longitudinal centre line, and on this drill a hole (No. 36 Morse) approximately ¼ inch from nose end or riblet. (c) Countersink hole on top and attach nose riblet to leading edge using casein glue and wood screws. (d) Pre-work lower nose riblet similarly except that the hole shall be drilled 0.3 inch from nose end of riblet. Compliance: By 1 July 1955 DCA/DH82/103 Safety harness - Modification Applicability: All model DH 82 Requirement: 1. Safety Harness, from cockpit group, P/N U2572, and rear cockpit group, P/N U2573, shall be modified to prevent release pin, P/N AD9426/2, from turning, to ensure definite positioning of safety pin, P/N 9745/1, and to provide easier accessibility for pilot when inserting or withdrawing safety pin. 2. The release pin, is to be reworked to incorporate a mild steel, 18 gauge, strap riveted to the pin head. 3. No. 1 strap, P/N H26303A, is to be reworked to incorporate a 13-3/8 inch long webbing strip attached to its under side and assembled through the reworked head of the release pin. Compliance: By 1 July 1955 DCA/DH82/104A Fuselage, Joint E - Modification Applicability: All model DH 82 Requirement: To prevent the threaded portion of bolt in the joint plates from becoming worn, the left hand side bolt AGS. 749/4/1 must be replaced by bolt No. 2A15/12G, and the right hand side bolt by datum bolt P/N H37880 Compliance: Within next 50 hours TIS. Effective Date: DCA/DH82/104 - 1 July 1955 DCA/DH82/104A - 16 January 1998 Aeroplanes De Havilland DH82 Series (Tiger Moth) Issued 26 April 2018 Page 4 of 12 CAA of NZ DCA/DH82/105 Undercarriage Steel Fork Ends - Modification Applicability: All agricultural aircraft operated with overload Requirement: The fitting of steel fork ends, P/N 63063 is required for agricultural aircraft operated with overload and is recommended as an alternative to the standard dural fittings on other aircraft of the type. Compliance: By 1 July 1955 DCA/DH82/106 Undercarriage - Modification Applicability: All model DH 82 Requirement: To prevent the moving portion of the landing gear from becoming disengaged from the fixed portion in the event of failure, install a check cable in accordance with Drawing No. AWD/1/69. Compliance: By 1 July 1955 DCA/DH82/107 Control box - Inspection Applicability: All model DH 82 Requirement: 1. Remove the rear seat and examine the rearward extremities of the two longitudinal spruce members of the control box for cracks at the attachment of the quadrant which supports the elevator controls. 2. Cracked members must be renewed before further flight. Compliance: At intervals not exceeding 12 months Effective Date: 30 September 1954 DCA/DH82/108 Cancelled: Once only Inspection, purpose fulfilled DCA/DH82/109 Altitude Control - Inspection Applicability: All model DH 82 Requirement: Check that the Altitude Control Lever is locked to prevent the control being opened when operating the throttle lever. Should it be necessary to fly at a high altitude a light gauge wire which can be broken is to be used Compliance: Every periodic inspection Effective Date: 30 September 1954 DCA/DH82/110 Fuel Cock Slide - Inspection Applicability: All model DH 82 Requirement: 1. Examine the fuel cock to ensure that with the control disconnected, a force of not less than 6 lb is required to move the slide. 2. Should this requirement not be met, it may be corrected by adjustment of shim thickness between the body and the removable bottom portion or by replacement of the cork washer. Compliance: At intervals not exceeding 12 months Effective Date: 30 September 1954 Aeroplanes De Havilland DH82 Series (Tiger Moth) Issued 26 April 2018 Page 5 of 12 CAA of NZ DCA/DH82/111 Tailplane Support Bracket - Inspection Applicability: All model DH 82 Requirement: 1. Inspect the tailplane support bracket P/N H36619 for cracks, especially at the radius of the bend, particular attention being paid to the under surface. 2. All defective brackets must be replaced before further flight. Compliance: Every periodic inspection Effective Date: 30 September 1954 DCA/DH82/112A Fuel Tank Balance Pipe - Inspection and Annealing Applicability: All model DH 82 Requirement: 1. The fuel tank balance pipe, P/N H34886A is to be inspected for fracture, attention being paid to the point where the nipple is brazed to the pipe. Special care must be given to alignment of the pipe on replacement. 2. Subject pipe is to be annealed. Compliance: 1. Every periodic inspection. 2. At intervals not exceeding 300 hours TIS or whenever the fuel tank is removed. Effective Date: DCA/DH82/112 - 30 September 1954 DCA/DH82/112A - 16 January 1998 DCA/DH82/113 Fuselage Side Brace Struts - Inspection Applicability: All model DH 82 Requirement: The struts are to be inspected for cracks originating from the 3/16 inch hole in the fuselage port side bracing strut, joint C to E lower half. Ensure that the hole is uptaped Compliance: Every periodic inspection Effective Date: 30 April 1955 DCA/DH82/114 Mainplane Attachment Fittings - Inspection Applicability: All model DH 82 Requirement: Check that high tensile pins, P/N 37867, are used for the bottom mainplane front attachment fittings Compliance: Before C of A issue Effective Date: 30 April 1955 Aeroplanes De Havilland DH82 Series (Tiger Moth) Issued 26 April 2018 Page 6 of 12 CAA of NZ DCA/DH82/115 Elevator Control Bracket - Inspection Applicability: All model DH 82 Requirement: Defect reports have disclosed serious cracks in the corners of the rear control shaft support bracket. This bracket must be closely inspected for cracks by viewing through the rear control column opening in the top of the control box Compliance: Every 50 hours TIS until mod. DH.114 is embodied and thereafter at intervals of 150 hours TIS Effective Date: 30 April 1955 DCA/DH82/116 Cancelled: Once only inspection, purpose fulfilled DCA/DH82/117 Rudder Bar Pivot Pin - Inspection Applicability: All model DH 82 Requirement: Pivot pins in both the front and the rear rudder bar assemblies are to be inspected as follows: 1. Remove felt wick from bore of pin. 2. Measure the depth of the bore which shall not exceed 1-1/16 inch. If the depth of the bore exceeds this dimension, replace with a pin having the correct bore depth. Compliance: Next periodic inspection and whenever pins are replaced Effective Date: 30 September 1954 DCA/DH82/118 Fin Spar - Inspection Applicability: All model DH 82 Requirement: 1. Inspect fin post for crushing on each side face at the top longeron attachment. 2. If crushing does not exceed 1/32 inch in depth on either face, the fin post may continue in service. If crushing is between 1/32 inch and 1/16 inch in depth, the fin post may be repaired in accordance with the drawing RA 30. 3. If crushing exceeds 1/16 inch on either face the fin post must be renewed. Compliance: At intervals not exceeding 12 months Effective Date: 30 April 1955 DCA/DH82/119 Elevator Rock Shaft - Inspection Applicability: All model DH 82 Requirement: Inspect elevator rock shaft for end play. If measurement exceeds 1/8inch, rework in accordance with drawing EP 109 Compliance: At intervals not exceeding 12 months Effective Date: 30 September 1954 Aeroplanes De Havilland DH82 Series (Tiger Moth) Issued 26 April 2018 Page 7 of 12 CAA of NZ DCA/DH82/120A Front Fuselage Angle Fittings – Inspection and Replacement Applicability: Model DH 82 and DH 82A Tiger Moth aircraft, all S/N Note: This AD revised to introduce De Havilland Support Limited Technical News Sheet TNS CT(MOTH) No 17 issue 2, dated 1 December 2003. Requirement: To prevent failure of the front fuselage angle fittings accomplish the instructions in TNS CT(MOTH) No 17 issue 2 or later approved revisions. Compliance: At intervals not to exceed 50 hours TIS and after any reported heavy landing. Effective Date: DCA/DH82/120 - 30 April 1955 DCA/DH82/120A - 29 March 2012 DCA/DH82/121 Cancelled: Once only inspection, purpose fulfilled DCA/DH82/122A Cancelled: Once only inspection, purpose fulfilled DCA/DH82/123 Elevator Rock Shaft Lever - Inspection Applicability: All model DH 82 Requirement: The rear seat is to be inspected to confirm that a minimum clearance of 3/8 inch exists between the elevator rock shaft lever and the top edge of hole in back of the seat throughout the full range of movement of the elevator control Compliance: Every periodic inspection Effective Date: 30 April 1955 DCA/DH82/124A Flight Controls - Modifications Applicability: All model DH 82 Requirement: Accomplish the following modifications per British Aerospace TNS 5 Issue 1:- Mod No. 125 - Introduction of aileron sprocket chain guides and reduction of floor stop slot length. Mod No. 134 - To seal the aileron gear box and improve inspection facilities Mod No. 138 - To prevent splitting of aileron control box side members. (UK CAA ADs 2731, 2732 and 2733 refer) Compliance: At next wing removal or within 5 years, whichever is the sooner. Effective Date: DCA/DH82/124 - 16 January 1998 DCA/DH82/124A - 13 February 1998 DCA/DH82/125A Datum Bolts - Inspection Applicability: All model DH 82 Requirement: Inspect datum bolts per British Aerospace TNS 28 Issue 2. Rectify if necessary per TNS 28 Issue 2 before further flight. (UK CAA AD 002-10-97 refers) Compliance: Within next 50 hours TIS or 3 months, whichever is the sooner. Effective Date: DCA/DH82/125 - 16 January 1998 DCA/DH82/125A - 18 December 1998 Aeroplanes De Havilland DH82 Series (Tiger Moth) Issued 26 April 2018 Page 8 of 12 CAA of NZ DCA/DH82/126B Cancelled – De Havilland Support TNS No. 32 Issue 3 now refers (Cancelled UK CAA AD 002-03-98 refers) Note: AD 002-03-98 has been cancelled by the UK CAA. This is shown in UK CAA CAP 747 (Refer Appendix 6 in http://www.caa.co.uk/docs/33/CAP747.PDF) De Havilland Support Limited (DHSL) TNS 32 issue 3 makes various refinements with respect to actions taken in particular circumstances, so it becomes more onerous in the circumstances of a heavy landing, but less so for an aircraft just operating normally. It also includes good pictorial advice. In the NZ CAA and the UK CAA view the TNS should be assessed and actioned for normal maintenance anyway. The UK CAA have re-issued some of their Airworthiness Approval Notes covering Type Approval of these types. This is the same as SB information becoming part of normal maintenance manual with consequent withdrawal of the SB. DHSL have stated (and the fact that the UK CAA cancelled AD 002-03-98) that certifying personnel should adopt TNS 32 issue 3 recommendations to the extent indicated by their assessment of the individual condition and circumstances of each aircraft. The revised TNS may not be classified ‘Mandatory’, however DHSL (who provide Type Design Organisation advice) have stated that the TNS is to be treated as an extension of the relevant aircraft maintenance manual. In other words the revised TNS is now part of the manufacturer aircraft maintenance schedule and NZ CAA Rule 91.605(a)(3) addresses mandatory compliance with the manufacturer maintenance schedule. The CAA would expect an operator to comply with the new TNS which is now part of the manufacturer maintenance schedule. Effective Date: 26 March 2009 DCA/DH82/127C Fuselage Lateral Tie Rods – Inspection and Life Limitation Applicability: All model DH 82 series aircraft. Note 1: Revision C of this AD revised to clarify the requirement. Requirement: To prevent failure of the fuselage lateral tie rods, the port and starboard lower fuselage longerons, and the spar joint fittings, accomplish the following: Inspect the fuselage structure and the spar joint fittings, and repair/replace any defects found per the instructions in paragraph 2.A. of British Aerospace TNS 29 issue 3 or later UK CAA approved revisions. Replace the aft and forward lateral fuselage tie rods per paragraph 2.A. of TNS 29 before further flight. (UK CAA AD 006-10-97 refers) Compliance: Within the next 50 hours TIS or by 17 January 2010 whichever occurs sooner, unless previously accomplished within the last 2000 hours TIS or 18 years, and thereafter at intervals not to exceed 2000 hours TIS or 18 years whichever occurs sooner. Note 2: The 2000 hour/18 year life limitation applicable to the fuselage lateral tie rods is classified mandatory by the UK CAA. Effective Date: DCA/DH82/127A - 21 December 2000 DCA/DH82/127B - 29 October 2009 DCA/DH82/127C - 17 December 2009 DCA/DH82/128 Cancelled – DH82 Maintenance Documentation refers Effective Date: 30 April 2009 Aeroplanes De Havilland DH82 Series (Tiger Moth) Issued 26 April 2018 Page 9 of 12 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 http://www.caa.govt.nz/airworthiness-directives/states-of-design/ 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. UK CAA AD G-2014-0001-E Lower Fuselage Tie Rods – Inspection and Replacement Effective Date: 21 March 2014 UK CAA AD 007-03-99 Cockpit Safety Harness Installation – Inspection and Life Limitation Applicability: De Havilland DH60 series, DH82 series, DH83 series and DH94 series aircraft fitted with Sutton harnesses. Requirement: To prevent harness failure, inspect each Sutton harness per the instructions in British Aerospace Mandatory Technical News Sheet (TNS) No. 33, issue 2, dated 21 March 2002, or later revision. Inspect for evidence of broken stitches, cuts and tears, chafing, signs of contamination due to acid, oil, grease or water, and deterioration due to sunlight. Where any signs of degradation are found the harness is to be replaced before further flight. (UK CAA MPD 2001-012R2 also refers) Note: British Aerospace Mandatory TNS No. 33 (UK CAA AD No. 007–03–99 refers) is applicable to De Havilland DH60, DH60G, DH60M, DH60X, DH82, DH82A, Queen Bee, DH83, and DH94 aircraft. UK CAA AD 002-12-2001 revision 2, is applicable for other aircraft types fitted with Sutton harnesses not covered by TNS No. 33. Compliance: Initial compliance required before the issue of a New Zealand Certificate of Airworthiness, or at the next Review of Airworthiness (RA), whichever is the sooner, unless previously accomplished. Thereafter, compliance required with the repetitive requirements specified in TNS No. 33. Effective Date: 31 August 2017 De Havilland DH82 Series (Tiger Moth) Issued 26 April 2018 Page 10 of 12 CAA of NZ * DCA/DH82/129B Croydon Manufactured Wing and Aileron Spars – Flight Limitation Applicability: De Havilland DH82 Tiger Moth series aircraft fitted with replacement wing or aileron spars manufactured by Croydon Aircraft Company Limited prior to 31 May 2008. The affected DH82 Tiger Moth series wing spar part numbers are as follows: Wing spar position: LH P/N: RH P/N: Top front H34737 /C H34738 /C Top rear H34356 /C H34357 /C Bottom front H35096 /C H35097 /C Bottom rear H36830 /C H36831 /C The affected DH82 Tiger Moth series aileron (rear) spar part numbers are as follows: Spar: LH P/N: RH P/N: Aileron spar H37581A /C H37582A /C Mainplane spars may have been supplied under STC 0/21E/5 issued 20 March 2003, and aileron spars may have been supplied under STC number 0/21E/4 issued 22 January 2003, and. Note 1: DCA/DH82/129B revised to introduce a one-time inspection of the wing spars. If the spar section properties conform to the original de Havilland design shown in Figure 1, or if the wing spar section properties (minimum radius and dimensions) are no less than that shown in Figure 2, then no further action is required, and the previous flight limitations can be removed. Requirement: Review the aircraft records and determine if wing or aileron spars manufactured by Croydon Aircraft Company Limited (CACL) prior to 31 May 2008 are fitted to the aircraft. 1. If an affected wing or aileron spar is found installed, then aerobatics or other flights involving high load factors, including flight in turbulant conditions are prohibited until requirement 2 of this AD has been accomplished. 2. If an affected wing or aileron spar is found installed, accomplish the following: 2.1. If an affected aileron spar part number is found fitted, then conform the spar to the approved type design per the original de Havilland design, or replace the affected aileron spar, before further flight. 2.2. If an affected mainplane/wing spar is found fitted, then inspect the forward and the aft faces of the affected spars in four places, and determine if the spar section properties (i.e. area, shape) conform to the approved type design per the original de Havilland design shown in Figure 1. If the wing spar section properties conforms to the original de Havilland design shown in Figure1, then no further action is required, and the previous flight limitations can be removed. If the wing spar section properties do not conform to the original de Havilland design shown in Figure1, then accomplish requirement 3 of this AD, before further flight. 3. Inspect the affected wing spar and compare the spar section properties with the Croydon spar profile shown in Figure 2. If the wing spar section properties (minimum spar web radius and dimensions) are found not less than that shown in Figure 2, (i.e. the inside radii of the spar cut- De Havilland DH82 Series (Tiger Moth) Issued 26 April 2018 Page 11 of 12 CAA of NZ outs are found not less than 0.25 inches as shown in Figure 2), then no further action is required, and the previous flight limitations can be removed. If the wing spar section properties (minimum spar web radius and dimensions) are found less than that shown in Figure 2, (i.e. the inside radii of the spar cut- outs are found less than 0.25 inches as shown in Figure 2), then remove the affected spar from service, and replace with a serviceable part, before further flight. Note 2: Report any machined spars with section properties less than that shown in Fig.2 to the CAA by completing a CA005 Defect Report form. Please provide the spar part and serial numbers, and a copy of the release documentation. The form can be obtained from CA005@caa.govt.nz. The completed form can be emailed to the CAA at http://www.caa.govt.nz/Forms/CA005D_Form.pdf Figure 1 - De Havilland Design: De Havilland DH82 Series (Tiger Moth) Issued 26 April 2018 Page 12 of 12 CAA of NZ Figure 2 – Croydon Spar Profile: Compliance: 1. From 4 August 2017 (the effective date of DCA/DH82/129). 2. At the next periodic inspection when the spar is accessible, or at the next 100 hour inspection, or at the next annual inspection, whichever is the sooner. 3. If the wing spar section properties do not conform to the original de Havilland design shown in Figure1, then accomplish requirement 3 of this AD, before further flight. Effective Date: DCA/DH82/129 – 4 August 2017 DCA/DH82/129A – 10 August 2017 DCA/DH82/129B – 28 February 2018