Airworthiness Directive Schedule

Applicability: Part I - Model PA-38-112 aircraft, S/N 38-78A0001 through 38-79A0312 as detailed in Piper SB 637 Part II - Model PA-38-112 aircraft, S/N 38-78A0001 through 38-79A0254 Requirement: Part I - Inspect bracket P/N 77615-07 for forming cracks per Piper SB 637 Part I. Replace cracked fittings with undamaged part of same P/N before further flight. Part II - Check torque of stabiliser to fin and fin to fuselage attach bolts per Piper SB 637 Part II. (FAA AD 79-08-02 refers) Compliance: Part I - within next 10 hours TIS unless already accomplished Part II - within next 100 hours TIS Effective Date: DCA/PA38/6 - 9 January 1978 DCA/PA38/6A - 18 May 1979 Note: Requirement notified to registered owners on effective date DCA/PA38/7A Engine Mount - Inspection and Modification Applicability: Model PA-38-112 aircraft, S/N 38-78A0001 through 38-78A0678 not incorporating engine mount P/N 77651-02 Requirement: 1. Inspect per Piper SB 617B 2. Install engine mount P/N 77651-02 (FAA AD 81-23-07 refers) Compliance: 1. At intervals not exceeding 50 hours TIS until engine mount P/N 77651-02 installed. 2. At 1000 hours TIS since modification per Piper SB 617B, or within next 50 hours TIS, whichever is the later. Effective Date: DCA/PA38/7 - 23 February 1979 DCA/PA38/7A - 29 January 1982 DCA/PA38/8A Rudder Hinge - Modification Applicability: Model PA-38-112 aircraft, S/N 38-78A0001 through 38-80A0063 Requirement: Embody rudder lower hinge modification kit 763881 per Piper SB 613A (FAA AD 79-03-02 refers) Compliance: Within the next 50 hours TIS, unless already accomplished. Effective Date: DCA/PA38/8 - 23 February 1979 DCA/PA38/8A - 18 July 1980 Issued 27 October 2011 Page 3 of 9 CAA of NZ Aeroplanes Piper PA-38-112 (Tomahawk) DCA/PA38/9 Instrument Installation - Modification Applicability: Model PA-38-112 aircraft, S/N 38-78A0002 through 38-78A0104 as detailed in Piper SB 603 Requirement: Embody groundwire assembly per Piper SB 603. (FAA AD 79-17-05 refers) Compliance: Within the next 25 hours TIS unless already accomplished. Effective Date: 28 September 1979 DCA/PA38/10B Rudder Hinge - Inspection and Modification Applicability: Model PA-38-112 aircraft, S/N 38-78A0001 through 38-80A0099, 38-80A0113, 38- 80A0120 and 38-80A0123 through 38-80A0165 Requirement: 1. Inspection - remove rudder upper hinge pin and carefully displace rudder rearwards from fin to expose both parts of hinge P/N 77610-02. Inspect all hinge surfaces in area of hinge pin hole to forward edge of hinge for cracks using dye penetrant method. Install upper hinge bolt with torque of 50 to 70 inch lb. Do not exceed maximum value. Renew cracked fittings before further flight. 2. Modification - embody P/N 77610-03 brackets per Piper SB 686. 3. Replacement - Remove and replace the upper rudder hinge bracket, P/N 77610- 03, with a new upper rudder hinge bracket, P/N 77610-03 per Piper SB 686. (FAA AD 80-22-13 refers) Compliance: 1. Inspection at intervals not exceeding 50 hours TIS until modified. 2. Modification within the next 100 hours TIS. 3. At 5,000 hours TTIS or within the next 100 hours TIS, whichever is the later, and thereafter at intervals not to exceed 5,000 hours TIS. Effective Date: DCA/PA38/10A - 19 December 1980 DCA/PA38/10B - 13 March 1998 DCA/PA38/11 Cancelled – DCA/PA38/17B refers Effective Date: 29 November 2007 DCA/PA38/12A Fin Installation - Inspection and Parts Replacement Applicability: Model PA-38-112 aircraft as detailed in requirement Requirement: To preclude possible inflight failure due to fatigue, accomplish the following: 1. Aircraft S/N 38-78A0001 through 80A0198 not incorporating Piper kit P/N 764427. Inspect forward fin spar P/N 77601-03 per Piper SB 745 Part I at intervals not exceeding 100 hours TIS. 2. Aircraft not incorporating fuselage bulkhead assembly P/N 775553-06. Inspect fuselage bulkhead assembly P/N 77553-02 per Piper SB 745 Part II at intervals not exceeding 300 hours TIS. Issued 27 October 2011 Page 4 of 9 CAA of NZ Aeroplanes Piper PA-38-112 (Tomahawk) 3. Aircraft not incorporating aft vertical spar assembly P/N 77601-16, upper rudder hinge shim P/N 85606-02 and fuselage bulkhead assembly P/N 85615-02. Inspect aft vertical fin spar P/N 77601-02 per Piper SB 745 Part IV at 2500 hours TTIS, or within next 25 hours TIS whichever is the later, and thereafter at intervals not exceeding 200 hours TIS. Renew defective parts as prescribed before further flight. 4. Aircraft not incorporating Piper kit P/N 764421. Replace forward fin attachment plate P/N 77553-05 per Piper SB 745 Part III at 3000 hours TTIS, or within next 25 hours TIS, whichever is the later, and thereafter at intervals not exceeding 3000 hours TIS. 5. Aircraft incorporating Piper kit P/N 764421 and aircraft S/N 38-82A0102 through 82A0122. Replace forward fin spar attachment plate P/N 77553-05 per Piper SB 710 at 5000 hours TTIS, or within next 25 hours TIS whichever is the later and thereafter at intervals not exceeding 5000 hours TIS. (FAA AD 82-27-08 refers) Effective Date: DCA/PA38/12 - 16 March 1981 DCA/PA38/12A - 11 February 1983 DCA/PA38/13 Aileron Balance Weight Rib - Inspection Applicability: PA-38-112 aircraft, S/N 38-78A0001 through 38-81A0051 and 38-81A0105 Requirement: Inspect flange area of aileron balance weight rib P/N 77342-16 and -17 per Piper SB 723 for cracks. If cracked, embody Piper reinforcement kit P/N 764140 before further flight. (FAA AD 82-02-01 refers) Compliance: Within the next 50 hours TIS and thereafter at intervals not exceeding 100 hours TIS until Piper reinforcement kit P/N 764140 is embodied Effective Date: 13 November 1981 DCA/PA38/14A Elevator Assembly - Inspection Applicability: All model PA-38-112 aircraft Requirement: To preclude possibility of aircraft loss of controllability in flight due to elevator control surface assembly failure, accomplish the following, (unless already accomplished) 1. Visually inspect torque tube assembly P/N 77620-02 for cracks, paying particular attention to welded areas of each elevator attachment bracket to torque tube. Confirm any crack indication using magnetic particle method before further flight. 2. Remove torque tube assembly from elevator installation and inspect using magnetic particle method. Remove cracked assemblies from service before further flight. Reprotect uncracked assemblies before reinstallation. 3. Torque tube assemblies fitted as replacements are to be inspected using magnetic particle method before installation. Assemblies exhibiting cracking must not be fitted. Compliance: Visual Inspection - within the next 5 hours TIS Magnetic Particle Inspection - within the next 25 hours TIS Effective Date: DCA/PA38/14 - 12 June 1982 DCA/PA38/14A - 12 July 1985 Issued 27 October 2011 Page 5 of 9 CAA of NZ Aeroplanes Piper PA-38-112 (Tomahawk) DCA/PA38/15 Radio Support Installation - Modification Applicability: PA-38-112 aircraft, S/N 38-78A0001 through 38-82A0091 Requirement: To preclude possibility of flight control restriction due to radio support strap interference, replace all attachment strap non-self locking nuts with self locking nuts per Piper SB 748 Compliance: Within the next 25 hours TIS Effective Date: 1 September 1982 DCA/PA38/16 Fatigue Critical Components - Retirement Applicability: All model PA-38-112 aircraft Requirement: Retire the following components at the specified TTIS: Lower Longitudinal Trim Springs P/N 37523 or 61916-2 - 1,500 hours. Wing P/N 77352 and associated structure - 11,000 hours. Steel Upper Rudder Hinge P/N 77610-03 - 5,000 hours Effective Date: 11 February 1983 DCA/PA38/17B MLG Attachment - Modification and Inspection Applicability Model PA-38-112 aircraft, S/N 38-78A0001 through 38-82A0122 Requirement: To prevent failure of the MLG attachment bolts, accomplish the following: 1. Install MLG bolt replacement kit, Piper P/N 765-171 or P/N 765-172 as applicable per Piper SB 673B. 2. Inspect MLG attachment bolts for correct torque. If found loose, renew before further flight. Remove bolts and inspect. If bolts are found bent, cracked or corroded, renew before further flight. Inspect bolt holes in fittings for cracks and corrosion. Rectify any defects found before further flight. Reinstall MLG attachment bolts with a corrosion preventative grease. (FAA AD 90-19-03 refers) Compliance: 1. Within next 100 hours TIS. 2. At intervals not to exceed 100 hours TIS. Effective Date: DCA/PA38/17A - 24 November 1989 DCA/PA38/17B - 20 January 1995 DCA/PA38/18 Vertical Fin Spars - Inspection Applicability: Model PA-38-112 aircraft, S/N 38-78A0001 through 38-82A0122 Requirement: To preclude possible structural failure, inspect upper forward and aft vertical fin spars per Piper SB 763 and repair/reinforce as prescribed therein. (FAA AD 83-19-01 refers) Compliance: At 500 hours TTIS or within next 50 hours TIS whichever is the later and thereafter at intervals not exceeding 100 hours TIS until Piper kit 764 965 installed Effective Date: 19 August 1983 Issued 27 October 2011 Page 6 of 9 CAA of NZ Aeroplanes Piper PA-38-112 (Tomahawk) DCA/PA38/19A Flow Strip Installation – Modification Applicability: Model PA-38-112 aircraft, S/N 38-78A0001 through to 38-79A0582. Note 1: This AD revised to introduce an affected S/N range in the applicability and to clarify the AD requirement. Requirement: To standardise and improve stall characteristics, accomplish the following: 1. Install Piper Flow Strip Installation Kit P/N 763-930 and insert Piper P/N 761-658 revision 3, dated 18 December 1978 into the aircraft POH. The POH insert contains performance information applicable to aircraft fitted with Kit P/N 763-930. 2. Replace the Airspeed Indicator (ASI) with Piper ASI P/N 61906-02 or 61905-02, or alternatively change the original ASI markings as follows: • Red radial – 138 knots. • Yellow arc – from 110 to 138 knots. • Green arc – from 52 to 110 knots. • White arc – from 49 to 89 knots. Note 2: Piper SL No. 876 dated 12 April 1979 pertains to the subject of this AD. (FAA AD 83-14-08 refers) Compliance: 1. Within the next 100 hours TIS unless already accomplished. 2. Within the next 100 hours TIS unless already accomplished. Effective Date: DCA/PA38/19 - 19 August 1983 DCA/PA38/19A - 29 April 2010 DCA/PA38/20 Throttle Control - inspection and Modification Applicability: Model PA-38-112 aircraft, S/N 38-78A0001 through 38-82A0122 Requirement: To preclude possible loss of engine control, inspect and modify per Piper SB 760 Compliance: Inspection - within next 50 hours TIS Modification - by 30 September 1984 Effective Date: 8 June 1984 DCA/PA38/21 Elevator Control Installation - Modification Applicability: Model PA-38-112 aircraft, S/N 38-78A0001 through 38-82A0122 Requirement: To preclude possible control movement restriction modify per Piper SB 800 Compliance: Within the next 100 hours TIS or by 30 April 1985, whichever is the later Effective Date: 8 February 1985 DCA/PA38/22 Wing Skin - Inspection Applicability: Model PA-38-112 aircraft, S/N 38-78A0001 through 38-82A0122 Requirement: Inspect top inboard wing skin to spar rivets per Piper SB 879. Renew failed/loose rivets before further flight Compliance: At 3000 hours TTIS or within next 100 hours TIS whichever is the later, unless already accomplished, and thereafter at intervals not exceeding 1000 hours TIS Effective Date: 5 July 1988 Issued 27 October 2011 Page 7 of 9 CAA of NZ Aeroplanes Piper PA-38-112 (Tomahawk) DCA/PA38/23 Oil Pressure Line Fitting - Replacement Applicability: Model PA-38-112 aircraft, S/N 38-78A0001 through 38-82A0122 Requirement: To reduce engine oil loss in case of oil pressure line failure, replace the 90 degree fitting per Piper SB 936. If an optional hour meter oil pressure switch is installed, inspect the Tee fitting and nipple attaching the transducer and switch per the SB. If aluminium fittings are found, replace per the SB before further flight Compliance: Within the next 100 hours TIS Effective Date: 24 August 1990 DCA/PA38/24 Rear Frame Stiffener - Installation Applicability: Model PA-38-112 aircraft, S/N 38-78A0001 through 38-80A0198. Requirement: To prevent cracking and distortion of the rear spar frame assembly caused by hard landings and poor ground handling techniques, install rear spar frame reinforcement kit, per Piper SB 834. Compliance: Within next 200 hours TIS, unless already accomplished. Effective Date: 11 April 1997 DCA/PA38/25 Rudder Upper Hinge - Replacement Applicability: Model PA-38-112 aircraft, S/N 38-80A0166 through 38-82A0122. The aircraft S/Ns listed do not match those in Piper SB 686. This AD takes precedence over the applicability section of SB 686. Requirement: To prevent cracks in the upper rudder hinge bracket, which could result in separation of the rudder from the aircraft and loss of control, accomplish the following:- Remove and replace the upper rudder hinge bracket, P/N 77610-02, P/N 77610-03 or an FAA-approved equivalent P/N, with a new upper rudder hinge bracket, P/N 77610- 03 per Piper SB 686. (FAA AD 98-03-16 refers) Compliance: At 5,000 hours TTIS or within the next 100 hours TIS, whichever is the later, and thereafter at intervals not to exceed 5,000 hours TIS. Effective Date: 13 March 1998 * DCA/PA38/26A Gascolator Valve – Inspection and Replacement Applicability: Model PA-38-112 aircraft, all S/N. Note 1: This AD supersedes DCA/PA38/26 to extend the compliance with no change to the AD requirement. This AD is prompted by reports of finding locking type fuel drain valves fitted to the gascolators on certain PA-28 and PA-38 aircraft. This AD requires the replacement of locking gascolator fuel drain valves with a manufacturer approved non-locking drain valve. Requirement: To prevent the gascolator fuel drain inadvertantly being left open which could result in fuel starvation and a loss of engine power, accomplish the following: 1. Inspect the aircraft and determine the type of fuel drain valve installed on the gascolator. Issued 27 October 2011 Page 8 of 9 CAA of NZ Aeroplanes Piper PA-38-112 (Tomahawk) Issued 27 October 2011 Page 9 of 9 CAA of NZ If a locking fuel drain valve is found fitted, replace with Piper valve P/N 492-312 (CCA 36150) or an equivalent manufacturer approved non-locking valve. If a non-locking fuel drain valve is found fitted, no further AD action is required. 2. A locking fuel drain valve shall not be fitted to the gascolator on any affected aircraft. Note 2: For gascolator maintenance requirements refer to Piper SL No. 1141 date 27 April 2011 and the Piper PA-38-112 Maintenance/Service Manual. (NZ Occurrences 10/743 and 11/254 refer) Compliance: 1. By 5 January 2012. 2. From 5 October 2011. Effective Date: DCA/PA38/26 - 29 September 2011 DCA/PA38/26A - 5 October 2011