Airworthiness Directive Schedule Aeroplanes Cessna 150 and 152 Series

Electric Flap Actuator – Inspection, Maintenance and Modification Model 150F, G, H, J, K and L aircraft, S/Ns 15061533 through 15072629 Model F150F, G, H, J, K and L aircraft, S/Ns F15000001 through F15000738 Model A150K and L aircraft, S/Ns A1500001 through A1500277 Model FA150K and L aircraft, S/Ns FA1500001 through FA1500161 To prevent inadvertent retraction of the wing flaps and to insure positive operation of the electrical wing flap actuators, accomplish the following: 1. On all aircraft with more than 100 hours TTIS up to 500 hours TTIS, inspect the actuator jack screw for condition of lubricant and presence of contamination and scale, per the procedure in Cessna Service Letter SE70-16, supplement one, dated 10 July 1970. If any of the conditions prescribed in the inspection criteria are noted, remove, clean and relubricate the actuator jack screw, per Cessna Service Letter SE70-16, dated 12 June 1970, prior to further flight. 2. On all aircraft with more than 500 hours TTIS, remove, clean and relubricate the actuator jack screw, per the procedure in SL SE70-16. 3. Modify the aircraft per Cessna Service Letter SE72-2, dated 21 January 1972, and Cessna Service Letter SE72-2, supplement one, dated 24 March 1972, or alternatively Cessna Service Letter SE72-17, revision 1, dated 12 January 1973. Issued 26 November 2009 Page 4 of 16 CAA of NZ Aeroplanes Cessna 150 and 152 Series Note 1: Note 2: Compliance: Effective Date: The snubbers installed on certain aircraft, per SL SE72-2, supplement one, are not required with actuators specified by SL SE72-17, revision 1. (FAA AD 72-03-03 R3 refers) Modification of the aircraft per requirement three, is a terminating action to the requirements one and two of this AD. 1. Within the next 25 hours TIS, unless already accomplished within the previous 75 hours TIS, and thereafter at intervals not to exceed 100 hours TIS. 2. Within the next 25 hours TIS, unless already accomplished within the previous 75 hours TIS, and thereafter at intervals not to exceed 12 months or at each annual inspection, whichever occurs sooner. 3. By 1 December 2006, unless already accomplished. DCA/CESS150/119A DCA/CESS150/119B - 28 February 1969 - 1 December 2005 DCA/CESS150/120 Stall Warning Horn - Modification Applicability: Model 150 Series S/N 15061533 through 15069308 Model F150 Series S/N F150-00001 and up Requirement: Comply with Cessna SESL SE 68-22 and Supl. 1. (FAA AD 68-17-04 refers) Compliance: Within the next 10 hours TIS Effective Date: 28 February 1969 DCA/CESS150/121 Exhaust System - Inspection and Replacement Applicability: Requirement: Compliance: Model 150 Series S/N 17001 through 15061328 which have not been modified in accordance with Cessna SL 65-72 (FAA AD 67-03-01 refers) Inspect the right hand exhaust cabin heat exchanger for cracks by conducting a pressure test of 1½ PSI in accordance with Cessna 100 series Service Manual. Replace any found cracked with an exchanger inspected in accordance with this requirement and found free of cracks. Conduct a ground test with a carbon monoxide indicator by heading the aircraft into wind, warming the engine on the ground, advancing the throttle to full static rpm with cabin heater “ON” and taking carbon monoxide readings of the heated air stream at the cabin heater deflector P/N 0411824, on the fire wall inside the cabin. Within the next 50 hours TIS and thereafter at intervals not exceeding 100 hours TIS until modified. Effective Date: 28 February 1969 DCA/CESS150/122 Horizontal Stabiliser Attachment - Inspection Applicability: Model 150 Series S/N 15061533 through 15069190 Requirement: Compliance: Effective Date: Model F150 Series S/N F150-0001 through F150-0416 Comply with Cessna SESL SE 68-32 Every 100 hours TIS until modified in accordance with SK 150-33. 31 May 1969 Issued 26 November 2009 Page 5 of 16 CAA of NZ Aeroplanes Cessna 150 and 152 Series DCA/CESS150/123 Nose Gear Fork - Inspection and Modification Applicability: Model 150 Series S/N 17001 through 15059730 Requirement: Comply with Cessna SESL SE 71-34 Compliance: Effective Date: DCA/CESS150/124A Applicability: Requirement: Compliance: Effective Date: (FAA AD 71-22-02 refers) Inspect every 100 hours TIS until modified in accordance with Cessna service kit SK150-11 or approved equivalent 31 December 1971 Flap Actuator - Modification and Inspection Model 150 Series S/N 15061533 through 15072629 Model A150 Series S/N A15000001 through A15000277 Model F150 Series S/N F1500001 through F15000738 Model FA150 Series S/N FA1500001 through FA1500277 Model FRA150 Series S/N FRA1500122 through FRA1500161 Comply with Cessna SESL SE 72-2 & Supl 1 1. Modification by 1 January 1973 2. Inspection every 100 hours TIS or annually post modification. DCA/CESS150/124 - 31 March 1972 DCA/CESS150/124A -20 December 1996 DCA/CESS150/125 Wing Flap Actuator Ball Nut Assembly - Inspection, Placard and Replacement Applicability: Model 150 Series S/N 15078687 through 15078998 Model A150 Series S/N A1500697 through A1500711 Requirement: Compliance: Effective Date: DCA/CESS150/126D Applicability: Requirement: Compliance: Effective Date: Inspect and replace per. Cessna SE 76-25 (FAA AD 77-02-09 refers) If the date code stamp on the actuator is OH, HH, WH or ZH, install a placard near the flap control which reads: "FLAP EXTENSION PROHIBITED”, Until the ball nut assembly has been replaced per Cessna SESL SE 76-25 Inspection - before further flight, unless already accomplished. If assembly found defective, placard as above before further flight and replace assembly within next 50 hours TIS 18 February 1977 Seat Frame - Modification Model A150 Series S/N A1500277 through A1500647 Model FRA150 Series S/N FRA1500167 through FRA1500291. Embody Cessna service kit SK150-54 revision B or later per SESL SE 77-40. Within next 100 hours TIS. DCA/CESS150/126C - 20 December 1996 DCA/CESS150/126D - 12 March 1999 Issued 26 November 2009 Page 6 of 16 CAA of NZ Aeroplanes Cessna 150 and 152 Series DCA/CESS150/127D Applicability: Requirement: Note: Compliance: Effective Date: - Vertical Fin Attachment Nutplates – Inspection and Replacement Model 150F, 150G, 150H, 150J, 150K, 150L and 150M aircraft, S/Ns 15061533 through 15079405. Model A150K, A150L and A150M aircraft, S/Ns A1500001 through A1500734. Model 152 aircraft, S/Ns 15279406 through 15284541. Model A152 aircraft, S/Ns A1520735 through A1520943. Model F150F, F150G, F150H and F150J aircraft, S/Ns F150-0001 through F150- 0529. Model F150K, F150L and F150M aircraft, S/Ns F15000530 through F15001428. Model FA150K and FA150L aircraft, S/Ns FA1500001 through FA1500120. Model FRA150L and FRA150M aircraft, S/Ns FRA1500262 through FRA1500336. Model F152 aircraft, S/Ns F15201429 through F15201803. Model FA152 aircraft, S/Ns FA1520337 through FA1520372. To detect cracked nutplates P/N NAS 1068A4 which could result in separation of the vertical and/or horizontal tail assembly accomplish the following: Using a suitable light and mirror visually inspect the eight nutplates P/N NAS 1068A4 installed on the vertical fin aft attach bracket P/N 0432004-9 for cracks, per Cessna Single Engine Service Information Letter (SESIL) No. SE 79-49 revision 1. Replace defective parts, before further flight. (FAA AD 80-11-04 refers) The replacement of nutplates P/N NAS 1068A4 with nuts P/Ns AN365-428, MS20365-428, MS21042L4 or MS21044N4 is a terminating action to the requirement of this AD. Inspect within the next 100 hours TIS, unless already accomplished, and thereafter at intervals not to exceed 100 hours TIS until nutplates P/N NAS 1068A4 are replaced with nuts P/NS AN365-428, MS20365-428, MS2I042L4 or MS21044N4. DCA/CESS150/127B - 27 August 1982 DCA/CESS150/127C 22 October 1999 - DCA/CESS150/127D - 26 October 2006 DCA/CESS150/128A Applicability: Requirement: Compliance: Muffler Assembly - Inspection Model 152 Series S/N 15279406 through 15282919 Model A152 Series S/N A1520735 through A1520845 Model F152 Series S/N F15201429 through F15201547 Model FA152 Series S/N FA1520337 through FA1520350 with internally baffled KMR industries muffler assemblies with S/N 1 through 3999, or any S/N having prefix or suffix 'R' Part 1. Lock cabin heat in off position per Cessna SESL SE 78-71 para A3A. Part 2. Inspect heat exchanger per SE 78-71 paras A3 B1 and B2 and replace any found cracked per para S3, B3 and B4, or accomplish temporary repair per para D (FAA AD 79-02-06 refers) Part 1. Before further flight unless already accomplished. Issued 26 November 2009 Page 7 of 16 CAA of NZ Aeroplanes Cessna 150 and 152 Series Effective Date: Part 2. Within next 10 hours TIS, unless already accomplished and thereafter at intervals not exceeding 50 hours TIS until KMR industries heat exchanger can S/N 4000 or above installed and Cessna service kit 152-3 embodied. The cabin heat system may then be reactivated. DCA/CESS150/128 - 12 January 1979 DCA/CESS150/128A - 22 February 1980 DCA/CESS150/129 Vertical Fin Attachment Bkts.- Inspection and Modification Applicability: Model 150 Series S/N 15077789 through 15079405 Requirement: Compliance: Effective Date: DCA/CESS150/130A Applicability: Requirement: Compliance: Effective Date: Model F150 Series S/N F1500285 through F15001428 Model A150 Series S/N A1500654 through A1500734 Model FRA150 Series S/N FRA1500285 through FRA1500336 Model 152 Series S/N 15279406 through 15282617 Model F152 Series S/N F15201429 through F15201536 Model A152 Series S/N A1520735 through A1520833 Model FA152 Series S/N FA1520337 through FA1520348 Inspect fittings on models 150 and 152. Replace fittings on models A150, FRA150, A152 and FA152 per Cessna SESL SE 78-62. (FAA AD 78-25-07 refers) Inspection - At intervals not exceeding 100 hours TIS. Modification - within next 25 hours TIS unless already accomplished. 12 January 1979 Fuel Cap Modification - Model 150 Series S/N 17001 through 17999 and S/N 59001 through 15077005 Model A150 Series S/N A1500001 through A1500609 Model F150 Series S/N F150-0001 through F15001248 Model FA150 Series S/N FA1500001 through FA1500120 Model FRA150 Series FRA1500121 through FRA1500281 Fit vented fuel caps with related adapters and fuel servicing placards per Cessna SEB 92-27. (FAA AD 79-10-14 R1 refers) Within next 100 hours TIS unless already accomplished DCA/CESS150/130 - 23 March 1979 DCA/CESS150/130A - 20 December 1996 DCA/CESS150/131 Electrical System - Modification Applicability: Model 150 Series S/N 15065062 through 15075564 Requirement: Model A150 Series S/N A15000001 through A15000480 To prevent inflight electrical system failure, smoke in cockpit and/or fire in wire bundle behind instrument panel, accomplish the following: Issued 26 November 2009 Page 8 of 16 CAA of NZ Aeroplanes Cessna 150 and 152 Series Compliance: Disconnect at ammeter or electrical system bus, as applicable, wire which connects bus to cigar lighter receptacle (wire is connected to either the bus side, or equipment side of a circuit breaker, or to the ammeter) then either: 1. Reconnect wire to bus using an existing or newly installed circuit protection device properly rated for wire gauge used, or 2. Disconnect wire from lighter receptacle and remove it from aircraft, or 3. Insulate disconnected end of wire and secure it to bundle in which it is routed (FAA AD 79-08-03 refers) Note: FAA AC43.13-1A contains guidance information on wire gauge/circuit protection device ratings Within next 100 hours TIS Effective Date: 29 June 1979 DCA/CESS150/132 Flap Actuator - Modification Applicability: Model 152 Series S/N 15279406 through 15284080 Requirement: Model A152 Series S/N A1520735 through A1520919 Model F152 Series S/N 15201429 through F15201798 Model FA152 Series S/N FA15200337 through FA15200372 Install new mechanical stop nut per Cessna SESIL SE 79-57 or replacement actuator P/N C301002-0110. (FAA AD 80-01-06 refers) Compliance: Within next 50 hours TIS Effective Date: 22 February 1980 DCA/CESS150/133 Flap Cable Installation - Modification Applicability: Model 150 Series S/N 15078506 through 15079405 Model A150 Series S/N A1500685 through A1500734 Model F150 Series S/N F15001339 through F15001428 Model FRA150 Series S/N 1500312 through FRA1500336 Model 152 Series S/N 15279406 through 15283354 Model A152 Series S/N A1520735 through A1520867 Model FA152 Series S/N FA1520337 through FA1520357 Requirement: Compliance: Effective Date: Embody Cessna service kit SK172-60A per Cessna SESIL SE 79-16 Supl 1. (FAA AD 80-06-03 refers) Prior to accumulation of 1000 hours TTIS. Aircraft with 900 hours or more TIS, within next 100 hours TIS 18 April 1980 Issued 26 November 2009 Page 9 of 16 CAA of NZ Aeroplanes Cessna 150 and 152 Series DCA/CESS150/134A Applicability: Requirement: Compliance: Effective Date: DCA/CESS150/135A Applicability: Requirement: Aileron Hinge Pin Installation - Inspection Models 152 Series S/N 15282032 through 15285783 Model A152 Series S/N A1520809 through A1521022 Model F152 Series S/N F15201529 through F15201936 Model FA152 Series S/N FA1520348 through FA1520382 as respectively detailed in Cessna SIL SE 83-18 Inspect per Cessna SIL SE 83-18 and rectify defective installations as prescribed. (FAA AD 83-22-06 refers) Within next 100 hours TIS unless already accomplished DCA/CESS150/134 - 16 December 1983 DCA/CESS150/134A- 20 December 1996 Seat Adjustment Mechanism – Inspection Model 150A, 150B, 150C, 150D, 150E, 150F, 150G, 150H, 150J, 150K, 150L and 150M aircraft S/N 15059019 through 15079405. Model A150K, A150L and A150M aircraft S/N A1500001 through A1500734. All model 152 and A152 aircraft. All model F150G, F150H, F150J, F150K, F150L, F150M, FA150K, FA150L, FRA150L and FRA150M aircraft. All model FA152 and F152 aircraft. To assure proper engagement of the seat locking mechanism and to preclude inadvertent seat slippage, accomplish the following on each pilot and copilot seat and all associated seat rails: 1. Measure each hole in each seat track for excessive wear. If the wear dimension across any hole exceeds 10.67mm (0.42 inches), (see Figure 1), replace track before further flight. WEAR DIMENSION -NOMINAL MFG DIA 0.281 CROSS SECTION OF SEAT TRACK SHOWING HOLE WEAR Figure 1 2. Visually inspect the seat rail holes for dirt and any debris, which may preclude engagement of the seat pin. Remove any such material before further flight. Issued 26 November 2009 Page 10 of 16 CAA of NZ Aeroplanes Note 1: Cessna 150 and 152 Series 3. Lift up on the forward edge of each seat to eliminate all vertical play. With the seat in this position, measure the depth of engagement of each seat pin. If the engagement depth of any pin is less than 3.81mm (0.15 inches), (see Figure 2), replace or repair necessary components, before further flight. If the track is worn, this dimension is measured from the worn surface, not the manufactured surface. MIN PIN DEPTH ENGAGEMENT 0.15 inches SEAT LOCK PIN Figure 2 ROLLER HOUSING THICKNESS TANG THICKNESS Note 2: Compliance: 4. Visually inspect seat rollers for flat spots. Ensure that all rollers and washers, turn freely on their axle bolts (or bushings if installed) and move freely on seat rails. Replace rollers having flat spots and any worn washers, before further flight. If there is any binding between the roller bores, washers, and axle bolts (or bushings if installed), remove, clean, and reinstall these parts, before further flight. Do not lubricate rollers, washers, axle bolts or bushings as the lubricant will attract dust and other particles which can cause binding. 5. Measure the wall thickness of the tang (see Figure 2). If the tang thickness has worn to less than 1/2 the housing thickness, replace the roller housing, prior to further flight. 6. Check the springs that keep the lock pins in position in the track holes for positive engagement action. Replace any spring which does not provide positive engagement, before further flight. 7. Visually inspect the seat tracks for cracks per Cessna SIL SE83-6. Replace any seat track which does not satisfy the prescribed criteria, before further flight. (FAA AD 87-20-03 R2 refers) 1. Aircraft with less than 1000 hours TTIS, accomplish prior to accumulation of 1100 TIS. 2. 3. Aircraft with 1000 or more TTIS, accomplish within the next 100 hours TIS. Thereafter at intervals not exceeding 100 hours TIS. Effective Date: 31 March 2005 DCA/CESS150/136 Instrument Panel Light Rheostat - Replacement Applicability: Model 150 Series S/N 15061533 through 15071128 Model F150 Series S/N F150-0001 through F150-0529. Issued 26 November 2009 Page 11 of 16 CAA of NZ Aeroplanes Requirement: Cessna 150 and 152 Series To prevent an in-flight fire caused by a short circuit in the electrical wiring controlled by the instrument panel light dimming rheostat, accomplish the following:- Replace the existing rheostat with one of improved design that is current limited and heat protected, P/N RD-0015H-1600, refer Cessna SEB92-33R2. (FAA AD 93-24-15 refers) By 30 September 1994 Compliance: Effective Date: 18 March 1994 DCA/CESS150/137 Short Takeoff and Landing Kit - Inspection Applicability Requirement: Model 150 series, A150 series, 152 and A152 fitted with a Bush Conversions Inc, Short Takeoff and Landing (STOL) kit per STC SA1371SW. To prevent the aircraft entering a stall condition because of improper wing stall fence height which could result in loss of control of the aircraft, accomplish the following:- Measure the height of the wing stall fence at its trailing edge to ensure that its height does not exceed 1.28 inches. (see diagram) Wing Leading Edge Compliance: Stall Fence Point "A" Wing 1001-23 Stall Fence -90° to Wing Contour Upper Surface of Wing 18.00 (Distance from Point "A" along the Upper Surface of Wing) If Stall Fence is 1.16 ± 0.12 High that is correct height for Cessna 150/152. If Greater Than 1.28 high Remove Stall Fences and Install the Correct One. Figure 1 Mid-America Dwg No.1001 (STC SA1371 SW) If the height of the wing stall fence exceeds 1.28 inches, prior to further flight, install a smaller fence in accordance with instructions obtained from the Civil Aviation Authority. (FAA AD 96-12-23 refers) Within next 100 hours TIS. Effective Date: 2 August 1996 Issued 26 November 2009 Page 12 of 16 CAA of NZ Aeroplanes DCA/CESS150/138 Wing Spar Attachment - Modification Applicability: Model 150 Series S/N 15074635 through 15074799 Model A150 Series S/N A1500415 through 1500427 Requirement: Comply with Cessna SESL SE 73-20 (FAA AD 73-23-07 refers) Compliance: Within the next 50 hours TIS Cessna 150 and 152 Series Effective Date: 20 December 1996 DCA/CESS150/139 Fuel, Oil or Hydraulic Hose - Removal Applicability: All model 150, A150, F150, 152, A152 and F152 series. Requirement: To prevent fuel, oil or hydraulic systems failure caused by a collapsed hose, check the aircraft maintenance records for any fuel, oil or hydraulic hose, Cessna P/N S51- 10, replaced between March 1995 and 14 March 1997. If any fuel, oil or hydraulic hose, Cessna P/N S51-10, has been replaced between March 1995 and 14 March 1997, accomplish the following:- Compliance: Before further flight physically check for a diagonal or spiral external reinforcement wrap per Cessna SB SEB96-15. Replace any P/N S51-10 hose that has a diagonal or spiral pattern external reinforcement wrap with a P/N S51-10 hose that has a criss- cross pattern external wrap per SB SEB96-15. (FAA AD 97-01-13 refers) Within next 60 hours TIS or 60 days, whichever is the sooner. Effective Date: 14 March 1997 DCA/CESS150/140 Fuel Strainer Assembly - Inspection Applicability: Requirement: Models 150F, 150G, 150H, 150J, 150K, 150L, 150M, A150K, A150L, A150M, A- 150L, A-A150L, F150F, F150G, F150H, F150J, F150K, F150L, F150M, FA150K, FA150L, FA150M, FRA150L, FRA150M, 152, A152, F152, and FA152, that have fitted a Cessna P/N 0756005-2 top assembly, P/N 0756005-8 fuel strainer assembly, or a P/N 0756005-9 fuel strainer assembly shipped from Cessna between 12 December 1996, and 5 September 1997. Note: All aircraft S/Ns, including those manufactured in France that have a capital "F" or "FR" prefix on the model number: To prevent foreign material from entering the fuel system and engine, which could result in loss of engine power or complete engine stoppage during flight, accomplish the following: Issued 26 November 2009 Page 13 of 16 CAA of NZ Aeroplanes Cessna 150 and 152 Series 1. Measure the standpipe in the fuel strainer assembly (tube in the filter strainer top assembly) for a visible maximum length of 1.68 inches, per Cessna SEB 97-9. If the standpipe measures greater than 1.68 inches, prior to further flight, replace the filter strainer top assembly per SEB 97-9. 2. Do not fit to any aircraft a fuel strainer assembly where the standpipe measures greater than 1.68 inches. (FAA AD 2000-06-01 refers) Compliance: 1. By 27 April 2001 2. From 27 April 2000 Effective Date: 27 April 2000 - DCA/CESS150/141 Shoulder Harness – Inspection & Modification Applicability: All Model 150, A150, F150, series, which have incorporated Cessna Mod Kit AK150-7 or AK150-121. Requirement: Compliance: To prevent slippage of the pilot and copilot shoulder harness, which could result in serious injury to the pilot and copilot, accomplish the following: 1. Inspect the upper shoulder harness adjuster P/N 443030-401 for the presence of a retainer spring, in accordance with Cessna Single Engine Service Bulletin SEB86-8, Revision 1. 2. If a retainer spring is found during the inspection of the upper shoulder harness adjuster, prior to further flight remove the spring by cutting each side; and stamp out the -401 identification number in accordance with Cessna Single Engine Service Bulletin SEB86-8, Revision 1 3. If a retainer spring is not found during the inspection of the upper shoulder harness adjuster, make an entry in the airplane log book showing compliance with this AD. 4. Only incorporate Cessna Accessory Kits that have been inspected and modified in accordance with this AD. (FAA AD 2004-19-01 refers) Within the next 100 hours TIS Effective Date: 25 November 2004 DCA/CESS150/142 BRS-150 Parachute System - Modification Applicability: Model 150, 150A, 150B, 150C, 150D, 150E, 150F, 150G, 150H, 150J, 150K, A150K, 150L, A150L, 150M, A150M, 152 and A152 aircraft fitted with BRS-150 Parachute System, S/N 50001 through 50006 per STC SA64CH. Requirement: Compliance: Effective Date: To prevent unsuccessful parachute deployment due to possible premature separation of the pick-up collar from the launch tube, accomplish the following: Remove the pick-up collar support, nylon screws and launch tube, and replace with a new pick-up collar support, custom tension screws and a new launch tube per BRS SB 2008-04-01 revision 1, issued 24 April 2008. (FAA AD 2008-22-18 refers) Within the next 25 hours TIS unless already accomplished. 9 December 2008 Issued 26 November 2009 Page 14 of 16 CAA of NZ Aeroplanes * DCA/CESS150/143B Applicability: Cessna 150 and 152 Series Rudder Stop - AFM Amendment, Placard and Modification Model 150F aircraft, S/N 15061533 through to 15064532 Model 150G aircraft, S/N 15064533 through to 15064969 and 15064971 through to 15067198 Model 150H aircraft, S/N 15067199 through to 15069308 and 649 Model 150J aircraft, S/N 15069309 through to 15071128 Model 150K aircraft, S/N 15071129 through to 15072003 Model 150L aircraft, S/N 15072004 through to 15075781 Model 150M aircraft, S/N 15075782 through to 15079405 Model A150K aircraft, S/N A1500001 through to A1500226 Model A150L aircraft, S/N A1500227 through to A1500432 and A1500434 through to A1500523 Model A150M aircraft, S/N A1500524 through to A1500734 and 15064970 Model F150F aircraft, S/N F150-0001 through to F150-0067 Note 1: Note 2: Requirement: Model F150G aircraft, S/N F150-0068 through to F150-0219 Model F150H aircraft, S/N F150-0220 through to F150-0389 Model F150J aircraft, S/N F150-0390 through to F150-0529 Model F150K aircraft, S/N F15000530 through to F15000658 Model F150L aircraft, S/N F15000659 through to F15001143 Model F150M aircraft, S/N F15001144 through to F15001428 Model FA150K aircraft, S/N FA1500001 through to FA1500081 Model FA150L aircraft, S/N FA1500082 through to FA1500120 Model FA150L or FRA150L aircraft, S/N FA1500121 through to FA1500261 fitted with FKA150-2311 and FKA150-2316, or FRA1500121 through to FRA1500261 Model FA150M or FRA150M aircraft, S/N FA1500262 through to FA1500336 fitted with FKA150-2311 and FKA150-2316, or FRA1500262 through to FRA1500336 Model 152 aircraft, S/N 15279406 through to 15286033 Model A152 aircraft, S/N A1520735 through to A1521049, A1500433, and 681 Model F152 aircraft, S/N F15201429 through to F15201980 Model FA152 aircraft, S/N FA1520337 through to FA1520425 The applicability of DCA/CESS150/143B revised for model 150G, FA150L, FA150L, FRA150L, FA150M and FRA150M aircraft. This AD also revised to clarify the requirement with no change to the compliance. Aircraft may not be used for intentional spins and other acrobatic/aerobatic manoeuvres until the rudder stop modification per requirement 2 or 3 of this AD is accomplished. Amend the AFM and install a placard per requirement 1 of this AD until requirement 2 or 3 is accomplished. To prevent the rudder from traveling past the normal travel limit which could result in contact between the rudder and the elevator, accomplish the following: Issued 26 November 2009 Page 15 of 16 CAA of NZ