Results
69-22-02: 69-22-02 PIPER: Amdt. 39-865 as amended by Amendment 39-1288 is further amended by Amendment 39-3521. Applies to the following models: PA-28-140, /-150, /-160, /-180, /-235, and PA-32-260/-300. The following are affected serial numbers: PA-28-140, 28-20001 through 28-7725290 inclusive; PA-28-150/-160/-180, 28-1 through 28-4377 inclusive; PA-28-235, 28- 10001 through 28-11039 inclusive; PA-32-260, 32-1 through 32-1110 inclusive; and PA-32-300, 32-40001 through 32-40565 inclusive. Compliance required within 25 hours time in service from the effective date of this AD, unless already accomplished within the last 75 hours time in service, and thereafter at intervals not to exceed 100 hours time in service from the last inspection. To prevent possible failure of the control wheel, accomplish the following: (a) Remove the Piper medallion from the face of each control wheel. (b) Inspect each control wheel for cracks which may extend radially from the retaining pin.Cracks may be evident on the bottom of the control wheel hub where the pin enters the wheel as line cracks on the face or back of the hub as a crack in the hub cavity in line with the pin. The inspection is to be done using either of the following methods: (1) Use a small pen light next to the surface and inspect under at least a three-power glass. Inspect in at least a 1/2" path from the top of the pin to the bottom on the front and back of the control wheel hub. Cracks, either needle shaped or extending across the entire surface will show as black lines in the light field. If a line is only a scratch, the bottom will always be visible. The wheel should be cleaned with ordinary detergent and water only. The use of chemical cleaners and/or solvents such as acetone must be avoided. (2) An equivalent inspection method approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region. (c) If cracks are found in the path along the hub as described in (b)(1), replace the control wheel before further time in service. This AD is applicable to new control wheels of the same part number installed in accordance with this paragraph. (d) The control wheel medallion may be replaced with regular contact cement which has been allowed to dry thoroughly before assembly or with any commercial 2-part epoxy adhesive. Under no circumstances use acetate adhesive or other plastic cements or any form of Locktite as these materials may not be compatible with the plastic material in the wheel. (e) The repetitive inspection requirements of this AD may be terminated by replacing the plastic control wheel(s) with metal ramshorn type control wheel Piper part number 78729-02V (.750" o.d. shaft) or 79276-00V (1.125" o.d. shaft) as applicable. Replacement of one control wheel (i.e., left or right) does not terminate the requirement for continuing repetitive inspections of the other control wheel, if that other control wheel is the molded plastic type. (f) Piper Service Letter No. 527D, dated June 21, 1978, or later approved revisions, pertains to this same subject. (g) Make appropriate logbook entry indicating compliance with the provisions of this AD. Amendment 39-865 became effective November 4, 1969. Amendment 39-1288 became effective September 15, 1971. This amendment 39-3521 becomes effective July 30, 1979.
2023-08-04: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8, 787-9, and 787-10 airplanes. This AD was prompted by reports of a loss of water pressure during flight and water leaks that affected multiple pieces of electronic equipment. This AD requires a detailed visual inspection of all door 1 and door 3 lavatory and galley potable water systems for any missing or incorrectly installed clamshell couplings, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
79-13-03: 79-13-03 PIPER AIRCRAFT CORPORATION: Amendment 39-3485. Applies to the following Piper models of aircraft certificated in all categories: PA-28-161, S/N 28-7816340 through 28-7916410; PA-28-181, S/N 28-7890276 through 28-7990429; PA-28-236, S/N 28-7911001 through 28-7911167; PA-28-201T, S/N 28-7921001 through 28-7921028; PA-28R-201, S/N 28R-7837150 through 28R-7837317; PA-28R-201T, S/N 28R-7803185 through 28R-7803373; PA-28RT-201, S/N 28R-7918001 through 28R-7918128; PA-28RT-201T, S/N 28R-7931001 through 28R-7931187. \n\n\tCompliance is required as indicated, unless already accomplished. \n\n\tTo prevent a potential fire hazard, accomplish the following: \n\n\t(a)\tPrior to the next flight after the effective date of this AD and prior to each flight thereafter until compliance with the requirements of paragraph (b)(1) through (b)(7) have been accomplished, check for evidence of fuel leaks, wetting, fuel stains, and/or fumes at inboard area of both wings, and in the cabin area. Makeappropriate maintenance record entry. \n\n\t(b)\tIf, as a result of checks required by paragraph (a), leakage, wetting, fuel stains or fumes are evident, accomplish the following prior to further flight: \n\n\t\t(1)\tGain access to all Parker-Hannifin unions (identified D1 or D1PH6) located at inboard areas of both wings, under the left cabin side panel and in the spar box area. For 201T models only, include vent line fitting at lower aft corner of the door. \n\n\t\t(2)\tTorque each fitting to the requirements of Table I. \n\n\t\t(3)\tMeasure the distance between the face of union and face of tubing fitting. Refer to Figure I. \n\n\t\t(4)\tIf torque and/or dimensions are not in accordance with the requirements of Table I and Figure I, comply with paragraph (c). \n\n\t\t(5)\tFill the airplane tanks full of fuel and run engine for three (3) to five (5) minutes on each tank. \n\n\t\t(6)\tInspect fittings for leakage and if no leaks are found, no further action is necessary except for the appropriate maintenance record entry. \n\n\t\t(7)\tIf leakage is still evident, comply with the requirements of paragraph (c). \n\n\t(c)\tIf as a result of checks or inspections required by this Airworthiness Directive, the fittings or unions are found damaged, they continue to leak, or they do not comply with the requirements of Table I and Figure I, correct in accordance with (1), (2), or (3) below and accomplish paragraphs (b)(4), (b)(5), and (b)(6). \n\n\t\t(1)\tRemove the leaking union and replace it using a standard "AN" fitting as outlined in AC 43.13-1A, paragraphs 393 and 709, or \n\n\t\t(2)\tReplace with Piper preswaged and preseated tube and union and apply thread lube as outlined in Table II. Carefully align the tube, snug up the nut finger tight, and tighten the nut one (1) to two (2) flats (1/6 to 1/3 of a turn). Maintain dimensional tolerance of Figure I, or \n\n\t\t(3)\tRepair by using the same size Parker-Hannifin unions and fittings which have not been preswaged or preseated. Apply thread lube asoutlined in Table II, snug up the nut finger tight, and using a tube wrench tighten the nut one and one-quarter (1-1/4) turns. \n\n\t(d)\tWithin the next 100 hours time in service after the effective date of this Airworthiness Directive, comply with the requirements of paragraphs (b)(1) through (b)(7), unless already accomplished. \n\n\t(e)\tChecks specified in paragraph (a) may be accomplished by the pilot. \n\n\t(f)\tCompliance with the provisions of this Airworthiness Directive may be accomplished in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, Southern Region. \n\n\n\n\nTABLE I \nTUBE SIZE\nAPPLIED TORQUE\nEQUIPMENT \n1/4 OD\n75-95 inch pounds\nUse a tubing crows foot\n3/8 OD\n175-195 inch pounds\n\n\n\nTABLE II\nSlip spray lubricant (Dupont), or equivalent.\nFerulube (Parker-Hannifin), or equivalent. \nApply the lubricant to the male connector thread. \nDo not allow lubricant to enter the throat of the connector seat or contact the ferrule seat face.\n\t\n\n\t\n\n\n\tPiper Service Bulletin No. 638 pertains to this subject. \n\n\tThis amendment becomes effective June 8, 1979, except those for whom it became effective May 2, 1979 by airmail letter.
2023-09-02: The FAA is adopting a new airworthiness directive (AD) for all MHI RJ Aviation ULC Model CL-600-2B19 (Regional Jet Series 100 & 440); CL-600-2C10 (Regional Jet Series 700, 701, & 702); CL-600-2C11 (Regional Jet Series 550); CL-600-2D15 (Regional Jet Series 705); CL-600-2D24 (Regional Jet Series 900); and CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by a determination that aircraft maintenance manual (AMM) tasks and certification maintenance requirement (CMR) tasks are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive AMM and CMR tasks. The FAA is issuing this AD to address the unsafe condition on these products.
2001-25-52: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2001-25-52, which was sent previously to all known U.S. owners and operators of Schweizer Aircraft Corporation (Schweizer) Model 269A, 269A-1, 269B, 269C, and TH-55A helicopters by individual letters. This AD supersedes an existing AD that requires inspecting and modifying or replacing, if necessary, the aluminum end fittings of each tailboom support strut (strut). That AD also requires inspecting the tailboom center attach fittings and center frame aft cluster fittings for damage, and if damaged parts are found, replacing the damaged parts. This AD requires inspecting and replacing, if necessary, each strut clevis lug (lug) on each tailboom center frame aft cluster fitting (cluster fitting), certain strut assemblies, certain tailboom attachments, and certain frame aft cluster fittings. Modifying or replacing each strut assembly within a certain time period and serializing certain strut assemblies are also required. This AD is prompted by an accident in the United Kingdom involving the in-flight structural failure of a Schweizer Model 269C helicopter. The actions specified by this AD are intended to prevent failure of a lug on a cluster fitting, rotation of a tailboom into the main rotor blades, and subsequent loss of control of the helicopter.
2023-09-06: The FAA is adopting a new airworthiness directive (AD) for all CFM International, S.A. (CFM) LEAP-1A23, LEAP-1A24, LEAP-1A24E1, LEAP- 1A26, LEAP-1A26CJ, LEAP-1A26E1, LEAP-1A29, LEAP-1A29CJ, LEAP-1A30, LEAP-1A32, LEAP-1A33, LEAP-1A33B2, and LEAP-1A35A (LEAP-1A) model turbofan engines. This AD was prompted by a manufacturer investigation that revealed that certain high-pressure turbine (HPT) rotor stage 1 disks (HPT stage 1 disks), forward outer seals, and compressor rotor stages 6-10 spools were manufactured from material suspected to have reduced material properties due to iron inclusion. This AD requires replacement of certain HPT stage 1 disks, forward outer seals, and compressor rotor stages 6-10 spools. The FAA is issuing this AD to address the unsafe condition on these products.
2023-08-07: The FAA is adopting a new airworthiness directive (AD) for Allied Ag Cat Productions, Inc. (Allied Ag Cat) Model G-164A and G-164B airplanes with certain supplemental type certificates (STCs) installed. This AD was prompted by an accident involving an Allied Ag Cat Model G- 164B airplane where the airplane's propeller pitch control (PPC) linkage detached from the PPC of the engine and resulted in an accident that significantly damaged the airplane and injured the pilot. This AD requires installing a secondary retention feature (bolt, washer, and safety wire) on the PPC lever and the PPC assembly. The FAA is issuing this AD to address the unsafe condition on these products.
2002-08-09: This amendment adopts a new airworthiness directive (AD) that is applicable to one McDonnell Douglas Model DC-9-31 airplane. This action requires an inspection to determine if a certain alternating current (AC) cross-tie relay is installed; replacement of a certain AC cross-tie relay with a new AC cross-tie relay; and repetitive cleaning, inspection, repair, and testing of a certain AC cross-tie relay. This action is necessary to prevent AC cross-tie relay failures, which could result in internal arcing of the relay and smoke and/or fire in the cockpit and cabin. This action is intended to address the identified unsafe condition.
2002-08-08: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model CL-600-2B16 (CL-601-3R and CL-604) series airplanes. This action requires a one-time inspection to detect chafing and other damage of the integrated drive generator (IDG) cables on both left and right engines between the service pylon connections to the IDG, corrective action if necessary, and installation of protective Teflon tubing and additional clamps on the IDG cable harnesses. This action is necessary to prevent electrical arcing between the IDG cable and the engine cowling, which could result in in-flight fire and/or loss of electrical power. This action is intended to address the identified unsafe condition.
2023-07-06: The FAA is adopting a new airworthiness directive (AD) for certain De Havilland Aircraft of Canada Limited Model DHC-8-401 and - 402 airplanes. This AD was prompted by reports of corrosion on the horizontal stabilizer lower center skin panel, including a finding of corrosion where the skin thickness had been substantially reduced, which affected design margins. This AD requires inspecting the horizontal stabilizer lower center skin panel for corrosion, and reworking, repairing, or replacing the lower center skin panel if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2002-06-01: This amendment supersedes two existing airworthiness directives (ADs), applicable to certain Airbus Model A319, A320, and A321 series airplanes. The first AD currently requires removing the existing forward pintle nut and cross bolt on the main landing gear (MLG), and installing a new nylon spacer and cross bolt and nut. The second AD currently requires repetitive inspections for discrepancies of the lock bolt for the pintle pin on the MLG, follow-on corrective actions if necessary, and retorquing of the forward pintle pin lock bolt for certain airplanes. That AD also provides an optional terminating action. This amendment cancels the requirements of the first AD, continues the requirements of the second AD, and requires the previously optional terminating action that the second AD provides. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent a rotated, damaged, or missing lock bolt, which could result in disengagement of the pintle pin from the pintle fitting bearing, and consequent collapse of the MLG during landing.
2025-11-02: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A319-151N, -153N, -171N, and -173N airplanes; A320-251N, -252N, -253N, -271N, -272N, and -273N airplanes; A321-251N, -251NX, -252N, -252NX, -253N, -253NX, -253NY, -271N, -271NX, -272N, and -272NX airplanes. This AD was prompted by reports of lost synchronization between radio management panels (RMPs). This AD requires revising the existing airplane flight manual (AFM) by providing instructions to address dual loss of RMP data synchronization. The FAA is issuing this AD to address the unsafe condition on these products.
2002-08-04: This amendment adopts a new airworthiness directive (AD) that applies to certain PIAGGIO AERO INDUSTRIES S.p.A. (PIAGGIO) Model P-180 airplanes. This AD requires you to replace the four defective horizontal stabilizer hinge bushings with replacement bushings. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Italy. The actions specified by this AD are intended to replace defective bushings before they cause failure of the horizontal stabilizer. Such failure could lead to reduced or loss of control of the aircraft.
2025-10-05: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A321-111, -112, -131, -211, -212, -213, -231, -232, -251N, -252N, -253N, -271N, -272N, -251NX, -252NX, -253NX, -271NX, and -272NX airplanes. This AD was prompted by the identification of an erroneous value of the main landing gear (MLG) tire width in the aircraft data files used for aircraft performance computation. This AD requires revising the existing airplane flight manual (AFM) to incorporate a complementary performance data file (CPDF) update as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2023-07-07: The FAA is adopting a new airworthiness directive (AD) for certain MHI RJ Aviation ULC Model CL-600-2B19 (Regional Jet Series 100 & 440), CL-600-2C10 (Regional Jet Series 700, 701 & 702), CL-600-2C11 (Regional Jet Series 550), CL-600-2D15 (Regional Jet Series 705), CL- 600-2D24 (Regional Jet Series 900), and CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by reports from the supplier that sensing elements of the bleed air leak detection system were manufactured with insufficient salt fill, which can result in an inability to detect hot bleed air leaks. This AD requires testing of all affected overheat detection sensing elements of the bleed air leak detection system, and replacement if necessary. This AD also prohibits the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
78-23-01: 78-23-01 PIPER AIRCRAFT CORPORATION: Amendment 39-3330. Applies to Models PA-28-235, PA-32-260, PA-32-300, PA-32S-300, PA-32R-300, PA-32RT-300 and PA- 32RT-300T airplanes, certificated in all categories. Compliance is required as indicated. To prevent inadvertent fuel drain lever actuation, accomplish the following: (a) On Model PA-28-235 serial numbers 28-10003 through 28-10660, accomplish the following: (1) Within the next 50 hours time in service after the effective date of this AD, unless already accomplished, remove the fuel drain lever cover assembly Piper Part Number 65196-05, -06, or -07. (2) Remove snap studs from spar box if installed. (3) Using existing stud holes in spar box, install new drain cover assembly, Piper Kit 763 883V. (4) Actuate fuel drain valve handle and insure adequate clearance between the handle and cover assembly. (5) Make appropriate maintenance record entry. (b) On Models PA-28-235, PA-32-260, PA-32-300, PA-32S-300, PA-32R-300, PA-32RT-300, and PA-32RT-300T, all serial numbers, accomplish the following: (1) For airplanes with 300 hours or more time in service, within the next 50 hours time in service from the effective date of this AD, and at intervals not to exceed 100 hours time in service from the last check, check the fuel drain lever cover assembly door to determine whether the door freely opens and closes freely without manual assistance and prevents actuation of the lever when the door is in the closed position. (2) If the door does not open and close freely or if the door does not prevent access to the lever when it is in the closed position, replace the fuel drain lever cover assembly with a serviceable assembly, and make the appropriate maintenance record entry. (3) If the door opens and closes freely and prevents access to the lever when it is in the closed position, make the appropriate maintenance record entry. (c) An alternate method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. The checks in this AD may be accomplished by the pilot and appropriate maintenance record entries made in accordance with FAR 91.173. Replacement must be accomplished by a person authorized by FAR 43.3. (Piper Service Letter 856 dated September 15, 1978, pertains to paragraph (a).) This amendment becomes effective November 3, 1978.
2023-07-13: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by reports of broken lower attachment studs on the AFT galley complex. This AD requires repetitive detailed inspections of the lower attachment studs and, depending on findings, replacement of the lower attachment studs, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2002-08-07: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 767-200, -300, and -300F series airplanes. This AD requires examination of maintenance records to determine if Titanine JC5A (also known as Desoto 823E508) corrosion inhibiting compound ("C.I.C.") was ever used; inspection for cracks or corrosion and corrective action, if applicable; repetitive inspections and C.I.C. applications; and modification of the aft trunnion area of the outer cylinder, which terminates the need for the repetitive inspections and C.I.C. applications. This action is necessary to prevent severe corrosion in the main landing gear (MLG) outer cylinder at the aft trunnion, which could develop into stress corrosion cracking and consequent collapse of the MLG. This action is intended to address the identified unsafe condition. The FAA is also planning to issue additional rulemaking to exclude the use of Titanine JC5A for compliance with previously issued ADs.
2020-22-02: The FAA is adopting a new airworthiness directive (AD) for all General Electric Company (GE) CF6-80C2A5F, -80C2B1F, -80C2B2F, - 80C2B4F, -80C2B5F, -80C2B6F, -80C2B6FA, -80C2B7F, -80C2B8F, -80C2D1F, - 80C2K1F, -80C2L1F, -80E1A2, -80E1A3, -80E1A4, and -80E1A4/B model turbofan engines with a certain hydromechanical unit (HMU) installed. This AD was prompted by a report of fuel coking of the HMU fuel metering valve (FMV) electro-hydraulic servo valves (EHSV) resulting in tailpipe fire. This AD requires removal of the HMU and its replacement with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
78-12-07: 78-12-07 PIPER: Amendment 39-3235. Applies to Piper Aircraft PA-30 and PA-39 with Serial Numbers 30-1 through 30-2000 and 39-1 through 39-155 which have had a right fuel selector valve P/N 492137 (Airborne P/N 1H7-8) changed since April, 1977, with a valve containing the designation "4C" in the valve serial number. Compliance required before further flight unless already accomplished. 1. Replace any right fuel selector valve, Piper P/N 492137 (Airborne P/N 1H7-8) containing the designation "4C" in the valve serial number with a serviceable valve without the "4C" designation. 2. The replacement fuel selector valve shall be installed and adjusted in accordance with PA-30/39 Service Manual. (Piper Service Bulletin No. 597 dated April 19, 1978, pertains to this subject.) This amendment is effective June 19, 1978.
77-24-01: 77-24-01 PIPER: Amendment 39-3083 as amended by Amendment 39-3182. Applies to the following models: PA-31 and PA-31-325, Serial Nos. 31-465, 31-7712057 thru 31-7712078, 31-7712081 and 31-7712083; PA-31-350 Serial Nos. 31-7752099, 31-7752101, 31-7752103, 31- 7752105 thru 31-7752114, 31-7752117 thru 31-7752131 and 31-7752134 thru 31-7752138, certificated in all categories. To prevent possible hazards in flight associated with missing horizontal stabilizer and fin skin to stiffener rivet attachments, accomplish the following within the next fifty hours in service from the effective date of this AD unless previously accomplished: (a) Inspect and, if required, repair the horizontal stabilizer and fin skin to stiffener rivet attachments in accordance with the "Instructions" section of Piper Service Bulletin No. 575 or equivalent procedures which must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (b) Upon submission of substantiatingdata through an FAA Maintenance Inspector, the compliance time specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. The affected airplanes may be flown in accordance with FAR 21.197 to a location where the AD compliance procedures can be accomplished. Amendment 39-3083 was effective November 24, 1977. This amendment 39-3182 is effective April 17, 1978.
2002-08-02: This amendment supersedes Airworthiness Directive (AD) 2001-20-14, which currently requires you to replace the brake shuttle valves with parts of improved design and install a shield over the hydraulic lines on certain Fairchild Aircraft SA226 and SA227 series airplanes. AD 2001-20-14 also requires you to replace the rubber fuel hose with a metal device for certain SA226 series airplanes. This AD is the result of FAA incorrectly referencing Model SA226-T(A) airplanes and inadvertently omitting certain serial numbers of Model SA227-AC airplanes from the applicability of AD 2001-20-14. This AD retains the actions of AD 2001-20-14, corrects the reference of Model SA226-T(A) airplanes and adds additional Model SA227-AC airplanes to the applicability section of the AD. The actions specified by this AD are intended to correct potential brake shuttle valve problems, which could cause the brake assembly to drag and overheat. Hydraulic or fuel line damage could then occur if the overheated brake assembly is retracted into the main wheel well with a consequent fire if the hydraulic or fuel lines ruptured.
2023-06-14: The FAA is adopting a new airworthiness directive (AD) for certain Pratt & Whitney Canada Corporation (P&WC) PW308A and PW308C model turbofan engines. This AD is prompted by a manufacturer's design review, which identified that the combustion chamber outer case (CCOC) to rear compressor case (RCC) flange bolt low cycle fatigue life was inadequate and that those flange bolts may develop cracks resulting in flange bolt fracture. This AD requires replacing all CCOC flange bolts and modifying the CCOC and inner bypass ducts. This AD also prohibits installation of certain flange bolts on any affected engine, as specified in a Transport Canada AD, which is proposed for incorporation by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
2009-18-03 R1: We are revising an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Findings of corrosion, wear and cracks in the upper wing strut fittings on some PC-6 aircraft have been reported in the past. It is possible that the spherical bearing of the wing strut fittings installed in the underwing can be loose in the fitting or cannot rotate because of corrosion. In this condition, the joint cannot function as designed and fatigue cracks may then develop. Undetected cracks, wear and/or corrosion in this area could cause failure of the upper attachment fitting, leading to failure of the wing structure and subsequent loss of control of the aircraft. To address this problem, FOCA published AD TM-L Nr. 80.627-6/ Index 72-2 andHB-2006-400 and EASA published AD 2007-0114 to require specific inspections and to obtain a fleet status. Since the issuance of AD 2007-0114, the reported data proved that it was necessary to establish and require repetitive inspections. EASA published Emergency AD 2007-0241-E to extend the applicability and to require repetitive eddy current and visual inspections of the upper wing strut fitting for evidence of cracks, wear and/or corrosion and examination of the spherical bearing and replacement of cracked fittings. Collected data received in response to Emergency AD 2007-0241-E resulted in the issuance of EASA AD 2007-0241R1 that permitted extending the intervals for the repetitive eddy current and visual inspections from 100 Flight Hours (FH) to 300 FH and from 150 Flight Cycles (FC) to 450 FC, respectively. In addition, oversize bolts were introduced by Pilatus PC-6 Service Bulletin (SB) 57-005 R1 and the fitting replacement procedure was adjusted accordingly. Based onfatigue test results, EASA AD 2007-0241R2 was issued to extend the repetitive inspection interval to 1100 FH or 12 calendar months, whichever occurs first, and to delete the related flight cycle intervals and the requirement for the "Mild Corrosion Severity Zone''. In addition, some editorial changes have been made for reasons of standardization and readability. Revision 3 of this AD referred to the latest revision of the PC- 6 Aircraft Maintenance Manual (AMM) Chapter 5 limitations which have included the same repetitive inspection intervals and procedures already mandated in the revision 2 of AD 2007-0241. Besides the inspections, in the latest revision of the PC-6 AMM, the replacement procedures for the fittings were included. Additionally, EASA AD 2007-0241R3 introduced the possibility to replace the wing strut fitting with a new designed wing strut fitting. With this optional part replacement, in the repetitive inspection procedure the 1100 FH interval is deleted so thatonly calendar defined intervals of inspections remained applicable. We are issuing this AD to require actions to correct the unsafe condition on these products.
77-23-03: 77-23-03 PIPER AIRCRAFT CORPORATION: Amendment 39-3071. Applies to Model PA-28-140 serial numbers 28-25001 through 28-7725172; Model PA-28-151 serial numbers 28-7415001 through 28-7615435; Model PA-28-161 serial numbers 28-7716001 through 28-7716071; Model PA-28-180 serial numbers 28-5153 through 28-7505260; Model PA-28-181 serial numbers 28-7690001 through 28-7790363; Model PA-28-235 serial numbers 28-7310001 through 28-7710016; Model PA-28R-180 serial numbers 28R-30737 through 28R-7130013; Model PA-28R-200 serial numbers 28R-35001 through 28R-7635512; Model PA-28R-201 serial numbers 28R-7737001 through 28R-7737023; Model PA-28R-201T serial numbers 28R-7703001 through 28R-7703043; Model PA-32-260 serial numbers 32-1111 through 32-7700013; Model PA-32-300 serial numbers 32-40566 through 32-7740040; Model PA-32R-300 serial numbers 32R-6780001 through 32R-7780215; Model PA-34-200 serial numbers 34-7250001 through 34-7450220; and Model PA-34-200T serial numbers 34-7570001 through 34-7770163, airplanes certificated in all categories. \n\n\tTo prevent a power loss due to thermal contraction binding a control rod end, accomplish the following: \n\n\t(a)\tWithin the next 25 hours time in service after the effective date of this A.D., unless already accomplished, perform the following check: \n\n\t\t(1)\tGain access to the engine by opening or removing the cowling as required to check the engine control rod end bearings in the engine compartment. \n\n\t\t(2)\tCheck the rod end bearings attached to the Mixture, Throttle, and Prop Governor (if applicable) Control Cables. (Refer to the picture below.) \n\n\t\t\t(i)\tIf a rod end bearing, as identified in the figure below as number two (2) (Brass Ball Retainer) or as number three (3) (Silver Ball Retainer) is installed, then no further action is required. Make appropriate log book entry. \n\n\t\t\t(ii)\tIf a rod end bearing, as identified in the figure below as number one (1) with a raised ball retainer is installed, have it removed andreplaced with an approved serviceable bearing which is identified in the figure below as number two (2) or number three (3). Refer to the appropriate Piper Service Manual for replacement and rigging instructions. \n\n\t(b)\tAn alternate method of compliance must be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. \n\n\tThe checks in this A.D. may be accomplished by the pilot and appropriate log book entries made in accordance with FAR 91.173. Replacement and rigging must be accomplished by a person authorized by FAR 43.3. \n\n\tThis amendment becomes effective November 14, 1977.