Results
2002-08-10: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747 series airplanes. This action requires a one-time inspection to identify all alloy steel bolts on the body station 1480 bulkhead splice, and corrective action if necessary. This action provides for optional terminating action for certain requirements of this AD. This action is necessary to detect and correct cracked or broken bolts, which could result in structural damage and rapid depressurization of the airplane. This action is intended to address the identified unsafe condition.
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.