Results
2007-05-07: The FAA is adopting a new airworthiness directive (AD) for all Fokker Model F.28 Mark 0070 and 0100 airplanes. This AD requires inspecting the carbon-fiber reinforced plastic main landing gear (MLG) door to determine whether certain part numbers are installed. For airplanes having certain doors, this AD requires inspecting the MLG outboard door for cracks, play, and loose sealant/bolts/nuts, and related investigative and corrective actions if necessary. This AD also requires, for airplanes having certain doors, modifying the rod bracket attachment of the MLG outboard door. This AD results from a report of a rod bracket of the MLG door detaching during flight. We are issuing this AD to detect and correct cracks in the rod bracket attachment bolts, which could result in the rod brackets detaching from the MLG door and blocking the proper functioning of the MLG.
2000-20-15: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 and A300-600 series airplanes, that requires a high frequency eddy current (HFEC) inspection to detect cracking of the rear fittings of fuselage frame FR40 at stringer 27, and repetitive inspections or repair, as applicable. In lieu of accomplishing the repetitive inspections, this amendment requires a modification that would allow the inspection to be deferred for a certain period of time. 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 detect and correct fatigue cracking of the rear fittings of fuselage frame FR40 at stringer 27, which could result in reduced structural integrity of the airplane.
2019-03-13: We are adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace LP Model Gulfstream G150 airplanes. This AD was prompted by reports of corrosion in the solder joints of the upper and lower front relay box connectors to the printed circuit board. This AD requires replacement of the existing relay boxes with modified boxes. We are issuing this AD to address the unsafe condition on these products.
77-13-08: 77-13-08 BEECH: Amendment 39-2933. Applies to Models 58P and 58PA (Serial Numbers TJ-2 thru TJ-117), 58TC and 58TCA (Serial Numbers TK-1 thru TK-63) airplanes certificated in all categories. \n\n\tCompliance: Required as indicated, unless already accomplished. \n\n\tTo assure structural integrity of the right and left truss tube assemblies in both the right and left engine nacelles, accomplish the following: \n\n\tA)\tOn Models 58P and 58PA (S/Ns TJ-2 thru TJ-99), 58TC and 58TCA (S/Ns TK-1 thru TK-54) airplanes that do not have Beech Kit No. 102-9001-1S installed, prior to the next flight (unless previously accomplished in accordance with Beechcraft mailgram dated February 17, 1977) and at each 50 hours' time in service interval thereafter, until Beech Kit No. 102-9001- 1S is installed: \n\n\t\t1.\tPursuant to Beechcraft Service Instructions No. 0903 or later approved revisions accomplish the following: \n\n\t\t\ta.\tReferring to Figure 1 of this AD dye penetrant inspect the right truss tubeassembly in both right and left engine nacelles for cracks which initiate from the two rivet holes attaching the turbocharger air intercooler mounting brackets; and \n\n\t\t\tb.\tReplace any cracked right truss tube assembly prior to the next flight. \n\n\t\t2.\tPursuant to Beechcraft Service Instructions No. 0903 or later approved revisions accomplish the following: \n\n\t\t\ta.\tReferring to Figure 1 of this AD visually inspect the left truss tube assembly in both right and left engine nacelles for chafing: \n\n\t\t\tb.\tDye penetrant said part for cracks; and \n\n\t\t\tc.\tReplace any cracked left truss tube assembly and repair or replace any chafed left truss tube assembly prior to the next flight. \n\n\tB)\tOn Models and serial numbers listed in Paragraph A of this AD that have Beech Kit No. 102-9001-1S installed and on Models 58P and 58PA (S/Ns TJ-100 thru TJ-117), 58TC and 58TCA (S/Ns TK-55 thru TK-63) airplanes, within the next 100 hours' time in service after the effective date of this AD, or within 100 hours' time in service after the last similar inspection accomplished in accordance with Beechcraft Service Instructions No. 0903, whichever occurs first, and at each 100 hours' time in service interval thereafter: \n\n\t\t1.\tPursuant to Beechcraft Service Instructions No. 0903 or later approved revisions: \n\n\t\t\ta.\tRemove cowlings from right and left engines; \n\n\t\t\tb.\tReferring to Figure 1 of this AD visually inspect the right and left truss tube assemblies in both right and left nacelles for cracks, chafing or other signs of structural weakening. Dye penetrant inspect right and left truss tube assemblies for cracks if chafing or other signs of structural weakening are detected by the visual inspection. \n\n\t\t\tc.\tReplace any cracked truss tube assembly prior to the next flight. \n\n\tC)\tWhen Beech P/Ns 102-910026-113 and -115 truss tube assemblies which have .072 inch thick walls are installed in the right and left engine nacelles the requirements of this AD no longer apply. Truss tube assemblies used prior to these improved assemblies had .035 inch thick walls. \n\n\tNOTE: The manufacturer has advised that the P/N 102-910026-113 and -115 truss tube assemblies will not be available until approximately September 1, 1977. \n\n\tD)\tThe intervals for repetitive inspections set forth in this AD may be adjusted up as much as 10% where required to fit user's maintenance cycles. No adjustment is allowed for the initial "prior to the next flight" inspection. \n\n\tE)\tAircraft may be flown in accordance with FAR 21.197 to a base where this AD can be accomplished, after coordination with the Chief, Engineering and Manufacturing Branch, FAA, Central Region. \n\n\tF)\tAny equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. \n\n\tThis amendment becomes effective July 1, 1977, to all persons except those to whom it has already been made effective by air mail letter from the FAA dated June 7, 1977.
95-24-13: This action makes a correction to Airworthiness Directive (AD) 95-24-13 concerning Jetstream Aircraft Limited (JAL) HP137 Mk1, Jetstream Series 200, and Jetstream Models 3101 and 3201 airplanes, which published in the Federal Register on December 22, 1995 (60 FR 246). That publication incorrectly references the number of aileron mounting spigot nut assemblies to be replaced on the wings of the airplanes. The AD currently requires "replacing the securing nut assemblies and split pins with new special nut assemblies (Part No. SL5022 (Qty. 2))". The intent of the AD is to require replacement of 2 special aileron mounting spigot nut assemblies on each wing, for a total of 4 nut assemblies. The Final Rule AD did not specify "each wing", and mentioned that only 2 nut assemblies are required, instead of 4 nut assemblies. This action corrects the AD to reflect this change.
2007-05-14: The FAA is adopting a new airworthiness directive (AD) for GE CF6-80C2 series turbofan engines. This AD requires replacing certain installed part number (P/N) and serial number (SN) cast titanium weld- repaired forward engine mount platforms and cast titanium forward mount yokes, with a forged titanium or a non-welded cast titanium part. This AD results from the discovery of cracks, in a weld-repaired area on a forward engine mount platform and a forward engine mount yoke, found during a fluorescent penetrant inspection (FPI). These parts were weld- repaired during manufacture. We are issuing this AD to prevent cracks in the forward engine mount platform and forward engine mount yoke that could result in possible separation of the engine from the airplane.
2007-05-04: The FAA adopts a new airworthiness directive (AD) for certain Mooney Airplane Company, Inc., Models M20M and M20R airplanes. This AD requires you to remove the upper left and upper right engine mount attaching hardware, cut out and remove the upholstery and insulation between the fuselage tubular frame and the firewall, and replace the upper left and upper right engine mount attaching hardware with the new parts kit. This AD results from failure of the engine mount attaching hardware to maintain torque as a result of firewall insulation and upholstery being compressed between the fuselage tubular frame and the firewall at the upper left and upper right engine mount attach points. We are issuing this AD to prevent the upper right and upper left engine mounting hardware from losing torque, which could result in a reduction in engine mount load carrying capability and could lead to engine mount failure.
2019-03-17: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A318 series airplanes; Model A319 series airplanes; Model A320 series airplanes; and Model A321 series airplanes. This AD was prompted by a revision of an airworthiness limitation item (ALI) document, which requires more restrictive maintenance requirements and airworthiness limitations. This AD requires revising the operator's maintenance or inspection program, as applicable, to incorporate new maintenance requirements and airworthiness limitations. We are issuing this AD to address the unsafe condition on these products.
2007-05-11: The FAA is superseding two existing airworthiness directives (ADs), that apply to certain Bombardier Model CL-600-2B16 (CL-604) airplanes and Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. These models may be referred to by their marketing designations as RJ100, RJ200, RJ440, CRJ100, CRJ200, CRJ440, and CL-65. One existing AD requires replacing the horizontal stabilizer trim control unit (HSTCU) with a new HSTCU. The other existing AD requires revising the airplane flight manual (AFM) to advise the flightcrew of procedures to follow in the event of stabilizer trim runaway, and in the event of MACH TRIM, STAB TRIM, and horizontal stabilizer trim malfunctions; and revising the AFM to require a review of the location of certain circuit breakers. That AD also requires doing a functional check of the stabilizer trim system and installing circuit breaker identification collars, and provides an optional terminating action. This new AD requires the previously optional terminating action and requires further revisions to the AFM. This AD also requires the removal of certain AFM revisions. This AD results from reports of trim problems including uncommanded trim, trim in the opposite direction to that selected, loss of trim position indication and, in one case, potential loss of trim disconnect capability. We are issuing this AD to prevent these events, which could result in conditions that vary from reduced controllability of the airplane to loss of control of the airplane.
2007-05-01: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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 follows: On 23 November 2006, Emergency Airworthiness Directive 2006- 0351-E was published requiring an inspection to be performed on C- 212 aeroplanes having been used for Maritime Patrol or other similar low altitude operations, due to the fact that, after initial examination of the evidences of a recent C-212 Maritime Patrol aircraft accident, cracks had been found in the centre wing lower skin at STA Y=1030. At the time of the accident, the aircraft had accumulated 17,000 flight hours and 7,300 flight cycles. The cracks were suspected to be caused by fatigue. After a more detailed examination in the laboratory, it has been determined that the initiation of the cracks was produced by fretting. * * * * * The above mentioned cracks, if not timely detected, could lead to reduced structural integrity of the aircraft. * * * * * This AD requires actions that are intended to address the unsafe condition.