Results
2019-07-04: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 757 airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the inner skin of the lap splices, at the lower fastener row, is subject to scratch cracks that may interact with widespread fatigue damage (WFD). This AD requires a general visual inspection (GVI) of certain lap splice inspection areas for any repair common to the fuselage skin lap splice dual frequency eddy current (DFEC) inspection areas, repetitive DFEC inspections of certain lap splice inner skins for any crack, and applicable on-condition actions. We are issuing this AD to address the unsafe condition on these products.
59-06-04: 59-06-04 NAVION: Tusco Corporation (Navion) Applies to All Models. Several failures of hydraulic actuating cylinders have occurred causing the loss of the use of the flaps and the landing gear to collapse. To prevent further difficulties of this nature, the following items must be accomplished by May 1, 1959, and at each periodic inspection thereafter. (1) Inspect the flap and landing gear actuating cylinders for cracks. If any cracks appear, the cylinder must be replaced. (2) Determine, by means of a hydraulic gage, that the hydraulic system pressure relief valve is adjusted to 1125+25, -0 p.s.i. Excessive pressures could cause damage to the components of the system. (3) Hydraulic fluid restrictors are required in the nose gear lines, Serial Numbers 1271 and subsequent, main gear lines, Serial Numbers 1790 and subsequent, and flap lines, all serial numbers. (4) Inspect the linkage adjustments of the landing gear bungee springs and the flap stops anddetermine that they have been properly adjusted in accordance with appropriate service manuals. (Tusco Corporation Service Letter No. 79 dated December 23, 1958, covers this same subject.)
2019-06-09: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 airplanes. This AD was prompted by reports that baby bassinet inserts installed on airplane stowages and partitions were found loose because a self-securing fixation device (Loctite) had not been applied. This AD requires repetitive tightness checks of the baby bassinet inserts installed on stowages and partitions and, depending on findings, accomplishment of applicable corrective actions, as specified in an European Aviation Safety Agency (EASA) AD, which is incorporated by reference. We are issuing this AD to address the unsafe condition on these products.
2005-25-20: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A330-300, A340-200, and 340-300 series airplanes. The existing AD requires repetitive inspections to detect cracking of the fuselage skin in the area of the VHF2 antenna, and repair if necessary. The existing AD also provides for optional terminating action for the repetitive inspections. This new AD requires accomplishment of the previously optional terminating action, and revises the applicability by removing certain airplanes. This AD is prompted by the need to change the applicability of the existing AD and to mandate the formerly optional terminating action. We are issuing this AD to prevent cracking of the fuselage skin in the area of the VHF2 antenna, which could result in depressurization of the airplane. DATES: Effective December 29, 2005. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of December 29, 2005. The incorporation by reference of certain other publications, as listed in the regulations, was approved previously by the Director of the Federal Register as of April 12, 2000 (65 FR 12075, March 8, 2000). We must receive comments on this AD by February 13, 2006.
2005-25-15: The FAA is adopting a new airworthiness directive (AD) for certain Dassault Model Falcon 2000 airplanes equipped with CFE Company CFE738- 1-1B turbofan engines. This AD requires determining the serial number of the engines installed on the airplane, inspecting any affected engine to verify that a spherical bearing is installed on the attachment fitting of the engine mount, and corrective action if necessary. This AD results from a report of a missing spherical bearing on the attachment fitting of the front engine mount on an in-service airplane, and subsequent damage and abnormal fatigue of the attachment fitting. We are issuing this AD to prevent reduced structural integrity of the engine mount, which could result in possible separation of an engine from the airplane.
2011-17-10: 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: * * * [T]he Federal Aviation Administration (FAA) have published Special Federal Aviation Regulation (SFAR) 88, and the Joint Aviation Authorities (JAA) have published Interim Policy INT/POL/25/ 12. The review conducted by Fokker Services on the Fokker F28 type design in response to these regulations revealed that, on certain aeroplanes, an interrupted shield contact may exist or develop between the housing of an in-tank Fuel Quantity Indication (FQI) cable plug and the cable shield of the shielded FQI system cables in the main and collector fuel tanks which can, under certain conditions, form a spark gap. This condition, if not detected and corrected, may create an ignition source in the tank vapour space, possibly resulting in a wing fuel tank explosion and consequent loss of the aeroplane. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
57-23-01: 57-23-01 LOCKHEED: Applies to All Model 18 Aircraft Equipped With Vacuum Systems. Compliance required at next engine overhaul but not later than July 15, 1958. To guard against the possibility of excessive air temperature and associated fire hazards in the vacuum system discharge line, one of the following modifications must be accomplished: 1. Install a fusible plug in the side of the vacuum pump discharge port at right angles to the axis of the discharge port boss. Some pumps incorporate a plugged hole in the discharge port which may be enlarged to a 3/8-inch pipe tapped hole to accommodate the fusible plug. This plug should employ an AN 840-8D fitting with a binary eutectic mixture of 67.8 percent tin and 32.2 percent cadmium, which has a melting point of 351 degrees F. A drawing describing the design of such a plug is shown in Douglas Figure 2. The 3/8-inch plug fitting is intended for pumps such as the Model 3P-211 and 3P-485. For smaller pumps such as the 3P-207, and AN 840-6D fitting, incorporating the same modification as shown below, should be used. Brass fittings of the same design as the above dural fittings are acceptable. Incorporation of an overboard drain line clamped to the fusible plug is recommended but is not mandatory. On installations which do not use an overboard discharge line the possibility exists that the plug may damage other nacelle components if it can hit them upon being blown out of the adapter at high velocity. Therefore, if no overboard discharge line is provided, the installation must be made in such a manner that the plug will not be directed toward any vulnerable components when it issues from the adapter, or 2. Employ an oil separator equivalent in principle to the Genisco No. 40081 incorporating a pressure relief valve which can be disassembled for cleaning.
2019-06-08: We are adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-223, A330-223F, A330-321, A330-322, and A330-323 airplanes. This AD was prompted by a report of fatigue cracking in the latch beam gussets on a certain thrust reverser (T/R). This AD requires a one-time special detailed inspection of certain latch beam gussets of certain T/Rs for cracks, and modifying the latch beam gussets of the T/Rs, if necessary, as specified in an European Aviation Safety Agency (EASA) AD, which is incorporated by reference. We are issuing this AD to address the unsafe condition on these products.
2005-25-13: The FAA is adopting a new airworthiness directive (AD) for Turbomeca Arriel 2B and 2B1 turboshaft engines without modification TU22 incorporated. This AD requires initial and repetitive visual checks of the free turbine shield for cracks. This AD results from reports of several free turbine shields found with large circumferential cracks. We are issuing this AD to prevent failure of the free turbine shield, leading to engine misalignment, in-flight engine shutdown, emergency autorotation landing, or accident.
56-06-02: 56-06-02 PRATT & WHITNEY: Applies to All Models Engines. Compliance required as indicated. As a result of engine fire reported due to cylinder failure as a result of stud failures, the following must be accomplished to reduce cylinder and stud failures: A. If a cylinder flange attaching stud fails during engine operation, the adjacent studs may be subjected to severe overstress. The same is true if an attaching nut becomes loosened to the extent that there is clearance between the nut and the cylinder flange. If more than two adjacent studs have broken, or the nuts have become loose, there is a probability that the cylinder flange has been overstressed. B. If, during line inspection or at engine teardown prior to overhaul, a nut is found to be loose or there has been failure of a stud, replace that stud and the two adjacent studs. C. If more than two adjacent studs have failed or if more than two adjacent nuts are known to have been loose during engine operation, the cylinder should be scraped or rebarreled and all the studs on the cylinder mounting pad replaced. D. If only two adjacent studs have failed or two adjacent nuts have been found loose, the cylinder should be replaced, but it need not be scrapped provided that the nuts adjacent to the failed studs or loose nuts are found to be at least to minimum torque and that the cylinder flange has not become distorted more than 0.003 inch; also, that the flange and area above the flange are magnafluxed and show no crack indicators. If the bottom of the cylinder flange is not perfectly flat, but is not distorted more than 0.003 inch, it should be lapped flat before reinstallation. Before a replacement cylinder is installed, the crankcase studs immediately adjacent to the two broken or loose ones should be replaced. E. During cylinder installation, securely tighten the cylinder flange attaching nuts. (P&W Service Bulletin No. 1000 describes approved methods and torques.)(This subject is also covered in P&W Alert Bulletin No. 42 entitled "Cylinder Attachment Inspection and Maintenance".)
2019-06-11: We are adopting a new airworthiness directive (AD) for Pacific Aerospace Limited Model 750XL airplanes. 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 non-compliant insulation lagging on the refrigerant hoses of the air-conditioning system. We are issuing this AD to require actions to address the unsafe condition on these products.
2007-12-18: 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: It has been found that the fuel quantity probes harnesses installed in the left and right wing stub tanks on some Embraer ERJ- 170( ) aircraft models may not be protected in accordance with RBHA/ FAR (Regulamento Brasileiro de Homologacao Aeronautica/Federal Aviation Regulation) 25.981(a) and (b) requirements. The unsafe condition is potential ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
2019-06-02: We are adopting a new airworthiness directive (AD) for certain Pratt & Whitney Division (PW) PW4158 turbofan engines. This AD was prompted by several reports of high cycle fatigue (HCF) cracks found in the fuel nozzle supply manifold. This AD requires replacement of the affected fuel nozzles and fuel nozzle manifold supply assemblies with parts eligible for installation. This AD also requires installation of new brackets and clamps on the fuel nozzle supply manifold assemblies. We are issuing this AD to address the unsafe condition on these products.
2019-04-01: We are adopting a new airworthiness directive (AD) for HPH s. r.o. Models Glasf[uuml]gel 304C, Glasf[uuml]gel 304CZ, and Glasf[uuml]gel 304CZ-17 gliders. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as jamming between the double two-ring end of the towing cable and the deflector angles of the center of gravity (C.G.) release mechanism. We are issuing this AD to require actions to address the unsafe condition on these products.
54-24-04: 54-24-04 MARTIN: Applies to All Models 202 and 202A Aircraft. Compliance required as indicated. Several cases of cracks in the main landing gear trunnion fittings (P/N 2021A23307, 2021A23308, 2021A23309, 2021A23310) have been reported. These cracks have been in the area of the boss and the web. To preclude failure of these parts all aircraft must be inspected and reworked as follows: I. Compliance required as soon as practical but not later than December 10, 1954, unless already accomplished. Thoroughly clean fittings and inspect using a dye penetrant inspection method. If a crack is found, rework the part in accordance with item II. If no cracks exist the part must be reinspected using an 8- power magnifying glass, dye penetrant method or equivalent every 250 hours plus or minus 75 hours. II. Compliance required prior to return to service if a crack is found. The fitting may be repaired by grinding provided the crack does not exceed either 2 inches in length or exceed 0.060 inch in depth. Parts having cracks exceeding either of the above limitations must be replaced. Repaired parts must be etch inspected. Repaired parts must be reinspected using an 8-power magnifying glass, dye penetrant method or equivalent every 250 hours plus or minus 75 hours. III. New parts of the same design (P/N 2021A23307 through 23310) must be inspected at the first regular inspection period of approximately 1,000 hours after installation, and thereafter at every 250 hours plus or minus 75 hours using an 8-power magnifying glass, dye penetrant method or equivalent. IV. Replacement parts of the improved design (P/N 2021A23307-1 through 23310-1) must be inspected visually at the first regular inspection period of 1,000 hours after installation, and thereafter at intervals not exceeding 500 hours. At 7,500 hours after installation, and thereafter at every 250 hours plus or minus 75 hours, inspect the fitting using a dye penetrant method orequivalent. (NOTE: All specified inspection intervals are based on an average landing frequency of one per hour. Where average landing frequency exceeds this, there should be a corresponding decrease in the inspection intervals.) (Martin telegram of November 3, 1954, to all 202 and 202A operators covers this subject.)
2019-06-04: We are adopting a new airworthiness directive (AD) for Bell Helicopter Textron Canada Limited (BHTC) Model 429 helicopters. This AD requires inspecting each main rotor pitch link rod end bearing assembly (bearing) for wear and play. This AD was prompted by reports of worn bearings. The actions of this AD are intended to prevent an unsafe condition on these products.
2005-25-08: The FAA adopts a new airworthiness directive (AD) for certain Shadin ADC-2000 air data computers (ADC) installed on airplanes. This AD requires you to replace affected ADC-2000 units with a modified unit. This AD results from reports that certain ADC-2000 units display incorrect altitude information on the Electronic Flight Information System (EFIS) to the pilot. We are issuing this AD to prevent ADC-2000 units, part numbers (P/Ns) 962830A-1-S-8, 962830A-2-S-8, and 962830A-3- S-8, configurations B, C, and D, from displaying incorrect altitude information. This could cause the flight crew to react to this incorrect flight information and possibly result in an unsafe operating condition.
2005-25-09: The FAA is superseding an existing airworthiness directive (AD) for Pratt & Whitney (PW) PW4000 series turbofan engines. That AD currently requires revisions to the engine manufacturer's time limits section (TLS) to include enhanced inspection of selected critical life- limited parts at each piece-part opportunity. This AD modifies the airworthiness limitations section of the manufacturer's manuals and an air carrier's approved continuous airworthiness maintenance program by adding eddy current inspections for front compressor hubs installed in PW 4000-94" engine models. This AD also adds the PW4062A engine to the applicability. An FAA study of in-service events involving uncontained failures of critical rotating engine parts has indicated the need for mandatory inspections. The mandatory inspections are needed to identify those critical rotating parts with conditions, which if allowed to continue in service, could result in uncontained failures. We are issuing this AD to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
2019-06-07: We are superseding Airworthiness Directive (AD) 2016-22-05 for certain Pratt & Whitney Division (PW) PW4164, PW4164-1D, PW4168, PW4168-1D, PW4168A, PW4168A-1D, and PW4170 model turbofan engines. AD 2016-22-05 required initial and repetitive inspections of the affected fuel nozzles and their replacement with parts eligible for installation. This AD requires initial and repetitive inspections of the affected fuel nozzles and fuel nozzle supply manifold assemblies, replacement of the affected fuel nozzles with parts eligible for installation, and the installation of new brackets and clamps on the fuel nozzle supply manifold assemblies. This AD was prompted by several instances of fuel leaks on PW engines with the Talon IIB combustion chamber configuration installed. We are issuing this AD to address the unsafe condition on these products.
66-19-04: 66-19-04 SIKORSKY: Amdt. 39-269 Part 39 Federal Register August 4, 1966. Applies to Models S-58 and S-61 Series Helicopters Equipped With Tail Rotor Blades With Serial Numbers Listed in the Appendix of Sikorsky Service Bulletin 58B15-6A, Dated May 18, 1966, or 61B15-5A, Dated May 18, 1966, As Applicable. Compliance required within the next 50 hours' time in service after the effective date of this AD unless already accomplished. To prevent operation with tail rotor blades of less than minimum hardness in the flex shank area of the spar, accomplish the following: (a) Inspect S 1615-30100, S 6115-30001, and S 6117-30001 Series tail rotor blades in the manner set forth in Sikorsky Service Bulletin 58B15-6A or 61B15-5A as applicable. (b) Before further flight, remove from service blades that do not meet the minimum hardness requirements for the flex shank area of the spar specified in the applicable Service Bulletin. This directive effective August 14, 1966.
64-10-01: 64-10-01 BOEING: Amdt. 723 Part 507 Federal Register May 2, 1964. Applies to Models 707 and 720 Series Aircraft, Serial Numbers 17586 through 17628, 17630 through 17632, 17634 through 17640, 17642 through 17652, 17658 through 17690, 17692 through 17710, 17718 through 17720, 17722 through 17724, 17903 through 17906, 17908 through 17930, 18012 through 18019, on Which Boeing Service Bulletin No. 942 or an FAA Approved Equivalent Has Not Been Accomplished.\n \n\tCompliance required as indicated, unless already accomplished. \n\n\tBecause of recently discovered cracks in the stabilizer center section rear spar fitting, accomplish the following inspections and modification: \n\n\t(a) Within 125 hours' time in service after May 2, 1964, for all affected aircraft except aircraft with Serial Numbers 17658 through 17690, and within 125 hours' time in service after the effective date of this amendment for aircraft with Serial Numbers 17658 through 17690, remove upper left-hand and right-hand rear stabilizer attach pins. Inspect pins and holes in fitting lugs for cracks, by magnetic particle or dye penetrant method. Clean up any corrosion on pins and lugs. Replace any cracked part before further flight. (Boeing Service Bulletin No. 1967 (R-1) covers this same subject.) \n\n\t(b) Within 550 hours' time in service after May 2, 1964, for all affected aircraft except aircraft with Serial Numbers 17658 through 17690, and within 550 hours' time in service after the effective date of this amendment for aircraft with Serial Numbers 17658 through 17690, and at intervals not to exceed 1,650 hours' time in service from the last inspection, until (c) is accomplished, remove all stabilizer attach pins. Inspect pins and holes in fitting lugs for cracks, by magnetic particle or dye penetrant method. Clean up any corrosion on pins and lugs. Regrease pins with MIL-G-7118 grease and reinstall. Install cadmium plated pins only, unless chrome plating is required to build up pin diameter.Replace any cracked part before further flight. (Boeing Service Bulletin No. 1967 (R-1) covers this same subject.)\n \n\t(c) Within 5,000 hours' time in service after the effective date of this AD, remove left- hand and right-hand stabilizers and ream the terminal fittings on the stabilizers and torque box. Install bushings in the reamed holes according to Boeing Service Bulletin No. 942 or an FAA approved equivalent. (Boeing Service Bulletin No. 942 covers this same subject.) \n\n\tNOTE. - This AD supplements AD 64-04-02, concerning the same subject issued on February 4, 1964, and does not cancel nor supersede that AD. \n\n\tThis directive effective May 2, 1964. \n\n\tRevised August 12, 1964.
2005-25-07: The FAA adopts a new airworthiness directive (AD) for certain Raytheon Aircraft Company (Raytheon), Model 390, Premier 1 airplanes. For certain airplanes, this AD requires you (unless already done) to replace the plastic cover over the air conditioning motor module with a metallic cover and modify the air conditioning compressor motor module electromagnetic interference-radio frequency interference (EMI-RFI) filter located under the cover and reidentify the module part number. For all airplanes, the AD limits future installations of the cover for the air conditioner and the air conditioning compressor motor module. This AD results from reports that the plastic cover over the air conditioning motor module was found melted or burned and that the overheating of the EMI-RFI filter assembly located under the cover caused this damage. We are issuing this AD to prevent the melting or burning of the plastic cover. The burning of the plastic cover could result in a fire.
70-19-02: 70-19-02 AIRSEARCH: Amendment 39-1082 as amended by Amendment 39-1789. The AiResearch Manufacturing Company of Arizona. Applies to Turbopropeller Engines Model TPE331-1 and -2 installed in, but not limited to Mooney MU-2, Merlin 2B, Volpar Turboliner and Short Skyvan Aircraft. Compliance required as indicated. To detect impeding failure of the high speed pinion bearings accomplish the following: (a) New engines with less than 25 hours time in service or overhauled engines with less than 25 hours time in service since overhaul on the effective date of this AD must have the following accomplished: (1) After more than 5 hours time in service, but before exceeding 25 hours time in service after the effective date of this AD, an engine oil sample and the engine oil filter element must be returned to AiResearch Manufacturing Company, or a facility approved by the Chief, Aircraft Engineering Division, FAA, Western Region, for laboratory examination. (2) Priorto operation of the engine in excess of 35 hours time in service, either since new or since time of overhaul, the owner or operator must receive written confirmation from AiResearch, or other approved facility, that an acceptable level of oil contamination exists. (3) The provisions of (a)(1) and (a)(2), above, must be complied with after each subsequent overhaul unless the engine log book indicates that the engine was subjected to a 5 hour acceptance test as described in the FAA approved overhaul procedures as revised 1 September 1970, and a determination of acceptable oil and filter contamination was made by AiResearch or other FAA approved facility prior to returning the engine to service. (4) The provisions of (a)(1), (a)(2) and (a)(3) above do not apply to engines which have been modified in accordance with either Service Bulletin 632, Revision 2, dated December 4, 1972 or Service Bulletin TPE331-72-0064 dated February 1, 1974 and which have been subjected to the acceptance test as described in the FAA-approved overhaul procedures as revised February 1, 1974, and a determination of acceptable oil filter contamination was made by AiResearch or other FAA-approved facility prior to returning the engine to service. (b) A one time inspection of new engines with more than 25 hours but less than 50 hours time in service or overhauled engines with more than 25 hours time in service but less than 50 hours time in service since overhaul on the effective date of this AD must be accomplished: (1) Within 10 hours time in service after the effective date of this AD conduct a visual inspection of the oil filter in accordance with the engine maintenance manual. If a significant quantity of metal particles are found, the cause must be determined before further operation. NOTE: AiResearch Service Bulletin No. 624, dated 28 August 1970, or later FAA approved revision, lists for reference the serial number of all new or overhauled engines which had less than 50 hours time in service since new or overhaul on 28 August 1970, and describes an acceptable means of accomplishing items (a) and (b). (c) Within 50 hours time in service after the effective date of this AD, revise the normal procedures section of the applicable FAA approved Airplane Flight Manuals for aircraft equipped with AiResearch Model TPE331-1 and -2 engines to include a cautionary note to read as follows: "If sudden loss or significant fluctuation of torque pressure indication occurs, the engine should be promptly shut down and the cause determined before further operation." Amendment 39-1082 became effective on September 22, 1970. This Amendment 39-1789 becomes effective February 20, 1974.
2005-25-04: The FAA is adopting a new airworthiness directive (AD) for all EMBRAER Model EMB-135BJ, -135ER, -135KE, -135KL, -135LR, -145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP airplanes. This AD requires reviewing the airplane maintenance records for recent reports of vibration from the tail section or rudder pedals. This AD also requires repetitively inspecting the skin, attachment fittings, and control rods of rudder II to detect cracking, loose parts, wear, or damage; and related investigative/corrective actions if necessary. This AD results from reports of rudder vibration due to wear. We are issuing this AD to prevent failure of multiple hinge fittings, which could result in severe vibration, and to prevent failure of the rudder control rods, which could result in jamming of the rudder II; and possible structural failure and reduced controllability of the airplane.
2019-05-10: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 airplanes. This AD was prompted by a report of un-torqued nuts on certain slat and flap shaft junctions of the wings. This AD requires a one-time inspection on each junction of certain slat and flap shafts for discrepancies, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.