Results
2015-08-51: We are publishing a new airworthiness directive (AD) for Enstrom Helicopter Corporation (Enstrom) Model F-28A, 280, F-28C, F- 28C-2, F-28C-2R, 280C, F-28F, F-28F-R, 280F, 280FX, and 480 helicopters. This AD was sent previously to all known U.S. owners and operators of these helicopters and supersedes Emergency AD (EAD) 2015- 04-51, dated February 12, 2015. This AD requires inspecting certain main rotor spindles (spindles) for cracks and reporting the inspection results to the FAA. This AD is prompted by a fatal accident and reports of spindles with cracks. The actions specified in this AD are intended to detect a crack in a spindle and prevent loss of a main rotor blade and subsequent loss of control of the helicopter.
2015-09-06: We are superseding Airworthiness Directive (AD) 2014-26-04 for certain GROB-WERKE Models G115EG and G120A 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 a defective starter solenoid. We are issuing this AD to require actions to address the unsafe condition on these products.
98-13-28: This amendment adopts a new airworthiness directive (AD) that is applicable to Agusta S.p.A. (Agusta) Model A109C and A109K2 helicopters. This action requires a one-time inspection of each tail rotor blade (blade) for debonding, and if debonding exists which exceeds certain limits, replacement of the blade with an airworthy blade. This amendment is prompted by two incidents in which helicopters lost a blade tip fairing during ground run-up. The actions specified in this AD are intended to prevent loss of the tip fairing on a blade, which could result in increased vibrations, loss of the tail rotor assembly, and subsequent loss of control of the helicopter.
2015-08-07: We are adopting a new airworthiness directive (AD) for certain Zodiac Aerotechnics (formerly Intertechnique Aircraft Systems) oxygen [[Page 27082]] mask regulators. This AD was prompted by a report of a malfunctioning mask having an inflatable harness with a high premature rupture rate due to defective silicon. This AD requires inspecting and replacing defective harnesses with new or modified serviceable units. We are issuing this AD to detect and correct defective harnesses, which could lead, in case of a sudden depressurization event, to a harness rupture, thereby providing inadequate protection against hypoxia and possibly resulting in unconsciousness of the affected flightcrew member and consequent reduced control of the airplane.
2015-09-01: We are adopting a new airworthiness directive (AD) for Airbus Model EC225LP helicopters. This AD requires repetitive visual and tap test inspections of each main rotor blade (blade) leading edge stainless steel protective strip (strip) for a crack, cut, or blind or open debonding (debonding), and taking approved corrective measures. If there is a crack or if there is debonding that exceeds acceptable limits, this AD requires, before further flight, repairing or replacing the blade with an airworthy part. This AD was prompted by suspected water seepage through a crack in the blade strip resulting in significant debonding. The actions of this AD are intended to prevent loss of the blade strip, excessive vibrations induced by blade weight imbalance, and subsequent loss of control of the helicopter.
75-08-14: 75-08-14 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-2166 as amended by Amendment 39-2201 is further amended by Amendment 39-2627. Applies to Lockheed- California Company Model L-1011-385-1 series airplanes certificated in all categories. To prevent possible failures of the C-1, C-2, and C-3 cargo door hooks due to cracks, accomplish the following: (a) Within 275 additional flight hours after the effective date of this AD, unless already accomplished, perform the following per Lockheed Alert Service Bulletin 093-52-A079, Revision 1, dated March 26, 1975 or later FAA-approved revision. (1) An inspection of the C-1, C-2 and C-3 cargo door hooks for identification configuration and affixing of appropriate part numbers; (2) A dye penetrant inspection of all hooks for cracks; (3) Replace all cracked hooks prior to further flight. (4) Scrap hooks identified as P/N's 1517205-103/-105. (5) Check rigging of hooks and doors for usage, and rerigg, as required.(b) Perform a dye penetrant inspection for cracks at intervals not to exceed 1500 hours time in service, of the C-1 and C-2 cargo door hooks identified as P/N's 1517205-107/-109 (per the inspection of (a)(1), above). Replace all cracked hooks prior to further flight. (c) Within 3000 flight hours after the initial inspections performed per (a)(1) and (2), above, replace all hooks identified as P/N's 1517205-107/-109 with hooks identified as P/N's 1517205-111/-113 on the C-1 and C-2 cargo doors. (d) The repetitive inspections required by paragraph (b) of this AD may be discontinued after accomplishment of modifications and checks in accordance with FAA-approved Lockheed-California Company Service Bulletin 093-52-087, dated March 11, 1976, or later FAA- approved revisions or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region. (Reference: Paragraph (f), AD 76-09-03). (e) Equivalent inspections and replacements may be approved by the Chief, Aircraft Engineering Division, FAA Western Region. (f) Airplanes may be flown to a base for the accomplishment of the inspections and replacements required by this AD, per FAR's 21.197 and 21.199. Amendment 39-2166 became effective April 16, 1975. Amendment 39-2201 became effective May 19, 1975. This amendment 39-2627 becomes effective June 7, 1976.
2025-02-12: The FAA is superseding Airworthiness Directive (AD) 2023-20-03 for certain Austro Engine GmbH Model E4 and E4P engines. AD 2023-20-03 required repetitive engine oil analysis for aluminum content outside the acceptable limits and, if necessary, replacement of the pistons, piston rings, con-rods assembly, and crankcase or, as an alternative, replacement of the engine core. Since the FAA issued AD 2023-20-03, the manufacturer identified errors in the lists of affected engines and provided updated information, which prompted this AD. This AD retains the requirements of AD 2023-20-03, adds compliance times for additional affected engine serial numbers, and removes certain engine serial numbers from the applicability of the existing AD. The FAA is issuing this AD to address the unsafe condition on these products.
2025-02-14: The FAA is adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG Model Trent 1000-AE3, Trent 1000- CE3, Trent 1000-D3, Trent 1000-G3, Trent 1000-H3, Trent 1000-J3, Trent 1000-K3, Trent 1000-L3, Trent 1000-M3, Trent 1000-N3, Trent 1000-P3, Trent 1000-Q3, Trent 1000-R3, Trent 7000-72, and Trent 7000-72C engines. This AD was prompted by reports of cracked intermediate pressure compressor (IPC) shaft assembly front air seals. This AD requires an inspection of the affected IPC shaft assembly for cracking and, depending on the results of the inspection, repetitive inspections or replacement of the IPC shaft assembly front air seals, 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.
2015-09-07: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 787 airplanes. This AD requires a repetitive maintenance task for electrical power deactivation on Model 787 airplanes. This AD was prompted by the determination that a Model 787 airplane that has been powered continuously for 248 days can lose all alternating current (AC) electrical power due to the generator control units (GCUs) simultaneously going into failsafe mode. This condition is caused by a software counter internal to the GCUs that will overflow after 248 days of continuous power. We are issuing this AD to prevent loss of all AC electrical power, which could result in loss of control of the airplane.
2015-07-02: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604 Variants) airplanes. This AD was prompted by a determination that the forward lugs of the flap hinge box might not conform to engineering drawings, which could result in premature fatigue cracking. This AD requires revising the maintenance or inspection program to include new airworthiness limitations tasks; and measuring the forward lug edge distance of each flap hinge box, inspecting for cracking and damage (i.e., deformation or bearing failure) of the forward lug edge of each flap hinge box, and repairing any cracking or damage if necessary. We are issuing this AD to detect and correct non-conforming flap hinge box forward lugs, which could result in failure of the lugs and detachment of the flap hinge box and consequent detachment of the flap surface.
2015-08-09: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600 and -700 series airplanes. This AD was prompted by reports of cracking in the body station (STA) 727 bulkhead lower frame. This AD requires a detailed and open hole high frequency eddy current (HFEC) inspection of the left- and right-side lower frame webs and inner chords for cracking, and corrective actions and preventative modifications if necessary. This AD also provides for optional terminating action of the repetitive inspections, under certain conditions. We are issuing this AD to detect and correct cracking in a bulkhead lower frame web and inner chord, which could result in a severed frame and induced skin cracks, and could lead to rapid decompression of the fuselage.
72-13-07: 72-13-07 FAIRCHILD-HILLER: Amdt. 39-1465. Applies to Models 1100 and FH-1100 helicopters certificated in all categories. Compliance required after the effective date of this AD as follows: 1. For helicopters incorporating P/N 19E49-3A or -3B engine-to-transmission drive shaft assemblies, replace the assemblies within 15 hours in service with P/N 19E49-3C assemblies which have accumulated less than 350 hours on their diaphragm end packs, or with P/N 19E49-3E assemblies. 2. For helicopters incorporating P/N 19E49-3C engine-to-transmission drive shaft assemblies with 350 hours or more in service on their diaphragm end packs, replace the assemblies with P/N 19E49-3E assemblies within the next 50 hours in service. 3. For helicopters incorporating P/N 19E49-3C engine-to-transmission drive shaft assemblies with less than 350 hours in service on their diaphragm end packs, replace the assemblies with P/N 19E49-3E assemblies prior to the accumulation of 400 hours in service.4. Within the next 50 hours in service, unless already accomplished within the last 50 hours in service and every 50 hours in service thereafter, inspect horizontal and vertical alignment, and axial end play of each drive shaft assembly in accordance with Sections 24-21-4 and 24-21-5 of Fairchild-Hiller FH-1100 Service Manual revised 1 March 1972 or alternative method approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. When alignment or axial end-play limits are exceeded, replace components and check engine and transmission rigging in accordance with the service manual instructions. 5. The repetitive inspections required by Item 4 above may be extended to 100-hour intervals when P/N 19E49-3E assembly is installed. These inspections shall be conducted whenever a hard landing is made, the engine, the engine-to-transmission drive shaft, engine transmission support strut, or transmission isolation mount is removed or replaced. (Fairchild-Hiller Service Bulletin FH-1100-24-4 pertains to this subject.) This amendment 39-1465 revokes AD 69-15-11. This amendment is effective June 27, 1972.
2015-08-03: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by a report that during production, an incorrect clevis was used, resulting in improper installation onto the alternate release cable of the main landing gear (MLG). This AD requires a detailed visual inspection of the emergency release clevis of the MLG to determine if an incorrect clevis has been installed, and if necessary, replacing the clevis with a correct clevis and clevis pin. We are issuing this AD to detect and correct improper installation of the clevis, which could cause loss of the alternate release system and prevent the MLG from extending and retracting, and could consequently affect the airplane's continued safe flight and landing.
2015-06-10: We are adopting a new airworthiness directive (AD) for certain ATR-GIE Avions de Transport R[eacute]gional Model ATR72-212A airplanes. This AD requires inspection of the shock mount pick-up fittings and cone bolts, and replacement of certain shock mount pick-up fittings if necessary. This AD was prompted by reports of several cases of engine shock mount pick-up fittings with cracks or failure on the engine left- hand (LH) aft side attachment. We are issuing this AD to detect and correct an aft side attachment [[Page 21640]] pick-up fitting failure associated with a cone bolt failure that could reduce the structural integrity of the concerned engine nacelle, and possibly result in detachment of the engine and consequent reduced control of the airplane.
2023-20-03: The FAA is adopting a new airworthiness directive (AD) for certain Austro Engine GmbH Model E4 and E4P engines. This AD is prompted by reports of piston failures and the determination that certain batches of pistons were manufactured with a dimensional deviation in the piston pin bore and piston diameter. This AD requires repetitive engine oil analysis for aluminum content outside the acceptable limits and, if necessary, replacement of the pistons, piston rings, con-rods assembly, and crankcase or, as an alternative, replacement of the engine core. The FAA is issuing this AD to address the unsafe condition on these products.
2015-07-05: We are adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model BAe 146 series airplanes, and Model Avro 146-RJ series airplanes. This AD was prompted by a report of a pressurization problem on an airplane during climb-out; a subsequent investigation showed a crack in the fuselage skin. This AD requires require repetitive external eddy current inspections on the aft skin lap joints of the rear fuselage for cracking, corrosion, and other defects, and repair if necessary. We are issuing this AD to detect and correct cracking, corrosion, and other defects, which could affect the structural integrity of the airplane.
2015-08-02: We are superseding Airworthiness Directive (AD) 2015-02-04 for certain Dassault Aviation Model MYSTERE-FALCON 50 airplanes. AD 2015- 02-04 required installing two protective plates between the electrical wiring under the glare shield and the engine fire pull handles. This new AD continues to require installing two protective plates between the electrical wiring under the glare shield and the engine fire pull handles. This AD was prompted by our determination that the published version of AD 2015-02-04 incorrectly identified the AD number as ``AD 2014-02-04'' in a certain paragraph. We are issuing this AD to prevent chafing of the electrical wiring, which could result in a short circuit and generation of smoke in the cockpit, potential loss of several functions essential for safe flight, and consequent reduced controllability of the airplane.
74-13-06: 74-13-06 McCAULEY: Amendment 39-1878. Applies to main wheel assemblies P/N's D-30063-1, -2, and -4, S/N's 720000 thru 739999 typically used on, but not limited to, Cessna Aircraft Models 180J, A185F, U206F, TU206F, 210L and T210L. Compliance required as indicated unless already accomplished. To prevent possible wheel failures due to breakage of the wheel flange attaching bolts, accomplish the following: (a) For main wheel assemblies used on the Cessna Aircraft Models 180J, A185F, U206F, TU206F, 210L, and T210L manufactured in the Model Year 1974 and any other aircraft with these main wheel assemblies installed, within the next 25 hours' time in service, modify main wheel assemblies in accordance with the instructions contained in McCauley Industrial Corporation Service Bulletin WB-1-A dated June 10, 1974, or subsequent Federal Aviation Administration approved revisions. Equivalent methods of compliance with this Airworthiness Directive must be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration Great Lakes Region, Des Plaines, Illinois. (b) For main wheel assemblies used on Cessna Aircraft Models 180J and A185F, manufactured in the Model Year 1973; within 25 hours' time in service after the effective date of this Airworthiness Directive and thereafter, at intervals not to exceed 25 hours' time in service visually inspect the 1/4" bolts attaching the wheel flanges for broken bolts until compliance with the modification in Paragraph (a) above is accomplished. If indications of broken bolts exist modify wheels in accordance with Paragraph (a). (c) Upon completion of the modification in Paragraph (a), record compliance with this particular part of the Airworthiness Directive in the aircraft logbook. NOTE: Cessna Service Letter SE 74-8 or subsequent revisions pertains to the same subject. The McCauley wheels may additionally be marked with Cessna P/N's C163002-0102, -0103 or -0104. Thisamendment becomes effective June 24, 1974.
2015-07-06: We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4- 605R, F4-622R, and C4-605R Variant F airplanes; and Model A310-203, - 204, -221, -222, -304, -322, -324, and -325 airplanes. This AD was prompted by a report of inner skin disbonding damage on a rudder. This AD requires repetitive ultrasonic inspections for disbonding of certain rudders; an elasticity of laminate [[Page 19010]] checker inspection; a woodpecker or tap test inspection; venting the core, if necessary; and repairing, if necessary. We are issuing this AD to detect and correct rudder disbonding, which could affect the structural integrity of the rudder.
2015-06-08: We are superseding Airworthiness Directive (AD) 2011-09-03 for all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes. AD 2011-09-03 required repetitive eddy current inspections to detect cracks in the center wing upper and lower rainbow fittings, and corrective actions if necessary; and repetitive replacement of rainbow fittings, which would extend the repetitive interval for the next inspection. This new AD requires reduced intervals for inspections of the upper rainbow fittings. This AD was prompted by analysis of in-service cracking, which has shown that a reduction in the inspection intervals is necessary for the upper rainbow fittings. We are issuing this AD to detect and correct fatigue cracking of the upper and lower rainbow fittings on the center wings, which could grow large and lead to the failure of the fitting and a catastrophic failure of the center wing.
75-20-08: 75-20-08 BEECH: Amendment 39-2374. Applies to Model B24R (Serial Numbers MC-151 thru MC-302, MC-304, MC-307, MC-309, MC-310, MC-312 thru MC-315, MC-317, MC-324, MC-328, MC-333, MC-336, MC-344, MC-345, MC-347 thru MC-357, MC-359 and MC-361 thru MC-364) airplanes. Compliance: Required as indicated, unless already accomplished. To preclude the possibility of propeller governor failure, accomplish the following: 1) Unless previously accomplished, prior to further flight, drain the Rust Ban Preservative Oil installed by the airplane manufacturer and refill with SAE 30 or SAE 50 straight mineral oil or the type and grade of oil recommended by the engine manufacturer. 2) If the airplane has less than 25 hours' total time in service, prior to further flight, remove the propeller governor and replace with a new or serviceable P/N A210490 propeller governor. 3) Aircraft may be flown to a place where the AD can be accomplished in accordance with FAR 21.197 providing the propeller governor is found to govern engine RPM properly during pre-flight runup. Beechcraft Service Instruction No. 0765-254 pertains to this subject. This amendment becomes effective October 3, 1975, to all persons except those to whom it was made effective earlier by air mail letter issued September 15, 1975.
2015-06-07: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-100, 737-200, 737-200C, 737-300, 737-400, and 737-500 series airplanes. This AD was prompted by reports of cracking in the lower corners of the forward entry doorway and the upper corners of the airstairs cutout. This AD requires inspections for cracking of the forward entry doorway and airstairs cutout, and corrective actions if necessary. This AD also provides terminating action for the repetitive inspections. We are issuing this AD to detect and correct cracks in the lower corners of the forward entry door cutout and the upper corners of the airstairs cutout, which could progress and result in an inability to maintain cabin pressurization.
2015-06-05: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 and A310 series airplanes, and certain Model A300 B4- 600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). This AD was prompted by a review of certain repairs, which revealed that the structural integrity of the airplane could be negatively affected if those repairs are not re-worked. This AD requires an inspection to identify certain repairs, and corrective action if necessary. We are issuing this AD to detect and correct certain repairs on the floor cross beams flange. If those repairs are not reworked, the structural integrity of the airplane could be negatively affected.
76-02-07: 76-02-07 PRESTOLITE: Amendment 39-2500. Applies to Prestolite ALV-9400 through ALV-9410 series gear driven alternators. For aircraft having Prestolite ALV-9400 through ALV-9410 series alternators with more than 100 hours time in service compliance is required within the next 25 hours time in service after 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 check. To detect defective alternator slip ring end bearings and minimize the probability of in-service failures, accomplish the following: Remove the slip ring end bearing cover by using a small sharp chisel, knife blade, or screwdriver to pry it out of the alternator slip ring head. Care must be taken not to damage the end head or bearing cover. If the bearing cover is damaged during removal it must be replaced. Without further disassembly visually inspect the bearing and shaftend for discoloration or any sign of overheating or wear. Pay particular attention to the bearing inner and outer race. If there is any sign of overheating or an indication that the rotor shaft has been turning in the inner race or the outer race has been turning in the end head, the alternator must be removed and repaired. If the rotor shaft has been turning in the bearing inner race, the rotor and bearing must be replaced. If the bearing outer race has been turning in the end head, the bearing and end head must be replaced. Check the bearing grease for any sign of overheating or contamination such as dirt, or metal filings. If the grease is a dark brown or black color, or is so contaminated, the alternator must be removed and the bearing replaced. If the bearing shows no sign of discoloration, overheating, wear, or contamination, the bearing only (not the entire cavity) should be filled with Chevron BRB#2 or Chevron SRI#2 grease or an equivalent approved by Chief, Engineering and Manufacturing Branch, Great Lakes Region. At this time we are not aware of an equivalent lubricant for this application. NOTE: Refer to Continental Service Bulletin No. TCM M75-30 for further information concerning this subject. The checks required by this AD may be performed by the pilot. Operators who have not kept records of hours time in service on individual alternators shall substitute aircraft hours time in service in lieu thereof. This amendment becomes effective February 2, 1976.
2015-05-02: We are superseding Airworthiness Directive (AD) 2014-23-15 for all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2014- 23-15 required revising the maintenance or inspection program to incorporate new, more restrictive airworthiness limitations. This new AD retains the requirement to revise the maintenance or inspection program and removes a conflicting requirement. This AD was prompted by a determination that certain limitations required by AD 2014-23-15 conflict with limitations required by another AD. We are issuing this AD to prevent fatigue cracking, accidental damage, or corrosion in principal structural elements, and possible failure of certain life limited parts, which could result in reduced structural integrity of the airplane.