Results
58-05-01: 58-05-01 DOUGLAS: Applies to Goodyear Outboard Wheel Halves P/N 9531419 Installed on Douglas DC-7C 17.00-20 Main Wheel Assembly P/N 9540934. Affects Wheel Assemblies Manufactured Prior to Serial Number 157-1569 and Also Wheel Halves Serial Numbers 1573, 1574, 1575, 1595, 1596, 1597, 1771, 1833 and 1834. \n\n\tCompliance required at the first wheel or tire change after May 10, 1958, and at each 100 landings thereafter. If wheel inspection is performed during any portion of the 100-landing interval, no inspection will be required until the next 100 landings thereafter. \n\n\tAs the result of failures of Goodyear wheel half P/N 9531419 and in order to reduce the possibility of recurrence of these failures, the following inspection is required: \n\n\tInspect the outboard half P/N 9531419 in accordance with Goodyear Service Letter DC7C-3, dated January 15, 1957, or equivalent (Goodyear Service Letter DC7C-6, dated November 15, 1957, covers this same subject.) The inspections may be adjusted to tire change periods where the individual operators service experience justifies.
2021-02-19: 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 requires repetitive general visual inspections of the bilge barriers located in the forward and aft cargo compartments for disengaged or damaged decompression panels, reinstallation of disengaged but undamaged decompression panels, and replacement of damaged decompression panels. This AD was prompted by reports of multiple incidents of torn decompression panels being found in the bilge area. The FAA is issuing this AD to address the unsafe condition on these products.
2004-01-19: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and -11F airplanes, that requires replacement of the wire assembly connectors of the bag rack lighting with new, moisture-resistant connectors and reidentification of the bag racks. This action is necessary to prevent arcing of the wire assembly connectors of the overhead storage bin, and service module and bin extension assemblies, and consequent smoke/fire in the cabin. This action is intended to address the identified unsafe condition.
2010-05-13: The FAA is superseding an existing airworthiness directive (AD) that applies to all Model 737-100, -200, -200C, -300, -400, and - 500 series airplanes. That AD currently requires a one-time inspection for scribe lines and cracks in the fuselage skin at certain lap joints, butt joints, external repair doublers, and other areas; and related investigative/corrective actions if necessary. This new AD expands the area to be inspected and, for certain airplanes, requires earlier inspections for certain inspection zones. This AD results from additional detailed analysis of fuselage skin cracks adjacent to the skin lap joints on airplanes that had scribe lines. The analysis resulted in different inspection zones, thresholds and repetitive intervals, and airplane groupings. We are issuing this AD to prevent rapid decompression of the airplane due to fatigue cracks resulting from scribe lines on pressurized fuselage structure.
2021-03-16: The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS350B, AS350B1, AS350B2, AS350B3, AS350BA, AS350D, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters. This AD was prompted by the in-flight loss of a sliding door. This AD requires inspecting each sliding door and replacing the upper rail or front roller or removing the front roller from service if necessary. The actions of this AD are intended to address an unsafe condition on these products.
2009-25-05: 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: Several operators have reported cases of inadvertent single spoiler deployment during flight on the DHC-8 Series 400 aircraft. Investigation has revealed that the probable cause for this deployment is internal contamination of the Lift/Dump (L/D) valve and moisture ingress into the L/D valve armature. This condition, if not corrected, could cause uncommanded deployment of the spoilers resulting in increased drag and in combination with a loss of aileron, could result in a significant reduction in aircraft roll control. We are issuing this AD to require actions to correct the unsafe condition on these products.
59-01-03: 59-01-03 HARTZELL: Applies to HC-12X20, HC-13X20, HC-82X and HC-83X Series Propellers With Hub Serial Numbers As Indicated Herein. Compliance required as indicated. To minimize the possibility of failure of the split rings used to retain the blades in the hub, replace (if not previously accomplished) all unmarked split rings with new split rings marked with the letter "N", as follows: (1) Prior to February 15, 1959. HUB MODEL HUB SERIAL NO. INCLUSIVE HC-82XF-1DB, -1BB T-913 to T-2891 HC-82XF-2B F-400 to F-1675 (2) Prior to April 15, 1959. HUB MODEL HUB SERIAL NO. INCLUSIVE HC-82X20-1B C-104 to C-267 HC-12X20-7D, 7C, 7E R-118 to R-260 HC-12X20-8D, 3C, 3E P-157 to P-494 HC-83X20-2C D-448 to D-1530 HC-83XF-2A U-105 to U-437 HC-83X20-2CL V-104 to V-179 HC-13X20-6L X-101 to X-111 (3) Prior to June 1, 1959. HUB MODEL HUB SERIAL NO. INCLUSIVE HC-82XG-1D G-102 to G-305 HC-82XG-2B K-592 to K-2919 HC-82XL-1D100-Y to 121-Y HC-82XG-6B 100D to 169D After compliance, stamp the letter "N" after the hub serial number. This letter "N" should be stamped on propellers already modified. Serial numbers of propellers modified at the factory are listed in Hartzell Bulletin No. 64. The aircraft log book should contain this information for propellers modified in the field. (Hartzell Bulletin No. 64 covers this same subject.)
2004-01-16: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and -11F airplanes, that requires revising the wire connection stackups for the terminal strip of the generator feeder tail compartment of the auxiliary power unit (APU), and removing a nameplate, as applicable. For certain airplanes, this AD also requires replacing the terminal strips and revising the terminal hardware stackup for the feeder of the center cargo loading system. This action is necessary to prevent arcing damage to the terminal strips and damage to the adjacent structure, which could result in smoke and/or fire in the center and/or aft cargo compartments. This action is intended to address the identified unsafe condition.
2021-04-04: The FAA is superseding Airworthiness Directive (AD) 2020-19- 02, which applied to certain Airbus Helicopters (previously Eurocopter France) Model SA330J helicopters. AD 2020-19-02 required repetitively inspecting affected tail rotor (T/R) blades and depending on the inspection results, repairing or replacing the T/R blade. AD 2020-19-02 also prohibited installing an affected T/R blade unless it passed the inspections. This AD retains the requirements of AD 2020-19-02 and also clarifies the applicability, clarifies the affected T/R blades in the required actions, reduces a compliance time, and corrects the prohibition requirement. This AD was prompted by the determination that these corrections are necessary. The FAA is issuing this AD to address the unsafe condition on these products.
68-04-02: 68-04-02 BELL: Amdt. 39-555. Applies to Model 206A Helicopters, Serial Numbers 4 through 110, 112 through 116, 118, 119, 122, 124 through 126, 128, 129 and 133. Compliance required within the next 25 hours time in service after the effective date of this Airworthiness Directive, unless already accomplished in accordance with Bell Helicopter Service Letter, Model 206A No. 38, dated January 10, 1968. To prevent possible hazardous damage to the main rotor or the tail rotor due to failure of the exhaust stack clamps which attach the exhaust ducts to the engine exhaust flanges, accomplish the following modification: Replace exhaust stack clamp as follows: Remove clamps, P/N N3657, from the exhaust stacks. Install two new clamps, National Utilities Corporation, P/N 4656AA, on exhaust stacks with studs facing outboard. Tighten the two nuts on each clamp evenly until each nut is finger tight. Torque nuts to 30 inch pounds. Grasp top of stack and shake, at the same time tap clamp lightly with a plastic mallet and then recheck torque. Repeat this procedure until torque can be maintained at 30 inch pounds. Safety wire nuts to stud shanks with safety wire, P/N MS20995C32. This amendment becomes effective on March 15, 1968.