Results
2025-04-11: The FAA is adopting a new airworthiness directive (AD) for all Bombardier, Inc., Model BD-700-2A12 airplanes. This AD was prompted by the discovery that a partial loss of thrust after an engine failure during a required navigation performance authorization required (RNP- AR) approach under certain weight, altitude and temperature (WAT) conditions, may lead to a descent below the specified path guidance. This AD requires a revision to the existing airplane flight manual (AFM), to incorporate updated WAT tables for RNP-AR approach operations. The FAA is issuing this AD to address the unsafe condition on these products.
2014-23-01: We are superseding airworthiness directive (AD) 2013-15-09 for all Pratt & Whitney Division (PW) PW4074, PW4074D, PW4077, PW4077D, PW4084D, PW4090, and PW4090-3 turbofan engine models with certain second-stage high-pressure turbine (HPT) air seals installed. AD 2013- 15-09 required initial and repetitive inspections for cracks in second- stage HPT air seals. This new AD expands the applicability of AD 2013- 15-09 to include additional part numbers (P/Ns), requires removal of the mating hardware if the second-stage HPT air seal is found with a through-crack, and adds a mandatory terminating action. This AD was prompted by reports of cracking in the original location on two additional P/Ns and reports of through-cracks in a new location in the second-stage HPT air seal. We are issuing this AD to prevent failure of the second-stage HPT air seal, which could lead to uncontained engine failure and damage to the airplane.
66-27-03: 66-27-03\tBOEING: Amdt. 39-307 Part 39 Federal Register November 5, 1966. Applies to Models 707 and 720 Series Airplanes Equipped With Nylon Tube Conduit in the Tail Cone. \n\n\tCompliance required as indicated, unless already accomplished. \n\n\tTo prevent fire in the tail cone due to shorted tail navigation light wires, accomplish the following: \n\n\t(a)\tWithin the next 300 hours' time in service after October 12, 1966, unless already accomplished, inspect tail navigation light wiring for frayed or deteriorated wires and inspect protective nylon tube to ensure that it is secured to bulkhead. Replace frayed or deteriorated wires and secure nylon tube to bulkhead as necessary before further flight. \n\n\t(b)\tRepeat the inspection described in (a) every 300 hours' time in service until the following modifications or equivalent modifications approved by the Chief, Aircraft Engineering Division, FAA Western Region are accomplished but not later than 2,250 hours' time in service from theeffective date of this AD\n\n\t\t(1)\tTrim nylon tube flush with bulkhead 65-14660-3 at Fuselage Station 1653; \n\n\t\t(2)\tInstall cover plate and angle fabricated in accordance with Boeing Service Bulletin No. 2395(R-1) or later FAA-approved revision using a clamp and grommet in accordance with that Bulletin; and \n\n\t\t(3)\tReplace all frayed or chafed tail cone light wiring. \n\n\tThis supersedes AD 66-24-02. \n\n\tThis directive effective November 5, 1966.
2025-04-07: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A330-200, A330-200 Freighter, and A330-300 series airplanes. This AD was prompted by a report of contamination of the advanced pneumatic detector pressure switch of engine pylon fire detectors. This AD requires require replacement of the affected parts and prohibits installation of affected parts, 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.
2014-24-05: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-300, 747-400, 747-400D, and 747SR series airplanes. This AD was prompted by a report of a cracked reveal made from a casting found within a group of airplanes that should have machined reveals made only from 6061 aluminum. This AD requires an inspection to determine the material of the number 3 main entry door (MED) corner reveal, repetitive inspections of certain reveals for cracking, and corrective action if necessary. This AD also requires repetitive inspections for cracking of 6061 machined aluminum one-piece corner reveals, and replacement with 6061 machined aluminum two-piece corner reveals if necessary, which terminates certain repetitive inspections. We are issuing this AD to detect and correct fatigue cracking of the lower forward corner reveal of the number 3 MEDs, which could lead to the door escape slide departing the airplane when the door is opened and the slide is deployed, and consequent injuries to passengers and crew using the door escape slide during an emergency evacuation.
2014-25-08: We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 2000 and FALCON 2000EX airplanes. This AD was prompted by a design review, which revealed that the forward servicing compartment (FSC) is configured with tie-down points. This AD requires inspecting the FSC for installed tie-down points, and removing those tie-down points. We are issuing this AD to detect and correct installed tie-down points, which could lead to inadvertent use of the FSC as a cargo compartment, which could result in damage to the structure of the airplane or potential risk of fire.
76-01-01: 76-01-01 CESSNA and REIMS AVIATION: Amendment 39-2483. Applies to Cessna Models A150K and A150L and Reims Aviation Models FA150K and FA150L airplanes certified in the acrobatic category, which have been modified in accordance with STC SA1809WE, incorporating Flint Aero auxiliary fuel tanks in the outboard wing panels. \n\n\tCompliance is required within ten days after the effective date of this AD, unless already accomplished. \n\n\tTo prevent the possibility of encountering high speed flutter with fuel in these auxiliary fuel tanks, accomplish the following: \n\n\t(a)\tAdjacent to the airspeed indicator and in full view of the pilot, attach a placard which reads: \n\n\t\tAirspeed Limits when auxiliary tanks contain any amount of fuel: \n\n\nVne (never exceed)\n= 162 MPH (141 knots) \nVno (max. structural cruising)\n= 120 MPH (104 knots) \nVa (maneuvering)\n= 109 MPH ( 95 knots) \n\t\n\t(b)\tAny equivalent method of showing compliance with this AD or any demonstration of freedom from flutter of this design must be approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis amendment becomes effective January 9, 1976.
2018-07-21: We are superseding Airworthiness Directive (AD) 2005-12-16, which applied to all Fokker Services B.V. Model F28 Mark 0100 airplanes. AD 2005-12-16 required an inspection to determine the part number of the passenger service unit (PSU) panels for the PSU modification status, and corrective actions if applicable. This new AD requires an inspection of the PSU panels and the PSU panel/airplane interface connectors for discrepancies, and corrective actions if necessary. This AD also removes airplanes from the applicability. This AD was prompted by reports of smoke in the passenger compartment during ground operations and in-flight, and a determination that the modification actions required by AD 2005-12-16 might not have been implemented correctly. We are issuing this AD to address the unsafe condition on these products.
2014-25-06: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes; Airbus 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); and Airbus Model A310 series airplanes. This AD was prompted by a report of early ruptures on the levers of the nose landing gear (NLG) sequence valve. This AD requires a one-time inspection for damage of the landing gear sequence valve levers and pin shearing indicating areas on the NLG and the main landing gears (MLGs); and depending on findings, replacing the sequence valve and lever, or doing a one-time inspection to detect interference between control rods and sequence valves and corrective actions if necessary. We are issuing this AD to detect and correct interference between a landing gear leg and door, which could result in failure of that landing gear to extend and could damage the airplane and injure occupants.
2014-25-07: We are adopting a new airworthiness directive (AD) for certain Airbus Model A320-211, -212, -214, -231, -232, and -233 airplanes. This AD was prompted by a report of cracking at the splice plate of the frame (FR) 47 butt joint crossing area found during full-scale fatigue testing. This AD requires repetitive inspections for cracking of both sides of the splice plate of that frame butt joint crossing area, and corrective action if necessary. This AD also provides for an optional modification, which terminates the repetitive inspections. We are issuing this AD to detect and correct fatigue cracking of the splice plate of the FR 47 butt joint crossing area, which could result in reduced structural integrity of the airplane.
70-25-07: 70-25-07 BOEING: Amdt. 39-1125. Applies to Model 707 and 720 Series airplanes listed in Boeing Service Bulletin 2998, dated October 1, 1970, or later FAA approved revisions. \n\n\tTo prevent fluid bypassing within the Rudder Power Control Unit (PCU) accomplish the following: \n\n\tWithin the next 300 hours' time in service after the effective date of this AD, unless previously accomplished, modify the Rudder PCU in accordance with Boeing Service Bulletin 2998, dated October 1, 1970, or later FAA approved revision or an equivalent method approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis amendment becomes effective December 11, 1970.
2025-04-03: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by two engine fan blade- out (FBO) events that resulted in the separation of engine inlet cowl and fan cowl parts from the airplane damaging the fuselage, which caused loss of pressurization and subsequent emergency descent. The FBO events also resulted in cracks in the primary exhaust nozzle, potentially resulting in the departure of the primary exhaust nozzle and damaging a stabilizer or striking the fuselage and window. This AD requires an inspection or maintenance records check to determine if the primary exhaust nozzle has an affected part number and, for affected primary exhaust nozzles, an installation of bridge brackets onto the primary exhaust nozzle, or as an option, an installation of a serviceable primary exhaust nozzle. This AD also requires revising the existing maintenance or inspection program, as applicable, to incorporate new airworthiness limitations. The FAA is issuing this AD to address the unsafe condition on these products.
2014-25-01: We are superseding Airworthiness Directive (AD) 2010-13-04 for certain Bombardier, Inc. Model DHC-8-400 series airplanes. AD 2010-13- 04 required modifying the nose landing gear (NLG) trailing arm. This new AD requires installing a new pivot pin retention mechanism. This new AD also adds airplanes to the applicability. This AD was prompted by a report of several missing or damaged pivot pin retention bolts. We are issuing this AD to prevent failure of the pivot pin retention bolt, which could result in a loss of directional control or loss of a NLG tire during take-off or landing.
2008-14-02 R1: We are revising Airworthiness Directive (AD) 2008-14-02 for Agusta Model AB139 and AW139 helicopters. AD 2008-14-02 required inspecting the fuselage frame to detect fatigue cracks which could lead to structural failure and subsequent loss of control of the helicopter. Since we issued AD 2008-14-02, Agusta developed a frame reinforcement modification, which supports extending the interval for inspecting the fuselage frame for a fatigue crack. This new AD requires inspecting the fuselage frame for a crack and reduces the applicability from AD 2008- 14-02 to exclude helicopters with the frame reinforcement modification. The actions of this AD are intended to detect a fatigue crack that could result in failure of the fuselage frame and subsequent loss of control of the helicopter.
2014-25-05: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777 airplanes. This AD was prompted by reports of corroded, migrated, or broken spring pins of the girt bar floor fitting; in one case the broken pins prevented a door escape slide from deploying during a maintenance test. This AD requires replacing the existing spring pins at each passenger entry door at both girt bar floor fittings with new spring pins. We are issuing this AD to prevent broken or migrated spring pins of the girt bar floor fittings, which could result in improper deployment of the escape slide/raft and consequent delay and injury during evacuation of passengers and crew from the cabin in the event of an emergency.
2025-04-12: The FAA is adopting a new airworthiness directive (AD) for certain CFM International, S.A. (CFM) Model LEAP-1A, LEAP-1B, and LEAP- 1C engines. This AD was prompted by a manufacturer investigation that revealed a quality escape for low-pressure turbine (LPT) disks made from forgings with nonconforming grain size. This AD requires removal and replacement of the LPT stage 4 and stage 5 disks. The FAA is issuing this AD to address the unsafe condition on these products.
2014-24-07: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318, A319, A320, and A321 series airplanes. This AD was prompted by a report of a crack found in the fuselage during a fatigue test campaign. This AD requires repetitive rototest inspections for cracking; corrective actions if necessary; and modification of the torsion box, which would terminate the repetitive inspections. We are issuing this AD to prevent cracking in the side box beam flange of the fuselage, which could affect the structural integrity of the airplane.
2014-23-13: We are superseding Airworthiness Directive (AD) 2000-12-12, for certain Airbus Model A300, A300-600, and A310 series airplanes. AD 2000-12-12 required inspecting to detect cracks in the lower spar axis of the nacelle pylon between ribs 9 and 10, and repair if necessary. AD 2000-12-12 also provided for optional modification of the pylon, which terminated the inspections for Model A300 series airplanes. This new AD reduces the initial and repetitive inspection compliance times. This AD was prompted by reports of cracking of the lower pylon spar after accomplishing the existing modification. We are issuing this AD to detect and correct fatigue cracking, which could result in reduced structural integrity of the lower spar of the nacelle pylon.
2014-23-16: We are superseding Airworthiness Directive (AD) 2011-12-10 for Robinson Helicopter Company (Robinson) Model R22, R22 Alpha, R22 Beta, R22 Mariner, R44, and R44 II helicopters with certain main rotor blades (blade) installed. AD 2011-12-10 required inspecting each blade at the skin-to-spar line for debonding, corrosion, a separation, a gap, or a dent and replacing any damaged blade with an airworthy blade. This new AD also requires a terminating action for those inspection requirements. These actions are intended to detect debonding of the blade skin, which could result in blade failure and subsequent loss of control of the helicopter, and to correct the unsafe condition by replacing the main rotor blades with new blades that do not require the AD inspection.
2025-02-06: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500- 1A11 airplanes. This AD was prompted by a report that the nose radome lightning diverter strips on certain aircraft were painted in production; paint on the diverter strips can compromise the nose radome lightning protection. This AD requires inspecting for paint on the diverter strips on the nose radome, and replacing the nose radome if necessary, as specified in a Transport Canada AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2014-24-06: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 airplanes. This AD was prompted by failure during testing of the anchor attachment on the occupant restraint system on the standard attendant seat due to an understrength attachment fitting. This AD requires replacing the existing restraint attachment fitting on the standard attendant seat with a new, improved attachment fitting. We are issuing this AD to prevent failure of the restraint attachment fitting of the attendant seat during an emergency landing, which could cause injury to the cabin crew and passengers and could impede a rapid evacuation.
2014-23-17: We are superseding Airworthiness Directive (AD) 2013-20-06 for all Airbus Model A340-211, -212, -213, -311, -312, -313, -541, and -642 airplanes. AD 2013-20-06 required revising the maintenance program to incorporate certain maintenance requirements and airworthiness limitations. This new AD requires revising the maintenance or inspection program to incorporate certain other maintenance requirements and airworthiness limitations. This AD was prompted by a determination that existing maintenance requirements are not adequate to address the aging effects of aircraft systems. We are issuing this AD to address the aging effects of aircraft systems. Such aging effects could change the characteristics of systems' life-limited components leading to an increased potential for failure, which, in isolation or in combination with one or more other specific failures or events, could result in failure of certain life limited parts, which could reduce the structural integrity or the controllability of the airplane. [[Page 71305]]
75-16-08: 75-16-08 ROLLS ROYCE (1971) LIMITED: Amendment 39-2274. Applies to Rolls Royce RB211 series engines, serial numbers 10389 and prior. Compliance required by December 31, 1975, unless already accomplished. To prevent damage in the intermediate and high pressure compressors that contributes to the frequency of high power surges, accomplish the following: 1. Modify the inlet guide vane spherical trunnions, bearing pads, actuating rings, and bearing support segments in accordance with Rolls-Royce (1971) Limited Service Bulletin RB211-72-3326, dated November 14, 1973, or an FAA-approved equivalent. 2. Modify the intermediate pressure (IP) compressor inlet guide vanes in accordance with Rolls-Royce (1971) Limited Service Bulletin RB211-72-3335, Revision 2, dated March 12, 1974, or an FAA-approved equivalent. 3. Modify the IP compressor stator vanes in the 4th and 5th stage stator assemblies in accordance with Rolls-Royce (1971) Limited Service Bulletin RB211-72-3482, dated April 9, 1974, or an FAA-approved equivalent. This amendment becomes effective August 22, 1975.
2014-23-10: We are superseding Airworthiness Directive (AD) 2008-17-03 for certain The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. AD 2008-17-03 required repetitive inspections to detect fuselage frame cracking, and corrective action if necessary. AD 2008-17-03 also provided for optional terminating action (repair/ preventive change) for the repetitive inspections. This new AD adds airplanes to the applicability, but does not provide terminating action for the newly added airplanes. This AD was prompted by reports of cracks found at the cutout in the web of body station \n\n((Page 71297)) \n\nframe 303.9 inboard of stringer 16L, as well as a new report of cracking found on an airplane not identified in the applicability of AD 2008-17-03. We are issuing this AD to detect and correct fuselage frame cracking, which could prevent the left forward entry door from sealing correctly, and could cause in-flight decompression of the airplane.
2014-22-10: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model DC-8-55, DC-8F-54, and DC-8F-55 airplanes, Model DC-8-60 series airplanes, Model DC-8-60F series airplanes, Model DC-8-70 series airplanes, and Model DC-8-70F series airplanes. This AD was prompted by multiple reports of cracking of the upper aft skin panel of \n\n((Page 70788)) \n\nthe fuselage. An evaluation by the design approval holder (DAH) indicates that the upper aft skin panel of the fuselage is subject to widespread fatigue damage (WFD). This AD requires removing any previously installed local repairs; installing a full-length improvement modification with or without finger doublers, or a full- length repair with or without finger doublers, as applicable; and doing repetitive inspections for cracking of the doublers, and repair if necessary. We are issuing this AD to detect and correct fatigue cracking of the upper aft skin panel of the fuselage, which could result in loss of structural integrity and consequent rapid decompression of the airplane.