Results
2003-12-07: This amendment supersedes an existing airworthiness directive (AD), that is applicable to Pratt & Whitney JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR turbofan engines. That AD currently requires a determination of the utilization rate and protective coating type of the 7th, 8th, 9th, 10th, 11th, and 12th stage high pressure compressor (HPC) disks, and removal, inspection for corrosion, and recoating of those HPC disks based on utilization rate. This amendment requires removal and replacement of protective coating of 7th, 8th, 9th, 10th, 11th, and 12th stage HPC disks, initial and repetitive inspections for corrosion pits and cracks, and removal from service as required. This amendment is prompted by operator reports of cracks found on several JT8D steel HPC disks since the existing AD was published. The actions specified by this AD are intended to prevent fracture of the HPC disks, which can result in uncontained release of engine fragments, inflight engine shutdown, and airframe damage.
57-08-02: 57-08-02 BELL: Applies to All Models 47B3, 47D, 47D1, 47G, and 47H1 Helicopters Equipped With Parker Check Valves in the Oil System. Compliance required at next oil change and every 25 hours thereafter until replacement is accomplished. Several failures of the hinge in the oil system Parker check valve, P/N 1111-517703, 1111-517704, or 1111-517744, have occurred resulting in restriction of the flow of oil from the pump. To preclude recurrence of such failures, the following must be accomplished: 1. At the next oil change and every 25 hours thereafter, remove, disassemble, and inspect the oil system Parker check valve, P/N 1111-517703, 1111-517704, or 1111-517744, for wear or failure of the hinge and freedom of operation. If defects are found, replace the valve. 2. James Pond Clark check valve, P/N 879A-10TT, has been approved as a replacement valve. The 25-hour inspection outlined above may be discontinued when the valve is installed. (Bell Service Bulletin No. 119 dated March 15, 1957, covers this same subject.)
2000-20-13: This amendment adopts a new airworthiness directive (AD) that applies to certain British Aerospace HP137 Mk1, Jetstream series 200, and Jetstream Models 3101 and 3201 airplanes. This AD requires you to inspect the rudder quadrant support structure for cracks and correct D-washer installation; and also requires you to replace any cracked component and replace any incorrectly installed D-washers. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to detect, correct, and prevent further cracking in the rudder quadrant structure caused by incorrectly installed D-washers. Cracks in this structure could result in loss of rudder control with consequent airplane control problems.
97-08-01: This amendment adopts a new airworthiness directive (AD), applicable to CFM International CFM56-3, -3B, -3C series turbofan engines, that requires a reduction of the low cycle fatigue (LCF) retirement lives for certain fan disks. This amendment is prompted by the results of a refined life analysis performed by the manufacturer which revealed minimum calculated LCF lives significantly lower than published LCF retirement lives. The actions specified by this AD are intended to prevent a LCF failure of the fan disk, which could result in an uncontained engine failure and damage to the aircraft.
2025-06-03: The FAA is superseding Airworthiness Directive (AD) 2022-24-06 for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) Model BR700- 710A1-10, BR700-710A2-20, and BR700-710C4-11 engines. AD 2022-24-06 required initial and repetitive visual inspections of certain low- pressure compressor (LPC) rotor (fan) disks and replacement of any LPC rotor (fan) disk with cracks detected. AD 2022-24-06 also allows for modification of the engine in accordance with RRD service information as a terminating action to these inspections. Since the FAA issued AD 2022-24-06, the manufacturer published updated service information and revised the engine maintenance manual (EMM) to provide instructions for an improved ultrasonic inspection method, which prompted this AD. This AD requires initial and repetitive visual inspections of certain LPC rotor (fan) disks and replacement of any LPC rotor (fan) disk with cracks detected and would allow modification of the engine as a terminating action to the inspections, 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.
2013-18-08: We are superseding airworthiness directive (AD) 2004-18-06 for certain The Boeing Company Model 737-200, -200C, -300, -400, and -500 series airplanes. AD 2004-18-06 required repetitive inspections to find fatigue cracking of certain upper and lower skin panels of the fuselage, and follow-on and corrective actions if necessary. AD 2004- 18-06 also included a terminating action for the repetitive inspections of certain modified or repaired areas only. This new AD adds new inspections for cracking of the fuselage skin along certain chem-milled lines, and corrective actions if necessary. This new AD also reduces certain thresholds and intervals required by AD 2004-18-06. This AD was prompted by new findings of vertical cracks along chem-milled steps adjacent to the butt joints. We are issuing this AD to detect and correct fatigue cracking of the skin panels, which could result in sudden fracture and failure of the skin panels of the fuselage, and consequent rapid decompression ofthe airplane.
58-08-05: 58-08-05 HAMILTON STANDARD: Applies to All 34E, 43E, and 43H Propellers Installed on TC18DA and TC18EA Series Engines. Compliance required at first propeller overhaul after October 1, 1958, but not later than May 1, 1959. Cases of propeller-engine overspeeds have resulted in instances of failure to feather, reversing when feathering was initiated, and in aircraft fires. In order to provide a means for limiting propeller overspeeding so that the possibility of catastrophic conditions developing will be greatly minimized, install the "RPM-Sensitive Hydraulic Pitch Lock". (Hamilton Standard Service Bulletins Nos. 387, 472, and 472A cover this same subject.)
2000-20-07: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Beech Models 1900, 1900C, and 1900D airplanes. This AD requires you to modify the cockpit voice recorder (CVR) system. This AD is the result of instances where the recording quality of the CVR in the affected airplanes was so poor that the information was practically unrecoverable. The actions specified by this AD are intended to correct substandard quality cockpit voice recordings caused by the configuration of the present CVR system, which could affect air safety if important information that the CVR provides is not available after an accident. This information helps determine the probable cause of an accident and aids in developing necessary corrective action or design changes to prevent future accidents.
2000-20-01: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Turbomeca Arriel 1 series turboshaft engines. This action requires the installation of a chip detector with electronic warning on the rear bearing oil return system. This amendment is prompted by reports of gas generator rear bearing failures. The actions specified in this AD are intended to prevent gas generator rear bearing failure, which could lead to an uncommanded engine shutdown.
2013-19-08: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 727 airplanes; Model 737-100, -200, and -200C series airplanes; and Model 747-100, -100B, -100B SUD, -200B, -200C, - 200F, -300, -400, -400D, -400F, 747SR, and 747SP series airplanes. This AD was prompted by a report of an activation of the control column shaker during takeoff. This AD requires performing a general visual inspection to determine if a certain angle of attack (AOA) sensor with a paddle type vane is installed, and, for affected sensors, performing an operational test of the stall warning system, and replacing the AOA sensor with a new sensor if necessary. We are issuing this AD to prevent erroneous activation of the control column shaker during takeoff, which could result in runway overrun, failure to clear terrain or obstacles after takeoff, or reduced controllability of the airplane.