Results
2005-01-17: The FAA adopts a new airworthiness directive (AD) to supersede AD 98-03-14, which applies to certain EXTRA Flugzeugbau GmbH (EXTRA) Model EA-300 and EA-300/S airplanes. AD 98-03-14 currently requires you to inspect the upper longeron cutout-bridge for cracks, to repair any cracks found, and to modify this area. This AD retains the actions of AD 98-03-14 and incorporates new service information. For owner/ operators of the affected airplanes that were able to do the modification required in AD 98-03-14, no further action is required. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to detect and correct cracks in the upper longeron cutout-bridge, which could cause the upper longeron cutout-bridge to fail resulting in structural damage to the fuselage. This condition could lead to loss of control of the airplane. DATES: This AD becomes effective on February 28, 2005. On March 16, 1998 (63 FR 5881, February 5, 1998), the Director of the Federal Register approved the incorporation by reference of EXTRA Flugzeugbau GmbH Service Bulletin EA-300 & EA-300/S Doc: SB-300-3-93, Issue: A, Date: January 12, 1994. As of February 28, 2005, the Director of the Federal Register approved the incorporation by reference of EXTRA Flugzeugbau GmbH Service Bulletin EA-300 & EA-300/S Doc: SB-300-3-93, Issue: B, Date: June 10, 1998.
2023-12-21: The FAA is superseding Airworthiness Directive (AD) 2021-26- 13, which applied to all Rolls-Royce Deutschland Ltd & Co KG (RRD) Model Trent 1000-A2, Trent 1000-AE2, Trent 1000-C2, Trent 1000-CE2, Trent 1000-D2, Trent 1000-E2, Trent 1000-G2, Trent 1000-H2, Trent 1000- J2, Trent 1000-K2, and Trent 1000-L2 engines. AD 2021-26-13 required revision of the engine Time Limits Manual (TLM) life limits of certain critical rotating parts and direct accumulation counting (DAC) data files. Since the FAA issued AD 2021-26-13, RRD has revised the TLM with more restrictive airworthiness limitations, including updated life limits for certain critical parts and updated DAC data files. This AD was prompted by the manufacturer revising the engine TLM life limits of certain critical rotating parts, updating the DAC data files, and updating certain maintenance tasks. This AD requires revising the existing approved maintenance or inspection program, as applicable, to incorporate more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
79-16-06: 79-16-06 DETROIT DIESEL ALLISON: Amendment 39-3527 is further amended by Amendment 39- 3650. Applies to all Model 250-C28 and 250-C30 series engines equipped with generator idler gearshaft P/N 6898980, or 6898591, or 77 tooth spur idler gearshaft P/N 6898652 installed in, but not limited to Bell 206L-1 and Sikorsky S-76 rotorcraft certificated in all categories. Compliance required as indicated unless previously accomplished. To preclude engine power loss as a result of an accessory drive gearbox failure, remove the referenced gearshafts from service prior to reaching 9000 cycles if installed in a 250-C28 series engine and prior to reaching 2000 cycles if installed in a 250-C30 engine. For those gearshafts that are within 50 cycles of the appropriate limit on the effective date of this AD, compliance is required within 100 cycles. For the purpose of this AD, a cycle is defined as an attempted or completed start, or a motoring of the engine using the starter. The start counter is activated and accumulates the count of cycles only when the ignition circuit is energized. Therefore, cycles due to motoring with the starter (ignition circuit not energized) must be added to the cycle count. (Detroit Diesel Allison Commercial Engine Bulletins CEB 72-2003 for the 250-C28B and CEB 72-3003 for the 250-C30 also pertain to this subject.) Amendment 39-3527 became effective August 15, 1979. This amendment 39-3650 becomes effective January 11, 1980.
97-03-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that requires modification and sealing of the firezone compartment of the nacelle of the left and right engines. This amendment is prompted by reports indicating that firezone compartments have not been completely sealed. The actions specified by this AD are intended to prevent flame, fuel, and vapor from entering compartments behind the firezone compartment. This condition, if not corrected, and if combined with a fire source in the firezone compartment, could result in an uncontrollable fire outside the firezone compartment.
2005-02-01: The FAA is adopting a new airworthiness directive (AD) for certain The Lancair Company (Lancair) Models LC40-550FG and LC42-550FG airplanes. This AD requires you to incorporate additional takeoff chart distance values information into the Performance Section of the FAA- approved Airplane Flight Manual (AFM). This AD results from flight testing that revealed that the takeoff distance values for the affected airplanes could not be duplicated. We are issuing this AD to prevent potential impact with terrain or obstruction during takeoff due to incorrect takeoff distance values.
2023-12-23: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-300F airplanes. This AD was prompted by a report indicating that the installation requirements were not followed for the first observer seat in the flight deck. This AD requires installing placards in various locations of the flight deck to indicate the proper position for the first observer seat during taxi, takeoff, and landing, and revising the existing airplane flight manual (AFM). The FAA is issuing this AD to address the unsafe condition on these products.
62-18-01: 62-18-01 GENERAL DYNAMICS/CONVAIR: Amdt. 475 Part 507 Federal Register August 18, 1962. Applies to All Models 22, 22M, and 30 Series Aircraft. Compliance required within 150 hours' time in service following the effective date of this AD, unless already accomplished. To prevent loose rudder flight tab balance weights, the following shall be accomplished: Inspect the rudder flight tab balance weight attachments for looseness of the balance weight, missing weights, missing attachment nuts and/or bolts, and for elongation of the attachment bolt holes in the balance weights and attachment arms in accordance with General Dynamics/Convair Alert Service Bulletins A27-60, A27-31, or A27-32, as appropriate. If any of the noted defects are found, they shall be corrected prior to the next flight, as specified in General Dynamics/Convair Alert Service Bulletins A27-60, A27-31, or A27-32, as appropriate, or by an FAA engineering approved equivalent method. (General Dynamics/Convair Alert Service Bulletins A27-60, A27-31, and A27-32 for the Models 22, 22M, and 30 respectively cover this same subject.) This directive effective August 18, 1962.
2023-13-14: The FAA is superseding Airworthiness Directive (AD) 2023-01- 12, which applied to all Safran Helicopter Engines, S.A. (Safran) Model Arriel 1C, Arriel 1C1, and Arriel 1C2 engines. AD 2023-01-12 required replacing affected fire detectors and prohibited installation of affected fire detectors. Since the FAA issued AD 2023-01-12, the FAA has determined that Model Arriel 1K1 engines are also affected by the unsafe condition. This AD is prompted by reports of false engine fire warnings. This AD requires replacing the affected fire detectors, prohibits installation of affected fire detectors, and adds Model Arriel 1K1 engines to the applicability, as specified in an European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
2005-01-15: The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce plc (RR) RB211 Trent 875, 877, 884, 892, 892B, and 895 series turbofan engines with certain part number (P/N) low pressure compressor (LPC) fan blades installed. That AD currently requires initial and repetitive ultrasonic inspections of the fan blade dovetail roots. This AD requires the same actions except at reduced compliance times for certain blades, defines a specific terminating action to the repetitive blade inspection requirements, and adds the 884B series to the applicability. This AD results from a report of a cracked fan blade found before the blade reached the initial inspection threshold of AD 2002-11-08. This AD also results from the need to reduce a repetitive inspection compliance time due to potential breakdown of blade coating and lubrication on certain blades. We are issuing this AD to prevent multiple LPC fan blade failures due to cracks, which could result in uncontained enginefailure and possible damage to the airplane.
80-19-03: 80-19-03 PRATT & WHITNEY AIRCRAFT: Amendment 39-3911. Applies to all Pratt & Whitney Aircraft JT3D-1-MC7 turbofan engine models. Compliance required not later than December 31, 1980. To preclude high cycle fatigue cracking of fifth stage compressor disks which could result in disk fracture, retire from service all fifth stage compressor disks, P/N 426505, and replace with either disk P/N 697105 or P/N 749605. Upon submission of substantiating data, through an FAA Aviation Safety Inspector, the Chief, Engineering and Manufacturing Branch, New England Region, may adjust the compliance date. A historical file on this AD is maintained in full by the FAA at its headquarters in Washington, D.C., and at the New England Region. This amendment becomes effective October 7, 1980.