Results
2021-01-03: The FAA is adopting a new airworthiness directive (AD) for certain International Aero Engines AG (IAE) V2500-A1, V2522-A5, V2524- A5, V2525-D5, V2527-A5, V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, V2531-E5, and V2533-A5 model turbofan engines. This AD was prompted by a root cause analysis of an event involving an uncontained failure of a high-pressure turbine (HPT) 1st-stage disk that resulted in high-energy debris penetrating the engine cowling. This AD requires removing certain HPT 1st-stage and HPT 2nd-stage disks from service. The FAA is issuing this AD to address the unsafe condition on these products.
2004-01-04: This amendment supersedes an existing airworthiness directive (AD), applicable to certain EMBRAER Model EMB-120 series airplanes, that currently requires revising the airplane flight manual (AFM), and either installing hydraulic tube assemblies incorporating a check valve, or visually inspecting the check valve if already installed and performing corrective actions if necessary. This action adds airplanes to the applicability of the existing AD. The actions specified by this AD are intended to prevent the landing gear doors from becoming blocked from opening during application of emergency procedures in the event of a loss of hydraulics. This action is intended to address the identified unsafe condition.
55-15-01: 55-15-01 BOEING: Applies to All Boeing 377 Series Aircraft with Hamilton Standard Propellers. Compliance required by first scheduled engine change after November 1, 1955, but not later than November 1, 1956. To increase the fire resistance integrity of the propeller feathering system against damage by a powerplant fire, all flexible hose components of propeller feathering lines forward of the firewall in zone 2 must be replaced with lines and fittings which will meet current fire resistance requirements. The following hose assemblies are considered acceptable for this applications: (a) Aeroquip 680-10S hose assemblies with Aeroquip 304 protective sleeves over end fittings (Aeroquip assembly P/N 304000). (b) Resistoflex SSFR-3800-10 hose assemblies. (c) Aeroquip 309009-10S hose assemblies.
2010-04-01: 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: A quality control performed during completion of one Falcon 900EX aeroplane has shown that the crew and passenger Right-Hand (RH) oxygen lines may both interfere with the frame 8 of the aeroplane structure. A subsequent design review of the oxygen lines routing has confirmed that, on certain aeroplanes, equipped in RH mid-cabin with a 115 cu-ft oxygen cylinder, the installation of the line support assembly at frame 8 needs to be accomplished with precaution; otherwise, the oxygen lines might interfere with the structure, and this condition could lead to an oxygen leak. * * * * * The unsafe condition is an oxygen leak, which would result in insufficient oxygen flow to passenger oxygen masks during a depressurization event. We are issuing this AD to require actions to correct the unsafe condition on these products.
2004-01-09: This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (ECF) model helicopters that requires revising the Limitations section of the Rotorcraft Flight Manual (RFM) to prohibit using the landing light except for landing and takeoff until the 40 amp 10P1 and 10P2 contactors are replaced with 50 amp circuit breakers. Also, this amendment requires upgrading the electrical master boxes. This amendment is prompted by three reports of complete loss of electrical power generating systems, except for the direct battery power, due to a combination of high outside temperature and long flight duration with the landing light on that causes the nontemperature compensated trip switches to prematurely trip. The actions specified by this AD are intended to prevent failure of the helicopter power generator systems, loss of the use of flight instruments, and subsequent loss of control of the helicopter.
95-16-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 SP, SR, -100, -200, and -300 series airplanes, that requires repetitive operational tests of the reversible gearbox pneumatic drive unit (PDU) or the reversing air motor PDU to ensure that the unit can restrain the thrust reverser sleeve, and correction of any discrepancy found. This amendment is prompted by the results of an investigation, which revealed that, in the event of thrust reverser deployment during high-speed climb or during cruise, these airplanes could experience control problems. The actions specified by this AD are intended to ensure the integrity of the fail safe features of the thrust reverser system by preventing possible failure modes in the thrust reverser control system that can result in inadvertent deployment of a thrust reverser during flight.
91-06-16: 91-06-16 BRITISH AEROSPACE: Amendment 39-6935. Docket No. 90-NM-257-AD. Applicability: Model BAC 1-11 200 and 400 series airplanes, as listed in British Aerospace Service Bulletin 52-PM-5970, dated August 16, 1990, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent reduced structural integrity of the rear pressure bulkhead door, accomplish the following: A. Prior to the accumulation of 55,000 landings or within 15 months after the effective date of this AD, whichever occurs later, install horizontal members, various angle bracket assemblies, throat strips, cleats, furnishing bracket assemblies, furnishing angles, stiffeners, and a detachable door panel, in accordance with British Aerospace Service Bulletin 52-PM-5970, dated August 16, 1990. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041-0414. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6935, AD 91-06-16) becomes effective on April 18, 1991.
2020-26-18: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A330-243, -343, and -941 airplanes. This AD was prompted by a report that during an inspection of the wing/fuselage fillet interface, evidence of black stains and white oxidation was found on several areas of the fillet fairing adjustable rods due to surface corrosion. This AD requires replacing each affected fillet fairing adjustable rod with a serviceable part, 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.
2004-01-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 series airplanes (Regional Jet Series 100 & 440), that requires a one-time inspection of the dust covers for the flight data recorder (FDR) and cockpit voice recorder (CVR) equipment for the presence of markings that indicate the presence of a chemical-resistant coating, and corrective actions if necessary. The actions specified by this AD are intended to prevent peeling of the paint and markings from the dust covers for FDR and CVR equipment due to hydraulic mist from the actuators, which could result in the inability to identify FDR and CVR equipment in the event of an accident-recovery mission. The lack of data from FDR and CVR equipment could hamper discovery of the unsafe condition that caused an accident or an incident and prevent the FAA from developing and mandating actions to prevent additional accidents or incidents caused by that same unsafe condition. This action is intended to address the identified unsafe condition.
78-12-04: 78-12-04 PRATT & WHITNEY AIRCRAFT: Amendment 39-3234. Applies to all Pratt & Whitney Aircraft of Canada, Limited PT6A-38 engines prior to Serial Number PCE-79179, PT6A-41 engines prior to Serial Number PCE-80718, PT6A-45A engines prior to Serial Number PCE-84108 and Pratt & Whitney Aircraft PT6A-38 engines prior to Serial Number P-79179 with Part Number 3019268 or 3027054 No. 2 bearing pressure oil transfer tube assemblies. Compliance required within the next 50 hours in service, after the effective date of this AD, unless already accomplished. To preclude oil leakage from the No. 2 bearing pressure oil transfer tube assembly replace the Part Number 3019268 and 3027054 tube assemblies with Part Number 3030150 tube assembly in accordance with Paragraph 2, accomplishment instructions in Pratt & Whitney Aircraft of Canada, Limited Service Bulletin No. 3099 or approved equivalent parts. Aircraft may be flown to a base for performance of maintenance required by this ADper FAR 21.197 or FAR 21.199. All equivalent parts must be approved by the Chief, Engineering and Manufacturing Branch of the Eastern Region of the FAA. This amendment is effective June 19, 1978.