Results
2020-03-14: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by reports of loss of retention of the regulator inlet filter retainer on certain crew oxygen cylinder assemblies. This AD requires an inspection of the crew oxygen cylinder assembly for any discrepancy and replacement of an affected crew oxygen cylinder assembly 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.
83-07-08: 83-07-08 SHORT BROTHERS AND HARLAND, LTD.: Amendment 39-4606. Applies to Model SC-7, Series 3 (all serial numbers) airplanes certificated in any category. Compliance: Required as indicated, unless already accomplished. To preclude malfunction of the ground/air lever mechanism which may prevent the power lever from entering the Beta mode, within the next 100 hours time-in-service after the effective date of this AD, accomplish the following: (a) Modify the ground/air lever P/N SC-7-47-5254 in the engine control system in accordance with Shorts Service Bulletin No. 76-58, Revision 1, dated December 4, 1980. (b) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. (c) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. This amendment supersedes AD 80-09-01, Amendment 39-3754. This amendment becomes effective on April 11, 1983.
2008-17-11: 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: It has been found that some "caution'' messages issued by the Flight Guidance Control System (FGCS) are not displayed on aircraft equipped with [certain] EPIC software load[s] * * *. Therefore, following a possible failure on one FGCS channel during a given flight, such a failure condition will remain undetected * * *. If another failure occurs on the second FGCS channel, the result may be a hardover command by the autopilot. An unexpected hardover command may cause a sudden roll, pitch, or yaw movement, which could result in reduced controllability of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
2008-03-08: 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: Subsequent to accidents involving Fuel Tank System explosions in flight * * * and on ground, the FAA has published Special Federal Aviation Regulation 88 (SFAR88) * * * [which] required * * * [conducting] a design review against explosion risks. The unsafe condition is the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
2020-02-19: The FAA is superseding Airworthiness Directive (AD) 2003-09-04 R1, which applied to certain Bombardier, Inc., Model CL-600-2B19 (Regional Jet series 100 & 440) airplanes. AD 2003-09-04 R1 required revising the airworthiness limitations for certain structural inspections; repair if necessary; and submission of inspection findings to the airplane manufacturer. This AD revises the applicability to include additional airplanes; revises certain compliance times; and requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a report of fatigue cracks occurring on the pressure floor skin at fuselage stations (FS) 460 and 513. The FAA is issuing this AD to address the unsafe condition on these products.
77-13-21: 77-13-21 PIPER AIRCRAFT CORPORATION: Amendment 39-2946 as amended by Amendment 39-3093. Applies to airplane models PA-24, PA-24-250, and PA-24-260; model PA- 24-400, except S/N 1; and models PA-30 and PA-39, certificated in all categories. For aircraft having 1000 hours or more in service on the effective date of this AD, compliance is required within the next 100 hours in service, and for aircraft having less than 1000 hours in service, compliance is required prior to 1100 hours in service, unless already accomplished in either case. To prevent collapse of the landing gear after manual extension; (a) Accomplish the inspection described on page 3 of Piper Aircraft Corporation Service Letter No. 782A, dated March 21, 1977, and replace components exceeding the specified wear limits, or an equivalent inspection and replacement procedure approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (b) Inspect the main landing gear bungee cords for frayed protective covering, breaks, soft areas, and replace cords exhibiting these conditions. In addition, replace cords every 500 hours in service, or every three years, whichever occurs first. (c) Repeat paragraph (a) at each 1000 hours in service after the prior inspection, and repeat paragraph (b) at each 500 hours in service after the prior inspection, or within one year after the prior inspection, whichever occurs first. (d) Airplanes may be flown in accordance with FAR 21.197 to a base where repairs can be performed. The Chief, Engineering and Manufacturing Branch may adjust the inspection interval upon submission of substantiating data submitted through an FAA maintenance inspector. Amendment 39-2946 became effective July 6, 1977. This amendment 39-3093 is effective December 16, 1977.
2008-03-11: We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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 distortion of the rudder bars due to rudder control forces during aerobatic operation and nose wheel steering reaction forces. Rudder bar distortion could result in reduced control or loss of control. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
61-19-03: 61-19-03 LOCKHEED: Amdt. 338 Part 507 Federal Register September 20, 1961. Applies to All 049, 149, 649, 749, and 1049 Series Aircraft. Compliance required as indicated. As a result of findings during investigation of a recent Lockheed Model 049 aircraft fatal accident, it is necessary to require the following corrective action. Unless already accomplished within the last 50 hours' time in service, the following special inspection is required at the first layover or stop where qualified maintenance personnel and facilities are available and the inspection can be conducted without undue delay but not to exceed the next 25 hours' time in service after the effective date of this AD. Inspect to ensure that the 5 bolts, nuts, and cotter pins in the parallelogram linkage between the elevator boost valve and boost mechanism are properly secured and safetied. This directive effective September 20, 1961, for all persons except those to whom it was made effective immediately by telegram dated September 8, 1961.
2020-03-13: The FAA is adopting a new airworthiness directive (AD) for Leonardo S.p.A. Model AW189 helicopters. This AD requires inspecting the hydraulic fluid level on each tail rotor (T/R) damper and depending on the inspection results, removing the T/R damper from service and reporting information or repetitively inspecting the T/R damper. This AD is prompted by reports of major leakage of hydraulic fluid in T/R dampers. This condition could result in degradation of T/R damper performance; multiple leaking T/R dampers could result in T/R damage and subsequent loss control of the helicopter. The actions of this AD are intended to address an unsafe condition on these products.
77-19-06: 77-19-06 PIPER: Amendment 39-3041. Applies to Models PA-31, PA-31-300 and PA- 31-325 Serial Numbers 31-2 to 31-7712051 inclusive, and PA-31-350 Serial Numbers 31-5001 to 31-7752092 inclusive, certificated in all categories. To prevent possible hazards in flight associated with a damaged aileron cable, accomplish the following: (a) Within 50 hours in service from the effective date of this AD, unless previously accomplished, inspect the aileron balance and interconnect cables and the flap solenoid for evidence of damage due to electrical arcing between the flap solenoid and the cables. If damage is found, repairs must be effected prior to further flight except that the aircraft may be flown in accordance with FAR 21.197 to a base where a repair can be made. (b) Within 100 hours in service from the effective date of this AD, unless previously accomplished, inspect and repair if necessary the aileron balance and interconnect cables and alter the flap solenoid installation in accordance with the "Instructions" section of Piper Service Bulletin No. 567 dated June 7, 1977, or equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (c) If the wing flap motor circuit breaker activates after the effective date of this AD, then within the next 10 hours in service, comply with the inspection and repair requirements of paragraph (a). (d) Upon compliance with paragraph b., the inspections requirements of this AD may be dispensed with. (e) Upon request, with substantiating data submitted through an FAA Maintenance Inspector, the compliance time specified in this AD may be adjusted by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment is effective September 27, 1977.