Results
99-12-05: This amendment adopts a new airworthiness directive (AD) that applies to certain The New Piper Aircraft, Inc. (Piper) Models PA-31, PA-31-300, PA-31-325, PA-31-350, and PA-31P-350 airplanes. This AD requires installing access holes for the inspection of the elevator spar; inspecting the elevator ice protection boots for looseness and reinstalling or replacing the elevator ice protection boots if looseness is found. This AD also requires repetitively inspecting the elevator spars for cracks, and replacing the elevators or elevator spar assemblies with parts of improved design either at a certain time period or when cracks are found, whichever occurs first. This AD is the result of reports of cracks developing in the elevator spar inboard of the outboard hinge location on the affected airplanes. The actions specified by this AD are intended to prevent failure of the elevator spar caused by fatigue cracking, which could result in reduced airplane controllability.
2012-18-10: We are adopting a new airworthiness directive (AD) for GA200 (Pty) Ltd Models GA200 and GA200C airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as failure of the strut bolt through the main spar. We are issuing this AD to require actions to address the unsafe condition on these products.
2012-18-01: We are adopting a new airworthiness directive (AD) for all M7 Aerospace LLC Models SA226-AT, SA226-T, SA226-T(B), SA226-TC, SA227-AC (C-26A), SA227-BC (C-26A), SA227-CC, SA227-DC (C-26B), SA227-AT, and SA227-TT airplanes. This AD requires repetitively inspecting the left and right forward (main) and aft spar wing-to-fuselage attach fittings for cracks and replacing any cracked fitting. This AD also requires reporting certain inspection results to the FAA. This AD was prompted by reports of fatigue cracking in the left and right forward (main) spar wing-to-fuselage attach fittings. We are issuing this AD to correct the unsafe condition on these products.
99-13-01: This amendment adopts a new airworthiness directive (AD) that is applicable to certain International Aero Engines AG (IAE) V2500-A1 and V2500-A5 series turbofan engines. This action requires determining the need for a special borescope inspection of the high pressure turbine (HPT) stage 1 inner rotating airseal (TOBI ID seal) for oil wetting after an in-flight shutdown (IFSD). It also requires, if necessary, the tear down and inspection of HPT hardware. This amendment is prompted by reports of overheat damage to the HPT hardware caused by ignition of oil that leaked into the HPT from the No. 4 bearing compartment during an IFSD. The actions specified in this AD are intended to prevent failure of the HPT hardware due to ignition of oil trapped by the HPT TOBI ID seal, which could result in an uncontained engine failure and damage to the airplane.
99-12-07: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Model 1900D airplanes. This AD requires replacing the passenger oxygen container and mask assembly with an improved design passenger oxygen container and mask assembly. This AD is the result of an incident where a passenger had put on the oxygen mask and the lanyard pin did not automatically pull and initiate oxygen flow during a loss of airplane pressurization while in-flight. The actions specified by this AD are intended to prevent the above situation from occurring on other airplanes, which could result in passenger injury if the lanyard pin is not manually pulled in a timely manner.
2012-18-03: We are adopting a new airworthiness directive (AD) for certain Pratt & Whitney Division PW4000-94'' and PW4000-100'' turbofan engines having a 1st stage high-pressure turbine (HPT) seal support, part number (P/N) 55K601 (contained within assembly P/N 55K602-01) or P/N 50K532 (contained within assembly P/N 50K530-01), installed. This AD was prompted by 58 reports of cracked 1st stage HPT air seal rings, including 15 in-flight engine shutdowns. This AD requires removal and replacement of the 1st stage HPT seal support and inspection of the 1st stage HPT air seal ring. We are issuing this AD to prevent failure of the 1st stage HPT air seal ring, which could lead to an internal oil fire, uncontained engine failure, and damage to the airplane.
58-13-02: 58-13-02 BEECH: Applies to Models B50, C50, D50, E50 and F50. Compliance required as soon as possible but not later than November 15, 1958. The AN 3158 tail light assembly does not meet the requirements of the Civil Air Regulations for intensity and light pattern. It must be replaced by an assembly meeting those requirements. Beech Kit 50-169 provides an acceptable assembly. (Beech Service Bulletin 33, 24, 17, 9 and 2 for B50, C50, D50, E50 and F50, issued April 1958, covers this same subject.)
2009-04-16: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747-100, 747-100B, 747- 200B, 747-200C, 747-200F, 747-300, 747SR, and 747SP series airplanes. That AD currently requires an inspection to determine if acceptable external skin doublers are installed at the stringer 6 (S-6) lap splices, between station (STA) 340 and STA 400. For airplanes without the acceptable external skin doublers, the existing AD also requires repetitive related investigative actions and corrective actions if necessary. The existing AD also provides an optional terminating modification for the repetitive related investigative actions. This new AD mandates the optional terminating modification. This AD results from a report of cracked fastener holes at the right S-6 lap splice between STA 340 and STA 380. We are issuing this AD to prevent cracking in the fuselage skin, which could result in rapid decompression and loss of structural integrity of the airplane.
2012-17-11: We are adopting a new airworthiness directive (AD) for all BAE SYSTEMS (Operations) Limited Model 4101 airplanes. This AD was prompted by reports that the fire extinguisher in the toilet vanity unit needs to be mounted vertically rather than horizontally. This AD requires inspecting to determine if a certain fire extinguisher bottle is installed, and repositioning the affected fire extinguisher bottle to the vertical position. We are issuing this AD to detect and correct the orientation of the fire extinguisher bottle in the toilet vanity unit to the vertical position, which if not corrected, could result in a toilet waste bin fire spreading, and consequent damage to the airplane and injury to its occupants.
74-04-04: 74-04-04 CANADAIR: Amendment 39-1787. Applies to all CL-44D4 and CL-44J airplanes which have experienced more than 7,000 landings. To detect cracks in the lugs of the rear spar attachment lower fitting, P/N 44-10149, of the main landing gear actuator, accomplish the following: 1. Within the next 100 landings after the effective date of this AD, unless accomplished within the last 900 landings, and at intervals thereafter not to exceed 1,000 landings, inspect the lower lugs of the main landing gear actuator rear spar attachment fitting, P/N 44-10149, for cracks using a dye penetrant method with a glass of at least 10-power or an approved equivalent inspection. 2. If cracks are found, reduce the inspection intervals as noted in the instructions of paragraphs i, ii, iii of the Inspection Data of Canadair Service Information Circular No. 371-CL- 44. 3. The compliance times may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, upon receipt of substantiating data, submitted through an FAA maintenance inspector. 4. Equivalent inspections and parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. 5. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552 (a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Canadair Limited, Attention: Mr. C. Bloom, P.O. Box 6078, Montreal, Canada. These documents may also be examined at the Engineering and Manufacturing Branch, FAA, Eastern Region, J.F.K. International Airport, Jamaica, New York 11430, and at FAA headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C. and at the Eastern Region. This amendment is effective February 18, 1974.