Results
2007-18-01: 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: During a BCM (back-up control module) retrofit campaign, one resistor manufactured by SRT (Siegert) was found with an abnormal resistance drift. * * * * * * * * When the aircraft is in control back-up configuration (considered to be an extremely remote case), an incorrect value on these resistors may cause degradation of the BCM piloting laws, potentially leading to erratic motion of the rudder and to possible impact on the Dutch Roll [uncommanded coupling of airplane roll and yaw motions]. * * * * * The unsafe condition is erratic motion of the rudder, which could result in reduced controllability of the airplane due to dutch roll characteristics. We are issuing this AD to require actions to correct the unsafe condition on these products.
2007-17-19: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-90-30 airplanes, that requires repetitive inspections and functional tests of the static port heater assemblies, and corrective actions if necessary. The actions specified by this AD are intended to prevent an electrical short of the static port heater from sparking and igniting the insulation blanket adjacent to the static port heater, which could result in smoke and/or fire in the cabin area. This action is intended to address the identified unsafe condition.
2018-09-03: We are superseding Airworthiness Directive (AD) 2009-11-08, which applied to certain Airbus Model A330-202, -223, -243, -301, -322, and -342 airplanes. AD 2009-11-08 required repetitive special detailed (high frequency eddy current) inspections to detect cracking of the keel beam fitting horizontal flange edge at a certain frame (FR) on the left- and right-hand sides of the fuselage, and repair if necessary. This AD was prompted by a new fatigue and damage tolerance evaluation that concluded the current inspection thresholds and intervals had to be modified. This AD requires contacting the FAA to obtain instructions for addressing the unsafe condition on these products, and doing the actions specified in those instructions. We are issuing this AD to address the unsafe condition on these products.
80-26-04 R1: 80-26-04 R1 PIPER: Amendment 39-3992 as amended by Amendment 39-4198. Applies to models: PA-23, PA-23-160, Serial Nos. 23-1 thru 23-2046; PA-23-235, Serial Nos. 27-505 thru 27-622; PA-23-250, Serial Nos. 27-1 thru 27-504; PA-23-250 (6 Place), Serial Nos. 27-2000 thru 27-8054049 certificated in all categories. To detect cracks and prevent possible misalignment of the rudder cable-pulley at the fuselage crossmember which supports the cabin entrance step, accomplish the following: a. For airplanes with 500 or more hours in service on the effective date of this AD, within the next 100 hours in service, inspect the cabin entrance step supporting frame structure for cracks, repair as necessary in accordance with paragraph (c), and unless already accomplished incorporate additional bracketry for the footstep attachment at the rudder pulley in accordance with paragraph (c). b. For airplanes with less than 500 hours in service on the effective date of this AD, before the accumulation of 600 hours in service, inspect the cabin entrance step supporting frame structure for cracks, repair as necessary in accordance with paragraph (c), and unless already accomplished, incorporate additional bracketry for the footstep attachment at the rudder pulley in accordance with paragraph (c). c. Accomplish steps 1 through 5 under the "Inspection and Repair Instructions" Section and steps 1 through 9 under "Footstep Reinforcement Brackets Installation Instructions" in Piper Service Bulletin No. 672 dated June 20, 1980, or equivalent. d. Equivalent inspections and alterations must be approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. e. Upon submittal of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the compliance times specified in this AD. NOTE: Since the cabin step is part of the approved type design, it must be in place. This includes those cases where temporary permission was granted for its removal. Amendment 39-3992 was effective December 19, 1980. This amendment 39-4198 is effective August 28, 1981.
2007-17-20: We are adopting a new 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: To prevent cracks developing in the aileron spar adjacent to the inboard hinge attachment * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2001-06-15: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-600, -700, -700C, and -800 series airplanes, that requires inspections of the fasteners in the elevator balance panel assemblies to detect various discrepancies; and corrective actions, if necessary. This amendment is prompted by a report that an elevator balance panel was found disconnected from the horizontal stabilizer due to the improper installation of fasteners during production. The actions specified by this AD are intended to prevent jamming, restricting, or binding of the elevator control surfaces due to loose or missing fasteners, which could make the movement of the elevator difficult and decrease aerodynamic control of the airplane.
2018-09-02: We are superseding Airworthiness Directive (AD) 99-23-16, which applied to certain Airbus Model A330 and A340 series airplanes. AD 99-23-16 required repetitive detailed visual inspections to detect cracking of the vertical flange of the inboard Z-stiffeners of the centerline panel of the fuselage belly fairing; and corrective actions, if necessary. This AD was prompted by a new fatigue and damage tolerance evaluation that concluded that the current inspection thresholds and intervals had to be more restrictive. This AD requires contacting the FAA to obtain instructions for addressing the unsafe condition on these products, and doing the actions specified in those instructions. We are issuing this AD to address the unsafe condition on these products.
81-10-04: 81-10-04 PIPER AIRCRAFT CORPORATION: Amendment 39-4094. Applies to Model PA-44-180 (Seminole), serial numbers 44-7995001 through 44-8095006, airplanes certificated in all categories. Compliance is required within the next 50 hours time in service after the effective date of the AD, unless already accomplished. To reduce aileron spar deflection and cracking which could result in loss of aileron control, accomplish the following: a. Modify the ailerons in accordance with Piper Aircraft Corporation Service Bulletin No. 702, dated December 4, 1980, and Piper Rework Kit P/N 764 088V. b. Make appropriate maintenance record entry. An equivalent method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. This amendment becomes effective April 30, 1981.
80-25-05: 80-25-05 PIPER: Amendment 39-4041. Applies to Piper PA-31T S/N 8120001 thru 8120010 and Piper PA-31T1 airplanes S/N 8104001 thru 8104012. Compliance required as indicated: To prevent failure of the voltage regulator which can result in complete electrical failure, prior to further flight either at night or into instrument weather conditions, alter the voltage regulator, Piper P/N 584152 in accordance with Piper telegraphic letter #31-26, dated November 26, 1980, or an approved equivalent. Equivalent alterations must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, Jamaica, New York. This amendment is effective February 12, 1981, and was effective upon receipt for all recipients of the letter of November 26, 1980, covering this same subject.
2007-17-17: The FAA is adopting a new airworthiness directive (AD) for certain Learjet Model 31, 31A, 35, 35A (C-21A), 36, 36A, 55, 55B, and 55C airplanes, and Model 45 airplanes. This AD requires inspecting for unsealed gaps on the pylon side of the engine firewall and cleaning/ sealing any unsealed gap; and, for certain airplanes, inspecting for unsealed gaps of the pylon trailing edge and cleaning/sealing any gap. This AD results from a report that unsealed gaps (penetration points) of the engine firewall were discovered during production. We are issuing this AD to prevent penetration of flammable liquids or fire through the engine firewall into the engine pylon, which could lead to fire inside the airplane.