Results
2018-15-06: We are adopting a new airworthiness directive (AD) for certain Honda Aircraft Company LLC Model HA-420 airplanes. This AD requires incorporating new and revised airworthiness limitations into the airplane's maintenance program. This AD was prompted by a report that several maintenance tasks were omitted from the airworthiness limitations section of the Honda Aircraft Company, Inc. Model HA-420 Airworthiness Limitation and Inspection Manual (ALIM). We are issuing this AD to address the unsafe condition on these products.
86-15-10 R2: This amendment revises an existing airworthiness directive (AD), applicable to Eurocopter France Model AS-350B, BA, B1, B2, C, D, and D1, and AS-355E, F, F1, F2 and N helicopters, that currently requires repetitive inspections of the main rotor head components, the main gearbox (MGB) suspension bars, and the ground resonance prevention system components at intervals not to exceed 400 hours time-in-service (TIS). This amendment requires the same inspections, but at intervals not to exceed 500 hours TIS. This amendment is prompted by reports of confusion and unnecessary costs associated with the difference in the current 400 hours TIS inspection interval and the current manufacturer's master service recommendation of 500 hours TIS inspection interval. The actions specified by this AD are intended to eliminate confusion and unnecessary costs and to prevent ground resonance due to reduced structural stiffness, which could lead to failure of a main rotor head or MGB suspensioncomponent and subsequent loss of control of the helicopter.
2000-07-26: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 series airplanes, that requires a one-time detailed visual inspection to detect corrosion on the outer surface of the fuselage skin panel; application of corrosion preventive protection; and corrective action, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct corrosion of the fuselage skin panel, which could result in cracking and consequent reduced structural integrity of the airplane.
2006-16-08: The FAA is adopting a new airworthiness directive (AD) for certain Aerospatiale Model ATR42 and ATR72 airplanes. This AD requires an inspection of the locking bolt of the upper attachment pin of the shock absorber on both main landing gears (MLGs) for the correct installation of the locking bolt and for any missing locking bolt, washer, nut, cotter pin, or compound, and applicable corrective action if necessary. This AD results from a report of migration and subsequent rupture of the attachment pin of the shock absorber of a MLG. We are issuing this AD to prevent failure of a MLG, which could result in significant structural damage to the airplane and possible injury to the occupants.
55-05-01: 55-05-01 BELL: Applies to All Models 47B, 47B3, 47D, 47D1, 47G Helicopters. Compliance required at the expiration of 50 flying hours total time. Twenty-five additional flying hours may be acceptable provided the inspection called for in Bell's Mandatory Service Bulletin No. 97, Revision A, is complied with. In order to prevent seizing, binding or brinelling of pitch control link bearings in the tail rotor pitch control links, P/N 47-641-032-1, it is necessary that these links be replaced with a newly designed tail rotor control link, P/N 47-641-070-1. This new control link incorporates a spherical type bearing in place of the self-aligning ball type bearing. (Bell Mandatory Service Bulletin No. 97, Revision "A" dated December 3, 1954, covers this same subject and outlines the details for the installation.)
2018-16-05: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 757 airplanes. This AD was prompted by reports of bolt rotation in the engine drag fitting joint and fasteners heads; an inspection of the fastener holes revealed that cracks were found in the skin on two airplanes. This AD requires repetitive inspections for skin cracking and shim migration at the upper link drag fittings, diagonal brace cracking, and fastener looseness; and applicable on- condition actions. We are issuing this AD to address the unsafe condition on these products.
2000-07-14: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires a one-time detailed visual inspection of a certain passenger seat wire assembly to detect chafed or damaged wires; repair, if necessary; and installation of protective sleeving. This amendment is prompted by a report of arcing emanating from a certain passenger seat wire assembly. The actions specified by this AD are intended to prevent chafing of the passenger seat wire assembly against a bracket at the lower sidewall panel due to insufficient clearance between the bracket and seat wire assembly, which could result in arcing damage to the passenger seat wire assembly and consequent smoke and fire in the main cabin.
69-20-01: 69-20-01 PILATUS AIRCRAFT WORKS, INC: Amdt. 39-853. Applies to Model PC- 6 Series Aircraft Serial Numbers 1 through 723 and 2001 through 2050. Compliance required as indicated unless already accomplished. To prevent the rudder trim control cable from coming off the pulleys aft of bulkhead 6 (rear cabin wall), accomplish the following: (a) Within the next 100 hours' time in service, inspect the clearance between the cable keeper and the cable pulleys aft of bulkhead 6 in accordance with Pilatus Service Bulletin No. 92, dated March 1969, or later Swiss Federal Air office approved revision or an FAA approved equivalent. (b) If the clearance between the keeper and the cable pulleys is found to be greater than .040 inch, replace the old cable keeper, P/N 6201.16, with a redesigned cable keeper, P/N 916.96.06.244 in accordance with Pilatus Service Bulletin No. 92, dated March 1969, or later Swiss Federal Air Office approved revision or an FAA approved equivalent. This amendment becomes effective October 27, 1969.
2006-16-02: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9- 83 (MD-83), DC-9-87 (MD-87), and MD-88 airplanes. This AD requires installing a clamp, a bonding jumper assembly, and attaching hardware to the refueling manifold in the right wing refueling station area. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent arcing on the in-tank side of the fueling valve during a lightning strike, which could result in an ignition source that could ignite fuel vapor and cause a fuel tank explosion.
2018-16-09: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by report indicating that cracks were found on the fuselage frame webs at stations forward and aft of the overwing emergency exits between stringer-7 (S-7) and S-8. This AD requires repetitive high frequency eddy current (HFEC) inspections for cracking of the fuselage frame webs at certain stations between S-7 and S-8 and applicable on-condition actions. We are issuing this AD to address the unsafe condition on these products.