Results
2003-04-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-200B and -200F series airplanes powered by Pratt & Whitney JT9D-70 series engines, that requires repetitive detailed inspections of the pylon skin and internal structure of the nacelle struts adjacent to and aft of the precooler exhaust vent for heat damage (discoloration), wrinkling, and cracking; and corrective action, if necessary. The actions specified by this AD are intended to find and fix such damage, which could result in cracking or fracture of the nacelle struts, and consequent reduced structural integrity and possible separation of the strut and engine from the airplane. This action is intended to address the identified unsafe condition.
2003-04-19: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 0070 and 0100 series airplanes, that requires a one-time general visual inspection to detect any missing attachment bolts in the replaceable frame struts, and corrective actions, if necessary. This action is necessary to prevent excessive deformation of the floor structure in the event of rapid decompression in the lower cargo hold due to missing attachment bolts in the replaceable frame struts. Such deformation may result in the flight and engine control cables becoming jammed, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2003-04-21: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 440) series airplanes, that requires replacement of the overwing emergency exit placards, door weight placards, and no baggage placards with new placards. This action is necessary to prevent the inability of a passenger to open and dispose of the overwing emergency exit door during an emergency evacuation due to incorrect placards. This action is intended to address the identified unsafe condition.
54-05-02: 54-05-02 SENSENICH: Applies to All Model M76AM-2 Propellers Installed on Lycoming Models O-290-D and O-290-D2 Engines. Compliance required by March 15, 1954, and at intervals not to exceed each 25 hours operation thereafter. To eliminate the possibility of blade tip failures on Model M76AM-2 propellers installed on the above Lycoming engines, all nicks, gouges and scratches within 8 inches of the blade tip should be removed. Care should be taken to be sure all trace of the damage is removed. Minor damaged areas may be removed by using coarse emery cloth. The repaired area should then be polished with fine emery cloth. Rebalancing is not necessary when repairing minor damage areas as defined in Civil Aeronautics Manual 18 (18.30-15) (Sensenich Service Bulletin No. R-2 covers this same subject.)
2003-04-02: This amendment supersedes Airworthiness Directive (AD) 98-12-10 and AD 99-21-23, which currently apply to APEX Aircraft (APEX) Model CAP 10B airplanes. AD 98-12-10 requires installing an inspection opening in the wing, repetitively inspecting the upper and lower wing spars for structural cracking, and, if any cracks are found, repairing the cracks in accordance with a repair method. AD 99-21-23 requires restricting the entry speed for performing flick maneuvers to 97 knots, inserting a copy of the AD into the Limitations Section of the CAP 10B flight manual, and fabricating and installing a placard (in the cockpit of the airplane within the pilot's clear view) that indicates this limitation. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. This AD retains the wing modification and repair requirements from AD 98-12-10. This AD also incorporates new repetitive inspection procedures, further reduces the flick maneuver speed specified in AD 99-21-23, and temporarily reduces the load factor limits prior to the initial inspection. The actions specified by this AD are intended to provide the flight information necessary to the pilot so that excessive speed is not used during aerobatic maneuvers and to detect and correct structural cracks in the wing spar, which could result in the wing separating from the airplane. Such failure could lead to loss of control of the airplane.
2003-04-04: This amendment adopts a new airworthiness directive (AD) for Robinson Helicopter Company (RHC) Model R22 helicopters that requires inspecting the tail rotor pitch control assembly for roughness or binding of the pitch control bearings (bearings) by hand-rotating the pitch control bearing housing (housing). If the housing does not rotate freely, the AD requires replacing the unairworthy pitch control assembly with an airworthy unit. This amendment is prompted by reports of failure of the tail rotor pitch control assembly due to improperly lubricated bearings on the RHC Model R22 helicopters. The actions specified by this AD are intended to detect corrosion of the bearings and to prevent bearing failure and subsequent loss of directional control of the helicopter.
2003-03-23: This amendment adopts a new airworthiness directive (AD) that is applicable to certain EMBRAER Model EMB-135 and -145 series airplanes. This action requires replacement of the horizontal stabilizer control units (HSCUs) with new upgraded HSCUs, and corrective actions if necessary. This action is necessary to prevent reversal of the pilot's pitch trim command for the horizontal stabilizer, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
92-13-02: 92-13-02 AEROSPATIALE: Amendment 39-8272. Docket No. 92-NM-19-AD. Applicability: Aerospatiale Model SN 601 Corvette series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent structural failure of the fuselage and associated decompression of the passenger cabin, accomplish the following: (a) Prior to the accumulation of 18,200 landings, or within 100 landings after the effective date of this AD, whichever occurs later, inspect the skin panels between Frame FR17 and FR19, on the right side below stringer 11, to detect cracks, using an eddy current procedure, in accordance with Aerospatiale Corvette Service Bulletin 53-24, dated January 25, 1991. (b) If no cracks are found as a result of the inspection required by paragraph (a) of this AD, repeat the eddy current inspection thereafter at intervals not to exceed 7,300 landings. (c) If any crack is found as a result of any inspection required by this AD, prior to further flight, install Modification 1399, in accordance with Aerospatiale Corvette Service Bulletin 53-15, dated January 22, 1991. (d) Installation of Modification 1399, in accordance with Aerospatiale Corvette Service Bulletin 53-15, dated January 22, 1991, constitutes terminating action for the requirements of this AD. (e) An alternative method 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. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from Standardization Branch, ANM-113. (f) Special flight permits may beissued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (g) The inspections and modifications shall be done in accordance with Aerospatiale Corvette Service Bulletin 53-24, dated January 25, 1991; and Aerospatiale Corvette Service Bulletin 53-15, dated January 22, 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. (h) This amendment becomes effective on July 23, 1992.
2003-03-08: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, DC-9-20, DC-9- 30, DC-9-40, and DC-9-50 series airplanes, that requires a one-time inspection at a certain disconnect panel in the left forward cargo compartment to find contamination of electrical connectors and to determine if a dripshield is installed over the disconnect panel, and corrective actions if necessary. The actions specified by this AD are intended to find and fix contamination of certain electrical connectors and prevent future contamination of these connectors, which could cause electrical arcing that could result in a fire on the airplane. This action is intended to address the identified unsafe condition.
2003-03-04: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300 B2 and B4; A300 B4-600, B4-600R, and F4-600R (collectively called A300-600); A310; and certain Airbus Model A319; A320; A321; A330; and A340 series airplanes, that requires repetitive visual inspections of the striker and guide valve of the passenger door actuators and certain emergency door actuators for corrosion, and corrective action, if necessary. This AD also requires modification of the striker mechanism of the emergency and passenger door actuators, which terminates the repetitive inspections. 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 prevent corrosion of the emergency actuator mechanism, which could cause failure of the emergency actuator striker mechanism on the passenger or emergency doors, and lead to difficulty in opening the passenger or emergency doors during an emergency evacuation.