Results
2015-08-02: We are superseding Airworthiness Directive (AD) 2015-02-04 for certain Dassault Aviation Model MYSTERE-FALCON 50 airplanes. AD 2015- 02-04 required installing two protective plates between the electrical wiring under the glare shield and the engine fire pull handles. This new AD continues to require installing two protective plates between the electrical wiring under the glare shield and the engine fire pull handles. This AD was prompted by our determination that the published version of AD 2015-02-04 incorrectly identified the AD number as ``AD 2014-02-04'' in a certain paragraph. We are issuing this AD to prevent chafing of the electrical wiring, which could result in a short circuit and generation of smoke in the cockpit, potential loss of several functions essential for safe flight, and consequent reduced controllability of the airplane.
74-13-06: 74-13-06 McCAULEY: Amendment 39-1878. Applies to main wheel assemblies P/N's D-30063-1, -2, and -4, S/N's 720000 thru 739999 typically used on, but not limited to, Cessna Aircraft Models 180J, A185F, U206F, TU206F, 210L and T210L. Compliance required as indicated unless already accomplished. To prevent possible wheel failures due to breakage of the wheel flange attaching bolts, accomplish the following: (a) For main wheel assemblies used on the Cessna Aircraft Models 180J, A185F, U206F, TU206F, 210L, and T210L manufactured in the Model Year 1974 and any other aircraft with these main wheel assemblies installed, within the next 25 hours' time in service, modify main wheel assemblies in accordance with the instructions contained in McCauley Industrial Corporation Service Bulletin WB-1-A dated June 10, 1974, or subsequent Federal Aviation Administration approved revisions. Equivalent methods of compliance with this Airworthiness Directive must be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration Great Lakes Region, Des Plaines, Illinois. (b) For main wheel assemblies used on Cessna Aircraft Models 180J and A185F, manufactured in the Model Year 1973; within 25 hours' time in service after the effective date of this Airworthiness Directive and thereafter, at intervals not to exceed 25 hours' time in service visually inspect the 1/4" bolts attaching the wheel flanges for broken bolts until compliance with the modification in Paragraph (a) above is accomplished. If indications of broken bolts exist modify wheels in accordance with Paragraph (a). (c) Upon completion of the modification in Paragraph (a), record compliance with this particular part of the Airworthiness Directive in the aircraft logbook. NOTE: Cessna Service Letter SE 74-8 or subsequent revisions pertains to the same subject. The McCauley wheels may additionally be marked with Cessna P/N's C163002-0102, -0103 or -0104. Thisamendment becomes effective June 24, 1974.
2015-07-06: We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4- 605R, F4-622R, and C4-605R Variant F airplanes; and Model A310-203, - 204, -221, -222, -304, -322, -324, and -325 airplanes. This AD was prompted by a report of inner skin disbonding damage on a rudder. This AD requires repetitive ultrasonic inspections for disbonding of certain rudders; an elasticity of laminate [[Page 19010]] checker inspection; a woodpecker or tap test inspection; venting the core, if necessary; and repairing, if necessary. We are issuing this AD to detect and correct rudder disbonding, which could affect the structural integrity of the rudder.
2015-06-08: We are superseding Airworthiness Directive (AD) 2011-09-03 for all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes. AD 2011-09-03 required repetitive eddy current inspections to detect cracks in the center wing upper and lower rainbow fittings, and corrective actions if necessary; and repetitive replacement of rainbow fittings, which would extend the repetitive interval for the next inspection. This new AD requires reduced intervals for inspections of the upper rainbow fittings. This AD was prompted by analysis of in-service cracking, which has shown that a reduction in the inspection intervals is necessary for the upper rainbow fittings. We are issuing this AD to detect and correct fatigue cracking of the upper and lower rainbow fittings on the center wings, which could grow large and lead to the failure of the fitting and a catastrophic failure of the center wing.
75-20-08: 75-20-08 BEECH: Amendment 39-2374. Applies to Model B24R (Serial Numbers MC-151 thru MC-302, MC-304, MC-307, MC-309, MC-310, MC-312 thru MC-315, MC-317, MC-324, MC-328, MC-333, MC-336, MC-344, MC-345, MC-347 thru MC-357, MC-359 and MC-361 thru MC-364) airplanes. Compliance: Required as indicated, unless already accomplished. To preclude the possibility of propeller governor failure, accomplish the following: 1) Unless previously accomplished, prior to further flight, drain the Rust Ban Preservative Oil installed by the airplane manufacturer and refill with SAE 30 or SAE 50 straight mineral oil or the type and grade of oil recommended by the engine manufacturer. 2) If the airplane has less than 25 hours' total time in service, prior to further flight, remove the propeller governor and replace with a new or serviceable P/N A210490 propeller governor. 3) Aircraft may be flown to a place where the AD can be accomplished in accordance with FAR 21.197 providing the propeller governor is found to govern engine RPM properly during pre-flight runup. Beechcraft Service Instruction No. 0765-254 pertains to this subject. This amendment becomes effective October 3, 1975, to all persons except those to whom it was made effective earlier by air mail letter issued September 15, 1975.
2015-06-07: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-100, 737-200, 737-200C, 737-300, 737-400, and 737-500 series airplanes. This AD was prompted by reports of cracking in the lower corners of the forward entry doorway and the upper corners of the airstairs cutout. This AD requires inspections for cracking of the forward entry doorway and airstairs cutout, and corrective actions if necessary. This AD also provides terminating action for the repetitive inspections. We are issuing this AD to detect and correct cracks in the lower corners of the forward entry door cutout and the upper corners of the airstairs cutout, which could progress and result in an inability to maintain cabin pressurization.
2015-06-05: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 and A310 series airplanes, and certain Model A300 B4- 600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). This AD was prompted by a review of certain repairs, which revealed that the structural integrity of the airplane could be negatively affected if those repairs are not re-worked. This AD requires an inspection to identify certain repairs, and corrective action if necessary. We are issuing this AD to detect and correct certain repairs on the floor cross beams flange. If those repairs are not reworked, the structural integrity of the airplane could be negatively affected.
76-02-07: 76-02-07 PRESTOLITE: Amendment 39-2500. Applies to Prestolite ALV-9400 through ALV-9410 series gear driven alternators. For aircraft having Prestolite ALV-9400 through ALV-9410 series alternators with more than 100 hours time in service compliance is required within the next 25 hours time in service after the effective date of this AD unless already accomplished within the last 75 hours time in service, and thereafter at intervals not to exceed 100 hours time in service from the last check. To detect defective alternator slip ring end bearings and minimize the probability of in-service failures, accomplish the following: Remove the slip ring end bearing cover by using a small sharp chisel, knife blade, or screwdriver to pry it out of the alternator slip ring head. Care must be taken not to damage the end head or bearing cover. If the bearing cover is damaged during removal it must be replaced. Without further disassembly visually inspect the bearing and shaftend for discoloration or any sign of overheating or wear. Pay particular attention to the bearing inner and outer race. If there is any sign of overheating or an indication that the rotor shaft has been turning in the inner race or the outer race has been turning in the end head, the alternator must be removed and repaired. If the rotor shaft has been turning in the bearing inner race, the rotor and bearing must be replaced. If the bearing outer race has been turning in the end head, the bearing and end head must be replaced. Check the bearing grease for any sign of overheating or contamination such as dirt, or metal filings. If the grease is a dark brown or black color, or is so contaminated, the alternator must be removed and the bearing replaced. If the bearing shows no sign of discoloration, overheating, wear, or contamination, the bearing only (not the entire cavity) should be filled with Chevron BRB#2 or Chevron SRI#2 grease or an equivalent approved by Chief, Engineering and Manufacturing Branch, Great Lakes Region. At this time we are not aware of an equivalent lubricant for this application. NOTE: Refer to Continental Service Bulletin No. TCM M75-30 for further information concerning this subject. The checks required by this AD may be performed by the pilot. Operators who have not kept records of hours time in service on individual alternators shall substitute aircraft hours time in service in lieu thereof. This amendment becomes effective February 2, 1976.
2015-05-02: We are superseding Airworthiness Directive (AD) 2014-23-15 for all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2014- 23-15 required revising the maintenance or inspection program to incorporate new, more restrictive airworthiness limitations. This new AD retains the requirement to revise the maintenance or inspection program and removes a conflicting requirement. This AD was prompted by a determination that certain limitations required by AD 2014-23-15 conflict with limitations required by another AD. We are issuing this AD to prevent fatigue cracking, accidental damage, or corrosion in principal structural elements, and possible failure of certain life limited parts, which could result in reduced structural integrity of the airplane.
2015-04-08: We are superseding Airworthiness Directive (AD) 2014-06-08 for certain Bombardier, Inc. Model DHC-8-100, -200, and -300 series airplanes. AD 2014-06-08 required repetitive functional checks of the nose and main landing gear, and corrective actions if necessary; and also provided optional terminating action modification for the repetitive functional checks. This new AD requires a terminating action modification. This AD was prompted by a report that the emergency downlock indication system (EDIS) had given a false landing gear down- and-locked indication and a determination that a terminating action modification is necessary to address the identified unsafe condition. We are issuing this AD to detect and correct a false down-and-locked landing gear indication, which, on landing, could result in possible collapse of the landing gear.