Results
2018-03-09: We are adopting a new airworthiness directive (AD) for certain Airbus Model A321-211 and -231 airplanes. 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. This AD was prompted by a determination that the flat-headed pin at the upper attachment point of the overhead stowage compartments at a certain frame may not sustain the maximum weight load for each flight phase. We are issuing this AD to address the unsafe condition on these products.
2001-01-01: This amendment adopts a new airworthiness directive (AD) that is applicable to BMW Rolls-Royce (RR) GmbH models BR700-710A1-10 and BR700-710A2-20 turbofan engines with oil filter differential pressure switch part number (P/N) 21SN04-419 or P/N 21SN04-431 installed. This action requires inspections of oil filter differential pressure switches, and replacement if necessary, in accordance with Rolls-Royce Service Bulletin No. SB-BR700-79-900215, Revision 2, dated August 2, 2000. This amendment is prompted by a report of severe engine oil loss, caused by oil leakage from a defective oil filter differential pressure switch. The actions specified in this AD are intended to prevent defective oil filter differential pressure switches from causing severe engine oil loss, resulting in in-flight shutdowns.
71-12-05: 71-12-05 PIPER AIRCRAFT: Amdt. 39-1226. Applies to Models PA-23-250 (Six Place) and PA-E23-250 (Six Place) Serial Numbers: 27-3837, 27-3944 through 27-4467, 27- 4469 through 27-4527, 27-4529 through 27-4559, 27-4561 through 27-4567, 27-4569 through 27-4575, 27-4577 through 27-4579, 27-4581, 27-4582, 27-4584 through 27-4592, 27-4594, 27- 4596 through 27-4604 and 27-4606. Model PA-24-260, Serial Nos. 24-4783, 24-4804 through 24-4953, 24-4955 through 24-4959, 24-4962 and 24-4964. Model PA-30, Serial Nos. 30-1717, 30-1745 through 30-2000. Model PA-31 and 31-300, Serial Nos.; 31-2 through 31-694, 31-696 and 31-697. Model PA-31P; Serial Nos. 31P-1 through 31P-24, 31P-26 through 31P-29, 31P-31 and 31P-33. Model PA-39; Serial Nos. 39-1 through 39-83 and any other of the above model A/C equipped with Scott Electric Trim Switch P/N 800452-01. Compliance required within the next 100 hours' time in service after the effective date of this AD, unless already accomplished. (a)Modify the Electric Trim Switch P/N 800452-01 in accordance with Piper Kit No. 760505 as referenced in Piper Service Bulletin No. 331, dated 5 February 1971 or equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (b) Upon request with substantiating data submitted through an FAA maintenance inspector, the compliance time specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment is effective June 16, 1971.
2018-02-13: We are superseding Airworthiness Directive (AD) 2017-07-02 for Sikorsky Aircraft Corporation (Sikorsky) Model 269D and Model 269D Configuration A helicopters. AD 2017-07-02 required reducing the life limit of and inspecting certain drive shafts. This new AD retains the requirements of AD 2017-07-02 and requires repeating the inspections. The actions of this AD are intended to detect and prevent an unsafe condition on these products.
2000-26-19: This amendment adopts a new airworthiness directive (AD) that applies to certain SOCATA - Groupe AEROSPATIALE (Socata) Model TBM 700 airplanes. This AD requires you to inspect for a low point in the fuel tank air vent valve hose; and reroute the hose as necessary. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent in-flight damage to the wing skins caused by abnormal venting conditions of the wing fuel tank, which could result in severe handling problems or reduced structural capability. Continued operation with such structural deformation or handling problems could result in loss of control of the airplane.
71-01-04: 71-01-04 PIPER AIRCRAFT: Amdt. 39-1139. Applies to Model PA-31 and PA-31-300 S/Nos 31-2 to 31-591. Compliance required within the next 100 hours time in service after the effective date of this AD, unless already accomplished. To prevent the hazards associated with toxic fumes from the battery being drawn into the cabin, accomplish the following: (a) Relocate the battery drain in accordance with Piper Service Bulletin No. 325 dated November 10, 1970 or equivalent method approved by the Chief, Engineering & Manufacturing Branch, FAA Eastern Region. This amendment is effective January 14, 1971.
2018-03-01: We are adopting a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model AB139 and AW139 helicopters. This AD requires inspecting the main rotor blade (MRB) tip cap for disbonding. This AD is prompted by a report of the in-flight loss of an MRB tip cap. The actions of this AD are intended to prevent an unsafe condition on these helicopters.
70-18-05: 70-18-05 PIPER: Amendment 39-1076. Applies to the following models: PA-28-140, /- 150, /-160, /-180, /-235, and PA-32-260, /-300. The following are affected serial numbers: PA- 28-140, 28-20001 through 28-22354; PA-28-150, /-160, /-180, 28-1 through 28-3782; PA-28-235, 28-10001 through 28-10806; PA-32-260, 32-1 through 32-853; PA-32-300, 32-40001 through 32-40057. Compliance required within the next 50 hours' time in service after the effective date of this AD, unless already accomplished. To preclude the possibility of failure of the main landing gear torque link bolts accomplish the following: The bolt and lock nut attaching the upper torque link to the main landing gear housing assembly must be replaced with an AN5-23 bolt, AN310-C5 nut, and AN381-2-8 cotter pin. The bolt and lock nut attaching the lower torque link to the main landing gear housing assembly must be replaced with an AN5-22 bolt, AN310-C5 nut, and AN381-2-8 cotter pin. The bolt or grease boltand lock nut attaching the torque links at the scissor joint must be replaced with a grease bolt, Piper part number 65788-00, (hole in threaded end of bolt for cotter pin safety), AN944-101 lubricator fitting, AN 310-C5 nut, AN381-2-8 cotter pin, and appropriate washers. Piper Kit 757-123 contains the necessary hardware and instructions to accomplish this modification. Equivalent replacement parts approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region, may be used. Piper Service Bulletin No. 248 dated 12 May 1967 pertains to this same subject. This amendment becomes effective 7 September 1970.
2000-26-20: This amendment adopts a new airworthiness directive (AD), applicable to certain Gulfstream Model G-1159A (G-III) series airplanes, that requires modification of the master caution panel by installing an additional legend labeled "BATT ON BUS" and associated wiring to indicate when the airplane batteries are powering the direct current (DC) essential bus. This action is necessary to ensure that the flight crew is aware that an electrical system failure has occurred and that the main airplane batteries are powering the essential DC bus. If the flight crew is unaware of this situation, action to stop the depletion of the airplane batteries will not be taken and critical equipment, such as communications and navigation equipment, could fail. This action is intended to address the identified unsafe condition.
2000-26-18: This amendment adopts a new airworthiness directive (AD) that applies to certain Stemme GmbH & Co. KG (Stemme) Models S10 and S10-V sailplanes. This AD requires you to replace the eyebolts on the airbrake, inspect the airbrake sheets for proper clearance and adjust as necessary, and inspect for damage to the landing gear doors and replace any damaged parts. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent aerodynamic flutter of the upper covering straps on the airbrake cover caused by the current design airbrake eyebolts, which could result in damage to the airbrake system and landing gear doors. Continued operation with such damaged components could result in loss of control of the sailplane.