Results
2001-01-04: This amendment adopts a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-76A, S-76B, and S-76C helicopters. This AD requires initial and repetitive inspections of the main landing gear positioning rod assembly (rod assembly) and the side brace rod end (rod end) for corrosion. If any corrosion is found, this AD requires replacing any part that is corroded with an airworthy part before further flight. This amendment is prompted by a landing gear collapse caused by corrosion due to dissimilar metals in the landing gear rod end. The actions specified in this AD are intended to detect corrosion of the threaded joint in the rod assembly to prevent a collapse of the landing gear, and subsequent loss of control of the helicopter during landing.
2018-02-20: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200, -200LR, -300, and -300ER series airplanes. This AD was prompted by reports of corrosion in the aft fuselage. This AD requires a one-time review of the operator's maintenance procedures, repetitive detailed internal and external inspections for corrosion or cracking, and applicable on-condition actions. This AD also includes an optional terminating action for the inspections. We are issuing this AD to address the unsafe condition on these products.
2001-01-06: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Industrie Model A300, A300-600, and A310 series airplanes; equipped with Dowty ram air turbines (RAT). That AD currently requires repetitive deployment tests of the RAT and checks of the adjustment of the locking rod. This amendment also requires modification of the RAT, which terminates the repetitive tests and checks. 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 ensure the availability of the RAT in case of need.
2019-12-07: The FAA is superseding Airworthiness Directive (AD) 2007-11-11 and AD 2017-01-11, which applied to all Airbus SAS Model A318 and Model A319 series airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321 series airplanes. AD 2007-11-11 required an inspection to determine the serial number of both main landing gear (MLG) sliding tubes, repetitive inspections for cracking of the affected MLG sliding tubes and corrective actions if necessary, and eventual replacement of both MLG shock absorbers. AD 2017-01-11 required identification of the part number and serial number of the MLG sliding tubes; inspection of affected chromium plates and sliding tube axles for damage; and replacement of the sliding tube if [[Page 30580]] necessary. This AD retains certain requirements of AD 2007-11-11 and AD 2017-01-11. This AD also requires repetitive inspections of affected MLG sliding tubes for cracking, replacement of cracked MLG sliding tubes, and eventualreplacement of each affected MLG sliding tube. This AD was prompted by cracks found in the MLG sliding tubes due to certain manufacturing defects that might not be identified using the current on-wing scheduled inspections. The FAA is issuing this AD to address the unsafe condition on these products.
72-01-07: 72-01-07 PIPER: Amdt. 39-1369 as amended by Amendment 39-1434. Applies to Piper Model PA-18, PA-18-105, -125, -135, PA-18A, PA-18A-125, -135, and seaplane versions of those models which have been modified after May 14, 1968 in accordance with Supplemental Type Certificate SA 136 AL to incorporate the installation of the Lycoming O-320 engine (150 HP). Factory delivered models having serial numbers 18-3771 and 18-3781 and above, incorporating the O-320 engine, are not affected by this AD. Compliance is required as indicated. To prevent possible failure of the engine mount, within the next 25 hours' time in service after the effective date of this AD, unless already accomplished, install engine mount, P/N 12351- 12, in accordance with Piper Drawing Number 12351, Mount Assembly-engine, including Revision J dated January 16, 1968, or an equivalent approved by the Chief, Engineering and Manufacturing Branch of an FAA region (or in the case of the Western Region, the Chief,Aircraft Engineering Division). NOTE: Engine mount assembly P/N 12351-12 may be identified by the gage of Tube "A" and Tube "B" which measure .049 inches, and by the incorporation of two reinforcing plates, number 14438, mounted at the lower right engine attachment points as shown on Piper Drawing Number 12351, Mount Assembly-Engine, including Revision J dated January 16, 1968. Amendment 39-1369 became effective January 27, 1972. This Amendment 39-1434 becomes effective April 17, 1972.
2001-01-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Dassault Model Falcon 10 and Model Mystere-Falcon 50 series airplanes. For certain airplanes, this amendment requires modification of the aircraft wiring to illuminate the "T/O CONFIG" red warning light on the cockpit warning panel. For certain other airplanes, this amendment requires installation of a "NO TAKEOFF" red light on each pilot's instrument panel; modification of the associated aircraft wiring to activate the lights whenever the aircraft is not in the proper configuration for takeoff; and a revision to the Airplane Flight Manual to check that the "NO TAKEOFF" lights are out prior to takeoff. 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 takeoff with the parking brake engaged, which could result in an extended takeoff roll or a rejected takeoff, and consequent runway overrun.
2007-11-19: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Installation of G-load monitoring units on some Zlin Z 42 series airplanes has revealed that certain aircraft during aerobatic manoeuvres exceeded the limit loads initially defined for the certification. As a consequence to restore the safety margins on aircraft operated in Utility ("U'') category; this Airworthiness Directive (AD) mandates a modification of the Airplane Flight Manual (AFM) so as to limit the permissible manoeuvres in "U'' category flights. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
68-07-04: 68-07-04 PIPER AIRCRAFT: Amdt. 39-576 as amended by Amendment 39-1324 is further amended by Amendment 39-1426. Applies to Piper PA-23-250 airplanes Serial Nos. 27- 2505 and up having engine mount part number 31215. Compliance required as indicated. a. With airplanes having engine mount date stamped prior to 26 May 1965, within the next 50 hours in service after the effective date of this AD unless already accomplished within the last 50 hours in service and thereafter at intervals not to exceed 100 hours in service from the last inspection visually inspect the mount for cracks in the following areas: (i) The lower forward lateral tube (ii) The three-tube horizontal diagonal truss in and around the three welded junctures with the lower forward lateral fore and aft tube, and (iii) The lower left horizontal fore and aft tube. b. With airplanes having engine mounts date stamped 26 May 1965 and after, and having 1000 or more hours in service, within the next 50 hours in service after the effective date of this AD, unless already accomplished within the last 50 hours in service, and thereafter at intervals not to exceed 100 hours in service from the last inspection visually inspect the engine mount tubes forward of the firewall for cracks. c. If cracks are found accomplish either of the following, (i) Replace the engine mount prior to further flight with a new mount part number 31215. After installation of new mount continue repetitive inspection of this mount after 1000 hours as described in paragraph b. (ii) Repair the engine mount prior to further flight in accordance with FAR 43. Conduct a magnetic particle, or equivalent method, inspection of the entire mount for cracks prior to approval of the repaired engine mount. Continue visual inspections of the mount within 100 hours in service and thereafter not to exceed 100 hours in service from the last inspection. NOTE: On engine mounts date-stamped prior to 26 May 1965, a pictorial description of the affected areas can be found in Piper Service Letter No. 462. The engine mount is date- stamped on either of the two diamond-shaped gusset plates located near the upper firewall attachment points. Amendment 39-576 was effective April 11, 1968. Amendment 39-1324 was effective November 2, 1971. This Amendment 39-1426 is effective April 11, 1972.
2007-11-14: 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: It has been found that both fuel level control units (LCU) and their associated harnesses throughout the aircraft does not comply with the requirements of proper segregation, in order to preclude a possible ignition source in the vicinity of the fuel tanks, as required by SFAR (Special Federal Aviation Regulation) 88 regulations. We are issuing this AD to require actions to correct the unsafe condition on these products.
2007-11-16: The FAA is adopting a new airworthiness directive (AD) for all McDonnell Douglas Model MD-11 and MD-11F airplanes. This AD requires installing bracket assemblies and jumper wires in the center main wheel well to improve the bonding path between the structure (wall) of the lower auxiliary fuel tank and its internal fuel pumps; measuring the electrical resistance between the fuel pump housings and the fuel tank structure; and doing corrective actions if necessary. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to detect and correct an inadequate bond between the internal fuel pump housings and the structure of the lower auxiliary fuel tank. This condition, if not corrected, could fail to meet fault current requirements and result in a potential ignition source that, in combination with flammable fuel vapors, could cause a fuel tank explosion and consequent loss of the airplane.
2018-03-06: We are superseding Airworthiness Directive (AD) 2015-02-18, which applied to all Airbus Model A330-201, -202, -203, -301, -302, and -303 airplanes. AD 2015-02-18 required a one-time ultrasonic inspection for fractures of all aft mount-pylon bolts of each engine. This new AD was prompted by the failure of a bolt on the aft engine mount upper beam, which was found to be caused by inappropriate in-production upper beam installation. 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.
2001-01-08: This amendment adopts a new airworthiness directive (AD), applicable to all BAE Systems (Operations) Limited (Jetstream) Model 4101 airplanes, that requires inspection for cracking of the mounting brackets of the hydraulic hand pump at the frame attachment flanges, replacement of any cracked bracket with a new bracket, replacement of all bolts and nuts with new bolts and nuts, and installation of a particular `D' packer. The actions specified by this AD are intended to prevent failure of these brackets, which could result in inability to extend the landing gear in an emergency situation where the main hydraulic system is lost. This action is intended to address the identified unsafe condition.
63-26-03: 63-26-03 PIPER: Amdt. 663 Part 507 Federal Register December 24, 1963 as amended by Amendment 39-1240. Applies to Piper Models PA-23 and PA-23-160 Aircraft, Serial Numbers 23-1 through 23-1267, inclusive. Compliance required as indicated: (a) Within the next 50 hours in service after the effective date of this AD, unless already accomplished within the last 50 hours in service, and thereafter at intervals not to exceed 100 hours in service from the last inspection, visually inspect for cracks each of the castings listed herein. When any casting is replaced by the respective forging listed herein, the repetitive inspections of this paragraph and paragraph (b) are no longer required for that forging. NAME CASTING PART NO. FORGING Elevator Torque Tube Bracket 17033-00 and 17033-01 19407-00 Front Stabilizer Attachment 17049-00 and 19253-00 19409-02 Rudder Torque Tube Horn 17060-00 19405-00 Elevator Torque Tube Horn 17066-00 19404-00 RudderTorque Tube Bracket 17062-00 19408-00 Fin Attachment Bracket 17072-00 19406-00 or 19406-02 (b) For airplanes having 1,000 or more hours in service, remove the subject castings from the aircraft, clean thoroughly removing all paint, and perform a dye penetrant inspection for cracks, within the next 100 hours in service after the effective date of this AD, unless already accomplished within the last 400 hours in service, and thereafter at intervals not to exceed 500 hours in service from the last inspection. Prior to reinstallation of castings without cracks, clean thoroughly, and apply zinc chromate primer. (c) Replace cracked castings before further flight with a replacement forged or cast part. (d) Inspection and reassembly shall be accomplished in accordance with Piper Service Bulletin No. 155B, dated October 28, 1963, or FAA-approved equivalent. NOTE: For paragraph (a), it is necessary to remove the tail cone, covers, and fairings to gain access to most of the parts to be inspected. However, parts need not be disassembled and/or removed from the aircraft to accomplish this inspection. All of the forged parts listed herein have integral raised digit forging numbers. Therefore, the absence of raised digits will serve to identify the part as a casting. AD 63-26-03 Amendment 663 supersedes AD 57-13-09. Amendment 663 was effective December 24, 1963. Revised on April 26, 1966 and December 16, 1966. This Amendment 39-1240 is effective July 13, 1971.
2007-11-10: The FAA is adopting a new airworthiness directive (AD) for all Fokker Model F.28 Mark 0070 and 0100 airplanes. This AD requires a detailed inspection for wear of the attachment holes of the control levers of the braking system and applicable corrective actions. This AD results from a report that, after landing, the flightcrew of a Model F.28 Mark 0100 airplane noted that an extreme difference in pedal angle was required to achieve equal braking action. We are issuing this AD to prevent failure of one or more brake control levers, which could result in uncommanded braking and loss of control of the airplane during takeoff, landing, or taxiing.
2007-11-01: This amendment adopts a new airworthiness directive (AD) for Robinson Helicopter Company (Robinson) Model R44 and R44 II helicopters that have a certain seat belt buckle (buckle) assembly installed, that requires removing the buckle assembly and the buckle assembly spacer, and replacing them with airworthy parts. This amendment is prompted by an accident in which a seat belt failed, and also by reports of cracking in the buckle assembly stainless support strap (support strap). The actions specified by this AD are intended to prevent cracking in the support strap and failure of a seat belt.
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.