Results
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.
2019-11-06: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by reports of cracks in the skin and a certain chord at three fastener locations common to the drag link assembly at the chord. This AD requires repetitive inspections of the skin under the drag link assembly for any cracks, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2000-26-16: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Beech Models A36, B36TC, and 58 airplanes. This AD requires you to inspect for missing rivets on the right hand side of the fuselage and, if necessary, install rivets. Raytheon has identified several instances of missing rivets on these airplanes. The actions specified by this AD are intended to install missing rivets in the right hand fuselage panel assembly in the area above the right wing and below the cabin door threshold. These rivets must be present for the fuselage to carry the ultimate load and prevent critical structural failure with loss of airplane control.
2007-11-08: The FAA is superseding an existing airworthiness directive (AD) that applies to all Boeing Model 727 airplanes. The existing AD requires a boost pump dry bay inspection to detect leakage of fuel through an arced-through conduit, and corrective action as necessary. The existing AD also requires repetitive inspections of the in-tank fuel boost pump wiring to detect chafing of the wire insulation, evidence of electrical arcing, or arc-through of the conduit wall, and applicable corrective action; and installation of sleeving over the in- tank fuel boost pump wires as a method to protect the wiring from chafing. This new AD removes certain inspection requirements from the existing AD. This new AD adds new repetitive inspections for damage of the electrical wire and sleeve that run to the fuel boost pump through a conduit in the fuel tank, and arcing damage of the conduit and signs of fuel leakage into the conduit; applicable investigative and corrective actions; and a new repetitive engine fuel suction feed operational test. Initiation of the new inspections terminates the requirements of the existing AD. This AD results from reports of a fuel tank explosion on a Model 727-200F airplane on the ground; and of chafed wires and a damaged power cable sleeve of a fuel boost pump that were discovered during an inspection required by an existing AD on a Model 737-300 airplane. We are issuing this AD to detect and correct chafing of the fuel boost pump electrical wiring and leakage of fuel into the conduit, and to prevent electrical arcing between the wiring and the surrounding conduit, which could result in arc-through of the conduit, and consequent fire or explosion of the fuel tank. \n\n\nDATES: This AD becomes effective June 6, 2007. \n\n\tThe Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of June 6, 2007. \n\tOn June 28, 1999 (64 FR 33394, June 23, 1999), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 727-28A0126, dated May 24, 1999. \n\n\tWe must receive any comments on this AD by July 23, 2007.
2010-03-06: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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: Several events of uncoupling of the low-pressure (LP) fuel pump impeller and the high-pressure (HP) fuel pump shaft have been reported on Arriel 2 engines which do not incorporate Modification TU 147. In most cases the "low fuel pressure switch'' enlightened, the pilot activated the aircraft booster pump in accordance with the Flight Manual Instructions and landed safely with no other incident. One case, on a single-engine helicopter, led to a sudden engine power loss. The uncoupling of the LP fuel pump impeller and the HP fuel pump shaft may lead to a limitation of engine power or, at worst, an uncommanded in-flight shutdown. On a single-engine helicopter,the result may be an emergency autorotation landing. We are issuing this AD to prevent a forced autorotation landing or an accident.
2000-26-17: This amendment adopts a new airworthiness directive (AD) that applies to Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes that are equipped with a certain windshield configuration. This AD requires you to incorporate pilot's operating handbook (POH) information that prohibits the operation of the windshield heating system in the "LIGHT" mode, and requires you to modify the windshield deicing system wiring and circuit breakers. You can remove the POH information after accomplishing the modification. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to prevent loss of electrical power to the windshield deicing system due to operation in the "LIGHT" mode, which could result in icing of the windshield and loss of control of the airplane.
2007-11-06: The FAA is superseding an existing airworthiness directive (AD) for Turbomeca Arrius 2F turboshaft engines. That AD currently requires removing from service certain serial number (SN) fuel control units (FCUs) or replacing the constant delta pressure (delta P) diaphragm in those FCUs. This AD requires replacing all FCUs not incorporating modification Tf 55 with FCUs that incorporate modification Tf 55. This AD results from the European Aviation Safety Agency (EASA) and Turbomeca expanding the applicability to the full population of FCUs installed on Arrius 2F turboshaft engines. FCUs not incorporating modification Tf 55 are susceptible to having an improperly assembled constant delta P diaphragm. We are issuing this AD to prevent an uncommanded engine in-flight shutdown on a single-engine helicopter, resulting in a forced autorotation landing or an accident.
2000-26-09: This amendment adopts a new airworthiness directive (AD), applicable to all Dornier Model 328-100 series airplanes, that requires revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate life limits for certain items and inspections to detect fatigue cracking in certain structures. This amendment is prompted by issuance of new revisions to the Dornier 328 Airworthiness Limitations Document. The actions specified by this AD are intended to ensure that fatigue cracking of certain structural elements is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes.
74-24-02: 74-24-02 SWEARINGEN: Amendment 39-2012 as amended by Amendment 39-2529. Applies to Models SA226-T, SA226-AT, and SA226-TC airplane. Compliance required as indicated. To detect cracks and provide for repair and reinforcement of the horizontal stabilizer rear spar at the outboard elevator hinge bracket attachment accomplish the following inspection and modifications: (a) After September 2, 1974, conduct the following inspection for the Model SA226-TC before the next flight unless already accomplished and for the Models SA226-T and SA226-AT within the next 10 hours time in service unless already accomplished. Inspect horizontal stabilizer rear spar in the vicinity of the left and right outboard elevator hinge bracket attachment for spanwise cracking above and below the hinge bracket in the bend radii of the spar flanges in accordance with paragraphs II.A.1. through 4. of Swearingen Service Bulletins A27-40-3067, revised October 9, 1974, for the Model SA226-T and A27-40-2064-4067, revised October 9, 1974, for the Models SA226-TC and SA226-AT or later FAA approved revisions. (b) If cracks are found, before further flight, repair horizontal stabilizer rear spar in accordance with: (1) Paragraph II.B. of Swearingen Service Bulletin A27-40-3067, revised October 9, 1974 or later FAA approved revision for the Model SA226-T, or (2) Paragraph II.B. of Swearingen Service Bulletin A27-40-2064-4067 revised October 9, 1974 or later FAA approved revision for the Models SA226-TC and SA226-AT. (c) If no cracks are found, accomplish the following: (1) Continue the inspections specified in (a) for the Model SA226-T at intervals not to exceed 200 hours time in service after the effective date of this AD. These periodic inspections may be discontinued after installation of the spar reinforcement specified in paragraph II.C. of Swearingen Service Bulletin A27-40-3067 revised October 9, 1974 or later FAA approved revision. (2) Within 50 hours timein service after the effective date of this AD, unless already accomplished for the Models SA226-TC and SA226-AT, install the spar reinforcement specified in paragraph II.C. of Swearingen Service Bulletin A27-40-2064-4067 revised October 9, 1974, or later FAA approved revisions. (3) After the rework specified in (c)(2), continue the inspections specified in (a) for the Models SA226-TC and SA226-AT at intervals not to exceed 500 hours' time in service from the date of rework or from the effective date of this AD if the rework was accomplished before the effective date. (d) Alternate methods of spar repair and reinforcement must be approved by the Chief, Engineering and Manufacturing Branch, Southwest Region, FAA. Amendment 39-2012 superseded Amendment 39-1950, AD 74-18-14, and became effective November 18, 1974. This amendment 39-2529 becomes effective March 8, 1976.
2018-02-05: We are adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. Models PA-28-140, PA-28-150, PA-28-151, PA-28-160, PA-28-161, PA-28-180, PA-28-181, [[Page 3065]] PA-28-236, PA-28-201T, PA-28R-180, PA-28R-200, PA-28R-201, PA-28R-201T, PA-28RT-201, and PA-28RT-201T airplanes. This AD requires inspecting the fuel tank selector cover to verify the left and right fuel tank selector placards are located at the proper positions and replacing those that are improperly located with new placards. This AD was prompted by a quality control issue at the manufacturer that resulted in the installation of the fuel tank selector covers with the left and right fuel tank selector placards improperly located. We are issuing this AD to address the unsafe condition on these products.
89-18-06: 89-18-06 AMERICAN CHAMPION AIRCRAFT (BELLANCA, CHAMPION): Amendment 39-6306. Applicability: Models 7ECA, 7GCAA, 7GCBC, 7KCAB, 8GCBC, and 8KCAB (all serial numbers) airplanes certificated in any category, when equipped with front folding seats. Compliance: Required as indicated in the body of the AD, unless already accomplished. To prevent failure of the seat back which could result in loss of control of the airplane, accomplish the following: (a) Within the next 25 hours time-in-service after the effective date of this AD and, thereafter at intervals not to exceed 25 hours time-in-service from the last inspection until the actions specified in paragraph (b) below are accomplished, accomplish the following: (1) Magnetic particle or dye penetrant inspect the left and right sides of the welded lower seat frame side-tube/side-brace junction and seatback hinges for evidence of cracks. If any cracks are found, prior to further flight repair, in accordancewith the recommended procedures in Advisory Circular (AC) 43.13-1A, the crack or replace the cracked part with a serviceable part. (2) Fabricate and install on the instrument panel in clear view of the pilot a placard with letters of minimum 0.2 inches in height which reads as follows: "Warning: Do not pull or push on upper seat back." (b) Within the next 150 hours time-in-service after the effective date of this AD, replace the front folding seat frame with an exchange unit in accordance with American Champion Aircraft Service Letter No. 401, dated June 14, 1989. The repetitive inspections and the placard specified in paragraph (a) above are no longer required after the actions specified in this paragraph have been accomplished. (c) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (d) An equivalent means of compliance with this AD may be used if approved by the Manager, Chicago Aircraft Certification Office,ACE-115C, 2300 East Devon Avenue, Des Plaines, Illinois 60018. All persons affected by this directive may obtain copies of the documents referred to herein upon request to American Champion Aircraft, P.O. Box 37, Rochester, Wisconsin 53167, or may examine these documents at the FAA, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment (39-6306, AD 89-18-06) becomes effective on September 21, 1989.
98-24-01: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace (Jetstream) Model 4101 airplanes, that requires repetitive detailed visual inspections to detect cracking or other damage of certain diaphragm support structures of the forward equipment compartment; and repair, if necessary. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct failure of the two diaphragms that support the upper structure of the forward equipment compartment, which could accelerate fatigue damage in adjacent structure and result in reduced structural integrity of the airframe.
2019-08-04: We are superseding Airworthiness Directive (AD) 2012-25-02, which applied to certain Bombardier, Inc., Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. AD 2012-25-02 required revising the airworthiness limitations section (AWL) of the instructions for continued airworthiness (ICA) of the maintenance requirements manual (MRM) by incorporating new procedures for repetitive inspections for cracking of the rear pressure bulkhead (RPB). AD 2012-25-02 also required revising the maintenance or inspection program to incorporate a revised task. This AD also mandates modification of the RPB and adds repetitive inspections for cracking of the RPB web, which terminates certain actions in this AD. This AD was prompted by additional in- service crack findings, which resulted in the development of a structural modification to the RPB. We are issuing this AD to address the unsafe condition on these products.
2007-10-11: The FAA is adopting a new airworthiness directive (AD) for certain EMBRAER Model EMB-145LR, -145XR, and -145MP airplanes; and Model EMB-135BJ and -135LR airplanes. This AD requires replacing the electrical bonding clamps inside the fuel tanks and adjacent areas. This AD results from a report of the failure of a fitting clamp of an electrical bonding cable for the fuel tubing. We are issuing this AD to prevent loss of bonding protection in the interior of the fuel tanks or adjacent areas, and a consequent potential source of ignition in a fuel tank and possible fire or explosion.
2007-10-07: We are superseding an existing airworthiness directive (AD) by adopting a new AD for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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: The deterioration of the splines on the HP/LP pump assembly drive shaft may eventually interrupt fuel supply and cause uncommanded in-flight engine shutdown. The result may be an emergency autorotation landing or, at worst, an accident. Two cases of in-flight shutdown resulting from splines deterioration have been reported for the ARRIUS 2B1 engine, which has the same HP/LP pump drive design as the ARRIEL 2. These cases prompted us to require the inspection at 500 hours and each time the HMU is removed/installed. This AD modifies the content of the previous DGAC France AD F- 2005-188 (EASA Approval Number 2005-6408) in adding a one time inspection within 30 operating hours from effective date of this AD as well as HMU re- installation according to a maintenance task modified to avoid this kind of wrong assembly. This has been set up following one case of improper clipping of the coupling shaft onto the drive gear shaft, which resulted in an uncommanded in-flight engine shutdown (on a twin engine rotorcraft). This precaution measure has been taken only on engines powering single engine rotorcraft. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
94-04-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Canadair Model CL-215-6B11 series airplanes, that requires inspections to detect cracking in the rear engine mount struts, and replacement of struts with new struts, if necessary; and the eventual replacement of all struts with new struts. This amendment is prompted by reports of failures of these rear engine mount struts due to cracking that was caused by rosette welds on the shank of the struts not achieving full weld penetration during manufacture. The actions specified by this AD are intended to prevent failure of the rear engine mount struts, which could subsequently result in reduced structural integrity of the nacelle and engine support structure.
2007-10-08: 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: * * *failure of the Autopilot System Computer resulting in the possibility of an out of trim condition, which may lead to loss of aircraft control * * * This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2000-26-13: This amendment adopts a new airworthiness directive (AD) that is applicable to all Dornier Model 328-300 series airplanes. This action requires inspections of all three hydraulic accumulators for signs of leaks, corrective actions if necessary, and eventual installation of an additional locking device to secure the nuts in the hydraulic accumulators, which will terminate the repetitive inspections. This action is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. This action is necessary to prevent possible loss of one or more of the hydraulic accumulators, which could result in a complete loss of the hydraulic system and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.