Results
2004-09-23: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 series airplanes, that requires repetitive inspections of the control panel of the direct current (DC) generator for discrepancies, and replacement of any discrepant part. This action is necessary to prevent loss of both DC generator systems and loss of several other airplane systems, which could lead to the pilot's inability to maintain controlled flight. This action is intended to address the identified unsafe condition.
2011-25-10: We are adopting a new airworthiness directive (AD) for all PW JT9D-7R4H1 turbofan engines. This AD was prompted by reports of cracks in five high-pressure compressor (HPC) shafts. This AD requires removing certain HPC shafts before their certified life limits and establishes a new, lower life-limit for these parts. We are issuing this AD to correct the unsafe condition on these products.
2011-25-02: We are adopting a new airworthiness directive (AD) for BRP- Powertrain GmbH & Co. KG Rotax 912 F2, 912 F3, 912 F4, 912 S2, 912 S3, 912 S4, 914 F2, 914 F3, and 914 F4 reciprocating engines. 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: During a production process review, a deviation in the manufacturing process of certain part number (P/N) 888164 crankshafts has been detected, which may have resulted in a latent defect. This condition, if not corrected, could lead to crack formation on the power takeoff side of the crankshaft journal, possibly resulting in failure of the crankshaft support bearing, in- flight engine shutdown and forced landing, damage to the aeroplane and injury to the occupants. We are issuing this AD to prevent in-flight failure of the engine and forced landing.
2021-18-12: The FAA is adopting a new airworthiness directive (AD) for certain PZL Swidnik S.A. Model PZL W-3A helicopters. This AD was prompted by a report of fractured hoist carrying assembly bracket (bracket) bolts. This AD requires repetitively inspecting the sealing compound of certain part-numbered brackets, and depending on the results, removing the hoist or removing the hardware from service and installing new hardware. As an option to replacing the bolts, this AD allows deactivating the hoist, turning the circuit breaker panel switches to the OFF position, installing inoperative placards on the circuit breaker panel switches, and before each flight, inspecting the sealing compound. This AD also establishes a life limit for the bracket bolts, and prohibits installing an affected hoist or an affected bracket and hoist unless the actions required by this AD have been accomplished. The FAA is issuing this AD to address the unsafe condition on these products.
67-29-04: 67-29-04 GRUMMAN: Amdt. 39-497 Part 39 Federal Register October 25, 1967. Applies to Type G-164 aircraft, Serial Numbers 1 through 400. Compliance required as indicated. Gulfstream G-164 type aircraft have experienced loose rivets which attach the rod ends of the elevator forward pushrod assembly. To detect loose rivets on the assembly, P/N A1847-1 (Aircraft Serial Numbers 1 through 100) and P/N A1847-3 (Aircraft Serial Numbers 101 through 400), accomplish the following: (a) For aircraft with 250 or more hours' total time in service on the effective date of this AD comply with paragraph (c) within the next 50 hours' time in service, and thereafter at intervals not to exceed 100 hours' time in service from the last inspection. (b) For aircraft with less than 250 hours' total time in service on the effective date of this AD comply with paragraph (c) before the accumulation of 300 hours' total time in service, and thereafter at intervals not to exceed 100 hours' time inservice from the last inspection. (c) Visually inspect the fore and aft ends of the pushrod assemblies to determine if there are loose rivets or elongated holes. (d) If loose rivets or elongated holes are found during the inspection required in paragraphs (a) or (b), before further flight, remove rivets (4 places) and repair as follows: (1) Line ream original rivet holes .190 + .001 inch. (4 places) (2) Install AN3-13A bolt, AN960-10 washer (under nut), and AN365-1032 nut. (4 places) If holes have elongated in excess of .191 inches, repair as follows: (3) Line ream original rivet holes .250 + .001 inch. (4 places) (4) Install AN4-14A bolt, AN960-416 washer (under nut), and AN365-428 nut. (4 places) If holes have been elongated in excess of .251 inch then replace the assembly. (e) The repetitive inspection required by paragraphs (a) and (b) of this AD may be discontinued upon accomplishment of the repair specified in paragraph (d) or equivalent repair approved by the Chief, Engineering & Manufacturing Branch, FAA Eastern Region. (f) Upon request, with substantiating data submitted through an FAA maintenance inspector, compliance time may be increased by the Chief, Engineering & Manufacturing Branch, FAA Eastern Region. This amendment effective October 27, 1967.
52-01-01: 52-01-01 BELL: Applies to All Models 47B, 47B3, 47D Helicopters and to Model 47D1 Helicopters Serial Numbers 145 to 164, Inclusive. Compliance required at next 300-hour overhaul, but not later than March 1, 1952. To provide locks of increased tensile strength which will resist shearing should the blade grip adapters tend to loosen, remove the existing lockwire or blade grip adapter locks (P/N 47- 120-154-1), check the torque (3,000-3,300 inch-pounds) of the adapters and install revised locks (P/N 47-120-154-2). (Bell Service Bulletin No. 76 covers this same subject.)
2004-09-17: This amendment adopts a new airworthiness directive (AD), applicable to all Dornier Model 328-100 and -300 series airplanes, that requires a one-time inspection for fracture and/or breakage of the hinge bolt of the output rod of the rudder spring tab lever assembly, and corrective action if necessary. This AD also requires modification of the hinge bolt. This action is necessary to prevent fracture and/or breakage of the hinge bolt, which could result in migration of the bolt tail, a loose spring tab, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
98-12-03: This amendment adopts a new airworthiness directive (AD) that applies to certain Alexander Schleicher Segelflugzeugbau (Alexander Schleicher) Models ASW-19 and ASK 21 sailplanes. This AD requires: modifying the rudder surface panels; replacing the airbrake bellcrank; and modifying the rear canopy hinge structure. 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 loss of the canopy caused by design deficiency, airbrake failure caused by cracking, and rudder panel flutter caused by high density altitude conditions, all of which could result in reduced sailplane controllability.
2021-20-02: The FAA is adopting a new airworthiness directive (AD) for certain Bell Textron Inc. (type certificate previously held by Bell Helicopter Textron Inc.) Model 205B helicopters. This AD was prompted by a notification of certain parts needing a life limit. This AD requires determining the total hours time-in-service (TIS) of certain part-numbered main rotor grip assemblies (grip assemblies), establishing a life limit for certain part-numbered grip assemblies, removing from service any grip assembly that has reached or exceeded its retirement life, creating a component history card, and removing any grip assembly from service before reaching its retirement life. This AD also prohibits installing certain grip assemblies unless the life limit was established in accordance with this AD. The FAA is issuing this AD to address the unsafe condition on these products.
96-10-03: This amendment adopts a new airworthiness directive (AD) that applies to certain The New Piper Aircraft, Inc. (Piper) PA28, PA32, PA34, and PA44 series airplanes. This action will require inspecting and modifying the flap lever assembly. Reports of worn flap handle attach bolts and elongated holes in the flap lever to cable mounting attach point prompted this AD action. The actions specified by this AD are intended to prevent failure of the flap handle attach bolt and sudden retraction of the flaps, which, if not detected and corrected, could result in loss of control of the airplane.