Results
2001-05-07: This amendment supersedes airworthiness directive (AD) 2000-25-06, dated December 5, 2000, that is applicable to certain Pratt & Whitney (PW) PW4000 turbofan engines with the current design low pressure turbine (LPT) 4th stage air seal installed. That AD currently requires, based on engine model, replacement of the current design seal with a new design seal, or with a modified seal. This amendment adds the listing of certain engine serial numbers, to correct an error in the applicability section of AD 2000-25-06, for engines affected by PW Service Bulletin (SB) PW4 ENG 72-657, Revision 1, dated July, 19, 2000. This correction is prompted by comments received on AD 2000-25-06. The actions specified by this AD are intended to reduce stresses that could lead to LPT 4th stage air seal cracking, resulting in seal fracture, uncontained engine failure, and damage to the airplane.
2019-17-06: The FAA is adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F28 Mark 0070 and 0100 airplanes. This AD was prompted by reports of cracks on certain nose landing gear (NLG) turning tubes resulting from incorrectly applied repairs. This AD requires removing the affected parts and replacing them with serviceable parts. The FAA is issuing this AD to address the unsafe condition on these products.
2007-16-02: 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 airworthiness authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as keel beam rupture, which affects the structural integrity of the area. We are issuing this AD to require actions to correct the unsafe condition on these products.
78-26-11: 78-26-11 PIPER AIRCRAFT CORPORATION: Amendment 39-3380. Applies to Piper PA-31-350 Navajo Chieftain aircraft, Serial Numbers 31-5001 through 31-7852151, certificated in all categories. Compliance required within the next 25 hours of operation after the effective date of this AD. To insure free operation of the elevator control system, accomplish the following: 1. Install cable guide tube, Piper Part Number 71045-2, around the lightening hole in the frame at Fuselage Station 87.50, in accordance with the "Instructions" section of Piper Service Bulletin 621, dated October 13, 1978, or later edition approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. 2. Install nylon spiral sleeving around hydraulic line in accordance with the above referenced instructions. 3. Adjust elevator control cable tension in accordance with the above referenced instructions and instructions contained in the Piper PA-31-350 Navajo Chieftain Service Manual. Compliance with the provisions of this AD may be accomplished in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. This amendment becomes effective January 4, 1979.
2001-05-06: This amendment adopts a new airworthiness directive (AD) that is applicable to BMW Rolls-Royce (RR) GmbH models BR700-710A1-10 turbofan engines with fan disk part numbers (P/N's) BRR18803, BRR19248, or BRR20791 installed, and BR700-710A2-20 turbofan engines with fan disks P/N's BRR19248 or BRR20791 installed. This action requires initial and repetitive inspections of these fan disks for cracks, and if necessary replacement with serviceable parts. This amendment is prompted by reports of cracks in several fan disks in the dovetail area. The actions specified in this AD are intended to detect cracks in the fan disk, that could result in an uncontained engine failure and damage to the airplane.
2001-05-03: 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 apply Loctite on attaching bolt/screw threads of inboard, central, and outboard carriages; increase tightening torques of associated hardware; and replace central carriage attaching bolts. 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 loose, or the loss of, flap attaching bolts/screws, which could cause rough or irregular control. Such rough or irregular control could lead to the loss of control of the airplane.
2007-16-09: The FAA is superseding an existing airworthiness directive (AD), which applies to all EMBRAER Model ERJ 170-100 LR, -100 STD, -100 SE, and -100 SU airplanes. That AD currently requires repetitively replacing the low-stage check valve and associated seals of the right- hand engine bleed system. This new AD adds new airplanes to that existing requirement. For all airplanes, this AD also requires repetitively replacing the low-stage check valve and associated seals of the left-hand engine bleed system with a new check valve and new seals. This AD results from a report that an engine shut down during flight due to the failure of the low-stage check valve to close. We are issuing this AD to prevent failure of the low-stage check valve, which could result in an engine shutting down during flight.
2004-12-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42-500 and ATR72-212A series airplanes, that requires repetitive inspections for cracking of the upper closing rib of the vertical fin, related investigative actions, and corrective actions if necessary. This action is necessary to prevent interference between the upper closing rib and the rudder, which could result in a rudder jam and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2001-05-02: This amendment supersedes Airworthiness Directive (AD) 98-08-22, which currently requires inspecting the elevator and rudder attachment brackets for cracks and corrosion on certain Pilatus Aircraft Ltd. (Pilatus) Model PC-7 airplanes and replacing any cracked or corrosion-damaged parts . Since the issuance of AD 98-08-22, Pilatus has redesigned the brackets. Installation of these brackets should inhibit corrosion, which resulted in cracks or corrosion damage. This AD requires you to replace the elevator and rudder attachment brackets with parts of improved design. 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 failure of the elevator and rudder attachment brackets because of cracks or corrosion damage. Such failure could result in the elevator or rudder separating from the airplane with consequent loss of airplane control.
2018-07-02: We are adopting a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109E, A109S, AW109SP, A119, and AW119 MKII 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 products.