Results
2002-23-10: This amendment adopts a new airworthiness directive (AD) that applies to all Piaggio Aero Industries S.p.A. Model P-180 airplanes. This AD requires you to inspect for proper clearance between the first outboard flap control rod and the bleed air duct for interference, replace worn or damaged parts or correct interference, and adjust clearance. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Italy. The actions specified by this AD are intended to detect and correct interference or damage of the first outboard flap control rod and bleed air duct, which could result in failure of the flap control rod. Such failure could lead to loss of airplane control.
75-16-03: 75-16-03 MCDONNELL DOUGLAS: Amendment 39-2276. Applies to all Model DC-9 Series airplanes, certificated in all categories, including Military C-9A, C-9B, and VC-9C. \n\n\tCompliance required as indicated. \n\n\tTo prevent possible restriction of operation of the nose landing gear manual release system as the result of the accumulation of liquids and formation of ice in the nose landing gear emergency uplock release mechanism pressure can, P/N 9910073-87, accomplish the following: \n\n\t(a)\tWithin 12 flight hours time in service after the effective date of this AD, unless already accomplished: \n\n\t\t(1)\tPermanently remove the pressure can drain plug, P/N 1103-1 (refer to paragraph (c)(2) for disposition of plug); and, \n\n\t\t(2)\tInspect for and drain any liquid. \n\n\t(b)\tThereafter, for those airplanes with the nutplate retained and the cover not installed: \n\n\t\t(1)\tCheck once daily while in service, until (c) below is accomplished, to ascertain that the drain hole is clear; or,(2)\tDrill a .190/.194 diameter hole in bottom of the can, 5/8 inch outboard of centerline of and in line with the existing .190/.194 diameter nutplate clearance hole, and inspect at intervals not to exceed 100 hours time in service, until (c) below, is accomplished, to ascertain that the drain hole is clear. \n\n\t(c)\tWithin the next 1600 hours time in service after the effective date of this AD, unless already accomplished: \n\n\t\t(1)\tModify the nose landing gear emergency uplock release mechanism pressure can, P/N 9910073-87, in accordance with the instructions in Douglas Service Bulletin 53-91, or later FAA-approved revisions, or an equivalent means approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tNOTE: 1. The drain plug nutplate, listed in S/B 53-91 as an optional removal item, must be permanently removed per the requirements of this paragraph; or, \n\n\t\t2.\tIncorporate a .190/.194 diameter hole as outlined in (b) (2), above, in lieu of removing the nutplate. \n\n\t\t(2)\tFor those airplanes that do not have the nutplate removed after compliance with (c)(1), above, the drain plug may be reinstalled at the operator's discretion, provided that the drain hole is incorporated. \n\n\tNOTE: The checks required per this AD may be performed by a flight crew member or other person designated by the operator. \n\n\t(d)\tThe requirements of this AD may be terminated when (c), above, has been accomplished. \n\n\tThis supersedes Amendment 39-2215, 40 F.R. 22538, AD 75-11-08. \n\n\tThis amendment is effective August 1, 1975 for all persons except those to whom it was made effective by airmail letters dated May 28, 1975, which contained this amendment.
96-04-01: This amendment supersedes an existing airworthiness directive (AD), applicable to AlliedSignal Inc. (formerly Garrett Engine Division) TFE731 series turbofan engines, that currently requires eddy current inspection of certain fan rotor disks for cracks, and replacement, if necessary, with serviceable parts. This amendment requires reinspection of 33 additional fan rotor disks, beyond the quantity of reinspections required by AD 93-25-16. This amendment is prompted by discrepancies in several magnetic tape records discovered as a result of recent improvements in the inspection tape review process. The actions specified by this AD are intended to prevent an uncontained failure of the fan rotor disk due to fatigue cracking in the dovetail slots, which can result in inflight engine shutdowns, severe secondary damage, and fan rotor assembly separation from the engine.
2024-06-07: The FAA is superseding Airworthiness Directive (AD) 2020-05- 16, which applied to certain Airbus SAS Model A319-115 airplanes; Model A320-214, -216, -232, -251N, and -271N airplanes; and Model A321-211, - 231, -251N, -251NX, -253N, -271N, -271NX, and -272N airplanes. AD 2020- 05-16 required a one-time detailed inspection of certain attaching points on the left-hand and right-hand wings for the correct installation of certain hardware, and, depending on findings, accomplishment of applicable corrective actions. This AD was prompted by reports of incomplete installations of the over wing panel lug attachments in the production assembly line and a determination that additional airplanes are subject to the unsafe condition. This AD continues to require the actions in AD 2020-05-16 and adds airplanes to the applicability, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2024-06-11: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A310 series airplanes. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2002-23-11: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) 200, 300, and 1900 series, and Models F90 and A100-1 airplanes. This AD requires you to check the airplane logbook to determine if the elevator(s) has/have been removed from the airplane. If the elevator(s) has/have been removed, this AD also requires you to inspect the elevator balance weight attachment screws for correct length, and, if necessary, install new bolts that are of improved design and rebalance the elevator, depending on the results of the inspection. This AD is the result of the elevator balance weight attachment screws and balance weights being improperly installed when balancing the elevator after it had been removed for repair or repainting. The actions specified by this AD are intended to prevent the balance weight attachment screws from becoming loose. Loose screws could come into contact and interfere with the horizontal stabilizer. This interference could restrict elevator movement and result in loss of elevator pitch control.
2002-23-06: This amendment supersedes an emergency airworthiness directive (AD) that was sent previously to all known U.S. owners and operators of Textron Lycoming (T/L) AEIO-540, IO-540, LTIO-540, O-540, and TIO-540 series reciprocating engines. That action requires replacing certain zinc-plated crankshaft gear retaining bolts. This action still requires replacing certain zinc-plated crankshaft gear retaining bolts, but expands the population of affected engines. This amendment is prompted by two recent failures of zinc-plated crankshaft gear retaining bolts, and a reassessment of the extent to which the suspect bolts may still be present in the field. The actions specified by this AD are intended to prevent loss of all engine power and possible forced landing.
99-21-17: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A321 series airplanes. This action requires reinforcement of the fuselage structure between frames 62 and 64. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent the loss of structural integrity of the rear part of the fuselage structure in the event of an undetected tail scrape during landing or takeoff.
2024-05-07: The FAA is adopting a new airworthiness directive (AD) for all Leonardo S.p.a. Model AW189 helicopters. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the airworthiness limitations section (ALS) of the existing helicopter maintenance manual or instructions for continued airworthiness (ICA) for your helicopter and the existing approved maintenance or inspection program for your helicopter, as applicable, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2011-05-12: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires repetitive detailed inspections for disbonding and tearing and measurements for wear of the internal diameter (ID) of the Karon-lined bushings of the bulkhead support jackscrew fitting and of the jackscrew fitting of the horizontal stabilizer; and reinstallation of the horizontal stabilizer trim actuator (HSTA) after inspection and measurement; and if necessary, replacement of the bushings with new bushings and all applicable related investigative and corrective actions. This AD was prompted by a report indicating that a Karon-lined bushing with the liner broken into five pieces was found during a scheduled inspection of the HSTA components; the broken liner had worn and disbonded from the bushing. We are issuing this AD to detect and correct discrepancies of the HSTA attachment locations, which could result in reduced structural integrity of the horizontal stabilizer and consequent loss of controllability of the airplane.
2002-23-01: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Gulfstream Aerospace LP Model Galaxy and Gulfstream 200 airplanes. This action requires a one-time inspection for evidence of damage to the forward engine cross spar assembly; and repair if necessary. This action is necessary to detect and correct damage to the forward engine cross spar assembly, which could result in reduced structural integrity of the forward engine cross spar assembly. This action is intended to address the identified unsafe condition.
2024-06-51: The FAA is superseding airworthiness directive (AD) 2024-05- 51, which applied to certain General Electric Company (GE) Model CT7- 2E1, CT7-2F1, CT7-8A, CT7-8E, and CT7-8F5 engines, and various restricted category helicopters with GE Model T700-GE-700, -701A, - 701C, -701D/CC, -701D, -401, -401C, CT7-2D, or CT7-2D1 engines installed. AD 2024-05-51 required a phase array ultrasonic inspection of the torque reference tube magnetic insert braze joint of the power turbine (PT) drive shaft assembly for inadequate braze coverage, and repair or replacement of the PT drive shaft assembly if necessary. This AD was prompted by at least four reports of failures of the torque reference tube magnetic insert braze joint of the PT drive shaft assembly within the last several months. This AD retains the requirements of AD 2024-05-51 and expands the applicability to include a PT drive shaft assembly part number that was inadvertently omitted. The FAA previously sent an emergency AD to all known U.S. owners and operators of these engines and helicopters and is now issuing this AD to address the unsafe condition on these products.
98-12-28: This amendment adopts a new airworthiness directive (AD), applicable to all CASA Model C-212 series airplanes, that requires repetitive inspections for cracking in the false spar of the wing, and repair, if necessary. 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 detect and correct cracking in the false spar, which could result in reduced structural integrity of the wing.
81-06-51 R1: 81-06-51 R1 BOEING: Amendment 39-4110 as amended by Amendment 39-4445. Applies to Boeing Model 707/720 series airplanes, certificated in all categories, prior to line number 885. To assure continued structural integrity of the outboard wing, accomplish the following within the next 75 hours time-in-service unless accomplished since January 1, 1980: \n\n\t1.\tPerform a one-time visual inspection and repeat visual inspections at intervals not exceeding one year, in accordance with Boeing Service Bulletin A3308, Revision 2, dated July 10, 1981, or later revision approved by the Manager, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region. The first repetitive inspection shall be accomplished within a year of the last inspection (AD 81-06-51) or within 90 days after the effective date of this amendment, whichever occurs later. \n\n\t2.\tAfter inspection, spray the area with BMS 3-23 organic corrosion inhibitor or equivalent.\n \n\t3.\tParts found cracked must be repaired in accordance with Boeing Service Bulletin A3308 or replaced prior to further flight except that airplanes may be flown to a maintenance base for repairs or replacement in accordance with FAR 21.197 and 21.199 with prior approval of the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Region.\n\n \t4.\tEquivalent inspections and repairs may be used when approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Region.\n \n\tThe manufacturers specifications and procedures identified and described in this amendment are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). \n\n\tAll persons affected by this directive who have not already received the service document from the manufacturer may obtain copies upon request to The Boeing Company, P.O. Box 3707, Seattle, Washington 98124. These documents also may be examined at FAA Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tAmendment 39-4110 became effective May 18, 1981, and was effective earlier to those recipients of telegraphic AD T81-06-51, dated March 6, 1981. \n\n\tThis Amendment 39-4445 becomes effective September 30, 1982.
2024-05-06: The FAA is adopting a new airworthiness directive (AD) for all Leonardo S.p.a Model AW169 helicopters. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the airworthiness limitations section (ALS) of the existing helicopter maintenance manual or instructions for continued airworthiness (ICA) for your helicopter and the existing approved maintenance or inspection program for your helicopter, as applicable, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2002-22-17: This amendment adopts a new airworthiness directive (AD) that applies to all Cessna Aircraft Company (Cessna) Models 208 and 208B airplanes. This AD requires you to repetitively inspect the inboard forward flap bellcranks for cracks or replace bellcranks depending on the amount of usage. This AD is the result of Cessna re-evaluating the bellcrank life limit analysis and determining that the original estimate is too high. The actions specified by this AD are intended to detect, correct, and prevent future cracks in the bellcrank, which could result in failure of this part. Such failure could lead to damage to the flap system and surrounding structure and result in reduced or loss of control of the airplane.
2018-02-11: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-301, -321, -322 and -342 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 report of cracking in the top skin of the horizontal stabilizer (HS) center box (CB) of an airplane in pre-modification 41330 configuration. We are issuing this AD to address the unsafe condition on these products.
2002-22-14: This amendment supersedes an existing airworthiness directive (AD) for specified Bell Helicopter Textron, Inc. (BHTI) model helicopters that requires reducing the retirement time for certain main rotor tension-torsion (TT) straps on those models and on the Model UH-1 series helicopters. This document contains the same requirements as the existing AD but removes the Model UH-1 series restricted category helicopters and adds the BHTI Model 205A and 205B helicopters to the applicability. This amendment is prompted by the issuance of a separate AD for the Model UH-1 series helicopters and the need to add the BHTI Model 205A and 205B helicopters to the applicability because the affected straps are eligible for installation on these model helicopters. The actions specified by this AD are intended to prevent failure of a TT strap, loss of a main rotor blade, and subsequent loss of control of the helicopter.
98-16-23: This amendment adopts a new airworthiness directive (AD), applicable to all CASA Model CN-235 series airplanes, that requires repetitive high frequency eddy current (HFEC) inspections of the flap transmission shafts to detect cracking, and repetitive functional tests (checks) to verify proper operation of the flap braking sub-system; and corrective actions, if necessary. 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 detect and correct cracking in the flap transmission shafts, and to correct a malfunctioning flap braking sub-system, which could result in the inability to move the flaps, or in an asymmetric flap condition, and consequent reduced controllability of the airplane.
95-26-02: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Textron Lycoming reciprocating engines installed on certain aircraft identified by registration numbers. This action supersedes priority letter AD 94-14-13 that currently requires engines certified to operate on 91 octane or higher aviation gasoline (avgas) to undergo a teardown and analytical inspection for detonation damage, and engines certified to operate on 80 octane avgas to undergo inspection for evidence of possible internal engine damage. This action revises incorrect engine model numbers and aircraft registration numbers listed in the priority letter AD. This amendment is prompted by the Federal Aviation Administration (FAA) receiving more accurate information concerning which aircraft were fueled with the contaminated mixture at the affected airports. The actions specified by this AD are intended to prevent detonation due to low octane, which can result in severe engine damage and subsequent failure.
2024-05-09: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 757-200, -200CB, and -300 series airplanes. This AD was prompted by a report of a crack at fuselage station (STA) 1640 frame web common to the lower hinge intercostal tee clip center hole of the upper fastener row. This AD requires a maintenance records check for existing repairs at STA 1640, repetitive ultrasonic (UT) inspections for cracking of the frame web, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
95-26-14: This amendment adopts a new airworthiness directive (AD) that applies to Beech Aircraft Corporation (Beech) Model 1900D airplanes. This action will require inspecting the cabin partition to ensure that a right-hand forward partition bracket exists on certain airplanes, installing this bracket if it does not exist, and improving the right-hand forward partition installation on all affected airplanes. The actions specified by this AD are intended to prevent cabin partition failure because of a structural deficiency in the bracket or if the bracket is not installed, which, if not detected and corrected, could cause passenger injury if the partition could not withstand the load incurred with the baggage compartment loaded to its 250-pound limit.
96-01-02: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that currently requires a visual inspection to detect cracks or discrepancies in the aft mount beam assembly of the engines; and replacement of the cracked or discrepant aft mount beam assembly with a new assembly, or a previously inspected and re-identified assembly. That amendment was prompted by reports of cracking in a certain aft mount beam assembly. This new amendment requires additional inspections to detect cracks or discrepancies in the subject area, and various follow-on actions. The actions specified by this amendment are intended to prevent cracks in the aft mount beam assembly of the engines, which could result in loss of the capability of the aft mount beam assembly to support engine loads, and possible separation of the engine from the airplane.
2002-20-07 R1: This amendment revises an existing airworthiness directive (AD), applicable to all Boeing Model 737 series airplanes, that currently requires installation of a new rudder control system and changes to the adjacent systems to accommodate that new rudder control system. That amendment would have superseded seven existing ADs; however, this new amendment removes any reference to superseding four of those seven ADs. This new amendment is prompted by an FAA determination that the requirements of those four ADs must remain in effect until installation of the new rudder control system and corresponding changes to the adjacent systems. The actions specified in this AD are intended to prevent an uncommanded rudder hardover event and consequent loss of control of the airplane due to inherent failure modes, including single-jam modes, and certain latent failures or jams combined with a second failure or jam.
2024-03-08: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by reports that some overheat detection sensing elements of the bleed air leak detection system were manufactured with insufficient salt fill, which can result in an inability to detect hot bleed air leaks. This AD requires maintenance records verification, and if an affected part is installed, would prohibit the use of certain Master Minimum Equipment List (MMEL) items under certain conditions by requiring revising the operator's existing Minimum Equipment List (MEL). This AD also requires testing the overheat detection sensing elements, marking each serviceable sensing element with a witness mark, and replacing each nonserviceable part with a serviceable part. This AD also prohibits the installation of affected parts under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.