Results
2001-14-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires repetitive high frequency eddy current inspections to find cracking of the bulkhead frame support at body station 2598 under the hinge support fittings of the horizontal stabilizer, and repair if cracking is found. These actions are necessary to find and fix fatigue cracking in the frame support, which could result in inability of the structure to carry horizontal stabilizer flight loads and reduced controllability of the horizontal stabilizer. This action is intended to address the identified unsafe condition.
78-16-05: 78-16-05 PRATT & WHITNEY AIRCRAFT: Amendment 39-3274. Applies to all Pratt & Whitney Aircraft JT9D turbofan engines not incorporating an annular strainer element, in accordance with Pratt & Whitney Service Bulletin 4860 dated March 16, 1978, or later FAA approved revision, in the No. 4 bearing compartment. Compliance is required as indicated. To preclude failures of sixth stage turbine disks due to a plugged No. 4 bearing compartment oil scavenge tube, inspect the inside of the No. 4 bearing compartment sump for coke in accordance with the provisions of Pratt & Whitney Alert Service Bulletin No. 4826, dated October 17, 1977, or later FAA approved revision, in accordance with the following schedule: Engines with No. 4 bearing compartments having more than 6000 hours time in service since new or the last cleaning per ASB 4826: 1. Must have a daily visual tailpipe check for oil leakage from the No. 4 bearing compartment. If leakage is noted, the compartment must be inspected prior to further flight. The daily visual check may be discontinued after accomplishing the compartment inspection noted below. A flight crewmember may perform the daily check. NOTE: For the purpose of this AD, compliance with the daily visual check may be shown by recording accomplishment in accordance with FAR 121.380 or by amending the manual required by FAR 121.133 to include the check. 2. Must have the compartment inspected within the next 1500 hours time in service after the effective date of this AD, unless already accomplished, and every 5000 hours time in service thereafter. Engines having unacceptable coke formation in the forward portion of the No. 4 compartment sump area, as defined in Figure 2 of ASB 4826, must have the sump and compartment oil scavenge tube cleaned in accordance with the JT9D Engine Manual, P/N 646028, Section 72-53-00, prior to further flight. Upon request of the operator, an equivalent method of compliance with the requirements of this AD may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, New England Region. Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, New England Region, may adjust the initial inspection interval specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive, who have not already received these documents from the manufacturer, may obtain copies upon request to Pratt & Whitney Aircraft, Division of United Technologies Corporation, 400 Main Street, East Hartford, Connecticut 06108. These documents may also be examined at the Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD, which includes the incorporated material in full, is maintained by the FAA at its Headquarters in Washington, D.C., and at FAA, New England Region Headquarters, Burlington, Massachusetts. This amendment becomes effective September 12, 1978.
2016-22-10: We are adopting a new airworthiness directive (AD) for certain Turbomeca S.A. Arriel 1, 1A, 1A1, 1A2, 1B, 1B2, 1C, 1C1, 1C2, 1D, 1D1, 1E, 1E2, 1K1, 1S, and 1S1 turboshaft engines. This AD requires removing the centrifugal impeller and replacing with a part eligible for installation. This AD was prompted by an anomaly that occurred during the grinding operation required by modification TU376, which increases the clearance between the rear curvic coupling of the centrifugal impeller and the fuel injection manifold. We are issuing this AD to prevent failure of the centrifugal impeller, uncontained centrifugal impeller release, damage to the engine, and damage to the helicopter.
2010-18-52: This document publishes in the Federal Register an amendment adopting Emergency Airworthiness Directive (AD) 2010-18-52 which was sent previously to all known owners and operators of MD Helicopters, Inc. (MDHI) Model MD900 helicopters by individual letters. This AD requires visually inspecting the main rotor hub (hub) for a crack. If a crack is found, this AD requires, before further flight, replacing the unairworthy hub with an airworthy hub. Additionally, if a cracked hub is found, this AD requires reporting the finding to the Los Angeles Aircraft Certification Office within 10 days of finding the crack. This AD is prompted by two reports of cracks detected in the hub in the area near the flex beam bolt hole locations during maintenance on two MDHI Model MD900 helicopters. The actions specified by this AD are intended to detect a crack in the hub and prevent failure of the hub and subsequent loss of control of the helicopter.
47-10-30: 47-10-30 LOCKHEED: (Was Mandatory Note 33 of AD-763-3.) Applies to Model 49 Serials 2047 Up to and Including 2075 and to Serials Prior to 2047 Which Have Had 68092 Surge Box Flapper Valves Replaced by 285750 Valves in Accordance With Lockheed SI-15, Dated June 18, 1946. Compliance required prior to April 1, 1947. Replace fuel tank surge box flapper valves, LAC P/N 285750, with new type valve, LAC P/N 285750-600. (LAC Service Instructions 49/SI-15, revised August 10, 1946, and 49/SI-15A, revised August 3, 1946, or subsequent, cover this same subject.)
2001-14-11: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 747-100 and -200 series airplanes modified by Supplemental Type Certificate SA8622SW, that requires deactivation of the in-flight entertainment (IFE) system. This action is necessary to ensure that the flight crew is able to remove power from the IFE system when necessary. Inability to remove power from the IFE system during a non-normal or emergency situation could result in inability to control smoke or fumes in the airplane flight deck or cabin. This action is intended to address the identified unsafe condition.
2016-22-01: We are adopting a new airworthiness directive (AD) for Schempp-Hirth Flugzeugbau GmbH Models Discus-2a, Discus-2b, Discus-2c, Discus 2cT, Ventus-2a, and Ventus-2b gliders. 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 insufficient overlap of the airbrake panels. We are issuing this AD to correct the unsafe condition on these products.
2001-14-15: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 747-400 series airplanes modified by Supplemental Type Certificate (STC) SA8843SW, that requires modifying the passenger entertainment system (PES) installed by that STC and revising the Airplane Flight Manual. This action is necessary to ensure that the flight crew is able to remove electrical power from the PES when necessary and is advised of appropriate procedures for such action. Inability to remove power from the PES during a non-normal or emergency situation could result in inability to control smoke or fumes in the airplane flight deck or cabin. This action is intended to address the identified unsafe condition.
50-38-02: 50-38-02 BELL: (a) Applies to All Models 47B, 47B-S, 47B3, 47B3-S, 47D and 47D-S; (b) Applies to Model 47D1, Serial Numbers 145 Through 164, 174 Through 183. Compliance required before November 15, 1950. Service difficulties have been experienced involving fan bearing failure due to improper adjustment of the cooling fan belt. This allows the cooling fan to move forward and jam the cyclic controls. To prevent such failures, fan belt tension should be properly adjusted. In addition, a fan shaft washer should be incorporated to prevent the fan from jamming the cyclic control in case bearing failure does occur. (Bell Service Bulletin No. 61 dated July 20, 1950, covers this subject for models under (a). Bell Service Bulletin No. 72 dated August 4, 1950, covers this subject for models under (b).)
2022-25-11: 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 maintenance requirements and airworthiness tasks are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness tasks, 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.
2025-13-03: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by a determination that the applicable aircraft flight manual (AFM) was providing an incorrect value for maximum cumulative taxi time in freezing fog conditions. This AD requires revising the existing AFM to provide the flightcrew with normal procedures to follow under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
2001-14-10: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 737-300 series airplanes modified by Supplemental Type Certificate ST00171SE, that requires installation of a master switch to apply and remove power from the in-flight entertainment (IFE) system, and revision of the Airplane Flight Manual. This action is necessary to ensure that the flight crew is able to remove electrical power from the IFE system when necessary and is advised of appropriate procedures for such action. Inability to remove power from the IFE system during a non-normal or emergency situation could result in inability to control smoke or fumes in the airplane flight deck or cabin. This action is intended to address the identified unsafe condition.
2001-14-14: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 747SP series airplanes modified by Supplemental Type Certificate (STC) ST09097AC-D, that requires modifying the passenger entertainment system (PES) installed by that STC and revising the Airplane Flight Manual. This action is necessary to ensure that the flight crew is able to remove electrical power from the PES when necessary and is advised of appropriate procedures for such action. Inability to remove power from the PES during a non-normal or emergency situation could result in inability to control smoke or fumes in the airplane flight deck or cabin. This action is intended to address the identified unsafe condition.
98-01-20: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A310 and A300-600 series airplanes. This action requires a one-time inspection of the attachment bolts and washers for the forward cargo container and pallet latches in the aft cargo compartment to determine if bolts and washers having the correct part numbers are installed; and replacement of the bolts and washers with parts having the correct part numbers, if necessary. This AD also requires revising the Airplane Flight Manual and certain supplements to specify certain cargo loading procedures that must be used until the inspection is accomplished. 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 cargo from shifting in flight, and consequent structural damage and reduced controllability of the airplane.
46-06-05: 46-06-05 STINSON: (Was Service Note 1 of AD-556-1.) Applies to All Model A Aircraft. After each 100 hours of operation, make a visual inspection (using at least a 4-power magnifying glass) of the main spar lower fittings at the outer wing panel to inner wing panel connection for small fatigue cracks at the fish-mouth weld connecting the fittings to the chord tubes of the spar. These cracks are most likely to originate at the inboard corners of the fish- mouth weld on the outer panel fitting. If any cracks are found, repairs should be made before further operation of the aircraft. Proposed methods of repair should be submitted for engineering approval.
2016-22-06: We are adopting a new airworthiness directive (AD) for all Diamond Aircraft Industries GmbH Models DA 40 NG, DA 42 NG, and DA 42 M-NG airplanes. 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 cracked autopilot bridle cable clamps. We are issuing this AD to correct the unsafe condition on these products
89-18-03 R1: 89-18-03 R1 AEROSPATIALE: Amendment 39-6304 as revised by Amendment 39-6569. Docket No. 89-NM-245-AD. Applicability: Model ATR42 series airplanes, Serial Numbers 003 through 147, certificated in any category. Compliance is required as indicated, unless previously accomplished. To prevent migration of the aileron control tab hinge pins, accomplish the following: A. Within 7 days after June 12, 1989 (the effective date of AD 89-12-05, Amendment 39-6229), for airplanes Serial Numbers 003 through 068, modify the aileron control tab hinge pins in accordance with Part B of Aerospatiale Service Bulletin ATR42-57-0019, Revision 1, dated June 7, 1989. B. Within 7 days after June 12, 1989 (the effective date of AD 89-12-05, Amendment 39-6229), for airplanes Serial Numbers 003 through 135, perform an inspection of the aileron control tab hinge pins in accordance with Part B of Aerospatiale Service Bulletin ATR42-57-0028, Revision 2, dated July 25, 1989. If the inspection reveals that the end knuckle is not peened, prior to further flight, modify the aileron control tab hinge pins in accordance with the service bulletin. C. Within 7 days after September 5, 1989 (the effective date of AD 89-18-03, Amendment 39-6304), for airplanes Serial Numbers 003 through 147, unless accomplished within the last 50 hours time-in-service, inspect all aileroncontrol tab hinges to determine if the hinge pin has visibly migrated out of its housing. If the inspection reveals that a hinge pin has migrated, prior to further flight, push the hinge pin back into its housing. Repeat the inspection for hinge pin migration, and the associated repair, if necessary, at intervals not to exceed 50 hours time-in-service. D. Within 60 days after the effective date of this amendment, for airplanes Serial Numbers 003 through 147, install new hinge pins and stop plates, in accordance with Service Bulletin ATR42-57-0030, Revision 2, dated September 18, 1989; or Revision 3,dated September 18, 1989; or Revision 4, dated January 10, 1990. This modification constitutes terminating action for the repetitive inspections required by paragraph C., above. E. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Standardization Branch, ANM-113. F. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. Airworthiness Directive 89-18-03 superseded AD 89-12-05, Amendment 39-6229. This AD revises AD 89-18-03, Amendment 39-6304 . This amendment (39-6569, AD 89-18-03 R1) becomes effective on May 14, 1990.
2001-14-17: This amendment adopts a new airworthiness directive (AD) that is applicable to all Airbus Model A300 B2 and B4 series airplanes. This action requires a one-time inspection to detect and correct corrosion of the lower bulkhead attachment, and corrective action, if necessary. This action is necessary to detect and correct corrosion of the lower bulkhead attachment, which could result in reduced structural integrity of the rear pressure bulkhead and consequent damage to components of the flight control, hydraulic, and auxiliary power unit fuel systems. This action is intended to address the identified unsafe condition.
78-11-05: 78-11-05 CESSNA: Amendment 39-3225. Applies to Model 210M, T210M and P210 (Serial Numbers 21061574 through 21062583, and P2100001 through P2100010); Model 310R and T310R (Serial Numbers 310R0501 through 310R1302, 310R1304 through 310R1315, 310R1317, and 310R1318); Model 340A (Serial Numbers 340A0001 through 340A0458, 340A0460 through 340A0466, 340A0468, and 340A0470 through 340A0483); Model 402B (Serial Numbers 402B1001 through 402B1331 and 402B1333 through 402B1338); Model 404 (Serial Numbers 404-0001 through 404-0218, and 404-0220 through 404-0222); Model 414 and 414A (Serial Numbers 414-0801 through 414-0965, 414A0001 through 414A0032, 414A0034 through 414A0038, and 414A0040 through 414A0047); and Model 421C (Serial Numbers 421C0001 through 421C0479 and 421C0481 through 421C0488) airplanes incorporating ARC Model 400B autopilot installations. To preclude increased flight control forces caused by an autopilot actuator that has failed to disengage when the autopilot is disconnected, unless already accomplished: A) On airplanes not modified in accordance with Cessna Service Letter No. AV78-6, dated March 31, 1978, or later revision, before next flight, disable the Model 400B autopilot: 1. On affected 300 and 400 series airplanes by pulling and banding autopilot computer (COMP.) and actuator (ACT.) circuit breakers; 2. On affected 210 series airplanes by disconnecting the connector at the roll and pitch actuators and securing these connectors to prevent them from interfering with the flight controls; and install a locally fabricated placard in plain view of the pilot indicating "AUTOPILOT INOPERATIVE." NOTE: The autopilot disabling and installation of a locally fabricated placard required by Paragraph A on affected 300 and 400 series airplanes constitutes preventative maintenance and may be performed by persons authorized to perform preventative maintenance under FAR 43. B) Upon accomplishment of the electrical autopilot actuator modification set forth in Cessna Service Letter No. AV78-6, dated March 31, 1978, or later revision, the autopilot may be returned to service and the "AUTOPILOT INOPERATIVE" placard removed. C) Airplanes may be flown to a base where Paragraph A of this AD may be accomplished if the autopilot is not used. D) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective June 5, 1978, to all persons except those to whom it has already been made effective by air mail letter from the FAA dated May 11, 1978.
2025-13-07: The FAA is adopting a new airworthiness directive (AD) for all Safran Helicopter Engines, S.A. (Safran) Model ARRIUS 2B2 engines. This AD was prompted by a manufacturer review of collected data from in- service engines that indicated the preference injector may clog over time caused by fuel coking, which decreases the permeability of the preference injector. This AD requires initial and repetitive non- extinguishing tests for engine flameout and replacement of the preference injector if necessary, a one-time modification (software upgrade) of the electronic engine control unit (EECU) and, for certain engines, repetitive replacements of the preference injector. The FAA is issuing this AD to address the unsafe condition on these products.
2001-14-05: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 737-600, -700, -700C, and -800 series airplanes. This action prohibits installation of repairs of the elevator tab using previously approved repair procedures. This action is necessary to prevent installation of repairs of the elevator tab that are outside allowable limits, which could result in excessive in-flight vibrations of the elevator tab, and consequent loss of controllability of the airplane.
2016-20-13: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200 and -300 series airplanes; and Model A340-200 and -300 series airplanes. This AD was prompted by a determination that the compliance times for certain post-repair inspections and certain allowable damage limits (ADLs) must be reduced in order to address fatigue. This AD requires identifying any repairs and ADLs used to assess or control any structural damage on certain structural areas, and corrective action if necessary. We are issuing this AD to prevent fatigue damage on primary structure and structural repairs, which could result in reduced structural integrity of the airplane.
2001-13-28: This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce Limited, Aero Division-Bristol, S.N.E.C.M.A. (RR) Olympus 593 Mk. 610-14-28 turbofan engines. This action requires replacement of the low-oil pressure (LOP) switch. This amendment is prompted by a report of the failure of the low pressure (LP) and high pressure (HP) rotor thrust bearings due to oil starvation that was caused by the loss of the LOP switch function and resulted in a delayed engine shutdown. The actions specified in this AD are intended to prevent the failure of the LOP switch to indicate an LOP event, which could contribute to uncontained engine failure due to oil starvation in the thrust bearings.
2016-19-14: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318 and A319 series airplanes; Model A320-211, -212, - 214, -231, -232, and -233 airplanes; and Model A321 series airplanes. This AD was prompted by a report of cracks found during maintenance inspections on certain lugs of the 10VU rack side fittings in the cockpit. This AD requires repetitive inspections for cracking of the lugs on the 10VU rack side fittings, and repair of any cracking. We are issuing this AD to prevent reading difficulties of flight-critical information displayed to the flightcrew during a critical phase of flight, such as an approach or takeoff, which could result in loss of airplane control at an altitude insufficient for recovery.
2001-13-25: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-200 and -300 series airplanes, that currently requires repetitive inspections to detect chafing or arcing damage to the cable/wire and fuel tube assemblies on the right-hand side of each engine, and replacement with new components, if necessary. That AD also provides for an optional terminating action for the repetitive inspections required by that AD. This amendment requires accomplishment of the previously optional terminating action. The actions specified by this AD are intended to prevent chafing of the cable/wire bundles against the fuel line, which could result in arcing and a consequent fire or explosion. This action is intended to address the identified unsafe condition.