Results
2000-08-07: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Raytheon Model BAe 125-800A and BAe 125-800B, Model Hawker 800, and Model Hawker 800XP series airplanes, that currently requires the filling of two tooling holes on the firewalls of the left and right engine pylons with firewall sealant. This amendment requires the sealing of all unused (open) tooling holes on the firewalls of the left and right engine pylons, and expands the applicability to include additional airplanes. This amendment is prompted by reports of additional unused (open) tooling holes, found at locations other than those currently addressed. The actions specified by this AD are intended to prevent an engine fire from moving to the fuselage and to the lines that carry flammable fluid that are located inboard of the firewall. The incorporation by reference of Raytheon Service Bulletin SB.54-1-3815B, dated March 26, 1996, as listed in the regulations, was approved previously by the Director of the Federal Register as of January 27, 1997 (61 FR 66878, December 19, 1996).
2018-17-09: We are superseding Airworthiness Directive (AD) 2014-05-28, which applied to certain Bombardier, Inc., Model DHC-8-400 series airplanes. AD 2014-05-28 required revising the maintenance or inspection program, as applicable. This AD requires revising the maintenance or inspection program, as applicable, to include a revised task. This AD was prompted by a determination that the interval from Maintenance Review Board (MRB) task number 323100-202 should not be escalated, and that Certification Maintenance Requirements (CMR) task number 323100-102 should be applicable to all Model DHC-8-400 series airplanes, regardless of which main landing gear (MLG) up-lock assembly is installed. We are issuing this AD to address the unsafe condition on these products.
86-24-04: 86-24-04 BRITISH AIRCRAFT CORPORATION: Amendment 39-5477. Applies to Model 1-11 200 and 400 series airplanes, modified in accordance with Air Cruisers Company STC SA840EA, as listed in Air Cruisers Company Alert Service Bulletin 203-25-A2, dated November 17, 1986, certificated in any category. Compliance required as indicated, unless previously accomplished. To preclude the potential for jamming of the passenger or service doors, accomplish the following: A. Within the next 10 hours time-in-service and at intervals not to exceed 120 hours time-in-service thereafter, perform the visual inspection of the container latch release cable, and replace, if necessary, in accordance with Air Cruisers Alert Service Bulletin 203-25-A2, dated November 17, 1986, or later FAA-approved revisions. B. Prior to modification of any airplane in accordance with Air Cruisers Company STC SA840EA, visually inspect the container latch release cable and replace, if necessary, in accordancewith Paragraph 3.0 of Air Cruisers Alert Service Bulletin 203-25-A2, dated November 17, 1986, or later FAA-approved revisions. C. Inspections required by paragraph A., above, may be discontinued upon incorporation of a modification approved by the Manager, New York Aircraft Certification Office, FAA, New England Region. D. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, New York Aircraft Certification Office, FAA, New England Region. E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a location where the requirements of this AD may be accomplished. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to Air Cruisers Company, P.O. Box 180, Belmar, New Jersey 07719-0180. This information may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or FAA, New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York. This amendment becomes effective December 19, 1986.
67-17-02: 67-17-02 BRITISH AIRCRAFT: Amdt. 39-421 Part 39 Federal Register May 18, 1967. Applies to Model BAC 1-11 Series Airplanes. Compliance required within the next 1,000 hours' time in service after the effective date of this AD, unless already accomplished. To prevent a potential fire hazard in the forward and aft freight compartments, modify the light assemblies, as shown in the table (below), by providing ventilating holes in the light cup assemblies and by replacing the nylon lamp cover with a 5/32 inch toughened glass lamp cover, or FAA-approved equivalent, in accordance with British Aircraft Corporation BAC 1-11 Service Bulletin No. 33-PM 1706, or later ARB-approved issue. Sta. No. Mod.App. Pre-Mod.BAC P/N Post Mod.BAC P/N 200 Ser.Post Mod.P/N 400 256 200&400 AB 28A 15593 AC 28A 5099 AK 28A 26277 296 200&400 AB 28A 15591 AC 28A 5097 AC 28A 5097 336 200&400 AB 28A 15593 AC 28A 5099 AK 28A 26277 376 200&400 AB 28A 15591 AC 28A 5097 AC 28A 5097 396 200&400 AB 28A 15593 AC 28A 5099 AC 28A 5099 670 200&400 AB 27A 17335 AC 27A 5487 AC 27A 5487 710 200&400 AB 28A 15591 AC 28A 5097 AC 28A 5097 750 200 Ser. AB 27A 17336 AC 27A 14439 750 400 Ser. AB 27A 17335 AC 28A 14439 This directive effective June 17, 1967.
2018-17-08: We are superseding Airworthiness Directive (AD) 2016-03-03 for all Rolls-Royce plc (RR) Viper Mk. 521, Viper Mk. 522, and Viper Mk. 601-22 turbojet engines. AD 2016-03-03 required reducing the life of certain critical parts. This AD requires reducing the life of certain critical parts and adds additional engine parts to the applicability. This AD was prompted by a determination made by RR that additional parts for the applicable RR Viper turbojet engine models are affected. We are issuing this AD to address the unsafe condition on these products.
2018-17-10: We are superseding Airworthiness Directive (AD) 2017-15-17, which applied to certain Airbus Model A300 B4-600R series airplanes, Model A300 C4-605R Variant F airplanes, and Model A300 F4-600R series airplanes. AD 2017-15-17 required an inspection of the lower area of a certain frame (FR) radius for cracking, and corrective action if necessary. This AD requires new repetitive inspections of the forward fitting lower radius of a certain frame for cracking, and corrective actions if necessary. This AD was prompted by a determination that repetitive inspections and applicable corrective actions are necessary. We are issuing this AD to address the unsafe condition on these products.
99-23-14: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300, series airplanes, that currently requires certain changes to the procedures in the Airplane Flight Manual (AFM) related to operation of the emergency lighting system. This action requires modification of the emergency lighting system and a revision to the AFM to ensure the preservation of the airplane batteries. This action also provides, for certain airplanes, terminating action for the existing AFM revision, and replacement with a different AFM revision. This action also expands the applicability to include certain model A310 and A300-600 series airplanes. 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 ensure that the emergency lighting is available for evacuation in an emergency situation.
2006-17-09: The FAA is adopting a new airworthiness directive (AD) for all Fokker Model F27 Mark 050 airplanes. This AD requires doing an initial inspection of the leading edge sections of the elevators to detect loose leading edges and to ensure that there is no gap between the sections and the front spar, and corrective actions if necessary. This AD also requires determining the type of leading edge installed on the elevators. For certain airplanes, this AD requires repetitive inspections until the modification of the leading edge sections of the elevators and the application of sealant, which would end the repetitive inspections. This AD results from reports that the leading edges of the elevators were found loose, although the fasteners were still in place; in one case a stud was broken. In addition, the fastener attachment holes were elongated and worn out, and fretting damage was found on the elevator front spar and balance weights. Investigation revealed that vibration, induced bythe propeller slipstream, was the cause of these discrepancies; the stud failure was due to improper installation of the fasteners. We are issuing this AD to prevent jamming, restricting, or binding of the elevators due to loose or missing fasteners, which could make the movement of the elevator difficult and decrease aerodynamic control of the airplane.
2006-16-18: The FAA is adopting a new airworthiness directive (AD). The new AD is for Sandel Avionics Incorporated Model ST3400 TAWS/RMI units as described above. This AD requires installing a warning placard on the TAWS/RMI and revising the Limitations section of the airplane flight manual (AFM). This AD also requires installing upgraded software in the TAWS/RMI. This AD results from a report that an in-flight bearing error occurred in a Model ST3400 TAWS/RMI configured to receive bearing information from a very high frequency omnidirectional range (VOR) receiver interface via a composite video signal, due to a combination of input signal fault and software error. We are issuing this AD to prevent a bearing error, which could lead to an airplane departing from its scheduled flight path, which could result in a reduction in separation from, and a possible collision with, other aircraft or terrain.
2018-17-04: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce Corporation (RRC) AE 2100D2A and AE 2100D3 model turboprop engines and AE 3007A2 model turbofan engines. This AD was prompted by the possibility of a low-cycle fatigue failure on certain turbine wheels. This AD requires removing the affected turbine wheels at the next engine shop visit or before reaching the new reduced life limit, whichever occurs first, and replacing them with parts eligible for installation. We are issuing this AD to address the unsafe condition on these products.
69-14-02: 69-14-02 VICKERS VISCOUNT: Amdt. 39-792. Applies to Viscount Model 745D and 810 Series Aircraft. Compliance required as indicated unless already accomplished. To prevent fatigue damage to the inner section and center section lower wing spar booms accomplish the following: (a) Replace the center section lower spar boom and the inner section lower spar boom with new booms of the same part number before they have exceeded 90 percent of the approved retirement time specified in the last applicable Viscount Instruction Manual, Chapter 3, Overhaul Schedule Section, dated before April 1, 1969, or within the next 250 landings whichever occurs later, after the effective date of this AD. (b) All new center section and inner section lower wing spar booms that are installed in accordance with the requirements of paragraph (a) of this AD must be replaced before the accumulation of the revised retirement times as specified in the latest amendment to the Viscount Instruction Manual, Chapter 3, Overhaul Schedule Section, dated after April 1, 1969. (c) For the purpose of complying with this AD, subject to acceptance by the assigned FAA maintenance inspector, the number of landings may be determined by dividing each airplane's hours' time in service by the operator's fleet average time from takeoff to landing for the airplane type. This amendment becomes effective July 7, 1969.
2006-12-26: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 777-200, -300, and -300ER series airplanes. This AD requires a one-time inspection of the first bonding jumper aft of the bulkhead fitting to detect damage or failure and to determine the mechanical integrity of its electrical bonding path, and repair if necessary; measuring the bonding resistance between the fitting for the fuel feed tube and the front spar in the left and right main fuel tanks, and repairing the bonding if necessary; and applying additional sealant to completely cover the bulkhead fittings inside the fuel tanks. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent arcing or sparking during a lightning strike at the interface between the bulkhead fittings of the engine fuel feed tube and the front spar inside the fuel tank. This arcing or sparking could provide a potential ignition source inside the fuel tank, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
2018-17-02: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-1A11 (600), CL-600-2A12 (601), and CL- 600-2B16 (601-3A, 601-3R, and 604 Variants) airplanes. This AD was prompted by a determination that the safe life limits of the horizontal stabilizer trim actuator (HSTA) attachment pins and trunnions were not listed in certain airworthiness limitations (AWLs) and that the HSTA attachment pins and trunnions were not serialized. This AD requires revision of the maintenance or inspection program, as applicable, to include the latest revision of the AWLs, serialization of the HSTA attachment pins and trunnions, and repair or replacement of damaged HSTA attachment pins and [[Page 40446]] trunnions. We are issuing this AD to address the unsafe condition on these products.
2000-08-10: This amendment supersedes an existing airworthiness directive (AD), applicable to certain General Electric Company GE90 series turbofan engines, that currently requires revisions to the Airworthiness Limitations Section (ALS) of the manufacturer s Instructions for Continued Airworthiness (ICA) to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This action adds additional critical life-limited parts for enhanced inspection. This amendment is prompted by additional focused inspection procedures for other critical life-limited rotating engine parts that have been developed by the manufacturer. The actions specified by this AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
2006-17-01: The FAA adopts a new airworthiness directive (AD) for all Mitsubishi Heavy Industries (MHI) MU-2B series airplanes. This AD requires you to incorporate power assurance charts into the Limitations Section of the Airplane Flight Manual (AFM), inspect the engine torque indication system, and recalibrate the torque pressure transducers as required. This AD results from a recent safety evaluation that used a data-driven approach to analyze the design, operation, and maintenance of the MU-2B series airplanes in order to determine their safety and define what steps, if any, are necessary for their safe operation. Part of that evaluation was the identification of unsafe conditions that exist or could develop on the affected type design airplanes. We are issuing this AD to detect and correct torque transducers that are out of calibration. The above issue, if uncorrected, could result in degraded performance and poor handling qualities with consequent loss of control of the airplane incertain situations.
2006-17-05: The FAA adopts a new airworthiness directive (AD) for all Mitsubishi Heavy Industries (MHI) MU-2B series airplanes. This AD requires you to do flight checks of the rigging of the engine and propeller systems. This AD results from a recent safety evaluation that used a data-driven approach to evaluate the design, operation, and maintenance of the MU-2B series airplanes in order to determine their safety and define what steps, if any, are necessary for their safe operation. Part of that evaluation was the identification of unsafe conditions that exist or could develop on the affected type design airplanes. We are issuing this AD to detect and correct improper adjustment of the flight idle fuel flow setting. This condition, if uncorrected, could result in degraded performance and poor handling qualities with consequent loss of control of the airplane in certain situations.
2018-16-04: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A318, A319, and A320 series airplanes, and Model A321- 111, -112, -131, -211, -212, -213, -231, -232, -251N, -253N, and -271N airplanes. This AD was prompted by a revision of an airworthiness limitations document that specifies more restrictive maintenance requirements and airworthiness limitations. This AD requires revising the maintenance or inspection program, as applicable, to incorporate the specified maintenance requirements and airworthiness limitations. We are issuing this AD to address the unsafe condition on these products.
2006-17-04: The FAA is adopting a new airworthiness directive (AD) for certain The Cessna Aircraft Company (Cessna) Models 172R, 172S, 182T, T182T, 206H, and T206H airplanes. This AD requires you to inspect the two end fittings on each of the flexible fuel hoses located in the engine compartment for the correct torque values, and, if any incorrect torque values are found during the inspection, tighten the hose end fittings to the correct torque values. This AD results from one report of loose fuel hose connections to the fuel injector servo on a Cessna Model 172S airplane. We are issuing this AD to detect and correct any incorrect torque values of the end fittings of flexible fuel hoses in the engine compartment, which could result in the loss of fuel flow and fuel leakage. Loss of fuel flow could result in partial or complete loss of engine power and fuel leakage could result in an engine compartment fire.
2006-02-08R1: The FAA is revising an existing airworthiness directive (AD) for certain Turbomeca Arriel 1B, 1D, 1D1, and 1S1 turboshaft engines. That AD currently requires initial and repetitive position checks of the gas generator 2nd stage turbine blades on all Turbomeca Arriel 1B, 1D, 1D1, and 1S1 turboshaft engines. That AD also currently requires initial and repetitive replacements of 2nd stage turbines on 1B, 1D, and 1D1 engines only. This AD revision requires the same actions, but would relax the compliance times for initially replacing 2nd stage turbines in Arriel 1B, 1D, and 1D1 turboshaft engines. We are issuing this AD revision to clarify and relax the AD compliance times for 2nd stage turbine initial replacement on Arriel 1B, 1D, and 1D1 turboshaft engines. We are also issuing this AD revision to prevent in-flight engine shutdown and subsequent forced autorotation landing or accident. DATES: This AD becomes effective September 13, 2006. The Director of the Federal Register previously approved the incorporation by reference of certain publications listed in the regulations as of February 28, 2006 (71 FR 3754, January 24, 2006).
2018-16-02: We are adopting a new airworthiness directive (AD) for all Airbus SAS Model A318-111 and -112 airplanes, Model A319-111, -112, - 113, -114, and -115 airplanes, Model A320-211, -212, -214, and -216 airplanes, and Model A321-111, -112, -211, -212, and -213 airplanes. This AD was prompted by a report of a production quality deficiency on the inner retainer installed on link assemblies of the aft engine mount, which could result in \n\n((Page 39327)) \n\nfailure of the retainer. This AD requires modifying and re-identifying the aft engine mount assemblies. We are issuing this AD to address the unsafe condition on these products.
2000-08-03: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that currently requires the deactivation of the forward and center cargo control units (CCU). That amendment was prompted by a report of failure of a CCU, which produced overheating of the electrical pins inside the CCU; the subsequent release of hot gases and flames ignited an adjacent insulation blanket. This amendment expands the applicability of the existing AD to include additional airplanes. The actions specified in this AD are intended to prevent overheating of the electrical pins inside the CCU's and subsequent release of hot gases and flames, which could result in smoke and fire in the cargo compartment.
59-18-05: 59-18-05 FAIRCHILD: Applies to all F-27 Series aircraft equipped with the heater system. Compliance required not later than October 15, 1959. (a) In order to provide drainage of possible leakage at the heater fuel line fittings, remove three shroud assemblies, P/N 27-774575-1, attached to tube connections at top of heater fuel control, P/N 43C80, and heater P/N 49C65. Modify shroud assemblies by punching one (1) 1/8-inch diameter hole in side of shroud 1 13/64 inches from top. (b) Remove fuel control drain tube assembly, P/N 27-774554-11 or -51, whichever installed. (c) On airplanes Nos. 1 to 6 inclusive, drill 5/8-inch diameter hole in bottom fuselage skin between stringers Nos. 102 and 103, 2 1/2 inches aft of Station 731, and install AN 931-6-10 grommet removed from former location of drain line. Install flush skin patch over former drain hole location in accordance with Chapter 51-7 of F-27 Structural Repair Manual. (d) On all affected airplanes, install new drain tube assembly, P/N 27-774750-11 in place of 27-774554-11 or -51. (e) Install modified shroud assemblies, using three each new half clamp assemblies, P/N 27-774749-11, half clamp P/N 27-774749-3, bolt P/N AN 3-3A, and nuts P/N MS 20365-1032. (f) Install one each new hose, P/N 27-774094-3 and -5 between heater fuel control shrouds and drain tube and P/N 27-774094-7 between heater shroud and drain tube, using six new clamps, P/N AN 737RM22. (g) Install two new plates, P/N 27-774749-9, on the heater fuel control unit, and four new clamps, P/N AN 742-8, two on the plates at the fuel control unit to support 27-774094-3 and -5 hose and two on the flanges of the fuselage former at Stations 730 and 731 to support 27-774094-7 hose. Use four each new screws P/N AN 525-10R6, and nuts P/N MS 20365-1032. (Fairchild F-27 Service Bulletin No. 21-49 dated June 12, 1959, covers this same subject.) Compliance with AD 59-12-01 no longer required after compliance with this directive.
2006-16-19: 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. We are issuing this AD to require actions to correct the unsafe condition on these products.
2006-16-20: We are adopting a new airworthiness directive (AD) for all DG Flugzeugbau GmbH Model DG-1000S sailplanes. This AD requires you to modify the elevator control at the stabilizer assembly, replace a placard on the fin, and incorporate changes in the FAA-approved sailplane flight manual (SFM). This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to prevent the rigging of the horizontal stabilizer without properly connecting the elevator, which, if not prevented, could lead to an inoperative elevator. An inoperative elevator could lead to loss of control of the sailplane.
2018-16-03: We are adopting a new airworthiness directive (AD) for all Airbus SAS Model A319-133 airplanes and Model A321-232 airplanes. This AD requires modification and re-identification, or replacement, of certain engine fan cowl doors (FCDs) and installation of a placard in the flight deck. This AD was prompted by reports of in-service engine FCD losses, and the development of a new FCD front latch and keeper assembly that addresses this unsafe condition. We are issuing this AD to address the unsafe condition on these products.