Results
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.