Results
2006-17-17: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-100, DHC-8-200, DHC-8-300, and DHC-8-400 series airplanes. This AD requires inspecting the left and right control column torque tube assemblies to determine the type of rivets installed and replacing incorrect or indeterminate type rivets with the correct type rivets. This AD results from a report that incorrect rivets having lower than required strength were installed on the control column torque tube during production. We are issuing this AD to prevent shear failure of control column torque tube rivets, which could cause unexpected decoupling of the elevators and large unwanted deflection of the free elevator, and consequent reduced controllability of the airplane.
2018-17-17: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model DHC-8-400 series airplanes. This AD was prompted by reports of arcing and smoke emanating from the windshields. This AD requires a revision to the maintenance or inspection program, as applicable, to include an inspection of the windshield moisture seal for signs of cracks, erosion, wear, and other deterioration; doing that inspection and repair if necessary; and re-torqueing the screws that fasten the windshield heater terminal lugs and applying sealant to the screw heads of the windshield heaters. We are issuing this AD to address the unsafe condition on these products.
2006-17-15: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model DC-10-10 and DC-10-10F airplanes; and Model MD-10-10F airplanes. This AD requires replacing the clamp bases for the fuel vent pipe with improved clamp bases. This AD results from reports that the foil wrapping on existing plastic clamp bases has migrated out of position, which compromises the bonding of the fuel vent pipes to the airplane structure. We are issuing this AD to ensure that the fuel vent pipes are properly bonded to the airplane structure. Improper bonding could prevent electrical energy from a lightning strike from dissipating to the airplane structure, and create an ignition source, which could result in a fuel tank explosion.
87-25-03: 87-25-03 BRITISH AEROSPACE: Amendment 39-5779. Applies to British Aerospace Model 125-800A series airplanes, listed in British Aerospace (BAe) Service Bulletin 57-64-(3067), dated November 29, 1985, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent entrapment of water within the aileron tab accomplish the following: A. Within the next 100 landings or within one year after the effective date of this AD, whichever occurs sooner, modify the aileron tab and the inboard aileron hinge to provide drainage in accordance with BAe Service Bulletin 57-64-(3067), dated November 29, 1985. B. 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. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the modification required by 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 British Aerospace, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective January 13, 1988.
2006-17-08: The FAA is adopting a new airworthiness directive (AD) for Pratt & Whitney (PW) PW4077D, PW4084D, PW4090, and PW4090-3 turbofan engines that were reassembled with certain previously used high pressure compressor (HPC) exit brush seal assembly parts and certain new or refurbished HPC exit diffuser air seal inner lands. This AD requires replacing the HPC exit inner and outer brush seal packs with new brush seal packs, or replacing the HPC exit brush seal assembly with a new HPC exit brush seal assembly. This AD results from a report of oil leaking into the high pressure turbine (HPT) interstage cavity and igniting, leading to an engine case penetration and engine in- flight shutdown. Although liberated engine parts did not penetrate the engine nacelle, we are issuing this AD to prevent uncontained engine failure, damage to the airplane, and injury to passengers.
2018-14-10: We are superseding Airworthiness Directive (AD) 2017-12-03 for certain Pratt & Whitney Division (PW) PW2037, PW2037M, and PW2040 turbofan engines. AD 2017-12-03 required installing a software standard eligible for installation and precludes the use of electronic engine control (EEC) software standards earlier than SCN 5B/I. This AD requires installing a software standard eligible for installation and preclude the use of EEC software standards earlier than SCN 5B/I or SCN 27A. This AD was prompted by an unrecoverable engine in-flight shutdown (IFSD) after an ice crystal icing event. We are issuing this AD to address the unsafe condition on these products.
2000-08-21: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 747 series airplanes, that requires repetitive inspections to detect cracking of the forward and aft inner chords and the splice fitting of the forward inner chord of the station 2598 bulkhead, and repair, if necessary. This amendment is prompted by reports of fatigue cracking found in those areas. The actions specified by this AD are intended to detect and correct such cracking, which could result in reduced structural capability of the bulkhead and the inability of the structure to carry horizontal stabilizer flight loads.
88-20-07: 88-20-07 BOEING: Amendment 39-6024. Applies to all Model 727 series airplanes, certificated in any category.\n \n\tCompliance required as indicated, unless previously accomplished. \n\n\tTo prevent jamming of the main landing gear door actuator caused by fracturing of the pivot trunnion, accomplish the following: \n\n\tA.\tWithin the next 1,600 flight cycles after the effective date of this AD, accomplish the visual inspection of the main landing gear door actuator pivots in accordance with Boeing Service Bulletin 727-32-0358, dated May 31, 1988. Repeat this inspection at intervals not to exceed 800 flight cycles. \n\n\tB.\tIf any of the pivot trunnion shafts are found loose or missing during the inspection performed in accordance with paragraph A., above, prior to further flight, replace the pivot in accordance with Boeing Service Bulletin 727-32-0358, dated May 31, 1988. \n\n\tC.\tAccomplishing the pivot replacement with a part number 3-3141-54 pivot, in accordance with Sargent Controls Service Bulletin 7-3141-32-06, Revision 1, dated November 2, 1987, constitutes terminating action for the initial and repetitive inspections required by paragraph A., above. \n\n\tD.\tAn 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, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington, 98124. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington or Seattle Aircraft CertificationOffice, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis Amendment, 39-6024, becomes effective November 1, 1988.
2006-17-11: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 767-400ER series airplanes and Model 777-200 and - 300 series airplanes. This AD requires, for certain airplanes, repetitive testing of the fill and safety fittings of the cargo fire extinguishing bottles in the forward cargo compartment for leaks; and repetitive application of a corrosion inhibiting compound (CIC) or replacement of the cargo fire extinguishing bottles with reworked fire extinguishing bottles, as necessary. For all airplanes, this AD requires replacement of the cargo fire extinguishing bottles with reworked fire extinguishing bottles, which ends the repetitive tests and CIC applications if applicable. This AD results from failure of the safety fittings for the cargo fire extinguishing bottles. We are issuing this AD to prevent failure of the safety fittings for the cargo fire extinguishing bottles due to corrosion, which could result in leakage of extinguishing agent. If a fire occurs in the cargo bay, the cargo fire extinguishing bottles could have less than enough extinguishing agent to control a fire.
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.