Results
2005-03-11: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 767 series airplanes. That AD currently requires repetitive detailed and eddy current inspections of the aft pressure bulkhead for damage and cracking, and repair if necessary. This new AD also requires one-time detailed and high frequency eddy current inspections of any "oil-can" located on the aft pressure bulkhead, and related corrective actions if necessary. An "oil-can" is an area on a pressure dome web that moves when pushed from the forward side. This AD is prompted by reports of cracking at "oil-can" boundaries on the aft pressure bulkhead. We are issuing this AD to detect and correct fatigue cracking of the aft pressure bulkhead, which could result in rapid depressurization of the airplane and possible damage or interference with the airplane control systems that penetrate the bulkhead, and consequent loss of controllability of the airplane. \n\nDATES: This AD becomes effective March 18, 2005. \n\n\tOn March 22, 2004 (69 FR 10321, March 5, 2004), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 767-53A0026, Revision 5, dated January 29, 2004.
2011-06-01: 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 aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: A fatal accident occurred to a CAP 10C, in which the pilot lost control of the aeroplane. The following investigation has revealed that the probable cause of the accident was the improper locking of a turnbuckle (locking clip missing) of the flight control cables, and the subsequent inadvertent release of the pitchup control cable from the turnbuckle. We are issuing this AD to require actions to correct the unsafe condition on these products.
2001-18-12: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767-200, -300, -300F and -400ER series airplanes. This action requires repetitive inspections to find discrepancies of the wire bundles located between the P50 panel and the nose wheel well structure, and corrective actions, if necessary. This action is necessary to find and fix such discrepancies, which could result in electrical arcing, smoke, or fire in the cabin, and failure of certain systems essential to safe flight and landing of the airplane. This action is intended to address the identified unsafe condition.
2008-12-03: We are adopting a new airworthiness directive (AD) for various transport category airplanes. This AD requires deactivation of Rogerson Aircraft Corporation auxiliary fuel tanks. This AD results from fuel system reviews conducted by the manufacturer, which identified potential unsafe conditions for which the manufacturer has not provided corrective actions. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
2008-11-12: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: To date, there have been at least 10 reported events on Fokker 70 (F28 Mark 0070) and Fokker 100 (F28 Mark 0100) aircraft where the flight crew manually overpowered the autopilot, inadvertently neglecting to disengage the autopilot. * * * When the autopilot is not disengaged, the elevator servomotor is overpowered and the horizontal stabilizer is moved by the Automatic Flight Control & Augmentation System (AFCAS) auto-trim in a direction opposite to the (manual) deflection of the elevator, causing high elevator control forces. This condition, if not corrected, could cause the stabilizer to move to an extreme out-of-trim position, creating the (remote) possibility of loss of control of the aircraft, due to the extreme control loads. We are issuing this AD to require actions to correct the unsafe condition on these products.
95-16-01: This amendment supersedes an existing airworthiness directive (AD), applicable to all McDonnell Douglas Model MD-11 series airplanes, that currently requires a revision to the Airplane Flight Manual (AFM) that prohibits autoland operation below 100 feet above ground level, and installation of flight control computer software. It also provides for an optional terminating action for the AFM revision. This amendment provides for a new optional terminating action for the AFM revision. This amendment is prompted by reports of erroneous central aural warning system altitude callouts and erroneous radio altimeter indications during autoland approaches due to radio frequency leakage (RF) on airplanes on which the optional terminating action had been accomplished. The actions specified in this AD are intended to prevent radio altimeter antenna/coaxial cable RF leakage, which could result in early and/or abnormal flare (pitch) control during autoland operation and potential degradation of the landing capability of the airplane.
86-24-03 R1: 86-24-03 R1 PIONEER PARACHUTE COMPANY: Amendment 39-5565. Applies to Model K-XX, K-XXII and 26 foot conical canopies with the following serial numbers: K-XX, P/N 5375-1 Color Patterns: Light Blue Upper Panels and Royal Blue Lower Panels or Yellow Upper Panels and Tan Lower Panels 598162 598927 598966 599000 599043 598318 598928 598967 599001 599048 598865 598929 598968 599004 599049 598866 598930 598969 599005 599050 598923 598937 598970 599006 599051 598924 598960 598971 599008 599087 598925 598961 598972 599009 599165 598926 598965 598995 599042 599166 Color Patterns: Light Blue Upper Panels and Tan Lower Panels or Yellow Upper Panels and Tan Lower Panels 598307 598345 598364 598526 598535 598317 598346 598366 598527 598536 598320 598347 598367 598528 598537 598340 598348 598521 598529 598545 598341 598349 598522 598530 598571 598342 598350 598523 598531 598572 598343 598351 598524 598532 598592 598344 598363 598525 598533 598863 Color Pattern: White Panels 598539 598550 598843 598998 599563 598540 598552 598844 598999 599613 598541 598553 598845 599002 599614 598542 598554 598858 599003 599640 598546 598555 598864 599007 599701 598547 598556 598962 599164 599702 598548 598579 598996 599561 599703 598549 598842 598997 599562 599711 K-XXII, P/N 5418-1 598557 598561 598565 598569 599076 598558 598562 598566 598650 599441 598559 598563 598567 598651 599638 598560 598564 598568 599044 599639 26 foot conical, P/N 2412-501 Color Pattern: All White 599093 To prevent use of affected canopies as FAA approved canopies, due to understrength material, remove or obliterate TSO-C23b marking prior to next use after receipt of this AD, unless already accomplished. NOTES: (1) Pioneer Parachute Company Safety Notice, dated December 22, 1986, applies to this AD. (2) Investigation is continuing, and this AD may be amended in light of the results of the investigation. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Boston Aircraft Certification Office, Aircraft Certification Division, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803, telephone (617) 273-7103. This amendment becomes effective March 20, 1987, as to all persons except those persons to whom it was made immediately effective by Priority Letter AD No. 86-24-03, issued November 21, 1986, and Priority Letter AD No. 86-24-03R1, issued January 13, 1987, which contained this amendment.
2020-19-08: The FAA is adopting a new airworthiness directive (AD) for Bell Textron Inc. (Type Certificate previously held by Bell Helicopter Textron Inc.) (Bell), Model 204B, 205A-1, and 212 helicopters. This AD was prompted by reports of corrosion on main rotor hub tension-torsion strap (TT strap) assemblies. This AD requires reducing the life limit of a certain part-numbered TT strap assembly and prohibits installing this TT strap assembly on any helicopter. The FAA is issuing this AD to address the unsafe condition on these products.
95-16-05: This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model MD-11 series airplanes. This action requires an inspection to identify defective lower drag links on the nose landing gear (NLG), and replacement of defective drag links with new parts. This amendment is prompted by a report indicating that a potential failure condition of the lower drag link on the NLG could occur due to improper de-embrittlement treatment of the drag link during manufacturing. The actions specified in this AD are intended to prevent collapse of the NLG due to failure of the lower drag link as a result of improper de-embrittlement treatment of the drag link.
2001-18-03: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 series airplanes, that requires a one-time inspection for correct installation of the left-and right-hand fuel differential pressure (FDP) switches and for correct connection of the pressure sensing lines to the switches, and corrective action, if necessary. The actions specified by this AD are intended to ensure that a warning light goes on when the fuel filter is partially blocked by ice, so that the blockage of the fuel filter does not increase, leading to reduced fuel flow to the engine and possibly to an engine flame-out. This action is intended to address the identified unsafe condition.
2017-23-06: We are adopting a new airworthiness directive (AD) for certain General Electric Company (GE) CF34-8C1, CF34-8C5, CF34-8C5A1, and CF34- 8C5B1 engines. This AD requires an inspection of the bleed air manifold link rod assemblies and the supply, return, and drain fuel fittings on the operability bleed valve (OBV). This AD was prompted by an engine fire that occurred as a result of malfunctions related to the OBV. We are issuing this AD to address the unsafe condition on these products.
61-07-01: 61-07-01 CONVAIR: Amdt. 272 Part 507 Federal Register April 4, 1961. Applies to All Model 22 (880) Aircraft. Compliance required as indicated. Conduct a daily inspection of all foreflaps, P/N 22-18600-5 or -807, left and right, for cracks in the upper surface skin. Particular attention should be given to the mid span area of each foreflap. Except as otherwise provided for in paragraphs (a), (b) and (c), cracked foreflaps must be modified per Convair Service Bulletin 27-22 or equivalent, or replaced prior to further flight. (a) Cracked foreflaps may be operated for an additional 10 hours' time in service provided: (1) The crack emanating from any one rivet hole does not extend more than 1/2 inch forward or 1 inch aft of the rivet hole. (2) No two cracks are closer together (spanwise) than 4 inches. (3) Each crack is stop drilled approximately 1/4-inch diameter. (4) Each crack is visually inspected after each flight. (b) Foreflaps operated under paragraph (a) shall be repaired in accordance with Convair Alert Service Bulletin A-27-22 or equivalent, modified per Convair Service Bulletin 27- 22 or replaced either at the end of this period of 10 hours' time in service or when a crack is found to progress beyond the stop drill hole, whichever occurs first. Repaired foreflaps may be operated for an additional 100 hours' time in service before modification or replacement provided that no further cracks are found during the daily inspections which exceed the limits specified in paragraph (a)(1) and (2). If such cracks are found, the foreflaps must be replaced or modified prior to further flight, except ferry flight in accordance with paragraph (c). (c) Aircraft having cracks in the foreflaps which exceed the limits specified in paragraph (a)(1) and (2) may be flown under the provisions of CAR's 1.76 and 1.77 to a base where the required replacements or modifications are to be made. (d) After the foreflaps are modifiedper Convair Service Bulletin 27-22 or equivalent, inspections may then be made at the normal inspection periods. (Convair Service Bulletin 27-22 and Alert Service Bulletin A-27-22 cover this subject.) This directive effective April 10, 1961.
95-15-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Corporate Jets Model BAe 125-800A and -1000A airplanes, that requires inspections to detect corrosion of the wing leading edge skins, including the wing anti-ice fluid distribution panel (TKS panel) rebate and radius; repair, if necessary; and subsequent corrosion protection treatment. This amendment also requires inspections and treatments of the landing/taxiing lamp window assembly recess and stall vane spoiler rebate/radius. This amendment is prompted by reports of corrosion of the wing leading edge skin at the interface with the TKS panels. The actions specified by this AD are intended to prevent reduced structural integrity of the wing leading edge section at the interface with the TKS panels and stall vane spoilers, which could adversely affect the flight characteristics of the airplane.
2008-10-51: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2008-10-51 that was sent previously to all known U.S. owners and operators of all Dornier Model 328-100 and -300 airplanes by individual notices. This AD requires detailed visual and eddy current inspections of both the left-hand and right-hand lower wing panel of the rear trailing edge (inboard and outboard of flap lever arm 1 (rib 3 and rib 5)) for cracks, and repair if necessary. This AD is prompted by cracks found in the lower wing panel of the rear trailing edge (inboard and outboard of flap lever arm 1 (rib 5)) during a routine inspection on a Model 328-100 airplane. Subsequent inspection of the other Model 328-100 airplanes in the same fleet revealed several more airplanes with cracks at the same location. We are issuing this AD to prevent structural failure of the affected wing panel, possible separation of the wing from the airplane, and consequent loss of control of theairplane.
2001-18-04: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747-400 series airplanes, that currently requires repetitive inspections to detect damage or deflection of the crew rest heat exchanger, and follow-on actions, if necessary. This amendment adds a new requirement for a one-time inspection to determine the part number and shop code of the shell of the crew rest heat exchanger; and follow-on actions, if necessary; which terminate the currently required repetitive inspections. This action is necessary to prevent cracking and buckling of the front edge of the crew rest heat exchanger, which could result in a jam of the rudder or elevator control cables, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition. \n\nThe incorporation by reference of Boeing Alert Service Bulletin 747-21A2412, dated January 20, 2000, as listed in the regulations, was approved previouslyby the Director of the Federal Register as of June 8, 2000 (65 FR 33444, May 24, 2000).\n\n\tComments for inclusion in the Rules Docket must be received on or before November 5, 2001.
2020-18-09: The FAA is adopting a new airworthiness directive (AD) for all Honeywell International Inc. (Honeywell) ALF502L, ALF502L-2, ALF502L- 2A, ALF502L-2C, ALF502L-3, ALF502R-3, ALF502R-3A, ALF502R-4, ALF502R-5, ALF502R-6, LF507-1F, and LF507-1H model turbofan engines. This AD was prompted by a report of an engine experiencing an uncontained release of low-pressure turbine (LPT) blades. This AD requires initial and repetitive visual inspections of the overspeed fuel solenoid valve assembly and the fuel filter outlet. Depending on the results of these inspections, the AD may require inspection of the adjacent fuel system tube assemblies as well as replacement or overhaul of the overspeed fuel solenoid valve assembly. This AD also requires periodic overhaul of the overspeed fuel solenoid valve assembly. The FAA is issuing this AD to address the unsafe condition on these products.
95-15-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727 and Model 737 series airplanes, that requires replacement of the actuator of the engine fuel shutoff valve and the fuel system crossfeed valve with an improved actuator. This amendment is prompted by reports indicating that, during laboratory tests on Model 737 series airplanes, the actuator clutch on the engine shutoff and crossfeed valves slipped at cold temperatures due to improper functioning. The actions specified by this AD are intended to prevent improper functioning of these actuators, which could result in a fuel imbalance due to the inability of the flight crew to crossfeed fuel; improperly functioning actuators could also prevent the pilot from shutting off the fuel to the engine following an engine failure and/or fire.
2008-11-08: We are adopting a new airworthiness directive (AD) for all Boeing Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD requires repetitive inspections for any cracking of or damage to the left side and right side flight deck No. 2, No. 4, and No. 5 windows, as necessary, and corrective actions if necessary. This AD results from reports of in-flight departure and separation of the flight deck windows. We are issuing this AD to detect and correct cracking in the vinyl interlayer or damage to the structural inner glass panes of the flight deck No. 2, No. 4, and No. 5 windows, which could result in loss of a window and rapid loss of cabin pressure. Loss of cabin pressure could cause crew communication difficulties or crew incapacitation.
2008-11-15: We are adopting a new airworthiness directive (AD) for all McDonnell Douglas airplanes identified above. This AD requires revising the FAA-approved maintenance program, or the Airworthiness Limitations (AWLs) section of the Instructions for Continued Airworthiness, as applicable, to incorporate new AWLs for fuel tank systems to satisfy Special Federal Aviation Regulation No. 88 requirements. This AD results from a design review of the fuel tank systems. We are issuing this AD to prevent the potential for ignition sources inside fuel tanks caused by latent failures, alterations, repairs, or maintenance actions, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
2023-06-13: The FAA is adopting a new airworthiness directive (AD) for all Bombardier, Inc., Model BD-700-2A12 airplanes. This AD was prompted by the determination that radio altimeters cannot be relied upon to perform their intended function if they experience interference from wireless broadband operations in the 3.7-3.98 GHz frequency band (5G C- Band), and a recent determination that this interference can result in unavailable or misleading radio altimeter information, adversely affecting the performance of the automatic flight control system (AFCS) and fly-by-wire (FBW) systems and resulting in increased flightcrew workload during takeoff, approach, and landing below 400 feet above ground level (AGL). This AD requires revising the existing airplane flight manual (AFM) with new limitations to mitigate identified hazards due to 5G C-Band interference as identified by Notices to Air Missions (NOTAMs). The FAA is issuing this AD to address the unsafe condition on these products.
2001-18-02: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 series airplanes, that requires a one-time eddy current inspection for cracks of the fuselage butt joint which is forward of the emergency exits on the left-and right-hand sides of the airplane at the level of stringers 27/48. This proposal would also require repair of any cracks detected. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign airworthiness authority. The actions specified by this AD are intended to detect and correct cracks in the area of the emergency escape hatches, which, if undetected, could result in depressurization during flight, possibly leading to structural failure of the airplane.
2011-18-18: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Several operators have reported pitch oscillations and/or elevator asymmetry caution lights illumination when flying with the autopilot engaged. Investigations revealed that loose rivets in the torque tube assemblies caused relative motion between the crank arms and torque tubes. Loose rivets could result in excessive wear and subsequent significant backlash in the driving crank arms. This condition, if left uncorrected, will progressively get worse and degrade the controllability of the aeroplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
95-12-17: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-100 and -200 series airplanes, that requires various inspections for cracks in the outboard chord of the frame at body station (BS) 727 and in the outboard chord of stringer 18A; and repair or replacement of cracked parts. This amendment is prompted by reports of fatigue cracks in those outboard chords. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in reduced structural integrity of the outboard chords, and subsequent rapid decompression of the airplane.
2008-11-07: We are adopting a new airworthiness directive (AD) for all Boeing Model 757 airplanes. This AD requires installation of an automatic shutoff system for the center tank fuel boost pumps, and installation of a placard in the airplane flight deck if necessary. This AD also requires revisions to the Limitations and Normal Procedures sections of the airplane flight manual to advise the flightcrew of certain operating restrictions for airplanes equipped with an automated center tank fuel pump shutoff control. This AD also requires a revision to the Airworthiness Limitations (AWLs) section of the Instructions for Continued Airworthiness to incorporate AWLs No. 28-AWL-20 and No. 28-AWL-26. This AD also requires replacement of the fuel control panel assembly with a modified part, installation of two secondary pump control relays for the center tank fuel pumps, other specified actions, and concurrent modification of the fuel control panel assembly. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent center tank fuel pump operation with continuous low pressure, which could lead to friction sparks or overheating in the fuel pump inlet that could create a potential ignition source inside the center fuel tank; these conditions, in combination with flammable fuel vapors, could result in a center fuel tank explosion and consequent loss of the airplane.
2001-18-05: This amendment adopts a new airworthiness directive (AD) that applies to certain Goodyear Tire and Rubber Company (Goodyear) Flight Eagle tires, 34X9.25-16 18PR 210MPH, Part Number (P/N) 348F83-2, that are installed on aircraft. This AD requires you to inspect these tires to determine if they are within a certain serial number range and replace any tires within this serial number range. This AD is the result of several instances of main landing gear (MLG) tire tread separations on Gulfstream aircraft. The actions specified by this AD are intended to remove these tires from service to prevent the potential of these tires experiencing tread separations during operation. These tread separations could result in structural damage to the aircraft, including damage to the flaps, engine nacelles, and wheel wells.