Results
99-16-05: This amendment adopts a new airworthiness directive (AD), applicable to Saab Model SAAB 2000 series airplanes, that requires repetitive inspections for excessive wear of the aileron control cables, cable guides, and cable pulleys located at the rear wing spars; and corrective actions, if necessary. This amendment also requires repetitive replacement of the control cables and cable guides with new or serviceable components. This amendment also provides for optional terminating action for the repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness. The actions specified by this AD are intended to detect and correct excessive wear on the aileron control cables, cable guides, and cable pulleys located at the rear wing spars, which could result in broken aileron control cables and consequent reduced controllability of the airplane.
99-02-16: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Models B300 and B300C airplanes (commonly referred to as Beech Models B300 and B300C airplanes). This AD requires modifying the elevator trim tab actuators by incorporating a new elevator trim tab actuator assembly kit, replacing the elevator trim tab pushrod assembly, or modifying the elevator spar opening, whichever is applicable. Reports from operators of ice forming on the elevator trim tab actuators and jamming the trim tab control prompted this action. The actions specified by this AD are intended to prevent jamming of the elevator trim tab actuator caused by ice formations, which could result in loss of control of the airplane.
2006-07-09: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A318-100 and A319-100 series airplanes; Model A320-111 airplanes; and Model A320-200, A321-100, and A321-200 series airplanes. This AD requires repetitive detailed inspections of the trimmable horizontal stabilizer actuator (THSA) attachments for proper clearances, and any crack, damage, or metallic particles; related corrective actions if necessary; and a report of the inspection results to the manufacturer. This AD results from a report that during lab testing to verify the performance of the THSA's secondary load path with a simulated failure of the THSA's primary load path, the secondary load path's nut did not jam (as it was supposed to do). We are issuing this AD to ensure the integrity of the THSA's primary load path, which if failed, could result in latent (undetected) loading and eventual failure of the THSA's secondary load path and consequent uncontrolled movement of the horizontal stabilizer and loss of control of the airplane.
99-19-41: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that requires modification of the insulation pads in the lower side of the fuselage at the wing aft area. 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 prevent loose insulation from interfering with an aileron control cable, which could result in reduced aileron control.
99-08-08: This amendment adopts a new airworthiness directive (AD), applicable to all Dornier Model 328-100 series airplanes, that requires repetitive lubrication of the engine control push-pull cables, and installation of heating tubes on the control cables in the cockpit area and in the left-hand and right-hand engine balconies, which terminates the repetitive lubrication requirement. 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 prevent ice from building up on the engine control push-pull cables, which could result in friction or jamming of the engine controls, and consequent reduced controllability of the airplane.
99-04-02: This amendment adopts a new airworthiness directive (AD), applicable to all CASA Model C-212 series airplanes, that requires repetitive visual inspections for damage or "electrical spark marks" on the cover plates for the fuel pumps, and corrective actions, if necessary. This AD also requires modification of the fuel pump installation by incorporating a non-conductive film on the cover plate, which constitutes terminating action for this AD. 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 prevent electrical shorting between the fuel pump electrical connections and the fuel pump cover plate, which could result in the ignition of fuel vapor and consequent fuel tank explosion/fire.
2006-07-11: The FAA is adopting a new airworthiness directive (AD) for all McDonnell Douglas airplanes identified above. This AD requires a one- time inspection of the aft attach fitting assembly of the spoiler link to determine the part number, and further investigative action and replacement of the assembly with a new or serviceable assembly, if necessary. This AD results from a determination that the holes of certain aft attach fitting assemblies of the spoiler link were not cold-worked during production. We are issuing this AD to prevent fatigue cracking of the aft attach fitting of the spoiler link and consequent failure of the fitting. Failure of the fitting could result in an asymmetrical lift condition and consequent reduced controllability of the airplane.
99-19-30: This amendment adopts a new airworthiness directive (AD) applicable to Sikorsky Aircraft Corporation (Sikorsky) Model S-76A, B, and C helicopters. This action requires conducting a visual inspection to detect disbonding of the attachment angle between the tail gearbox forward fairing (fairing) and the pylon and replacing or repairing the attachment angles as necessary. This amendment is prompted by incidents, two in flight and eight on the ground, of fairing bonding failures. The actions specified in this AD are intended to prevent separation of the fairing, damage to the tail rotor blades, and subsequent loss of control of the helicopter.
98-06-17: This amendment adopts a new airworthiness directive (AD), applicable to certain Dassault Aviation Model Mystere Falcon 900 series airplanes, that requires replacement of the water heater control relays with improved relays having high-power contactors; the addition of a testing and monitoring circuit for each contactor; and installation of improved electrical bonding of the potable water tank. 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 prevent overheating of the water heaters for the galley or the washbasin, which could result in damage to the water heater and nearby electrical wiring, and consequent smoke in the cabin.
2020-05-26: The FAA is adopting a new airworthiness directive (AD) for certain \n\n((Page 17481)) \n\nThe Boeing Company Model 787-8 airplanes. This AD was prompted by a report of failure of a wing strut leak test due to a missing bolt on the firewall. This AD requires a one-time leak test of the strut upper spar areas for the left and right wing struts, and corrective action if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
99-19-29: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that requires repetitive inspections of certain H-11 tension bolts at each side-of-body kick-load fitting and on the lower splice plate (both located on the wing rear spar) to detect damaged or broken bolts; and follow-on actions, if necessary. This amendment also requires eventual replacement of the existing bolts with new, improved bolts, which constitutes terminating action for the repetitive inspections. This amendment is prompted by a report that an operator found two broken H-11 tension bolts on the side-of-body kick-load fitting on one airplane. The actions specified by this AD are intended to prevent cracking of the bolts due to stress corrosion, which could result in reduced structural integrity of the wing-to-body joint structure.
87-04-09: 87-04-09 HELIO: Amendment 39-5533. Applies to Models H-700 and H-800 airplanes (all serial numbers) certificated in any category. Compliance: Required as indicated, unless already accomplished. To assure airworthiness of the composite main landing gear legs, accomplish the following: (a) Within the next 100 hours TIS after the effective date of this AD and each 100 hours TIS thereafter, remove landing gear fairings, if installed, and visually inspect the edges of the composite main landing gear legs for evidence of delamination. Delamination is evidenced by longitudinal splitting between the fiberglass plies. This could occur anywhere along the span of the landing gear leg. If any delamination is found, prior to further flight, install FAA-approved right and left metallic landing gear legs. NOTE: On the effective date of this AD, the only known FAA-approved replacement landing gear is per STC SA2171CE. (b) If, in between the inspections required in paragraph (a) above, it is observed that the wings do not appear level, or one side of the airplane appears to be drooping, prior to further flight, conduct the inspections and replacement, If necessary, required in paragraph (a) of this AD. (c) The inspection required in paragraphs (a) and (b) are no longer required when FAA-approved metallic landing gear legs have been installed. (d) Ferry permits issued in accordance with FAR 21.197 and equivalent methods of compliance with this AD may be used if approved by the Manager, Wichita Aircraft Certification Office, Federal Aviation Administration, 1801 Airport Road, Room 100, Wichita, Kansas 67209; Telephone (316) 946-4400. All persons affected by this directive may obtain copies of the documents referred to herein upon request to the Federal Aviation Administration, Office of the Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on March 9, 1987.
67-08-01: 67-08-01 AERO PRODUCTS: Amdt. 39-369 Part 39 Federal Register March 10, 1967. Applies to Models A6441FN-606 and A6441FN-606A Propellers Installed on General Dynamics Models 340 and 440 Airplanes Modified in Accordance with STC SA4-1100 or Lockheed Models 188A and 188C Airplanes. Before further flight of any airplane equipped with a propeller identified by the following list of propeller serial numbers and hub serial numbers, unless already accomplished, remove the propeller and replace with a propeller that does not bear a number on the following list or inspect and return to service in accordance with procedures established by Allison and approved by the Chief, Engineering and Manufacturing Branch, FAA Central Region. Further flight beyond the point where the aircraft is grounded pursuant to this airworthiness directive may be conducted only in accordance with FAR 21.197. PROPELLER NUMBER HUB NUMBER P807 H21260 P607 H21048 P791 H21126 P1001 H22073 P1002 H22074 P975 H22047 P978 H22050 P981 H22053 P982 H22054 P983 H22055 P989 H22061 P995 H22067 P996 H22068 P997 H22069 P998 H22070 P1003 H22075 P1006 H22078 P985 H22057 P986 H22058 P1004 H22076 P1019 H22091 P994 H22067 P990 H22062 P991 H22063 P971 H22043 P974 H22046 P992 H22064 P993 H22065 P999 H22071 P1000 H22072 P541 H21176 P625 H21234 P909 H21163 P984 H22056 P987 H22059 P976 H22048 P977 H22049 This directive effective upon publication in the Federal Register for all persons except those to whom it was made effective by telegram dated March 8, 1967.
87-25-10: 87-25-10 GROB: Amendment 39-5880. Applies to GROB Models G103 TWIN II and G103A TWIN II ACRO gliders, Serial Nos. 3730 through 3878, and Serial Nos. 33879 through 34078 (ACRO with supplement K), certificated in all categories. Compliance is required, as indicated, unless already accomplished. To prevent failure of the rudder lever, which could result in the glider becoming uncontrollable, accomplish the following: (a) Within the next 5 hours time in service after the effective date of this AD, unless compliance with Paragraph (c) has been accomplished, visually inspect the rudder lever, P/N 103B-4430, using a 10 power or greater magnifying glass and flashlight in accordance with Paragraph 1 of GROB Repair Instruction No. 315-33/1 for Service Bulletin (SB) TM 315-33, dated August 3, 1987. (b) Replace damaged parts before further flight, with rudder lever, P/N 103B- 4430/1, and two rudder stop screws, M 6 x 45 (mm), in accordance with GROB Repair Instruction No. 315-33/2 for SB TM 315-33, dated August 3, 1987. (c) Prior to March 15, 1988, replace any rudder lever and rudder stop screws not replaced in accordance with Paragraph (b) of this AD with rudder lever, P/N 103B-4430/1, and two rudder stop screws, M 6 x 45 (mm), in accordance with GROB Repair Instruction No. 315- 33/2 for SB TM 315-33, dated August 3, 1987. (d) Aircraft may be ferried in accordance with the provisions of Federal Aviation Regulations 21.197 and 21.199 to a base where the AD can be accomplished. (e) Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Brussels Aircraft Certification Office, Europe, Africa, and Middle East Office, FAA c/o American Embassy, 15 Rue de la Loi B-1040 Brussels, Belgium, or the Manager, New York Aircraft Certification Office, Aircraft Certification Division, New England Region, Federal Aviation Administration, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. (f) Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Brussels Aircraft Certification Office, or the Manager, New York Aircraft Certification Office, may adjust the compliance time specified in this AD. GROB Repair Instructions No. 315-33/1 and /2 for SB TM 315-33, dated August 3, 1987, identified and described in this document, 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 GROB Systems, Inc., Aircraft Division, I-75 and Airport Drive, Bluffton, Ohio 45817. These documents may also be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Room 311, Docket No. 87-ANE-45, between the hours of 8:00 a.m. and 4:30 p.m.,Monday through Friday, except federal holidays. This amendment 39-5880 becomes effective April 15, 1988, as to all persons except those persons to whom it was made immediately effective by individual priority letter AD 87- 25-10, issued December 11, 1987, which contained this amendment.
2006-07-13: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A310 airplanes, Model A300 B4-600 series airplanes, Model A300 B4-600R series airplanes, Model A300 F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes. This AD requires inspections of the rudder for discrepancies and corrective action if necessary. This AD also requires reporting all inspection results to the airplane manufacturer and the FAA. This AD results from two separate findings of inner skin disbonding discovered while undergoing unrelated repair and maintenance procedures. We are issuing this AD to detect discrepancies of the rudder, which could result in reduced structural integrity of the rudder.
88-22-09: 88-22-09 BOEING: Amendment 39-6054. Applies to Models 727 and 737 series airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished. \n\n\tTo prevent attempted takeoff with the airplane in the improper configuration and the takeoff warning system inoperative, accomplish the following: \n\n\tA.\tPrior to the accumulation of 200 flight hours after the effective date of this AD and thereafter at intervals not to exceed 200 flight hours, perform an operational and functional check of the takeoff configuration warning system in accordance with the established and approved procedures in Section 31-26-0 of the FAA-approved Boeing Model 727 or Model 737 Maintenance Manual, as appropriate. Repair or replace any inoperative component before further flight. \n\n\tNOTE: The following items are to be included in the required checks: \n\n\t\t1.\tThrottle Switch(s)- assure proper contact \n\t\t2.\tFlap position switches \n\t\t3.\tElevator out of green band switches \n\t\t4.\tSpeed brake switch \n\t\t5.\tAPU door switch (if installed) \n\t\t6.\tLeading edge slat switches \n\t\t7.\tAir/Ground Relay \n\n\tB.\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 for alternate means of compliance 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\tC.\tSpecial 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. \n\n\tAll persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. This information may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment, 39-6054, becomes effective November 10, 1988.
99-18-19: This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company CF6-80A1/A3 and CF6-80C2A series turbofan engines, installed on Airbus Industrie A300-600 and A310 series airplanes. This action requires, prior to further flight, one of the following: (1) performing a DPV pressure check for leakage, and, if necessary, replacing the DPV assembly with a serviceable assembly and performing an operational check of the thrust reverser, or deactivating the thrust reverser; or (2) replacing the directional pilot valve (DPV) assembly with a serviceable assembly and performing an operational check of the thrust reverser. Thereafter, this AD requires one of these actions on a repetitive basis. If a thrust reverser is deactivated, this action requires, prior to further flight, revising the FAA-approved airplane flight manual (AFM) to require performance penalties to be applied for certain takeoff conditions. The AD also requires a revision to theEmergency Procedures Section of the FAA approved AFM to include a flightcrew operational procedure in the event of any indication of an in-flight thrust reverser deployment. This amendment is prompted by review of thrust reverser safety analyses following a report of inadvertent thrust reverser deployment on another make and model engine. The actions specified in this AD are intended to prevent inadvertent thrust reverser deployment, which, if it occurred in-flight, could result in loss of control of the airplane.
99-22-11: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model BAe 146 and Avro 146-RJ series airplanes, that requires installation of modified roller sub-assemblies in both the main landing gear (MLG) door lock and the MLG uplock. 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 prevent failure of the roller sub-assemblies, which could result in failure of the MLG to retract and lock after takeoff, or to deploy properly for landing.
99-21-12: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace (Jetstream) Model 4101 airplanes, that requires a one-time visual inspection of the conduit pipe for distortion or repairs, and replacement of the conduit pipe with a new pipe, if necessary. This amendment also requires replacement of the cable assemblies to the fuel standby pumps with new cable assemblies that have improved sheathing protection. 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 prevent electrical arcing due to damaged fuel standby pump cable assemblies and conduit pipes, which could create a possible ignition source, and consequent fire hazard.
2006-07-03: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A321-100 and -200 series airplanes. This AD requires replacing the crashworthiness pins on the side-stay of the main landing gear (MLG) with new pins having an increased internal notch diameter. This AD results from testing on the side-stay crashworthiness pins on the MLG, which revealed that, in the case of an emergency landing, the crashworthiness pins installed will not ensure a correct MLG collapse. We are issuing this AD to prevent a punctured fuel tank, which could cause damage to the airplane or injury to passengers.
98-14-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires modification of the ground cooling fan. 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 prevent failure of the ground cooling fan, which could result in smoke in the flight deck and cabin and consequent inability of the flight crew to perform duties or possible passenger injury due to smoke inhalation.
99-18-18: This amendment adopts a new airworthiness directive (AD) that is applicable to Dowty Aerospace Propellers Model R381/6-123-F/5 propellers. This action requires initial and repetitive visual and ultrasonic (UT) inspections of propeller blades for cracks across the camber face, and, if blades are found cracked, replacement with serviceable blades. This amendment is prompted by reports of a cracked composite propeller blade. The actions specified in this AD are intended to prevent propeller blade cracks and propagation, which could result in propeller blade separation and possible aircraft loss of control.
2006-06-14: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A318-100 and A319-100 series airplanes, A320-111 airplanes, A320-200 series airplanes, and A321-100 and A321-200 series airplanes. This AD requires operators to review the airplane's maintenance records to determine the part numbers of the magnetic fuel level indicators (MFLI) of the wing fuel tanks, and related investigative and corrective actions if necessary. This AD results from several in-service incidents of wear and detachment of the top-stops from the MFLI. Such detachment allows the top-stop to move around the wing fuel tank, and the top-stop could come into contact or in close proximity with a gauging probe, resulting in compromise of the air gap between the probe and the structure and creating a potential ignition source. We are issuing this AD to prevent an ignition source in the wing fuel tank in the event of a lightning strike, which could result in a fire or explosion.
98-14-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires a one-time visual inspection to detect cracking in the axle adapter of the shock absorber of the nose landing gear (NLG), and corrective actions, if necessary. 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 correct cracking in the axle adapter of the shock absorber of the NLG, which could result in failure of the NLG and consequent damage to the airplane structure.
80-10-02: 80-10-02 MESSERSCHMITT-BOLKOW-BLOHM: Amendment 39-3765. Applies to Model BO-105 series helicopters with tail rotor blade grip P/N 105-31711 or P/N 105-31722 installed, certificated in any category. To prevent failure of the tail rotor system, accomplish the following: (a) Within the next 10 hours time in service after the effective date of this AD, unless already accomplished within the last 90 hours time in service, and thereafter at intervals not to exceed 100 hours time in service from the last inspection, inspect the visible part of the inner surface of the tail rotor blade grip clevis area (do not remove blade retaining bolt bushings) for cracks using the dye penetrant method in accordance with Messerschmitt-Bolkow-Blohm BO- 105 Alert Service Bulletin No. 18 dated March 15, 1979, or an FAA-approved equivalent. (b) Within the next 100 hours after installing a replacement tail rotor blade grip in accordance with paragraph (g) of this AD, and thereafter at intervals not to exceed 100 hours time in service from the last inspection, inspect the visible part of the inner surface of the tail rotor blade grip clevis area (do not remove blade retaining bolt bushings) for cracks using the dye penetrant method in accordance with Messerschmitt-Bolkow-Blohm BO-105 Alert Service Bulletin No. 18 dated March 15, 1979, or an FAA-approved equivalent. (c) Within the next 100 hours time in service after the effective date of this AD - (1) Visually inspect the inboard end of the tail rotor blade grip for cracks in accordance with paragraph 2.A.1 "Accomplishment Instructions" of Messerschmitt-Bolkow- Blohm Service Bulletin 30-24 dated December 1, 1978, or an FAA-approved equivalent; and (2) Inspect the tail rotor blade grip in the vicinity of the bore of the laminated pack retaining bolt (on the inner side) for cracks using the dye penetrant method in accordance with paragraph 2.A.2 "Accomplishment Instructions" of Messerschmitt-Bolkow- Blohm BO-105 Service Bulletin 30-24 dated December 1, 1978, or an FAA-approved equivalent. (d) Within the next 100 hours time in service after accomplishing the inspection required by paragraph (c)(1) of this AD or installing a replacement tail rotor blade grip in accordance with paragraph (g) of this AD, and thereafter at intervals not to exceed 100 hours time in service from the last inspection, visually inspect the inboard end of the tail rotor blade grip for cracks in accordance with "Special Inspections." Chapter 10 of the Messerschmitt-Bolkow- Blohm BO-105 Maintenance and Overhaul Manual or an FAA-approved equivalent. (e) Within the next 600 hours time in service after accomplishing the inspection required by paragraph (c)(2) of this AD or installing a replacement tail rotor blade grip in accordance with paragraph (g) of this AD, and thereafter at intervals not to exceed 600 hours from the last inspection, inspect the tail rotor blade grip in the vicinity of the bore of the laminated pack retaining bolt (on the inner side) for cracks using the dye penetrant method in accordance with "Special Inspections," Chapter 10, of the Messerschmitt-Bolkow-Blohm BO-105 Maintenance and Overhaul Manual or an FAA-approved equivalent. (f) If, during any inspection required by this AD, any cracks are found, before further flight, replace the cracked tail rotor blade grip in accordance with paragraph (g) of this AD. (g) For all replacement tail rotor blade grips installed after the effective date of this AD - (1) Use a new or used crack-free tail rotor blade grip of the same part number. Before installation of a used tail rotor blade grip, inspect the part using the dye penetrant method to ensure that it is crack-free; and (2) Comply with the repetitive inspection requirements of paragraphs (b), (d), and (e) of this AD. NOTE: This AD applies to both tail rotor blade grips installed on the helicopter. This amendment becomes effective May 1, 1980, as to all persons except those persons to whom it was made immediately effective by the telegram dated March 30, 1979, which contained this amendment.