Results
2015-12-11: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767 and 777 airplanes. This AD was prompted by reports of uncommanded door closure of a large lower lobe cargo door. This AD requires inspecting for part numbers and serial numbers of the rotary actuators of the forward and aft large lower lobe cargo doors, as applicable, and corrective action if necessary. We are issuing this AD to detect and correct rotary actuators made with a material having poor actuator gear wear characteristics, which could result in failure of the rotary actuators for the forward or aft large lower lobe cargo doors and subsequent uncommanded door closure, which could possibly result in fatal injury to people on the ground.
95-03-04: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model Viscount 744, 745D, and 810 series airplanes, that requires repetitive inspections to detect fatigue cracking in the pivot pins that attach both nose wheel steering actuators to the steering head assembly, and replacement of cracked pins. This amendment is prompted by a reported failure of a pivot pin due to fatigue cracking. The actions specified by this AD are intended to prevent failure of the pivot pin, which could result in the loss of nose wheel steering capability.
2005-06-08: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A330, A340-200, and A340-300 series airplanes. This AD requires repetitive inspections of a certain bracket that attaches the flight deck instrument panel to the airplane structure; replacement of the bracket with a new, improved bracket; and related investigative and corrective actions if necessary. This AD is prompted by reports of cracking of a certain bracket that attaches the flight deck instrument panel to the airplane structure. We are issuing this AD to detect and correct a cracked bracket. Failure of this bracket, combined with failure of the horizontal beam, could result in collapse of the left part of the flight deck instrument panel, and consequent reduced controllability of the airplane.
2024-02-51: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-9 airplanes. This AD was prompted by a report of an in-flight departure of a mid cabin door plug, which resulted in a rapid decompression of the airplane. This AD prohibits further flight of affected airplanes, until the airplane is inspected and all applicable corrective actions have been performed. The FAA previously sent an emergency AD to all known U.S. owners and operators of these airplanes. The FAA is issuing this AD to address the unsafe condition on these products.
2015-12-05: We are superseding Airworthiness Directive (AD) 2008-06-18 for all Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A300 series airplanes. AD 2008- 06-18 required repetitive inspections for any cracking of the wing lower skin panel and associated internal support structure, and if necessary, corrective actions such as modifying the lower panel inboard of rib 9 aft of the rear spar and repairing cracks. This new AD continues to require actions required by AD 2008-06-18, and reduces certain compliance times. This AD was prompted by a report that information from an analysis and a fleet survey shows a need for reduced compliance times and intervals. We are issuing this AD to detect and correct cracking, which could lead to reduced structural integrity of the airplane.
2005-05-52: The FAA is adopting a new airworthiness directive (AD) to supersede emergency AD 2005-05-51 and AD 2000-23-01 for The Cessna Aircraft Company (Cessna) Models 402C and 414A airplanes. This AD contains the same information as emergency AD 2005-05-52 and publishes the action in the Federal Register. It requires you to eddy current inspect the forward wing spars and visually inspect the aft and auxiliary spars. This AD is the result of extensive cracks found on three wing spars of the affected airplanes. We are issuing this AD to detect and correct cracking in the wing spars before the cracks grow to failure. Such a wing failure could result in the wing separating from the airplane with consequent loss of control of the airplane. DATES: This AD becomes effective on March 21, 2005, to all affected persons who did not receive emergency AD 2005-05-52, issued March 2, 2005. Emergency AD 2005-05-52 contained the requirements of this amendment and became effective immediately upon receipt. As of March 21, 2005, the Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations. We must receive any comments on this AD by April 30, 2005.
95-12-06: This amendment adopts a new airworthiness directive (AD) that applies to certain Jetstream Aircraft Limited (JAL) Jetstream Models 3101 and 3201 airplanes. The action requires modifying the shear fitting at the top of each escape hatch. A report of interference between the shear fitting on an escape hatch and a ceiling panel found while removing the escape hatch on one of the affected airplanes prompted this AD. The actions specified by this AD are intended to prevent the inability to utilize an escape hatch during an emergency situation because of interference.
2023-25-13: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-2B16 (604 Variant) airplanes. This AD was prompted by a report that some airplanes were delivered without a portable protective breathing equipment (PBE) device located in the left-side forward wardrobe, flight deck, or passenger cabin area of the airplane. This AD requires visually inspecting the forward left side cabin area of the airplane to determine if the portable PBE device is installed and, if not installed, requires installing the portable PBE device along with the associated placard. The FAA is issuing this AD to address the unsafe condition on these products.
96-09-19: This amendment adopts a new airworthiness directive (AD), applicable to all Jetstream Model 4101 airplanes, that requires revising the Airplane Flight Manual (AFM) to provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions, and to limit or prohibit the use of various flight control devices. This amendment is prompted by results of a review of the requirements for certification of the airplane in icing conditions, new information on the icing environment, and icing data provided currently to the flight crews. The actions specified by this AD are intended to prevent minimize the potential hazards associated with operating the airplane in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
2005-05-53 R1: The FAA is adopting a new airworthiness directive (AD) to revise emergency AD 2005-05-53 for The Cessna Aircraft Company (Cessna) Models 172R, 172S, 182T, and T182T airplanes. This AD contains the same information as emergency AD 2005-05-53 R1 and publishes the action in the Federal Register. It requires you to do a one-time detailed inspection of the flight control system, correct installations that do not conform to type design, and repair any damage. This AD is the result of flight control system problems found on airplanes within Cessna's control that could also exist on airplanes produced and delivered within a certain time period. We are issuing this AD to prevent loss of airplane control due to incorrect or inadequate rigging of critical flight systems. DATES: This AD becomes effective on March 21, 2005, to all affected persons who did not receive emergency AD 2005-05-53 R1, issued March 5, 2005. Emergency AD 2005-05-53 R1 contained the requirements of this amendment and became effective immediately upon receipt. As of March 21, 2005, the Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations. We must receive any comments on this AD by April 30, 2005.
2023-25-12: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A318-112 airplanes; Model A319-115, -132, -133, -151N, -153N, and -171N airplanes; Model A320-211, -212, -214, -231, -232, - 251N, -252N, -253N, -271N, -272N, and -273N airplanes; and Model A321- 112 airplanes. This AD was prompted by a report that the fatigue life limit of the motoreductor installed on the on-board entrance stairs is not demonstrated for the complete airplane design service goal (DSG). This AD requires repetitive replacement of the motoreductor for onboard entrance stairs, and it limits the installation of affected parts under certain conditions, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2023-26-01: The FAA is adopting a new airworthiness directive (AD) for all Embraer S.A. Model ERJ 190-300 and -400 airplanes. This AD was prompted by a report that the method for calculating level-off altitude by the computerized airplane flight manual (CAFM), may result in a non- conservative level-off height. This AD requires revising the existing airplane flight manual (AFM) to incorporate new CAFM versions as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2005-06-12: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-300, 747SP, and 747SR series airplanes. That AD currently requires one-time inspections for cracking in certain upper deck floor beams and follow-on actions. This new AD expands the existing inspection area and requires inspecting fastener holes in certain areas of airplanes modified previously, and taking corrective actions if necessary. This action also defines new sources for instructions for repairs and post-modification/repair inspections. This AD is prompted by reports of fatigue cracking of the upper chord of certain upper deck floor beams. We are issuing this AD to find and fix cracking in certain upper deck floor beams, which could extend and sever floor beams adjacent to the body frame and result in rapid depressurization and loss of controllability of the airplane. \n\n\nDATES: This AD becomes effective April 25, 2005.The incorporation by reference of Boeing Service Bulletin 747- 53A2459, Revision 1, dated March 11, 2004, is approved by the Director of the Federal Register as of April 25, 2005. \n\n\tOn October 16, 2002 (67 FR 57510, September 11, 2002), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 747-53A2459, dated January 11, 2001.
96-06-12: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 96-06-12 which was sent previously to all known U.S. owners and operators of Bell Helicopter Textron, Inc. (Bell) Model 47B, 47B-3, 47D, 47D-1, 47G, 47G-2, 47G-2A, 47G-2A-1, 47G-3, 47G-3B, 47G-3B-1, 47G-3B-2, 47G-3B-2A, 47G-4, 47G-4A, 47G-5, 47G-5A, 47H-1, 47J, 47J-2, 47J-2A, and 47-K helicopters by individual letters. This AD requires a visual inspection of each tail rotor blade (blade) tip, abrasion strip, blade skin, and blade butt for corrosion or delamination. This amendment is prompted by reports that a number of Model 47 helicopter blades were manufactured using a clad aluminum alloy material instead of a bare aluminum alloy material. The actions specified by this AD are intended to prevent premature delamination or separation of the blade tip block or the abrasion strip, which could lead to failure of the blade and subsequent loss of control of the helicopter.
2023-25-11: The FAA is superseding Airworthiness Directive (AD) 2021-02- 18, which applied to all Airbus Defense and Space S.A. Model CN-235, CN-235-100, CN-235-200, and CN-235-300 airplanes and Model C-295 airplanes. AD 2021-02-18 required repetitive inspections for cracking or broken rivets of certain left- and right-hand stringers and surrounding structure, and repair if necessary. This AD was prompted by a modification that was developed to reinforce the structure in the affected area, providing terminating action for the repetitive inspections required by AD 2021-02-18. This AD continues to require certain actions in AD 2021-02-18 and requires the new terminating action for the repetitive inspections, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
91-12-09: 91-12-09 GENERAL ELECTRIC COMPANY: Amendment 39-7020. Docket No. 91-ANE- 11. Applicability: General Electric Company (GE) CF6-6 series turbofan engines installed on, but not limited to, McDonnell Douglas DC10-10 aircraft. Compliance: Required as indicated, unless previously accomplished. To prevent an uncontained engine failure and damage to the aircraft, accomplish the following: (a) Eddy current inspect in accordance with GE CF6-6 Service Bulletin (SB) 72- 947, Revision 4, dated February 8, 1991, the bore forward corner of stage 1 fan disks identified by serial number (S\N) in Tables 2, 3, and 3 Addendum of GE CF6-6 SB 72-947, Revision 4, dated February 8, 1991, as follows: (1) For disks which have not received an eddy current inspection in accordance with the Accomplishment Instructions of GE CF6-6 SB 72-947, Revision 4, dated February 8, 1991, in accordance with the following schedule: (i) Within the next 100 cycles in service (CIS) after the effective date of this AD for those disks which on the effective date of this AD have accumulated 1,250 CIS or greater since accomplishing the immersion ultrasonic inspection of AD 89-20-01 R1, Amendment 39-6411 (54 FR 51015; December 12, 1989). (ii) Within the next 100 CIS after the effective date of this AD or prior to accumulating 1,250 CIS since accomplishing the immersion ultrasonic inspection of AD 89-20-01 R1, whichever comes later for those disks which on the effective date of this AD have accumulated less than 1,250 CIS since the immersion ultrasonic inspection. (2) For those disks which on the effective date of this AD have received an eddy current inspection in accordance with the Accomplishment Instructions of GE CF6-6 SB 72-947, Revision 4, dated February 8, 1991, in accordance with the following schedule: (i) Within the next 100 CIS after the effective date of this AD for those disks which on the effective date of this AD have accumulated 1,500 CIS or greater since accomplishing the immersion ultrasonic inspection of AD 89-20-01 R1. (ii) Within the next 100 CIS after the effective date of this AD or prior to accumulating 1,500 CIS since accomplishing the immersion ultrasonic inspection of AD 89-20-01 R1, whichever comes later, for those disks which on the effective date of this AD have accumulated less than 1,500 CIS since accomplishing the immersion ultrasonic inspection. (b) Thereafter, eddy current inspect the bore forward corner of stage 1 fan disks which meet the acceptance criteria of paragraph 2.B.(2)(c) of the Accomplishment Instructions of GE CF6-6 SB 72-947, Revision 4, dated February 8, 1991, at intervals not to exceed 500 CIS since last eddy current inspection. (c) Remove from service prior to further flight and replace with a serviceable part, disks inspected in accordance with paragraphs (a) and (b) of this AD, which do not meet the acceptance criteria of paragraph 2.B.(2)(c) of the Accomplishment Instructions of GE CF6-6 SB 72-947, Revision 4, dated February 8, 1991. (d) Remove from service all stage 1 fan disks identified by S/N in Tables 2, 3, and 3 Addendum of GE CF6-6 SB 72-947, Revision 4, dated February 8, 1991, at the next shop visit but no later than 2,500 CIS since immersion ultrasonic inspection or June 30, 1992, whichever occurs first. (e) For the purpose of this AD, "shop visit" is defined as the induction of the engine into the shop for any reason. (f) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (g) Upon submission of substantiating data by an owner or operator through an FAA (maintenance, avionics, or operations) Inspector, an alternate method of compliance with the requirements of this AD or adjustments to the compliance schedules specified in this AD may be approved by the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803- 5299. The inspections shall be done in accordance with the following General Electric service document: Document No. Page No. Issue Date CF6-6 SB 72-947 1 thru 13 Rev. 4 Feb. 8, 1991 Total Pages: 13 This incorporation was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to General Electric Company, Technical Publications Department, 1 Neumann Way, Cincinnati, Ohio 45215. This information may be examined at the FAA, New England Region, Office of the Assistant Chief Counsel, Room 311, 12 New England Executive Park, Burlington, Massachusetts 01803-5299. This amendment (39-7020, AD 91-12-09) becomes effective on June 27, 1991.
2023-24-08: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by reports that the nose wheel steering selector valve (SSV) can be slow to deactivate under low temperature conditions. This AD requires replacing the affected SSV with a re-designed SSV that has an improved response time. The FAA is issuing this AD to address the unsafe condition on these products.
90-01-05: 90-01-05 BOEING: Amendment 39-6443. Docket No. 89-NM-167-AD. Applicability: Model 767 series airplanes, as listed in Boeing Service Bulletin 767-25-0123, dated May 25,1989, certificated in any category. \n\n\tCompliance: Required within the next 90 days after the effective date of this AD, unless previously accomplished.\n \n\tTo ensure proper arming of the emergency evacuation slide mechanism for entry/service doors and to preventa false armed indication, accomplish the following: \n\n\tA. For Group 1 airplanes, perform the inspection and rework of the acoustical seal for entry/service doors in accordance with paragraph III., Part B., of Boeing Service Bulletin 767-25-0123, dated May 25, 1989, or Revision 1, dated September 14, 1989. \n\n\tB. For Group 2 airplanes, rework the acoustical seal for entry/service doors in accordance with paragraph III., Part C., of Boeing Service Bulletin 767-25-0123, dated May 25, 1989, or Revision 1, dated September 14, 1989. \n\n\tC. An alternate means ofcompliance 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. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment, and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tD. Special 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. All 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, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington.\n\n This amendment (39-6443, AD 90-01-05) becomes effective on February 5, 1990.
2023-25-04: The FAA is superseding Airworthiness Directive (AD) 2022-08- 04, which applied to all Airbus SAS Model A300 series airplanes. AD 2022-08-04 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. Since the FAA issued AD 2022-08-04, the FAA has determined new or more restrictive airworthiness limitations are necessary. This AD continues to require the actions of AD 2022-08-04, and requires new or more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2005-06-11: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747-100, -100B, -100B SUD, -200B, and -300 series airplanes; and Model 747SR and 747SP series airplanes. That AD currently requires repetitive inspections to detect fatigue cracking in the upper deck floor beams located at certain body stations, and repair, if necessary. This new AD lowers the threshold for the existing inspections and requires new repetitive inspections of previously repaired areas, and repair if necessary. This AD is prompted by the results of an additional detailed analysis that indicate fatigue cracks can initiate sooner than has previously been observed. We are issuing this AD to prevent failure of the upper deck floor beams at certain body stations due to fatigue cracking, which could result in rapid decompression and reduced controllability of the airplane.
2023-24-07: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A310 airplanes. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
78-16-04: 78-16-04 CESSNA: Amendment 39-3273. Applies to Model 336 airplanes. Compliance: Required as indicted, unless already accomplished. To provide loading instructions which will limit aircraft loading to an acceptable center of gravity, within the next 100 hours time-in-service after the effective date of this AD, accomplish the following: A) Modify the Cessna weight and balance data included in the Model 336 airplane as follows: 1. Modify the center of gravity moment envelope on Page 1 by drawing a straight line between the two points (3900 pounds - 548,730 pounds-inches and 2500 pounds - 351,751 pounds-inches) and cover or obliterate the lines establishing the right side of the existing center of gravity moment envelope. 2. Modify the normal category center of gravity limits chart on Page 2 by drawing a vertical line at the 140.7 inches aft of datum point from the 2500 to 3900 pounds lines and cover or obliterate the lines establishing the right side of the existing normal category center of gravity limits envelope. B) Below the existing capacity placard located on the baggage compartment door install a permanent placard which reads as follows: "CAUTION - AFT CENTER OF GRAVITY LIMITATION MAY RESTRICT LOADING OF THIS COMPARTMENT TO LESS THAN 365 POUNDS" and operate the aircraft in accordance with this limitation. This placard should be fabricated of .032 inch minimum thickness aluminum or plastic material with minimum 3/16-inch high stamped or engraved letters and installed using threaded or rivet type fasteners. C) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective October 14, 1978.
2005-06-06: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A319, A320, and A321 series airplanes. This AD requires modification of certain auxiliary power unit (APU) alternating current (AC) generators. This AD is prompted by a report of an explosion in the APU compartment, which blew open the compartment doors. We are issuing this AD to prevent oil vapor leakage from the APU AC generator, which, when combined with an electric arc at the electrical receptacle, could result in a fire or explosion in the APU compartment during flight.
2023-25-08: The FAA is adopting a new airworthiness directive (AD) for all Leonardo S.p.a. Model A109E, A109S, AW109SP, A119, and AW119 MKII helicopters. This AD was prompted by multiple reports of excessive axial play on the ball bearing of the lower half of the main rotor (MR) rotating scissor assembly. This AD requires one-time scissor coupling and axial play inspections and repetitive quantitative axial play inspections and, depending on the results, additional inspections and replacing certain parts. This AD also requires reporting information and prohibits installing certain parts unless certain inspections have been accomplished. These requirements are specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2023-25-14: The FAA is superseding Airworthiness Directive (AD) 2022-27- 09, which applied to certain Airbus Helicopters Model EC130T2 helicopters. AD 2022-27-09 required repetitively inspecting the vibration level on the tail rotor drive shaft and, depending on the results, taking corrective action. AD 2022-27-09 also required reporting information and prohibited installing certain rotor drive shafts unless the inspection was done. Since the FAA issued AD 2022-27- 09, Airbus Helicopters revised its service information to update the procedures for inspecting that vibration level, reduce an allowable vibration level, and clarify when a balance correction may be accomplished. This AD was prompted by the determination that a certain vibration measurement tool was providing unexpected results and therefore the threshold must be revised. This AD continues to require certain actions in AD 2022-27-09 and also revises the procedures for inspecting the vibration level on the tail rotor drive shaft and depending on these results, requires replacing certain parts, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.