Results
2003-04-24: This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model 717-200 airplanes. This action requires a one-time inspection for cracking of the support fitting assemblies and stop pads of the main spoiler actuators, and follow-on actions. This action is necessary to find and fix cracking of the support fitting assemblies of the main spoiler actuator, which could result in damage of adjacent structure such as the rear spar or upper skin panel, and consequent reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
2020-21-18: The FAA is superseding Airworthiness Directive (AD) 2019-14- 09, which applied to all Airbus SAS Model A330-200 Freighter series airplanes. AD 2019-14-09 required repetitive detailed inspections, including functional testing, of the oxygen crew and courier distribution system (OCCDS) and replacement of affected part(s) if necessary. This AD retains the requirements of AD 2019-14-09 and requires replacement of all affected parts with improved serviceable parts, which is terminating action for the repetitive inspections, as specified in a European Union Aviation Safety Agency (EASA) AD, which will be incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
66-29-03: 66-29-03 SIAI-MARCHETTI: Amdt. 39-313 Part 39 Federal Register November 23, 1966. Applies to Model S.205 Airplanes, Serial Numbers 101 through 222, 224, 228, 229, 231 through 233. Compliance required as indicated. To detect cracks on the rear spar web at areas adjacent to the aileron outboard hinge bracket bolts, 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, visually inspect the rear spar web for cracks in accordance with Siai Service Bulletin No. 205B4, dated September 14, 1966. If cracks are detected during this inspection, comply with (b) of this AD before further flight. (b) Modify the rear spar by incorporating a reinforcement as set forth in paragraph (b) of Siai Service Bulletin No. 205B4, dated September 14, 1966, or an FAA-approved equivalent. (c) The repetitive inspections required by (a) of this AD may be discontinued after the rear spar is reinforced in accordance with (b) of this AD. This directive effective November 23, 1966.
2003-04-20: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Raytheon Model DH.125, HS.125, BH.125, and BAe.125 (U-125 and C-29A) series airplanes; and Model Hawker 800, Hawker 800 (including variant U-125A), Hawker 800XP, and Hawker 1000 airplanes; that currently requires an inspection for cracking or corrosion of the cylinder head lugs of the main landing gear (MLG) actuator and follow-on/corrective actions. This amendment expands the applicability of the existing AD to add an airplane model and further clarify the applicability and, for certain airplanes, to clarify the compliance time of the inspection requirements. This action is necessary to prevent separation of the cylinder head lugs, which could prevent the MLG from extending and result in a partial gear-up landing. This action is intended to address the identified unsafe condition.
2018-03-13: We are adopting a new airworthiness directive (AD) for certain General Electric Company (GE) CT7-5A2, CT7-5A3, CT7-7A, CT7-7A1, CT7- 9B, CT7-9B1, CT7-9B2, CT7-9C and CT7-9C3 model turboprop engines. This AD requires initial and repetitive visual inspection and fluorescent- penetrant inspection (FPI) of the main propeller shaft. This AD was prompted by the failure of a main propeller shaft. We are issuing this AD to address the unsafe condition on these products.
97-01-11: 97-01-11 AIRBUS INDUSTRIE: Amendment 39-9882. Docket 92-NM-225-AD. Supersedes AD 96-20-02, amendment 39-9768. Applicability: Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 series airplanes, on which Modification 2626 has not been installed; certificated in any category. Compliance: Required as indicated, unless accomplished previously. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (f) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent fatigue cracking, which could result in reduced structural integrity of the airplane, accomplish the following: (a) For Model A300 B2-1C, B2K-3C, B2-203, B4-2C, and B4-103 series airplanes: Perform a detailed visual inspection to detect cracking of the fuselage, frame 47 at hole "I", in accordance with Airbus All Operator Telex (AOT) 53-02, dated November 2, 1992, at the times specified in paragraphs (a)(1) or (a)(2), as applicable. (1) For Model A300 B2-1C, B2K-3C, and B2-203 series airplanes: Perform the inspection prior to the accumulation of 15,000 total landings, or within 50 landings after November 4, 1996 (the effective date of AD 96-20-02, amendment 39-9768), whichever occurs later. (2) For Model A300 B4-2C and B4-103 series airplanes: Perform the inspection prior tothe accumulation of 18,700 total landings, or within 50 landings after November 4, 1996, whichever occurs later. (b) For Model A300 B4-203 series airplanes: Prior to the accumulation of 14,100 total landings, or within 50 landings after the effective date of this AD, whichever occurs later, perform a detailed visual inspection to detect cracking of the fuselage, frame 47 at hole "I", in accordance with Airbus All Operator Telex (AOT) 53-02, dated November 2, 1992. (c) If no crack is detected during the inspection required by paragraph (a) or (b) of this AD, repeat the detailed visual inspection at intervals not to exceed 200 landings. (d) If a crack is detected during any inspection required by paragraph (a), (b), or (c) of this AD, prior to further flight, repair in accordance with either paragraph (d)(1), (d)(2), or (d)(3) of this AD: (1) Repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate; or (2) Repair in accordance with crack repair procedures specified in Airbus A300 Service Bulletin 53-265, Revision 2, dated March 10, 1992; or (3) Repair in accordance with crack repair procedures specified in Airbus Service Bulletin A300-53-299, dated December 14, 1993. (e) Conducting a repetitive Rototest inspection of hole "I" in accordance with Airbus A300 Service Bulletin 53-265, Revision 2, dated March 10, 1992, or Airbus Service Bulletin A300-53-299, dated December 14, 1993, constitutes terminating action for the detailed visual inspections required by this AD. If any crack is found during a Rototest inspection, prior to further flight, repair it in accordance with that service bulletin. (f) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (g) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (h) The visual inspection shall be done in accordance with Airbus All Operator Telex (AOT) 53-02, dated November 2, 1992. This incorporation by reference was approved previously by the Director of the Federal Register, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51, as of November 4, 1996 (61 FR 50988, September 30, 1996). Copies may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (i) This amendment becomes effective on February 10, 1997.
2011-25-05: We are adopting a new airworthiness directive (AD) for The Boeing Company Model 767 airplanes. This AD requires installing new panel assemblies in the main equipment center or on the forward cargo compartment sidewall and removing certain relays from some panels in the main equipment center. This AD also requires revising the maintenance program to incorporate Airworthiness Limitations (AWLs) No. 28-AWL-27 and No. 28-AWL-28. This AD also includes an alternative location for the installation of the new panel assemblies for airplanes that have the optional water system drain plumbing and changing the interconnecting wiring between the P141 panel and the P36 and P37 panels. For airplanes with a deactivated center fuel tank, this AD also requires an alternative functional test for the left and right override/jettison pumps. We are issuing this AD to prevent possible sources of ignition in a fuel tank caused by electrical fault or uncommanded dry operation of the main tank boost pumps and center auxiliary tank override and jettison pumps. This AD was prompted by fuel system reviews conducted by the manufacturer. An ignition source in the fuel tank could result in a fire or an explosion and consequent loss of the airplane.
2003-04-18: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-90-30 airplanes, that requires measuring the length of the wear indicator on the brake stack of the main landing gear (MLG) brake assembly to determine the degree of wear, and follow-on actions. This action also requires eventual replacement of the existing MLG brake assembly with a new, improved or modified assembly, which constitutes terminating action for any repetitive actions being performed per this AD. The actions specified by this AD are intended to prevent failure of the MLG brakes and consequent loss of braking capability, which could result in the airplane overrunning the runway during take-off or landing. This action is intended to address the identified unsafe condition.
2018-03-21: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-202, -203, -223, and -243 airplanes. This AD requires contacting the FAA to obtain instructions for addressing the unsafe condition on these products, and doing the actions specified in those instructions. This AD was prompted by a design review of the airplane configuration incorporating certain fire extinguisher bottles and an optional galley cooling rack installation, which revealed that the air cooling rack is installed too close to the supply hose of a high rate fire extinguishing bottle. We are issuing this AD to address the unsafe condition on these products.
76-03-04: 76-03-04 RAVEN INDUSTRIES, INC.: Amendment 39-2508. Applies to Raven Model RX-6 hot air balloons certificated in all categories. Compliance required before further flight. To prevent cracking and breaking of the polyethylene gondola liner, accomplish the following: Install a placard on the instrument panel in clear view of the pilot, stating, "Operation limited to ground surface temperatures of 40 degrees F and above". The hot air balloon may be operated only when ground surface temperature is at or above 40 degrees F until modifications to reinforce the gondola liner, to be made available by Raven Industries, Inc., are installed. This amendment becomes effective February 13, 1976.