Results
2000-25-03: This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron Inc. (BHTI) Model 205A-1, 205B, 212, 412, and 412CF helicopters. This action requires inspecting the locking washer on each main rotor actuator (actuator) for twisting or damage to the tab and replacing any locking washer that has a twisted or damaged tab. Replacing certain locking washers, regardless of condition, is also required within a specified time period. Installing a certain airworthy locking device on each actuator constitutes terminating action for the requirements of this AD. This amendment is prompted by an incident in which a damaged locking washer allowed the rod end to detach from the collective actuator, causing loss of collective control of the main rotor. The current locking washer is subject to mechanical damage and failure, which allows the actuator piston to unthread itself from its rod end. This condition, if not corrected, could cause loss of control of the main rotor and subsequent loss of control of the helicopter.
2004-13-08: This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-60 series airplanes. This AD requires inspection of the welded joints of the balance weight brackets for the left and right elevator trim tabs for cracking; repetitive inspections, as applicable; and corrective actions including the eventual replacement of all brackets, which constitutes terminating action for the repetitive inspections. This action is necessary to prevent the loss of the balance weight for the elevator trim tab, which could result in incorrect trim during takeoff and landing, and reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2017-24-05: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports of cracking in the upper aft skin at the rear spar of the wings. This AD requires repetitive inspections for cracking of the upper aft skin of the wings, and repair if necessary. We are issuing this AD to address the unsafe condition on these products.
2000-25-05: This amendment supersedes an existing airworthiness directive (AD), applicable to certain EMBRAER Model EMB-135 and EMB-145 series airplanes, that currently requires a one-time inspection of the coupling hinge and locking fastener of the Gamah couplings of the fuel system tubing located in the wing dry bay to detect discrepancies, and follow-on corrective actions. This amendment retains those requirements and adds a requirement to revise the applicability of the existing AD to add certain airplanes. The actions specified in this AD are intended to prevent failure of the rivets of the Gamah couplings and consequent separation of a Gamah coupling, which could result in fuel leakage and consequent fire in or around the wing. This action is intended to address the unsafe condition.
2017-26-05: We are adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace Corporation Models G-1159A (GIII), G-IV, and GIV-X airplanes. This AD was prompted by a report that certain flap tracks were manufactured with the upper flange thickness less than design minimum. This AD requires replacing any defective flap track. We are issuing this AD to address the unsafe condition on these products.
2000-24-03: This amendment supersedes an existing airworthiness directive (AD), applicable to all Dornier Model 328-100 series airplanes, that currently requires revising the Airplane Flight Manual (AFM) to provide the flightcrew with additional information regarding procedures to ensure complete pressurization of the hydraulic lines for the flaps. This amendment requires revising the existing AFM revision to include a flap system test to be performed prior to the first flight of the day. This amendment also requires, for certain airplanes, modification of the flap actuators of the flight controls. The actions specified by this AD are intended to prevent an uncommanded retraction of the flaps during takeoff, which could result in an aborted takeoff and consequent potential for runway overrun.
86-25-07: 86-25-07 ROLLADEN-SCHNEIDER FLUGZEUGBAU GmbH: Amendment 39-5487. Applies to Model LS-6, all serial numbers. Compliance is required prior to further flight, after the effective date of this AD, unless already accomplished. To prevent possible damage of the control stick, accomplish the following: a) Remove Bezel from airspeed indicator and mask out the red arc with tape that would not interfere with airspeed indictor needle and readability of the instrument. b) Replace Bezel to airspeed indicator and mark a red radial line on the face of the Bezel 0.05" wide, 0.30" long at 200 km/h (108 kts) establishing a new maximum airspeed limit. c) Install a placard on the instrument panel in clear view of the pilot which states: "Maximum Airspeed (IAS): 200 km/h (108 kts)." d) On existing placard mask out with tape the yellow arc limitations 108 - 146 kts, and the following red arc airspeed indicator markings: Vne 6500 Ft 146 kts Vne 6501-9800 Ft 139kts Vne 9801-19700 Ft 118 kts e) Flight manual pages 2.2, Limitations; page 2.3, Airspeed Indicator Markings; page 2.7, Placards, are obsolete. f) Attach a copy of this Airworthiness Directive to the Flight Manual. NOTE: Rolladen-Schneider Technical Bulletin No. 6009 dated July 7, 1986, applies to this AD. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Aircraft Certification Office, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium 09667-1011; telephone 513.38.30 Ext 2710, or the Manager, New York Aircraft Certification Office, Aircraft Certification Division, FAA, New England Region, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581, telephone (516) 791-6220. 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. This amendmentbecomes effective December 30, 1986.
2000-24-15: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires a one-time detailed visual inspection to detect discrepancies of all electrical wiring installations in various areas of the airplane; and corrective actions, if necessary. This amendment is necessary to prevent electrical arcing and/or heat damaged wires due to improper wire installations during manufacture and/or maintenance of the airplane, and consequent fire and smoke in various areas of the airplane. This amendment is intended to address the identified unsafe condition.
98-14-08: 98-14-08 ROBINSON HELICOPTER COMPANY: Docket No. 98-SW-30-AD. Applicability: Model R22 helicopters, with forward flexplate, part number (P/N) A947-1 A through D, or P/N A193-1, installed, certificated in any category. NOTE 1: This AD applies to each helicopter 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 helicopters that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (b) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition, or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by thisAD. In no case does the presence of any modification, alteration, or repair remove any helicopter from the applicability of this AD. Compliance: Required within 25 hours time-in-service (TIS) or 15 calendar days, whichever occurs first, unless accomplished previously. To prevent failure of the flexplate, which could result in failure of the main rotor drive system and subsequent loss of control of the helicopter, accomplish the following: (a) Remove the flexplate and replace it with an airworthy flexplate, P/N A947-1 E or F, in accordance with the following: (1) With the clutch disengaged, support the forward end of the clutch shaft, P/N A166-1, and remove the forward flexplate, P/N A947-1 or A193-1, and the intermediate flexplate, P/N A947-2 or P/N A193-2. Record any shim locations for reinstallation. (2) Install a zero TIS forward flexplate, P/N A947-1 E or F, and any shims that were noted. Use washers, P/N AN960-516 or AN960-516L, under the nut so that 2-4threads are exposed. Torque the fasteners. (3) Inspect the sheave alignment. (4) Inspect the clutch shaft, P/N A166-1, angle. (5) Reinstall the intermediate flexplate and shim. NOTE 2: Robinson R22 Maintenance Manual, Sections 1.320, 7.230, 7.240, and 7.330 pertain to paragraphs (a)(2), (a)(3), (a)(4), and (a)(5) of this AD, respectively. NOTE 3: Robinson Helicopter Company R22 Service Bulletin SB-75, dated November 22, 1994, pertains to the subject of this AD. (b) 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, Los Angeles Aircraft Certification Office, FAA. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Los Angeles Aircraft Certification Office. NOTE 4: Information concerning the existence of approved alternative methods of compliance with thisAD, if any, may be obtained from the Los Angeles Aircraft Certification Office. (c) 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 helicopter to a location where the requirements of this AD can be accomplished. (d) Priority Letter AD 98-14-08, issued June 25, 1998, becomes effective upon receipt.
97-13-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires loosening certain nuts on the horizontal stabilizer control unit (HSCU) to reduce stress on bolts; a one-time inspection of certain bolts on the HSCU to detect cracking, and replacement, if necessary; application of corrosion protection to these bolts; and reassembly and reidentification of the modified HSCU. This amendment is prompted by reports indicating that stress corrosion, resulting from overtightening of nuts on these bolts, has caused some of these bolts to crack and fail. The actions specified by this AD are intended to prevent failure of these bolts because of stress corrosion cracking which, if not corrected, could lead to loss of control of the horizontal stabilizer and reduced controllability of the airplane.