Results
95-23-05: This amendment supersedes an existing airworthiness directive (AD), applicable to Robinson Helicopter Company Model R22 series helicopters, that currently requires an inspection and repetitive visual checks for slippage of the tail rotor (T/R) drive and replacement of the T/R gearbox, if necessary. This amendment requires disassembly of the T/R gearbox to verify the installation of the input and output shaft keys (keys) between the input and output pinions and their respective shafts. This amendment is prompted by two incidents in which the key was not installed between the output shaft and the output pinion during assembly of the T/R gearbox at Robinson Helicopter Company. The actions specified by this AD are intended to prevent slippage of the T/R drive, loss of directional control, and subsequent loss of control of the helicopter.
93-21-09: 93-21-09 AIRBUS INDUSTRIE: Amendment 39-8723. Docket 93-NM-62-AD. Applicability: Model A320-111 series airplanes, serial numbers 005 through 012 inclusive, on which Modification 20774, as described in Airbus Industrie Service Bulletin A320- 53-1004, Revision 1, dated July 30, 1992, has not been accomplished; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent loss of structural integrity of the fuselage, accomplish the following: (a) Prior to the accumulation of 10,000 total landings, or within the next 60 days after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 6,000 landings, perform an external detailed visual inspection to detect breakage of the rivet heads at the junction between frame 15 and the skin on the left and right side, between stops 3 and 7, in accordance with Airbus Industrie Service Bulletin A320-53 -1069, dated August 17, 1991. (1) Ifno breakage is detected on any rivet head: Prior to the accumulation of 22,000 total landings, or within 180 days after the effective date of this AD, whichever occurs later, replace all of the currently installed rivets with new or serviceable high-strength titanium Hilite bolts in accordance with Airbus Industrie Service Bulletin A320-53-1004, Revision 1, dated July 30, 1992, as revised by Change Notice 1.A., dated October 12, 1992. (2) If breakage is detected on fewer than 2 rivet heads on each side: Within the next 100 landings after discovery of breakage, replace all of the currently installed rivets with new or serviceable high-strength titanium Hilite bolts in accordance with Airbus Industrie Service Bulletin A320-53-1004, Revision 1, dated July 30, 1992, as revised by Change Notice 1.A., dated October 12, 1992. (3) If breakage is detected on 2 or more rivet heads on either side: Prior to further flight, replace all of the currently installed rivets with new or serviceable high-strength titanium Hilite bolts in accordance with Airbus Industrie Service Bulletin A320-53-1004, Revision 1, dated July 30, 1992, as revised by Change Notice 1.A., dated October 12, 1992. (b) Replacement of all of the currently installed rivets with new or serviceable high- strength titanium Hilite bolts in accordance with Airbus Industrie Service Bulletin A320-53-1004, Revision 1, dated July 30, 1992, as revised by Change Notice 1.A., dated October 12, 1992, constitutes terminating action for the repetitive inspection requirements of this AD. (c) 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: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (e) The inspection and replacement shall be done in accordance with Airbus Industrie Service Bulletin A320-53-1069, dated August 17, 1991; Airbus Industrie Service Bulletin A320-53-1004, Revision 1, dated July 30, 1992; and Service Bulletin Change Notice 1.A., dated October 12, 1992, for Airbus Industrie Service Bulletin A320-53-1004, Revision 1, dated July 30, 1992. Revision 1 of Airbus Industrie Service Bulletin A320-53-1004 contains the following list of effective pages: Page Number Revision Level Shown on Page Date Shown on Page 1-4, 6-8 1 July 30, 1992 5, 9-11 Original April 5, 1989 This incorporation by reference wasapproved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. 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. (f) This amendment becomes effective on December 13, 1993.
2008-16-03: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: This Airworthiness Directive (AD) is prompted due to the discovery of cracked or broken leaf springs P/N 6232.0175.01 installed in the overhead flap-operating mechanism of some PC-6 aircraft. A broken leaf spring could lead to an uncommanded flap retraction which could lead to hazardous situations and subsequent loss of control of the aircraft. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2020-21-09: The FAA is correcting an airworthiness directive (AD) that published in the Federal Register. That AD applies to all Airbus SAS Model A318 series airplanes; Model A319 series airplanes; Model A320 series airplanes; and Model A321 series airplanes. As published, a paragraph reference located in the reporting exception is incorrect. This document corrects that error. In all other respects, the original \ndocument remains the same.
2001-22-12: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 727 series airplanes. This action requires repetitive inspections for migration or corrosion of the outer hinge pins that attach the horizontal stabilizer to the vertical fin, and various follow-on actions, if necessary. This action also provides other repetitive inspections for cracking or corrosion of the hinge pins, which terminate the required repetitive inspections for migration or corrosion; these inspections are optional for airplanes on which no migration or corrosion is found. This action is necessary to find and fix corrosion or cracking in the hinge pins of the horizontal stabilizer, which could lead to structural degradation of the hinge of the horizontal stabilizer and result in loss of the horizontal stabilizer and consequent loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
88-18-07: 88-18-07 BRITISH AEROSPACE (BAe): Amendment 39-6000. Applies to Model 3101 (includes Model 3100) Jetstream (Serial Numbers 601 thru 646, 648 thru 655, 657, 658, 660 thru 666, 668 thru 695, 697 thru 708, 710 thru 713, 715 thru 741, 743 thru 756, and 758 thru 761) airplanes certificated in any category. Compliance: Required within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent electrical arcing and possible damage to the airplane with loss of essential electrical bus services, accomplish the following: (a) Visually inspect for correct cable terminal ends on cable PD4 and PD6 at terminal post T1BH-2 as described in British Aerospace (BAe) Alert Service Bulletin (ASB) Jetstream 24-A-JM7631, dated September 10, 1987, "Part A - Initial Inspection". If the installation is not as described in the above ASB, prior to further flight modify the cable terminal configuration of cables PD4 and PD6 at terminal postT1BH-2 as described in BAe ASB Jetstream 24-A-JM7631, dated September 10, 1987, "Part B - Rectification". (b) A 10 percent adjustment to the compliance time may be used to allow accomplishment of the AD with other scheduled maintenance activities. (c) The airplane may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (d) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA c/o American Embassy, 1000 Brussels, Belgium. All persons affected by this directive may obtain copies of the document referred to herein upon request to British Aerospace, Technical Librarian, Post Office Box 17414, Dulles International Airport, Washington, D.C. 20091; Telephone (703) 435-9100; or may examine this document at the FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106.This amendment, 39-6000, becomes effective on September 16, 1988.
95-23-11: This amendment adopts a new airworthiness directive (AD) that applies to certain Aerostar Aircraft Corporation (Aerostar) PA-60-600 series airplanes. This action requires repetitively inspecting the fuselage horizontal stabilizer attach fittings for cracks, and replacing any cracked fuselage horizontal stabilizer attach fitting. A report of several cracks found on the forward horizontal stabilizer attach spar fitting on an Aerostar Model PA-60-601P airplane prompted this action. The actions specified by this AD are intended to prevent undetected cracked fuselage horizontal attach fittings, which could result in the fuselage horizontal stabilizer separating from the airplane while in flight with subsequent loss of control of the airplane.
2008-15-06: We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) Models 175 and 175A airplanes. This AD requires you to check the airplane logbook to determine if the original engine mounting brackets have been replaced. If the original engine mounting brackets are still installed, this AD requires you to repetitively inspect those brackets for cracks and replace any cracked engine mounting bracket. After replacing all four original engine mounting brackets, no further action will be required by this AD. This AD was prompted by a report that the engine became detached from the firewall during landing on one of the affected airplanes. We are issuing this AD to detect and correct cracks in the engine mounting brackets, which could result in failure of the engine mounting bracket. This failure could lead to the engine detaching from the firewall.
2001-21-51: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2001-21-51 that was sent previously to all known U.S. owners and operators of certain Boeing Model 737-600, -700, and -800 series airplanes by individual notices. This AD requires a detailed visual inspection for damage of the aft pressure bulkhead at body station (BS) 1016 and the forward attachment of the vertical fin at body section 48, and corrective action, if necessary. This action is prompted by a report of damage to the web of the aft pressure bulkhead at BS 1016. The actions specified by this AD are intended to find and fix damage of the aft pressure bulkhead at BS 1016 and the forward attachment of the vertical fin at body section 48, which could result in structural failure of the aft pressure bulkhead and consequent uncontrolled decompression, or loss of structural integrity of the forward support of the vertical fin, loss of the vertical fin, and consequent loss of control of the airplane.
2020-21-14: The FAA is adopting a new airworthiness directive (AD) for all ATR--GIE Avions de Transport R(eacute)gional Model ATR72 airplanes. This AD was prompted by reports of main landing gear (MLG) hinge pins found cracked or thermally abused. This AD requires replacing certain MLG hinge pins with serviceable parts, or replacing an MLG equipped with any affected MLG hinge pin with an MLG equipped with serviceable MLG hinge pins, 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.