Results
2016-26-08: We are superseding Airworthiness Directive (AD) 2014-22-01 for all PILATUS AIRCRAFT LTD. Models PC-12, PC-12/45, PC-12/47, and PC-12/ 47E airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as a need to incorporate new revisions into the Limitations section, Chapter 4, of the FAA-approved maintenance program (e.g., maintenance manual). The limitations were revised to include repetitive inspections of the main landing gear (MLG) attachment bolts. We are issuing this AD to require actions to address the unsafe condition on these products.
2001-17-26: This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Model DH.125, HS.125, BH.125, and BAe. 125 (U-125 and C-29A) series airplanes; Model Hawker 800, Hawker 800 (U-125A), Hawker 800XP, and Hawker 1000 airplanes, that 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 is prompted by reports of attachment lugs cracking at the actuator cylinder head. The actions specified by this AD are intended to prevent separation of the cylinder head lugs, which could prevent the MLG from extending and result in a partial gear-up landing.
71-20-01: 71-20-01 BRITISH AIRCRAFT CORPORATION: Amendment 39-1293 as amended by Amendment 39-2275. Applies to Model BAC 1-11 200 and 400 series airplanes. Compliance is required as indicated. To prevent possible failures of the flap system secondary drive shafts at the trackside support bearing assemblies, accomplish the following at each bearing assembly (eight per airplane) which has not had British Aircraft Modification PM 4642 incorporated: (a) For each bearing assembly, within the next 1,000 landings after the effective date of this AD, or before the accumulation of 4,000 landings, whichever occurs later, and thereafter at intervals not to exceed 750 landings from the last inspection, visually inspect the bearing assembly for end float in accordance with British Aircraft Corp. Model BAC 1-11 Alert Service Bulletin No. 27-A-PM 4642, Issue 2, dated July 14, 1972, or an FAA-approved equivalent. (b) If the bearing assembly end float is found to exceed 0.050 inches during aninspection required by this AD and - (1) The four alternate locking tabs have not been bent over, before further flight, except that the airplane may be flown in accordance with FAR 21.197 to a base where the repair can be performed, comply with paragraph (c), (d), or (e). (2) The four alternate tabs have been bent over, before further flight, except that the airplane may be flown in accordance with FAR 21.197 to a base where the repair can be performed, comply with paragraph (d) or (e). (c) Bend over the four alternate locking tabs of the affected bearing assembly in accordance with paragraph 2.1.3 of British Aircraft Corp. Model BAC 1-11 Alert Service Bulletin No. 27-A-PM 4642, Issue 2, dated July 14, 1972, or an FAA-approved equivalent. Repeat the inspection specified in paragraph (a) on the affected bearing assembly at intervals not to exceed 750 landings from the last inspection. (d) Overhaul the affected bearing assembly by replacing the fork end, bushings, thrust washers, and retaining ring with serviceable parts of the same part number. Before the accumulation of a total of 4,000 landings on the overhauled bearing assembly and thereafter at intervals not to exceed 750 landings from the last inspection, repeat the inspection specified in paragraph (a). (e) Replace the affected bearing assembly with a serviceable bearing assembly which has BAC Modification PM 4642 incorporated. (f) Operators who have not kept records of the number of landings accumulated on individual bearing assemblies shall substitute airplane landings in lieu thereof. (g) For the purpose of complying with this AD, subject to acceptance by the assigned FAA Maintenance Inspector, the number of landings may be determined by dividing each airplane's hours' time in service by the operator's fleet average time from takeoff to landing for the BAC 1-11 airplane. (h) Upon request of the operator, an FAA Maintenance Inspector, subject to prior approval by the Chief, Aircraft Certification Staff, FAA Europe, Africa, and Middle East Region may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. Amendment 39-1293 became effective October 15, 1971. This amendment 39-2275 becomes effective August 25, 1975.
88-05-06: 88-05-06 GULFSTREAM AEROSPACE (ROCKWELL): Amendment 39-5864. Applies to Models 112 and 112B (S/N's 1 through 544 and 13000); 112TC and 112TCA (S/N's 13001 through 13309); and 114 and 114A (S/N's 14000 through 14540) airplanes certificated in any category. Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To prevent failure of the vertical fin attachment fitting (P/N 43255-1) and the fuselage frame (P/N 43205- 1) in the area of F.S. 230.5, accomplish the following: (a) Within the next 50 hours time-in-service (TIS), or upon the accumulation of 250 hours total TIS, whichever occurs later, inspect for cracks in fuselage frame (P/N 43205-1) and vertical fin attachment fitting (P/N 43255-1) in accordance with Part I of Gulfstream Aerospace Service Bulletin Nos. SB-112-72A or SB-114-23A, both dated August 31, 1987, as applicable. (b) If cracks are found in the fuselage frame or vertical fin attachment fitting, priorto further flight repair in accordance with Part II of Gulfstream Aerospace Service Bulletin Nos. SB-112-72A or SB-114-23A, both dated August 31, 1987, as applicable. (c) If no cracks are found, thereafter at intervals not to exceed 100 hours TIS accomplish the inspection as specified in paragraph (a) of this AD until the repair required by paragraph (b) of this AD is accomplished. (d) The repetitive inspections specified in paragraph (c) of this AD may be discontinued when the airplane is modified as specified in paragraph (b) of this AD. (e) The airplane may be flown in accordance with FAR 21.197 to a location where the repair can be performed. (f) An equivalent method of compliance with this AD may be used if approved by the Manager, Airplane Certification Branch, DOT, FAA, Southwest Regional Office, Fort Worth, Texas 76193-0150, Telephone (817) 624-5150. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Gulfstream Aerospace Corporation, Wiley Post Airport, P.O. Box 22500, Oklahoma City, Oklahoma 73123; or may examine these documents at the FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on April 8, 1988.
2001-17-28: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 767 series airplanes. This action requires a one-time inspection to detect abrasion damage and installation discrepancies of the wire bundles located below the P37 panel, and corrective action, if necessary. This action is necessary to detect and correct such damage and other discrepancies, which could result in arcing to structure and consequent fire or loss of function of affected systems. This action is intended to address the identified unsafe condition.
2017-02-03: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-200, -300, and -400ER series airplanes. This AD was prompted by a report of a malfunction of the engine indication and crew alerting system (EICAS) during flight. This AD requires, for certain airplanes, a general visual inspection of the spray shield, and related investigative and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
2017-02-07: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model MBB-BK 117 C-2 and MBB-BK 117 D-2 helicopters. This AD requires inspections and a torque of certain attachment points. This AD was prompted by a design reassessment. These actions are intended to prevent an unsafe condition on these products.
2001-17-16: This amendment supersedes an existing airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109E helicopters that currently requires visually checking and inspecting each tail rotor blade (blade) for a crack at specified intervals. That AD also requires replacing any cracked blade with an airworthy blade. This amendment contains the same requirements but adds another blade to the applicability. This amendment is necessary because the added blade is manufactured using the same process as the blade that failed. The actions specified by this AD are intended to prevent failure of a blade and subsequent loss of control of the helicopter.
86-21-08: 86-21-08 SOCATA: Amendment 39-5444. Applies to Models TB10 and TB20 (Serial Numbers 1 through 342, 344 through 381, 383 through 413, 415 through 422, 424, 430, 431, 433, and 439 through 441) airplanes certificated in any category. Compliance: Required within 50 hours time-in-service or 60 days, whichever occurs first, from the effective date of this AD, unless already accomplished. To prevent possible structural damage and loss of airframe integrity, accomplish the following: (a) Visually inspect the fuselage area under the battery tray for damage caused by battery electrolyte leaks. (1) If damage exists, before further flight, repair the damage or replace the damaged component(s) in accordance with Advisory Circular No. 43.13-1A and applicable manufacturer's maintenance information and modify the battery tray as specified in paragraph (a) (2) below. (2) If damage does not exist, modify the battery tray in accordance with the instructions in the "DESCRIPTION" Section1 of SOCATA Service Letter No. 18 dated February 1985. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) 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 AD may obtain copies of the documents referred to herein upon request to SOCATA Groupe Aerospatiale, B.P. 38, 65001 Tarbes, France, or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on October 24, 1986.
2017-02-11: We are adopting a new airworthiness directive (AD) for Alexander Schleicher GmbH & Co. Model ASK 21 gliders. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as cable slack in gliders equipped with a rudder hand control [[Page 10265]] system leading to a short-term blockage of the rudder control system and reduced control. We are issuing this AD to require actions to address the unsafe condition on these products.