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83-17-05: 83-17-05 BEECH: Amendment 39-4715. Applies to Model E33C (Serial Numbers CJ-1 through CJ-25) and Model F33C (Serial Numbers CJ-26 through CJ-155) airplanes certificated in acrobatic and utility categories. \n\n\tCOMPLIANCE: Required as indicated, unless previously accomplished. \n\n\tTo prevent maneuvers which may develop into an unrecoverable spin, within the next 100 hours time-in-service after the effective date of this AD, accomplish paragraph a) or b) below. \n\n\ta)\tInstall Beech Spin Improvement Kit 33-4002-3 (E33C Serial Numbers CJ-1 through CJ-25 airplanes and F33C Serial Numbers CJ-26 through CJ-38 and CJ-40 through CJ-51 airplanes) or 33-4002-1 (F33C Serial Number CJ-39 and Serial Numbers CJ-52 through CJ-155 airplanes) in accordance with instructions contained in Beechcraft Class I Service Instruction No. 1249. \n\n\tb)\tRemove approval for operation of the airplane in acrobatic category in accordance with the following: \n\n\t\t1.\tPlace a copy of this AD in the limitations section of the Pilot's Operating Manual and FAA Approved Airplane Flight Manual. \n\n\t\t2.\tRemove the Airplane Flight Manual Supplement (Beech Part Number 33-590006-11, -13, or -17) pertaining to operation in the Acrobatic Category. \n\n\t\t3.\tCut both electrical leads to the acrobatic category fuel boost pump P/N 4140-00-191 (E33C Serial Numbers CJ-1 through CJ-25 and F33C Serial Numbers CJ-26 through CJ-148 airplanes) or P/N 1297-00-1 (F33C Serial Numbers CJ-149 through CJ-155 (airplanes) at a point near the pump motor housing. Cap and stow these leads per AC 43-13. \n\n\t\t4.\tReplace existing 3-position fuel boost pump switch P/N 35-380053-27 with 2-position switch P/N 35-380053-21, restoring electrical connections for correct operation of the auxiliary fuel boost pump P/N 4140-00-39 (E33C Serial Numbers CJ-1 through CJ-25 and F33C Serial Numbers CJ-25 through CJ-148 airplanes) or P/N 1296-00-1 (F33C Serial Numbers CJ-149 through CJ-155 airplanes). Cap and stow the unused electrical leadper AC 43-13. Secure knob P/N 96-384050-9 to the installed switch with LOCTITE 222 or equivalent bonding agent. \n\n\t\t5.\tModify the auxiliary fuel pump operation placard (including switch position placarding) to read as follows: \n\n\n\n\n\n\n\t\t6.\tObliterate the words "Remove door hold open rod prior to operation in Acrobatic Category" from the placard on the cabin door side panel. \n\n\t\t7.\tRemove the following placards on the left hand sidewall: \n\n\nDURING ACROBATIC CATEGORY \nOPERATION OCCUPANCY \nLIMITED TO PILOT'S OR PILOT'S \nAND COPILOT'S SEAT \n\n\t\tand, if installed, \n\nREMOVE THIRD & FOURTH \nPASSENGER SEATS \nPRIOR TO OPERATION \nIN ACROBATIC CATEGORY \n\n\t\t8.\tObliterate from the airplane operation limitations placards on the left side panel the heading "Acrobatic Category Airplane" and all portions of the placard under that heading. \n\n\t\t9.\tObliterate the word "AEROBATIC" located below the pilot's and co-pilot's window on the exterior of the airplane. \n\n\t\t10.\tOn ModelE33C (Serial Numbers CJ-1 through CJ-25) airplanes, obliterate from P/N 33-590003-7 Pilot's Operating Handbook and FAA Approved Airplane Flight Manual: \n\n\t\t\ti)\tOn the cover page, the words "ACROBATIC See Flight Manual Supplement" after "E33C." \n\n\t\t\tii)\tOn page 9-3, "33-590006-17 Acrobatic Bonanza E33C." \n\n\t\t11.\tOn Model F33C (Serial Numbers CJ-26 through CJ-128) airplanes: \n\n\t\t\ti)\tIn P/N 33-590009-9 Pilot's Operating Manual and FAA Approved Airplane Flight Manual: \n\n\t\t\t\tA)\tObliterate the following: \n\n\t\t\t\t\t1)\tOn Page 5-8, all information pertaining to F33C Acrobatic Category limits. \n\n\t\t\t\t\t2)\tOn Page 8-1, "Pilot's Operating Manual Acrobatic Supplement P/N 33-590006-9." \n\n\t\t\t\t\t3)\tOn Page 8-3, "33-590006-11 Acrobatic Supplement for the F33C 11/3/72." \n\n\t\t\t\tB)\tRemove P/N 33-590006-9 Pilot's Operating Manual Supplement or \n\n\t\t12.\tIn P/N 33-590009-15A1 Pilot's Operating Handbook and FAA Approved Airplane Flight Manual: \n\n\t\t\ti)\tObliterate the following: \n\n\t\t\t\tA)\tOn the cover page, the word "Acrobatic" after F33C and the words "See Flight Manual Supplement" after CJ-128. \n\n\t\t\t\tB)\tOn page 6-1: \n\n\t\t\t\t\t1)\t"Sample Weight and Balance Load Form (Acrobatic Category) - 6-17." \n\n\t\t\t\t\t2)\t"Weight and Balance Loading Form (Acrobatic Category) - 6-18." \n\n\t\t\t\tC)\tOn page 6-12, all information pertaining to F33C Acrobatic Category limits. \n\n\t\t\t\tD)\tOn page 9-3, "33-590006-11 Acrobatic Supplement for the F33C, Rev. No. 2/11/77." \n\n\t\t\t\t\tii)\tRemove pages 6-17 and 6-18. \n\n\t\t13.\tOn Model F33C (Serial Numbers CJ-129 through CJ-155) airplanes, obliterate from P/N 33-590009-13A3 Pilot's Operating Handbook and FAA Approved Airplane Flight Manual the following: \n\n\t\t\ti)\tOn page 6-10, all information pertaining to F33C Acrobatic Category limits. \n\n\t\t\tii)\tOn cover page: \n\n\t\t\t\tThe word "Acrobatic" before F33C and the words "(See Flight Manual Supplement)" after "CJ-129 and after." \n\n\t\t\tiii)\tOn page 9-3, "33-590006-13 Acrobatic Supplement for the F33C Rev. No. 2/9/78." \n\n\t\t14.\tRemove the existing Utility/Acrobatic Category Airworthiness Certificate and replace it with a new Utility Category Airworthiness Certificate as provided in Paragraph b 15 of this AD. \n\n\t\t15.\tObtain a new Utility Category Airworthiness Certificate from any FAA General Aviation District Office or Flight Standards District Office by presenting a completed FAA Form 8130-6, Application for Airworthiness Certificate, together with the removed Utility/Acrobatic Category Airworthiness Certificate, citing compliance with this AD as reason for the replacement. \n\n\tc)\tAn equivalent method of compliance with this AD may be used if approved by the Manager, Wichita Aircraft Certification Office, FAA, Room 238, Terminal Building 2299, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 269-7000. \n\t\n\tThis amendment becomes effective October 1, 1983.
97-01-07: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model BAe 146 and Avro 146-RJ series airplanes, that requires modification of the left and right elevators, and replacement of the elevator spring with a stiffer spring. This amendment is prompted by reports indicating that water and ice have accumulated at the trailing edge of the left and right elevators; this accumulation can cause the elevators to become unbalanced, and oscillate or flutter. The actions specified by this AD are intended to prevent this oscillation or flutter. Elevator oscillation, if not corrected, could result in reduced controllability of the airplane. Elevator flutter, if not corrected, could couple with the natural vibrations of the airplane, and result in loss of the airplane s structural integrity.
90-21-05: 90-21-05 AEROSPATIALE: Amendment 39-6757. Docket No. 90-NM-68-AD. Applicability: All Model ATR42-300 and ATR42-320 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent the propeller brake from overheating and causing damage to the engine, accomplish the following: A. Within 100 hours time-in-service after May 29, 1989 (the effective date of AD 88- 14-06 R1) for airplanes listed in Aerospatiale Service Bulletin ATR42-61-0013, Revision 1, dated December 8, 1987, modify the propeller brake electronic control wiring, in accordance with this service bulletin. B. Within 100 hours time-in-service after May 29, 1989 (the effective date of AD 88- 14-06 R1), for the airplanes listed in Aerospatiale Service Bulletin ATR42-61-0014, Revision 2, dated November 15, 1988, modify the propeller brake control unit, in accordance with this service bulletin. C. Within 100 hours time-in-service after May 29, 1989 (the effective date of AD 88- 14-06 R1), for the airplanes listed in Aerospatiale Service Bulletin ATR42-61-0010, Revision 3, dated December 19, 1988, replace the pushbutton switch with a two-position mechanical switch, in accordance with this service bulletin. D. Within 180 days after the effective date of this AD, install a new brake control unit in accordance with Aerospatiale Service Bulletin ATR42-61-0005, Revision 2, dated January 2, 1990; Revision 3, dated March 15, 1990; or Revision 4, dated June 19, 1990. E. Within 180 days after the effective date of this AD, install a modified propeller brake in accordance with Aerospatiale Service Bulletin ATR42-61-0022, Revision 1, dated September 25, 1989, or Revision 2, dated March 15, 1990. F. Within 180 days after the effective date of this AD, modify the propeller brake indicating logic, in accordance with Aerospatiale Service Bulletin ATR42-61-0023, Revision 1, dated December 1, 1989; or Revision 2, dated March 15, 1990. G. As an alternative to paragraphs A. through F. of this AD, operators may remove the propeller brake from the airplane in accordance with Aerospatiale Service Bulletin ATR42-61- 0016, Revision 1, dated September 1, 1988. H. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113. I. 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 Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. Airworthiness Directive 90-21-05 supersedes AD 88-14-06 (Amendment 39-5967) as revised by AD 88-14-06 R1 (Amendment 39-6202). This amendment (39-6757, AD 90-21-05) becomes effective on October 30, 1990.
2022-17-10: The FAA is superseding Airworthiness Directive (AD) 2021-19- 20, which applied to all Dassault Aviation Model FALCON 7X airplanes. AD 2021-19-20 required amending the existing airplane flight manual (AFM) to incorporate a check and an operating limitation regarding the O<INF>2</INF> saver function. This AD was prompted by reports of defects that may prevent efficient deactivation of the O<INF>2</INF> saver function of crew oxygen masks and a determination that the AFM amendment required by AD 2021-19-20 may not be sufficient to mitigate the risk. This AD retains the requirements of AD 2021-19-20 and also requires physical deactivation of the O<INF>2</INF> saver function, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also limits the installation of affected parts under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
2000-04-09: This amendment adopts a new airworthiness directive (AD) that is applicable to certain EMBRAER Model EMB-135 and EMB-145 series airplanes. This action requires various inspections to detect discrepancies of the elevator servo tab and spring tab hinge fittings of the horizontal stabilizer, and follow-on corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent the linkage of the elevator servo tab or spring tab hinge fittings from separating from the horizontal stabilizer, which could result in loss of control of the airplane.
2000-04-11: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A319, A320, and A321 series airplanes. This action requires a revision to the Limitations and Normal Procedures Sections of the FAA-approved Airplane Flight Manual (AFM) to limit the use of the radio altimeter of the flight management guidance system (FMGS) during the approach phase of flight. This action also provides for an optional terminating modification, which, if accomplished, would terminate the requirement for the AFM revision. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent erroneous display of decision height information to the flight crew during final approach, which could result in an increased risk of collision with the terrain.
2000-04-04: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 0070 and 0100 series airplanes, that requires a measurement of the resistance of the electrical connectors of the auxiliary power unit (APU) to detect a short circuit; an inspection to determine if the grommets or shrink sleeves are present; and modification, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and prevent a short circuit of a fire extinguisher electrical system due to a lack of shrink sleeves or grommets, and consequent disabling of the affected fire extinguisher system.
86-21-06: 86-21-06 BRITISH AEROSPACE: Amendment 39-5417. Applies to BAe Model 125- 800A airplanes, serial numbers as listed in BAe Service Bulletin 24-251-(3014A), dated April 8, 1985, certificated in any category. Compliance is required within 60 days after the effective date of this AD, unless previously accomplished. To provide dedicated AC and DC ground terminals, accomplish the following: 1. Modify electrical wiring in accordance with BAe Service Bulletin 24-251- (3014A), dated April 8, 1985. 2. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. 3. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. All persons affected by this directive, who have not already received the appropriate service document from the manufacturer, may obtain copies upon request to British Aerospace, Inc., Librarian, Box 17414, Dulles International Airport, Washington, D.C. 20041. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This Amendment becomes effective October 20, 1986.
2014-20-08: We are adopting a new airworthiness directive (AD) for certain Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model L-1011 series airplanes. This AD was prompted by reports of cracked rib cap castellations. This AD requires repetitive inspections for castellation and skin clips cracked or damaged between stringers and cracked stringer clips of the wing box pylon back-up structure, and front spar to rear spar; repetitive inspections for cracking, damage, or failure of the pylon back-up torque box structure; repetitive inspections for cracking or damage of the wing box external areas at the drag brace aft wing fitting; repetitive inspections of the outer surface of the wing upper and lower skins for cracks or damage along the rib attachment at the fastener holes and between the two rows of attachment; and corrective actions if necessary. We are issuing this AD to detect and correct cracked or damaged rib cap castellations, which could degrade the structural capabilities of the airplane.
2000-04-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Israel Aircraft Industries Model Astra SPX series airplanes, that requires a one-time inspection to measure the countersink angle of the bolt holes in the lower scissors fitting of the horizontal stabilizer, and corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent cracks in the lower scissors fitting and fitting attachment bolts of the horizontal stabilizer, which could result in possible in-flight loss of the horizontal stabilizer and consequent reduced controllability of the airplane.