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2014-20-16: We are adopting a new airworthiness directive (AD) for Brantly International, Inc. (Brantly) Model B-2, Model B-2A, and Model B-2B helicopters with certain main rotor blades. This AD requires inspecting each main rotor (M/R) blade for a crack or delamination and removing the blade if a crack exists or if the delamination exceeds certain thresholds. This AD was prompted by multiple reports of M/R blade cracks and an incident in which a crack that originated near the M/R blade trailing edge resulted in the loss of a large section of the M/R blade. The actions of this AD are intended to prevent loss of the M/R blade and subsequent loss of control of the helicopter.
91-14-02: 91-14-02 SAAB-SCANIA: Amendment 39-7044. Docket No. 91-NM-28-AD. Supersedes AD 90-16-02. Applicability: Model SF-340A series airplanes, Serial Numbers 031 through 159; and SAAB 340B series airplanes, Serial Numbers 160 through 186; certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent inhibited airplane rudder control due to cracking in the vertical stabilizer top closure rib, accomplish the following: A. Prior to the accumulation of 500 hours time-in-service since new or within 100 hours time- in-service after August 30, 1990 (the effective date of Amendment 39-6676, AD 90-16-02), whichever occurs later, inspect the vertical stabilizer top closure rib for evidence of cracking, in accordance with SAAB Service Bulletin 340-55-022, Revision 1, dated February 27, 1990. B. If no evidence of cracking is found, reinspect the vertical stabilizer top closure rib for cracking at intervals not to exceed 500 flight hours time-in-service. C. If cracking is found, prior to further flight, stop drill the ends of the cracks, blend, clean, and apply aluminum tape, as specified in SAAB Service Bulletin 340-55-022, Revision 1, dated February 27, 1990. Reinspect for additional cracking and the condition of the aluminum tape at intervals not to exceed 100 hours time-in-service. D. Within one year after the effective date of this amendment, either replace the rib with a new thicker rib with a larger radius, or reinforce the rib and replace the attachment angle, in accordance with SAAB Service Bulletin 340-55-023, dated October 1, 1990. Accomplishment of either of these modifications constitutes terminating action for repetitive inspections required by paragraphs B. and C. of this AD. E. An alternative method 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 forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. F. 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 SAAB-Scania AB, Product Support, S-581.88, Linkoping, Sweden. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. Airworthiness Directive 39-7044 supersedes AD 90-16-02, Amendment 39-6676 which superseded AD 88-13-10, Amendment 39-5963. This amendment (39-7044, AD 91-14-02) becomes effective on July 29, 1991.
2000-03-09: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Cessna Model 560 series airplanes, that currently requires revising the FAA-approved Airplane Flight Manual (AFM) to provide the flightcrew with limitations, operational procedures, and performance information to be used during approach and landing when residual ice is present or can be expected. This amendment is prompted by reports indicating that, while operating in icing conditions or when ice is on the wings, some of these airplanes have experienced uncommanded roll at (or slightly higher than) the speed at which the stall warning system is activated. This amendment requires revising the AFM and revises the applicability of the existing AD. This amendment also requires modification of the stall warning system of the angle-of-attack computer. The actions specified by this AD are intended to prevent uncommanded roll of the airplane during approach and landing when residual ice ispresent or can be expected.
2014-20-01: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604 Variants) airplanes. This AD requires repetitive inspections for any fuel leak in the right-hand landing lights compartment, and related investigative and corrective actions if necessary. This AD also provides for an optional replacement of the connector of the fuel boost pump canister of the auxiliary power unit (APU), which terminates the repetitive inspections. This AD was prompted by a report of fuel leaks in the connector cavity of the APU fuel boost pump canister and at the electrical conduit connection of the APU fuel boost pump in the right- hand landing lights compartment. We are issuing this AD to detect and correct fuel leaks in the right-hand landing lights compartment, which, in combination with the heat generated by the taxi lights and landing lights on the ground reaching the auto-ignition temperature of the fuel, could result in ignition of any fuel or fumes present in the right-hand landing lights compartment.
2004-14-06: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A310 series airplanes, that currently requires repetitive inspections of the fuselage skin to detect corrosion or fatigue cracking around and under the chafing plates of the wing root; and corrective actions, if necessary. That AD also provides an optional terminating action for the repetitive inspections. This amendment reinstates repetitive inspections in certain areas where corrosion was detected and reworked as required by the existing AD. The actions specified by this AD are intended to detect and correct fatigue cracks and corrosion around and under the chafing plates of the wing root, which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition. DATES: Effective August 13, 2004. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of August 13, 2004. The incorporation by reference of certain other publications, as listed in the regulations, was approved previously by the Director of the Federal Register as of June 3, 1998 (63 FR 23377, April 29, 1998).
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.