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99-10-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that requires a detailed visual inspection to detect corrosion inside the forward trunnion joint of the main landing gear (MLG); follow-on actions; and repair, if necessary. This amendment also provides for optional terminating action for the repetitive inspections. This amendment is prompted by reports of corrosion at the forward trunnion thrust face, tabs, and the internal threads of the forward trunnion of the MLG due to moisture in the forward trunnion joint. The actions specified by this AD are intended to prevent corrosion of the forward trunnion joint, which could lead to a stress corrosion fracture of the forward trunnion and possible consequent collapse of the MLG.
90-03-15: 90-03-15 LOCKHEED AERONAUTICAL SYSTEMS COMPANY: Amendment 39-6494. Docket No. 89-NM-170-AD. Applicability: Model L-1011 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent the failure of No. 3 flap vane outboard carriage link assembly, accomplish the following: A. Prior to the accumulation of 6,000 landings or 15,000 flight hours, whichever occurs first, or within 30 days after the effective date of this AD, whichever occurs later, conduct the following in accordance with Section 2, "Accomplishment Instructions," of Lockheed Service Bulletin 093-57-209, dated August 10, 1989: 1. Inspect the left and right No. 3 flap vane outboard carriage link assembly for cracks, using the eddy-current procedure as described in the Service Bulletin. 2. If no cracks are found, conduct repetitive eddy current inspections in accordance with the Service Bulletin at intervals not to exceed 1,000 landings. 3. If a crack is found, replace the link assembly with a new link assembly, P/N 1562426-101/-105, or with a titanium No. 3 flap vane outboard carriage link assembly, P/N 1562426-109. 4. If not previously accomplished, remove existing rub strips on the lower surface of spoilers No. 3 through No. 6 in accordance with the procedure described in the Service Bulletin. Then conduct a No. 3 flap vane-to-flap contact check, rigging check, and adjustment in accordance with L-1011 Maintenance Manual, Section 27-51-00. Check the vane-to-spoiler clearance to ensure that a minimum clearance of 0.20 inch is maintained. 5. If rub strips were previously removed, check the vane-to-spoiler clearance as described in the L-1011 Maintenance Manual, Section 27-51-00. B. Installation of the titanium link assembly, P/N 1562426-109, constitutes terminating action for the repetitive inspections required by paragraph A.2., above. C. Within 2 1/2 years after the effective date of this AD, replace all aluminum fittings with titanium fittings. D. 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, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Los Angeles Aircraft Certification Office. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Lockheed Aeronautical Systems Company, P.O. Box 551, Burbank, California 91520, Attention: Commercial Order Administration, Dept. 65-33, U-33, B-1. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California. This amendment (39-6494, AD 90-03-15) becomes effective on March 5, 1990.
93-22-09: 93-22-09 JETSTREAM AIRCRAFT LIMITED (formerly British Aerospace): Amendment 39-8733. Docket 93-NM-57-AD. Applicability: All Model ATP airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent a gear-up landing, accomplish the following: (a) Within 3,375 landings after the effective date of this AD, remove the hydraulic selector valves, part numbers AIR44880-5 and AIR44882-6, and install new, improved hydraulic selector valves, part numbers AIR46658-0 or AIR46660-0, as appropriate, in the emergency extension system for the landing gear, in accordance with AP Precision Hydraulics, Ltd., Service Bulletin AIR44880-29-02, Revision 1, dated March 9, 1993. (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, 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. (c) 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. (d) The removal and installation shall be done in accordance with AP Precision Hydraulics, Ltd., Service Bulletin AIR44880-29-02, Revision 1, dated March 9, 1993, which contains the specified effective pages: Page Number Revision Level Shown on Page Date Shown on Page 1 1 March 9, 1993 2 Original January 1993 This incorporation by reference was approved 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 Jetstream Aircraft, Inc., P.O. Box 16029, Dulles International Airport, Washington, DC 20041-6029. 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. (e) This amendment becomes effective on December 16, 1993.
2022-13-06: The FAA is adopting a new airworthiness directive (AD) for all Diamond Aircraft Industries Inc. Model DA 40, DA 40 F, and DA 40 NG airplanes. This AD was prompted by mandatory continuing airworthiness information (MCAI) originated 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 baggage nets installed with defective buckles, which may result in failure of the baggage net to restrain the baggage or cargo, which could lead to injury to the occupants in the case of an emergency landing. This AD requires identifying and replacing the affected part. The FAA is issuing this AD to address the unsafe condition on these products.
83-14-07 R3: 83-14-07 R3 PIPER (AEROSTAR): Amendment 39-4686 as amended by Amendment 39-4720 and 39-4725 is further amended by Amendment 39-4759. Applies to Models PA-60-600 (Aerostar 600) (all S/Ns), PA-60-601 (Aerostar 601) (all S/Ns), PA-60-601P (Aerostar 601P) (all S/Ns) and PA-60-602P (Aerostar 602P) (all S/Ns), airplanes certificated in any category. Compliance: Required within the next 25 hours time-in-service after the effective date of this AD, unless already accomplished. To assure airplane controllability during power on stalls, accomplish the following: a) Revise the Limitations Section of the applicable Airplane Flight Manual (AFM) or Pilot's Operating Handbook (POH) now installed in the airplane by changing the aft CG limit to 166.0 inches in those manuals not now incorporating this limit and insert the phrase "Use of Flaps Prohibited for All Operations" at the beginning of the Normal Operations Section and the performance data. 1) Fabricate and install a placard using .10-inch-minimum height characters in full view of the pilot which reads as follows: "USE OF FLAPS PROHIBITED FOR ALL OPERATIONS. TAKEOFF AND LANDING DISTANCES WILL BE INCREASED WITHOUT FLAPS. REFER TO THE APPLICABLE AFM OR POH FOR PERFORMANCE INFORMATION AND APPROACH SPEEDS." Operate the airplane in accordance with this limitation, or b) Revise the aft CG limit in the Limitation Section of the applicable Airplane Flight Manual (AFM) or Pilot's Operating Handbook (POH) by obliterating or marking over all existing aft CG limitations numbers and inserting 163.0 inches, or c) Install Piper Kit 764 969V. This kit includes FAA approved AFM/POH Supplement for applicable airplane models. NOTE: Piper Kit 764 969V is not applicable on aircraft with aerodynamic and/or power increase modification(s), or d) Modify the airplane in accordance with Supplemental Type Certificate (STC) SA980NM (Machen, Inc., Superstar II) or e) Modify the airplane in accordance with STC SA2143NM (Machen, Inc., Stall Improvement Kit) alone or in combination with STC SA1658NM (Machen, Inc., Superstar I). f) Paragraph a) of the AD may be accomplished by the holder of a pilot certificate issued under Part 61 of the Federal Aviation Regulations on any airplane owned or operated by him. The person accomplishing the AD must make the appropriate aircraft maintenance record entry as prescribed by FAR 91.173. g) An equivalent method of compliance with this AD may be used, if approved by the Manager, Atlanta Aircraft Certification Office, 1075 Inner Loop Road, College Park, Georgia 30337. Amendment 39-4686 became effective on July 26, 1983. Amendment 39-4720 became effective on August 31, 1983. Amendment 39-4725 became effective on September 28, 1983. This Amendment 39-4759 becomes effective on November 25, 1983.
2013-20-01: We are adopting a new airworthiness directive (AD) for Agusta Model A109A, A109AII, and A109C helicopters with a certain third stage turbine wheel installed. This AD requires installing a placard on the instrument panel and revising the limitations section of the rotorcraft flight manual (RFM). This AD was prompted by several incidents of third stage engine turbine wheel failures, which were caused by excessive vibrations at certain engine speeds during steady-state operations. These actions are intended to alert pilots to avoid certain engine speeds during steady-state operations, prevent failure of the third stage engine turbine, engine power loss, and subsequent loss of control of the helicopter.
99-10-01: This amendment adopts a new airworthiness directive (AD) that applies to certain Avions Pierre Robin Model R2160 airplanes. This AD requires replacing the wing attachment bolts and associated hardware. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent a wing from separating from the airplane caused by damaged wing attachment bolts, which could result in loss of control of the airplane.
76-04-09: 76-04-09 BELL: Amendment 39-2528. Applies to Bell Models 206A, 206B, 206A-1, and 206B-1 helicopters certificated in all categories, except those having installed main rotor hub yokes delivered as replacement spare parts from Bell Helicopter Company after August 11, 1974, and Models 206A and 206B bearing serial numbers 1174, 1192, 1252, 1355, 1381, 1382, 1390, 1398, 1399, 1400, 1408 through 1411, 1444, 1464, 1466, and subsequent. Compliance required within 200 hours' time in service after the effective date of this AD unless already accomplished. To detect and prevent possible cracks in the main rotor hub yokes, accomplish the following: (a) Remove the main rotor hub assembly form the helicopter and remove the pillow blocks and trunnion from the hub assembly in accordance with the pertinent model maintenance manual. (b) Inspect the yoke for cracks in each trunnion bore and in each tooling hole in the yoke web section using a 10-power or higher magnifying glass or an equivalent inspection method. (c) If a crack is found, remove and replace the discrepant yoke before further flight. (d) Inspect each yoke trunnion bore edge for nicks, scratches, or tool marks using a 10-power or higher magnifying glass or an equivalent inspection method. (e) If nicks, scratches, or tool marks are found on these edges, they must be removed, before further flight, as prescribed in Bell Helicopter Company Service Bulletin No. 206-04-1-74-1, Revision A, dated August 22, 1974, or later approved revision or in accordance with an equivalent FAA approved procedure. (f) Assemble and install the main rotor hub on the helicopter in accordance with the pertinent model maintenance manual. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from themanufacturer may obtain copies upon request to the Service Manager, Bell Helicopter Company, P. O. Box 482, Fort Worth, Texas 76101. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and at the Southwest Regional Office in Fort Worth, Texas. This amendment becomes effective March 30, 1976.
91-12-11: 91-12-11 BEECH: Amendment 39-7022. Docket No. 90-CE-44-AD. Applicability: Model F90 airplanes (serial number (S/N) LA-2 through LA-236); Models 200 and B200 airplanes (S/N BB-2 through BB-1212); Models 200C and B200C airplanes (S/N BL-1 through BL-72); Models 200CT and B200CT airplanes (S/N BN-1 through BN-4); Models 200T and B200T airplanes (S/N BT-1 through BT-30); and Model 300 airplanes (S/N FA-2 through FA-56), certificated in any category. Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To prevent cracking and possible blowout of cast acrylic cockpit "D" side windows that could result in decompression injuries, accomplish the following: (a) Within the next 150 hours time-in-service after the effective date of this AD, accomplish the following: (1) Determine if the airplane "D" side window contains a placard bearing one of the part numbers presented below. If it does, then the window is made of stretched acrylic and no further action per this AD is required. MODEL PART NO. F90, 200, 200C, 200CT, 200T, B200 101-420081-5 through 101-420081-10; B200C, B200CT, and B200T 50-420066-419, 50-420066-420, 50-420066-437, or 50-420066-438. 300 101-420081-9 through 101-420081-12. (2) If a Model 300 airplane has a "D" side window installed in accordance with Beech Service Bulletin (SB) 2273, Revision 1, dated April 1990, then the window is stretched acrylic and no further action per this AD is required. (3) If a cast acrylic "D" side window is installed or if the window material cannot be determined, prior to further flight, inspect the window for cracks, chips, stress crazes, fissure scratches, or other damage in accordance with Part I of Beech SB No. 2208, Revision 1, dated July 1990. (i) If cracks, chips, stress crazes, fissure scratches, or other damage that exceeds the limits specified in Beech SB No. 2208, Revision 1, dated July 1990, is found, prior to further flight, except as noted in paragraph (b) of this AD, replace the window with the applicable stretched acrylic window listed in paragraph (a)(1) of this AD. (ii) If no cracks, chips, stress crazes, fissure scratches, or other damage that exceeds the limits specified in Beech SB No. 2208, Revision 1, dated July 1990, is found, within the next 12 calendar months, except as noted in paragraph (b) of this AD, replace each cast acrylic "D" side window in the crew compartment with the applicable stretched acrylic window listed in paragraph (a)(1) of this AD. (b) If stretched acrylic windows are not available, but have been ordered, the airplane may be operated unpressurized until the stretched acrylic windows are installed provided that the placards specified on page 10 of Beech SB No. 2208, Revision 1, dated July 1990, are installed in clear view of the pilot's position. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199to operate airplanes to a location where the requirements of this AD can be accomplished. (d) An alternative method of compliance or adjustment of the compliance times that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Room 100, Wichita, Kansas 67209. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and send it to the Manager, Wichita Aircraft Certification Office. (e) All persons affected by this directive may obtain copies of the documents referred to herein upon request to the Beech Aircraft Corporation, Commercial Service, Department 52, Wichita, Kansas 67201-0085 or may examine these documents at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. This amendment (39-7022, AD 91-12-11) becomes effective on July 15, 1991.
2022-13-09: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, 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.