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86-04-06: 86-04-06 FOKKER B.V.: Amendment 39-5230. Applies to Model F27 airplanes, serial numbers 10105 to 10635 inclusive, certificated in any category. Compliance is required within 180 days after the effective date of this AD, unless already accomplished: A. To prevent restricted aileron movement or jamming, modify the aileron inboard hinge bolt installations in accordance with Fokker Service Bulletin F27/57-58, dated May 16, 1983. B. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. C. 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 the modification required by this AD. All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the Manager, Maintenance and Engineering, Fokker B.V., Product Support, P.O. Box 7600, 11172J Schiphol Oost, The Netherlands. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective March 14, 1986.
99-22-12: This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model AS332C, L, and L1 helicopters, that requires replacing certain electrical modules with airworthy electrical modules. This amendment is prompted by the discovery of several defective electrical modules. The actions specified by this AD are intended to prevent loss of electrical continuity, which could cause loss of critical systems and subsequent loss of control of the helicopter.
2022-18-18: The FAA is adopting a new airworthiness directive (AD) for all Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by a report of a failed extension of inboard slats during the landing phase, which was not indicated to the flightcrew by the crew alerting system. This AD requires revising the existing airplane flight manual (AFM) to provide procedures for failed extension of inboard slats and flightcrew indication during landing, 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.
2014-05-14: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 727 airplanes. This AD was prompted by certain mandated programs intended to support the airplane reaching its limit of validity of the engineering data that support the established structural maintenance program. This AD requires an inspection for cracks in the main wheel well pressure floor and a preventive modification or permanent repair, as applicable. We are issuing this AD to prevent cracking in the main wheel well pressure floor, which could result in reduced structural integrity of the airplane, and decompression of the cabin.
99-22-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 series airplanes, that requires modification of the wiring of the emergency lighting system. 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 the pilots from having full authority over the cabin emergency lights, which could result in delayed egress of the passengers and crew from the cabin during emergency evacuation.
99-22-05: This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-60 series airplanes, that requires repetitive inspections of the elevator trim control cables for signs of wear damage or broken wires; replacement of damaged or broken cables with certain new cables; and replacement of all 7x7 cables with 7x19 cables. 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 failure of the elevator trim cable due to fatigue cracking, which if not corrected, could result in reduced controllability of the airplane.
81-07-51 R1: 81-07-51 R1 SIKORSKY AIRCRAFT: Amendment 39-4130 as amended by Amendment 39-4211. Applies to S-76A series helicopters certificated in all categories. Compliance required as indicated. To prevent fracture of main rotor spindles, accomplish the following: 1. For main rotor spindles, P/N 76102-08001-041 series, with more than 200 hours time in service on March 20, 1981, compliance required prior to further flight, unless already accomplished within the last 100 hours time in service, and thereafter for all spindles upon removal and/or replacement of either the main rotor spindle, P/N 76102-08001-041 series, the spindle bearing inner race, P/Ns SB 5206-102/-103/-104, or the spindle bearing outer race, P/N SB 5206-202. Remove and fluorescent penetrant inspect main rotor spindles, P/N 76102-08001-041 series, for cracks in accordance with Sikrosky Alert Service Bulletin 76-65-13A, paragraph G(6), dated April 24, 1980, or later FAA approved revision. If a crackindication is found, replace the main rotor blade spindle with a new or serviceable main rotor blade spindle, prior to next flight, in accordance with Sikorsky S-76A Maintenance Manual, SA4047-76-2, Section 65-12-02. 2. Prior to further flight, remove from service all main rotor spindles, P/N 76102-08001-041 series, with 700 or more hours time in service, and replace with a serviceable spindle in accordance with the instructions contained in Chapter 65 of the Sikorsky S-76A Maintenance Manual, SA4047-76-2. 3. Thereafter, remove from service all spindles, P/N 76102-08001-041 series, upon accumulation of 700 hours time in service, and replace with a serviceable spindle in accordance with the instructions contained in Chapter 65 of the Sikorsky S-76A Maintenance Manual, SA4047-76-2. 4. For main rotor spindles, P/N 76102-08001-041 series, or spindle shear bearing inner races, P/N SB 5206-202, with more than 200 hours time in service on March 20, 1981, compliance required within the next 5 hours time in service after March 20, 1981, unless already accomplished, and thereafter for all spindles upon removal and/or replacement of either the main rotor spindle, P/N 76102-08001-041 series, the spindle bearing inner race, P/Ns SB 5206-102/-103/-104, or the spindle bearing outer race, P/N SB 5206-202. Inspect the shear bearing inner/outer races fob diametrical clearance, and replace the main rotor spindle if the diametrical clearance exceeds 0.015 inches, in accordance with Sikorsky Customer Service Bulletin No. 76-65-22B, paragraph G(2), dated May 1, 1981, or later FAA-approved revision. Spindles known to have operated with less than 10 hours time in service with diametrical clearances in excess of 0.015 inches may be returned to service. 5. For all main rotor spindles with more than 200 hours time in service on March 20, 1981, and on all other spindles before the accumulation of 225 hours time in service which do not have a record of Kahr bearings installed, compliance required within the next 25 hours time in service after March 20, 1981, unless already accomplished, and thereafter for all spindle/bearings at intervals not to exceed 350 hours time in service. Inspect for wear and vendor origin the main rotor spindle shear bearings outer race, P/N SB 5206-202, and inner race, P/Ns SB 5206-102/-103/-104, and replace, as necessary, in accordance with Sikorsky Customer Service Bulletin No. 76-65-22B, paragraphs G(4) and G(5), dated May 1, 1981, or later FAA-approved revision. 6. Aircraft may be ferried to a base for compliance with this AD in accordance with Section 21.197 of the Federal Aviation Regulations. 7. Upon request of the operator, an alternate means of compliance with the requirements of this AD may be approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. 8. Report within 24 hours any discrepancies found and the spindle time in service to the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. Reporting approved by the Office of Management and Budget under OMB No. 04-R0174. 9. Prior to December 15, 1981, remove from service all spindle/cuff assemblies, P/N 76102-08001-041, and replace with spindle/cuff assemblies, P/N 76102-08001-043, with spindle preload bolt P/N 76102-08051-103/-104 in accordance with Sikorsky Service Bulletin No. 76-65-24B, dated 8-17-81, or later FAA approved revision. Mandatory requirements for the inspection and replacement of the spindle/cuff assemblies and the shear bearings continue in effect for the P/N 76102-08001-043 assemblies and have been incorporated in Chapter 4 of the Sikorsky S-76A Maintenance Manual, SA 4047-76-2, Airworthiness Limitations Section. 10. Installation of P/N 76102-08001-043 spindle/cuff assemblies with the 76102-08051-103 or -104 spindle preload bolts terminates the requirements ofAD 81-07-51. 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 the manufacturer, may obtain copies upon request to Sikorsky Aircraft, Division of United Technologies Corporation, Stratford, Connecticut 06602. These documents may also be examined at FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. Amendment 39-4130 became effective June 11, 1981, as to all persons except those persons to whom it was made immediately effective by the telegram dated March 20, 1981. This amendment 39-4211 becomes effective September 21, 1981.
2014-05-19: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-200B, 747-200F, 747-300, 747SP, 747-400, and 747-400F series airplanes equipped with Rolls-Royce RB211-524 engines; and certain Model 767-300 series airplanes equipped with Rolls-Royce RB211-524 engines. This AD was prompted by multiple reports of uncommanded thrust reverser unlock events. This AD requires replacing certain relays and relay sockets, and doing wiring changes. For certain airplanes, this AD also requires installing new relay panels, and removing and installing certain components. Additionally, this AD requires, for certain airplanes, accomplishing concurrent actions, which include installing an additional locking system on the thrust reversers and modifying system wiring for in-flight fault indications of the thrust reverser system. We are issuing this AD to prevent an uncommanded thrust reverser deployment during takeoff or in flight, resulting in decreased airplane control and performance, possible runway excursions, and failure to climb.
2010-16-06: We are adopting a new airworthiness directive (AD) for certain Model 737-300, -400, -500, -600, -700, and -800 series airplanes. This AD requires inspecting to verify the part number of the low-pressure flex-hoses of the crew oxygen system installed under the oxygen mask stowage boxes located within the flight deck, and replacing the flex- hose with a new non-conductive low-pressure flex-hose if necessary. This AD results from reports of low-pressure flex-hoses of the crew oxygen system that burned through due to inadvertent electrical current from a short circuit in the audio select panel. We are issuing this AD to prevent inadvertent electrical current, which can cause the low- pressure flex-hoses of the crew oxygen system to melt or burn, causing oxygen system leakage and smoke or fire.
99-22-02: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 757-200PF series airplanes, that requires revising the Airplane Weight & Balance (W&B) Manual to prohibit operation of any airplane without side vertical restraints installed on the main cargo deck when carrying a particular pallet. This amendment also provides for optional terminating action for the Airplane W&B Manual revision. This amendment is prompted by reports indicating that some airplanes have been operated without side vertical restraints installed on the main cargo deck when carrying certain pallets. The actions specified by this AD are intended to prevent inadvertent movement of a cargo pallet during flight, which could result in an adverse center of gravity condition and consequent reduced controllability of the airplane.