Results
81-10-07: 81-10-07 BELL HELICOPTER TEXTRON (BHT): Amendment 39-4108. Applies to all Model 212 series helicopters which have swashplate support part number (P/N) 204-011-404- 017 installed (Airworthiness Docket No. 81-ASW-18). To prevent possible loss of main rotor control, accomplish the following: (a) Within the next 10 flight hours following the effective date of this AD and continuing at intervals not to exceed 10 flight hours, thoroughly clean the 204-011-404-017 swashplate support-to-gimbal-ring attachment lugs. Using an inspection mirror and flashlight, inspect the lugs for cracks. Particular attention should be given to both inner attachment lugs. If a crack is found, remove and replace the swashplate support. (b) The inspection is not required after swashplate support P/N 204-011-404-017 is replaced with P/N 204-011-404-121. (c) Effective June 1, 1981, the retirement life of swashplate support P/N 204-011- 404-017 is reduced from 1,000 flight hours to 400 flight hours when used on the Model 212 helicopter. The new retirement life shall be recorded on the appropriate helicopter maintenance record. (d) Prior to April 30, 1982, all swashplate support assemblies P/N 204-011-404-017 on Bell Model 212 helicopters must be replaced with P/N 204-011-404-121. (e) Bell Helicopter Textron Alert Service Bulletin 212-81-22 applies for inspection techniques and areas to be inspected. Note: Swashplate supports P/N 204-011-404-017 may have been installed on Model 204 or 205 helicopters and subsequently removed and installed on Model 212 helicopters. For those parts having such a history, determine the equivalent hours as follows: Take the time the part has been installed on a Model 204 or 205 helicopter and divide this time by 2.5; to this result, add the time the part has been on a Model 212 helicopter. The answer is the equivalent hours on the part, and this number must not exceed 400 hours. (f) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration. (g) In accordance with FAR 21.197, flight is permitted to a base where the inspection and repairs required by this AD may be accomplished. This amendment becomes effective May 14, 1981.
2003-21-09: This amendment supersedes an existing airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) model helicopters. The existing AD currently requires certain checks of the magnetic chip detector plug (chip detector) and the main gearbox (MGB) oil-sight glass; and certain inspections of the lubrication pump (pump) and replacing the MGB and the pump with an airworthy MGB and pump, if necessary. Also, the AD requires that a before a MGB or pump with any time-in-service (TIS) can be installed, it must meet the AD requirements. This amendment requires the same actions as the existing AD but corrects the wording to state that the check of the chip detector is for sludge rather than metal particles. This amendment is prompted by the need to correct the wording because the term "metal particles" may be misleading. The actions specified by this AD are intended to detect sludge on the chip detector, to prevent failure of the MGB pump, seizure of the MGB, loss of drive to an engine and main rotor, and subsequent loss of control of the helicopter.
94-25-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Precision Airmotive Corporation (formerly Facet Aerospace Products and Marvel-Schebler) Model HA-6 series carburetors, that requires a modification in those carburetors not equipped with a mixture control retainer clip. This amendment is prompted by eight reports of excessive retention screw wear causing rough engine operation or engine power loss on engines equipped with a Model HA-6 series carburetor between January 1986 and August 1992. The actions specified by this AD are intended to prevent the interruption of fuel flow to the engine caused by the mixture control shaft moving out of position because of excessive wear of the mixture control shaft retention screw.
2020-21-08: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 airplanes. This AD was prompted by reports that the latches for the forward and aft pressure relief doors could be opened during exposure to fire, leading to a breach in the engine core firewall. This AD requires modification and re-identification of the affected thrust reversers (TRs) and latch access doors (LADs), 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.
60-10-03: 60-10-03\tBOEING: Amdt. 144 Part 507 Federal Register May 7, 1960. Applies to the following 707 series aircraft only: Serial Numbers 17586 through 17596, 17609 through 17612, 17628 through 17648, 17658 through 17672, 17696 through 17702, 17925 through 17927. \n\tCompliance required as indicated. \n\n\tAs a result of one known incident wherein aggravated dutch roll was experienced due to improper rigging of the outboard aileron balance tab, the following modifications shall be accomplished: \n\n\tUnless already accomplished, prior to July 1, 1960: \n\n\t(a)\tReplace aileron quadrant rod assembly P/N 90-2480-3001 with redesigned rod assembly P/N 69-10829 (LH and RH side). \n\n\t(b)\tReplace support channel P/N 6-83872-2000 located on beam installation P/N 9- 65133 (aileron lockout crank) with new channel P/N 69-10833. Adjust stop in accordance with maintenance manual procedure. \n\n\t(c)\tRevise rigging of outboard aileron balance tab to 1.5 degrees (plus-minus 0.5 degrees) down with the aileron in the neutral position. \n\n\t(Boeing Service Bulletin No. 583 dated September 24, 1959, pertains to this same subject.)
83-19-01: 83-19-01 PIPER: Amendment 39-4727. Applies to Model PA-38-112 (S/Ns 38-78A0001 thru 38-82A0122) airplanes certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent possible inflight failure of the fin and stabilizer attachment because of fatigue damage, accomplish the following: a) Within the next 25 hours time-in-service on airplanes that have 500 or more hours time-in-service on the effective date of this AD, or upon the accumulation of 525 hours time-in-service on airplanes that have less than 500 hours time-in-service on the effective date of this AD, and at intervals not exceeding 100 hours time-in-service thereafter: 1) Inspect and, if necessary, repair or modify the forward and aft fin spars in accordance with the directions and criteria contained in the INSTRUCTIONS section of Piper Service Bulletin No. 763A dated July 25, 1983. b) The repetitive inspections required by this AD may be discontinued upon the incorporation of Piper Kit No. 764 965. c) The interval between the repetitive inspections required by this AD may be adjusted up to 10 percent of the specified interval to allow accomplishing these inspections concurrent with other scheduled maintenance of the airplane. d) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. e) An equivalent method of compliance with this AD may be used if approved by the Manager, New York Aircraft Certification Office, FAA, Room 202, 181 South Franklin Avenue, Valley Stream, New York 11581. This amendment becomes effective on September 29, 1983.
80-11-08: 80-11-08 BOEING VERTOL (VERTOL): Amendment 39-3778. Applies to Vertol Model 107-II helicopters with pilot or copilot cyclic stick boots, P/Ns 107S2226-9, -13 or -17, certificated in all categories. To prevent possible restriction of cyclic stick travel accomplish the following within the next 25 hours in service after the effective date of this AD, unless already accomplished. a. Loosen the velcro tape and camloc fasteners securing the pilot and copilot cyclic stick boots, P/N 107S2226-9, -13 or -17, and remove the boots. b. Remove the two rivets which attach the forward spring, P/N 107S2226-12, to the forward end of the boot base and discard the forward spring. c. Install washers and new rivets to plug the resulting two empty holes in the boot base. d. Reinstall the pilot and copilot stick boots. e. Upon request with substantiating data submitted through an FAA Maintenance Inspector, the compliance time specified in this AD may be adjusted by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment is effective May 28, 1980.
2009-12-16: We are superseding an existing airworthiness directive (AD) for the products listed above. 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: The manufacturer reported findings of missing primer on the internal of the elevator and rudder of aircraft S/N 8200. The aircraft S/N 8200 was with RUAG for maintenance purposes. Investigation performed by RUAG showed that the paint removal procedure for the rudder and elevator was changed from a paint stripping with brush and scraper to a procedure where the parts were submerged in a tank filled with hot liquid stripper. The stripper is called TURCO 5669 from Henkel Surface Technologies. The stripping process is described in the Technical Process Bulletin No. 238799 dated 09/01/1999. This paint stripping process change was not communicated to andnot approved by the TC-Holder. We are issuing this AD to require actions to correct the unsafe condition on these products.
2020-21-07: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by a report that sticking effects have been observed affecting the breathing bag on certain passenger oxygen masks. This AD requires replacement of affected passenger oxygen masks, 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.
83-06-01: 83-06-01 BOEING: Amendment 39-4589. Applies to Boeing Model 767 Series Airplanes certificated in all categories. To prevent loss of engine throttle control due to power lever cable icing, accomplish the following within 30 days from the effective date of this AD, unless already accomplished. \n\tA.\tInstall ice shields on the number 6 and 7 slats per Boeing Service Bulletin 767-30-2, dated December 13, 1982, or later FAA approved revision. \n\tB.\tSpecial flight permits may be issued in accordance with FAR 21.199 to operate airplanes to a base for the accomplishment of this AD. \n\tC.\tAlternate means of compliance with the AD which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tThis amendment becomes effective April 4, 1983.