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90-01-05: 90-01-05 BOEING: Amendment 39-6443. Docket No. 89-NM-167-AD. Applicability: Model 767 series airplanes, as listed in Boeing Service Bulletin 767-25-0123, dated May 25,1989, certificated in any category. \n\n\tCompliance: Required within the next 90 days after the effective date of this AD, unless previously accomplished.\n \n\tTo ensure proper arming of the emergency evacuation slide mechanism for entry/service doors and to preventa false armed indication, accomplish the following: \n\n\tA. For Group 1 airplanes, perform the inspection and rework of the acoustical seal for entry/service doors in accordance with paragraph III., Part B., of Boeing Service Bulletin 767-25-0123, dated May 25, 1989, or Revision 1, dated September 14, 1989. \n\n\tB. For Group 2 airplanes, rework the acoustical seal for entry/service doors in accordance with paragraph III., Part C., of Boeing Service Bulletin 767-25-0123, dated May 25, 1989, or Revision 1, dated September 14, 1989. \n\n\tC. An alternate means ofcompliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle 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, Seattle Aircraft Certification Office. \n\n\tD. 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 Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington.\n\n This amendment (39-6443, AD 90-01-05) becomes effective on February 5, 1990.
2023-25-04: The FAA is superseding Airworthiness Directive (AD) 2022-08- 04, which applied to all Airbus SAS Model A300 series airplanes. AD 2022-08-04 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. Since the FAA issued AD 2022-08-04, the FAA has determined new or more restrictive airworthiness limitations are necessary. This AD continues to require the actions of AD 2022-08-04, and requires 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.
2005-06-11: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747-100, -100B, -100B SUD, -200B, and -300 series airplanes; and Model 747SR and 747SP series airplanes. That AD currently requires repetitive inspections to detect fatigue cracking in the upper deck floor beams located at certain body stations, and repair, if necessary. This new AD lowers the threshold for the existing inspections and requires new repetitive inspections of previously repaired areas, and repair if necessary. This AD is prompted by the results of an additional detailed analysis that indicate fatigue cracks can initiate sooner than has previously been observed. We are issuing this AD to prevent failure of the upper deck floor beams at certain body stations due to fatigue cracking, which could result in rapid decompression and reduced controllability of the airplane.
2023-24-07: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A310 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.
78-16-04: 78-16-04 CESSNA: Amendment 39-3273. Applies to Model 336 airplanes. Compliance: Required as indicted, unless already accomplished. To provide loading instructions which will limit aircraft loading to an acceptable center of gravity, within the next 100 hours time-in-service after the effective date of this AD, accomplish the following: A) Modify the Cessna weight and balance data included in the Model 336 airplane as follows: 1. Modify the center of gravity moment envelope on Page 1 by drawing a straight line between the two points (3900 pounds - 548,730 pounds-inches and 2500 pounds - 351,751 pounds-inches) and cover or obliterate the lines establishing the right side of the existing center of gravity moment envelope. 2. Modify the normal category center of gravity limits chart on Page 2 by drawing a vertical line at the 140.7 inches aft of datum point from the 2500 to 3900 pounds lines and cover or obliterate the lines establishing the right side of the existing normal category center of gravity limits envelope. B) Below the existing capacity placard located on the baggage compartment door install a permanent placard which reads as follows: "CAUTION - AFT CENTER OF GRAVITY LIMITATION MAY RESTRICT LOADING OF THIS COMPARTMENT TO LESS THAN 365 POUNDS" and operate the aircraft in accordance with this limitation. This placard should be fabricated of .032 inch minimum thickness aluminum or plastic material with minimum 3/16-inch high stamped or engraved letters and installed using threaded or rivet type fasteners. C) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective October 14, 1978.
2005-06-06: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A319, A320, and A321 series airplanes. This AD requires modification of certain auxiliary power unit (APU) alternating current (AC) generators. This AD is prompted by a report of an explosion in the APU compartment, which blew open the compartment doors. We are issuing this AD to prevent oil vapor leakage from the APU AC generator, which, when combined with an electric arc at the electrical receptacle, could result in a fire or explosion in the APU compartment during flight.
2023-25-08: The FAA is adopting a new airworthiness directive (AD) for all Leonardo S.p.a. Model A109E, A109S, AW109SP, A119, and AW119 MKII helicopters. This AD was prompted by multiple reports of excessive axial play on the ball bearing of the lower half of the main rotor (MR) rotating scissor assembly. This AD requires one-time scissor coupling and axial play inspections and repetitive quantitative axial play inspections and, depending on the results, additional inspections and replacing certain parts. This AD also requires reporting information and prohibits installing certain parts unless certain inspections have been accomplished. These requirements are 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.
2023-25-14: The FAA is superseding Airworthiness Directive (AD) 2022-27- 09, which applied to certain Airbus Helicopters Model EC130T2 helicopters. AD 2022-27-09 required repetitively inspecting the vibration level on the tail rotor drive shaft and, depending on the results, taking corrective action. AD 2022-27-09 also required reporting information and prohibited installing certain rotor drive shafts unless the inspection was done. Since the FAA issued AD 2022-27- 09, Airbus Helicopters revised its service information to update the procedures for inspecting that vibration level, reduce an allowable vibration level, and clarify when a balance correction may be accomplished. This AD was prompted by the determination that a certain vibration measurement tool was providing unexpected results and therefore the threshold must be revised. This AD continues to require certain actions in AD 2022-27-09 and also revises the procedures for inspecting the vibration level on the tail rotor drive shaft and depending on these results, requires replacing certain parts, 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.
76-06-06: 76-06-06 PIPER AIRCRAFT CORPORATION: Amendment 39-2547. Applies to Piper Model PA-12 airplanes certificated in all categories equipped with Piper Model PA-14 wing flaps in accordance with STC No. SA231AL. NOTE: STC No. SA231AL incorporates Rodney E. Schaeffer Drawing PA-12-1001, Revision "A", dated September 15, 1975. Compliance is required within the next 50 hours' time in service after the effective date of this AD, unless already accomplished. To prevent a loss of flap control, inspect the flap control system to ensure that six flap control pulley guards are installed in accordance with the Rodney E. Schaeffer Drawing PA-12- 1001, Revision "A", dated September 15, 1975, or an FAA approved equivalent. Install those pulley guards which are found to be missing. NOTE: Copies of the Rodney E. Schaeffer Drawing PA-12-1001, Revision "A", dated September 15, 1975, may be obtained from Rodney E. Schaeffer, 1253 Cramer, Wichita, Kansas, 67212. This drawing may also be examined at the FAA Alaska Region, 632 Sixth Avenue, Anchorage, Alaska 99501, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. This amendment becomes effective on March 25, 1976.
2023-23-11: The FAA is superseding Airworthiness Directive (AD) 2019-12- 07, which applied to all Airbus SAS Model A318-111, -112, -121, and - 122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2019-12-07 required replacement of both main landing gear (MLG) shock absorbers, an identification of affected MLG sliding tubes; inspection of affected chromium plates and sliding tube axles for damage; and replacement of the sliding tube if necessary. AD 2019- 12-07 also required repetitive inspections of affected MLG sliding tubes for cracking, replacement of cracked MLG sliding tubes, and eventual replacement of each affected MLG sliding tube. This AD continues to require the actions specified in AD 2019-12-07 and requires repetitive inspections of additional MLG sliding tubes, replacement if necessary, and eventual replacement of the additional MLG sliding tubes. This AD also extends the repetitive inspection interval. This AD also prohibits the installation of affected parts under certain conditions. This AD was prompted by the FAA's determination that additional MLG sliding tubes are affected by the unsafe condition and that the repetitive inspection interval may be extended. The FAA is issuing this AD to address the unsafe condition on these products.