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88-18-05: 88-18-05 SHORT BROTHERS, PLC: Amendment 39-5993. Applies to Model SD3-60 series airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent pitot tubes from becoming inoperative due to icing, which could result in erroneous airspeed and altitude indication, accomplish the following: A. Within the next 180 days after the effective date of this AD, replace pitot tubes having the code letter "Z" adjacent to the serial number with one containing a code letter other than "Z," in accordance with accomplishment instructions in Service Bulletin SD360-34-09, dated March 1984. B. 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, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to Manager, Standardization Branch, ANM-113. 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 inspections and/or modifications required by 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 Short Brothers, PLC, Service Representative, 2011 Crystal Drive, Suite 713, Arlington, Virginia 22202-3702. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment, 39-5993, becomes effective September 7, 1988.
2005-18-11: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A340-200 and A340-300 series airplanes. This AD requires a one-time inspection for discrepancies of the spotfacing for the pylon-to-engine attachment bolts on the pyramid forward fitting of the engine pylon, and repair if necessary. This AD results from a report that, during a routine inspection, it was found that the diameter of the spotfacings was too small for two of the pylon-to- engine attachment bolts on the pyramid forward fitting. We are issuing this AD to prevent reduced structural integrity of the pylon-to-engine attachment bolts on the pyramid forward fitting, which could result in separation of an engine from the airplane.
64-21-05: 64-21-05 PIPER: Amdt. 809 Part 507 Federal Register September 15, 1964. Applies to Model PA-30 Aircraft Equipped With the Hartzell HC-E2YL-2B/7663-4 Propeller and Model PA-23-250 Aircraft Equipped With the Hartzell HC-E2YK-2RB/8465-7R Propeller. Compliance required as indicated. There have been several instances of propeller failure on the Piper PA-30 aircraft. The replacement of governor relief valve springs in accordance with Hartzell Service Bulletin No. 88 dated July 2, 1964, as amended July 8, 1964, has not eliminated these failures. The propeller installation on Piper Model PA-23-250 is similar in design and operation to that used on the Model PA-30. Accordingly, this AD is being made applicable to both Models PA-30 and PA-23-250. To preclude further failures, comply with the following: (a) For aircraft having propellers previously serviced in accordance with Hartzell Service Bulletin No. 88 dated July 2, 1964, as amended July 8, 1964, service the propeller governors in accordance with Hartzell Service Bulletin No. 88A dated August 4, 1964, within 10 hours' time in service after the effective date of this AD. (b) For aircraft having propellers which have not been previously serviced in accordance with Hartzell Service Bulletin No. 88A dated July 2, 1964, as amended July 8, 1964, service the propellers in accordance with these service bulletins and, in addition, in accordance with Hartzell Service Bulletin No. 88A dated August 4, 1964, within 10 hours' time in service after the effective date of this AD. This supersedes AD 64-16-08. This directive effective September 16, 1964.
47-33-04: 47-33-04 BEECH: (Was Service Note 2 of AD-757-2.) Applies to C18S Aircraft. Compliance required prior to October 15, 1947, and each 100 hours of operation thereafter. Inspect gaskets between fuel tank liquidometer units and tanks for fuel leakage. If leakage is evident, replace gasket with Armstrong No. 710 gasket, Beech P/N 189631, without use of sealing compound. (Installation of 189631 gasket eliminates necessity for continued inspections.)
2018-11-04: We are adopting a new airworthiness directive (AD) for Aircraft Industries a.s. Models L 410 UVP-E20 and L 410 UVP-E20 CARGO airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as un-commanded negative thrust mode activated on an engine. We are issuing this AD to require actions to address the unsafe condition on these products.
2003-17-11: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce Deutschland Ltd & Co KG (RRD) (formerly Rolls-Royce plc) Dart 528-7E, 529-7H, -7E, -8E, -8H, -8X, -8Y, -8Z, 529D-7E, -7H, -8E, - 8H, -8X, -8Y, -8Z, 531, 532-2L, -7, -7N, -7P, -7L, -7R, 535-2, -7R, 542-4, -4K, -10, -10J, -10K, 552-2, 552-7, and -7R turboprop engines. This AD requires removal of any Sermetel coating (Omat 7/46) from certain high pressure (HP) turbine discs and intermediate pressure (IP) turbine discs, and inspection of discs after coating removal. This AD is prompted by reports of Sermetel coating (Omat 7/46) applied to certain turbine discs which, if allowed to remain on the discs would react adversely with the disc dry film lubricant, and could result in uncontained HP or IP turbine disc failure, resulting in possible damage to the airplane. We are issuing this AD to prevent uncontained HP or IP turbine disc failure, which could result in damage to the airplane.
70-03-01: 70-03-01 HAWKER SIDDELEY: Amdt. 39-928. Applies to Hawker Siddeley Dove Model DH-104 airplanes. Compliance is required within the next 300 landings after the effective date of this AD, unless already accomplished. To prevent fatigue failure of the nose landing gear locking lever and jack attachment lever, replace the existing nose landing gear locking lever and jack attachment lever with Modification 978 levers in accordance with Hawker Siddeley Technical News Sheet Series CT(104) No. 155, Issue 4, dated 29 September 1969, or an FAA-approved equivalent. This amendment becomes effective February 22, 1970.
64-22-03: 64-22-03 PIPER: Amdt. 802 Part 507 Federal Register August 28, 1964. Applies to Models PA-24 and PA-24-250 Aircraft Serial Numbers 24-1 through 24-3284. Compliance required within the next 50 hours' time in service after the effective date of this AD, unless already accomplished. To eliminate possible breakage or loosening of the wires leading to the landing gear safety switch with resultant malfunction of the landing gear safety switch accomplish the following: (a) On the left main landing gear, inspect for broken and loose wires and terminals at the connections to the landing gear safety switch. Repair any broken or loose wires and terminals before further flight. (b) Install Piper Kit No. 754475, or FAA approved equivalent, leaving sufficient slack in the wires between the new clamp and the safety switch to prevent pulling of the wires. (Piper Service Letter No. 379, dated July 12, 1962, pertains to this subject.) This directive effective September 28, 1964.
98-08-05: This amendment adopts a new airworthiness directive (AD) that applies to certain Industrie Aeronautiche e Meccaniche (I.A.M.) Model Piaggio P-180 airplanes. This AD requires inspecting the main landing gear (MLG) for interference between the MLG drag brace link and the MLG retraction actuator, and modifying this area if interference is found. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Italy. The actions specified by this AD are intended to prevent MLG failure caused by interference between the MLG retraction actuator and the MLG drag brace link, which could result in loss of control of the airplane during landing operations.
2018-11-14: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-300 and -300F series airplanes. This AD was prompted by reports of fatigue cracking on airplanes with Aviation Partners Boeing winglets installed. This AD requires high frequency eddy current (HFEC) inspections for cracking of the lower outboard wing skin, and repair or modification if necessary. This AD also requires one of three follow-on actions: Repeating the HFEC inspections, modifying certain internal stringers and oversizing and plugging the existing fastener holes of the lower wing, or modifying the external doubler/tripler and doing repetitive post-modification inspections. We are issuing this AD to address the unsafe condition on these products.