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99-08-05 R1: This amendment corrects information in an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 and C-9 (military) series airplanes, that currently requires repetitive inspections to detect fatigue cracking of the fuselage frames and longerons 16R and 17R above the forward lower cargo door; repair, if necessary; and modification of the fuselage frames and longerons, if necessary, and follow-on repetitive inspections to detect fatigue cracking of the skin adjacent to the modification. That AD was prompted by numerous instances of fatigue cracking of the fuselage frames and longerons. The actions specified by that AD are intended to prevent fatigue cracking of the fuselage frames and longerons 16R and 17R, which could result in reduced structural integrity of the airplane. This amendment corrects an erroneous reference to a certain volume of the Supplemental Inspection Document. \n\n\tThe incorporation by reference of McDonnell Douglas Service Bulletin DC9-53-267, dated October 20, 1997, was approved previously by the Director of the Federal Register as of May 12, 1999 (64 FR 16805, April 7, 1999).
67-03-07: 67-03-07 PIPER: Amdt. 39-334 Part 39 Federal Register January 4, 1967. Applies to Model PA-32-260 Airplanes, Serial Numbers 32-151 through 32-535. Compliance required within the next 50 hours' time in service after the effective date of this AD unless already accomplished. To prevent inadvertent fuel transfer from the outboard tanks to the inboard main tanks through a malfunctioning fuel tank selector valve, replace Airborne Mechanism fuel selector valve, Model 1H26-1, with Airborne Mechanism fuel selector valve, Model 1H26-2, (Piper P/N 492 104). (Piper Service Letter No. 476 pertains to this subject.) This directive effective February 3, 1967.
47-25-05: 47-25-05 CULVER: (Was Service Note 2 of AD-778-2.) Applies to Models V and V2 Aircraft. Inspect the nose-main gear interconnection tube located in the nose wheel well for evidence of corrosion and apply ANG-3a grease to the unpainted aft end every 50 hours of operation. Since the aft end of the tube slides through a trunnion just aft of the wing spar any pitting or scaling of the tube surface in this area may result in binding and failure of the landing gear retracting system and necessitates replacement of the tube. Where climatic conditions promote accelerated corrosive action, as in coastal regions, the tube should be inspected during each daily line check. (Culver Service Memorandum dated September 25, 1946, covers this same subject.)
47-06-07: 47-06-07 DOUGLAS: (Was Service Note 12 of AD-618-3, Supplement 1; Service Note 15 of AD-669-3, Supplement 1.) Applies to All DC3 Series Aircraft. \n\n\tTo be accomplished not later than the next periodic inspection, or in the case of scheduled air carrier aircraft, at the next major inspection. \n\n\tCheck the pull necessary to trip the trigger on the CO2 fire extinguishing system. If the trigger pull exceeds 50 pounds due to wear of the aluminum conduit covering the fire extinguisher release cable, this conduit must be replaced immediately. This procedure is to be repeated at each specified inspection period until such time as the aluminum cable conduit is replaced by stainless steel conduit. \n\n\t(Douglas Service Bulletin DC3 No. 246 dated November 22, 1946, covers this same subject.)
72-18-03: 72-18-03 BELLANCA: (Champion). Amdt. 39-1507. Applies to Model 7GCAA, 7GCBC, 7KCAB, and 8KCAB airplanes certificated in all categories. Compliance required within the next 10 hours time in service after the effective date of this AD, unless already accomplished within the last 15 hours time in service, and thereafter at intervals not to exceed 25 hours time in service from the last inspection, until modified in accordance with paragraph (c) below. Compliance with paragraph (c) required no later than March 1, 1973. To detect battery acid corrosion of elevator and rudder control cables and to detect corrosion of other airframe components in the battery area, accomplish the following: a) Inspect the elevator and rudder control cables in the battery area for evidence of corrosion caused by battery acid spillage. If any evidence of control cable corrosion is found, replace the corroded cables before further flight, except that the airplane may be flown in accordancewith FAR 21.197 to a base where the repair can be performed. b) Inspect the battery compartment area for evidence of battery acid corrosion of airframe components other than control cables. If any corrosion is found, neutralize the affected areas with a soda water solution. Repair damage, as necessary. c) The repetitive inspections required by paragraphs (a) and (b) may be discontinued when a battery box which will assure that any battery acid spillage is drained overboard is installed in accordance with data approved by the Chief, Engineering and Manufacturing Branch, Great Lakes Region. The battery box must be installed no later than March 1, 1973. This amendment becomes effective September 1, 1972.
67-01-04: 67-01-04 SUPERIOR FLOW: Amdt. 39-328 Part 39 Federal Register December 23, 1966. Applies to All Aircraft with Continental E185, E225, 0-470, IO-470 and Lycoming O-320, 0-360, and IO-360 Engines Incorporating Superior Flow Oil Filters Installed in Accordance with Supplemental Type Certificates SE325SW, SE419SW, and SA401SW. Unless already accomplished, compliance required before further flight except that the airplane may be flown in accordance with FAR 21.197 to a base where the replacement can be made. Several failures of Superior Flow oil filter elements, P/N US5003-27 and US5003-33, have occurred during cold weather starts and run-up, resulting in loss of oil and severe engine damage. To prevent additional failures of this nature, Superior Flow filter elements P/N US5003-27 and US5003-33 must be replaced with redesignated filter elements P/N US5003-27A and US5003-33A, respectively. If these new assemblies cannot be obtained, the entire oil filter system must be removed, and replaced with one approved for the engine. (Superior Flow Service Bulletin No. 1A, dated December 7, 1964, covers this subject.) This directive effective January 2, 1967.
2018-18-10: We are adopting a new airworthiness directive (AD) for all Airbus Defense and Space S.A. Model CN-235, CN-235-100, CN-235-200, CN- 235-300, and C-295 airplanes. This AD was prompted by reports that cracks were found on the door mechanism actuator shaft assemblies of the nose landing gear (NLG). This AD requires repetitive inspections of the NLG door mechanism actuator shaft assemblies having certain part numbers, and corrective actions if necessary. This AD would also provide an optional terminating action for the repetitive inspections for Model CN-235, CN-235-100, CN-235-200, and CN-235-300 airplanes. We are issuing this AD to address the unsafe condition on these products.
66-30-01: 66-30-01 BEECH: Amdt. 39-325 Part 39 Federal Register December 21, 1966. Applies to Model JRB-6, D18C, D18S, E18S, E18S-9700 with Serial Numbers prior to BA445, C-45G, TC-45G, C-45H, and TC-45J (SNB-5) Airplanes That Have Been Modified in Accordance with Volpar, Inc., Supplemental Type Certificate No. SA4-1531 or SA111WE. Compliance required within the next 100 hours' time in service after the effective date of this AD, unless already accomplished. To prevent moisture from collecting in the static line of the subject airplanes, accomplish the following: Install a drain in the static line in accordance with Volpar, Inc., Drawing No. 857, titled "Drain Installation - Static Pressure Line" dated 9-22-66 (Volpar, Inc., Service Bulletin No. 10, page 2) or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region. Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Regional Director, FAA Western Region, may adjust the compliance time if the request contains substantiating data to justify the adjustment for that operator. This directive effective December 21, 1966. This amendment effective March 1, 1967. Revised March 1, 1967.
2018-18-08: We are adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-200 Freighter series airplanes, Model A330-200 and -300 series airplanes, and Model A340-200 and -300 series airplanes. This AD was prompted by reports of cracked slat tracks at the location of the front stop attachment to the track. This AD requires a detailed inspection, repetitive special detailed inspections, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
2005-22-07: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 757-200, -200PF, and -300 series airplanes. This AD requires inspecting for damage of the ground brackets, ground wires, and terminal lugs of the auxiliary power unit (APU) battery and the APU start transformer rectifier unit (TRU) as applicable; and corrective and related investigative actions. This AD results from reports indicating that during inspections on two airplanes, the ground brackets for the APU battery were found damaged. We are issuing this AD to detect and correct a damaged electrical bonding surface of the APU battery and APU start TRU ground connections, which could cause overheating of the ground connections and lead to possible consequent ignition of the adjacent insulating blankets.