Results
2020-20-11: The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) GEnx-1B64/P2, -1B67/P2, -1B70/P2, -1B70C/P2, -1B70/75/P2, -1B74/75/P2, -1B76/P2, -1B76A/P2, and GEnx- 2B67/P model turbofan engines. This AD was prompted by the detection of melt-related freckles in the billet, which may reduce the life limits of certain high-pressure turbine (HPT) rotor stage 2 disks and a certain stages 6-10 compressor rotor spool. This AD requires the removal of certain HPT rotor stage 2 disk and the removal of a certain stages 6-10 compressor rotor spool before reaching their new life limits. The FAA is issuing this AD to address the unsafe condition on these products.
2020-18-20: The FAA is adopting a new airworthiness directive (AD) for certain MD Helicopters Inc. (MDHI) Model 369A, 369D, 369E, 369FF, 369H, 369HE, 369HM, 369HS, 500N, and 600N helicopters. This AD was prompted by reports of abrasion strips departing the main rotor (MR) blade in- flight. This AD requires tap inspecting each MR blade leading edge abrasion strip. The FAA is issuing this AD to address the unsafe condition on these products.
94-17-08: This amendment adopts a new airworthiness directive (AD), applicable to all de Havilland Model DHC-7 series airplanes, that requires removal of the aluminum or brass hardware in the firewall terminal block assembly and replacement with steel hardware. This amendment is prompted by the results of an investigation, which revealed that corroded aluminum washers in the DC firewall terminal block assembly may loosen the electrical connections. The actions specified by this AD are intended to prevent interruption of DC electrical power due to connections that may have loosened from corrosion.
81-02-05: 81-02-05 MCDONNELL DOUGLAS: Amendment 39-4022. Applies to all Model DC-8 series airplanes equipped with upper main cargo door, certificated in all categories. Compliance required as indicated unless already accomplished. To prevent stress corrosion cracking of the upper cargo door spool fitting attach bolts accomplish the following: \n\n\tA.\tFor airplanes not modified per Douglas Aircraft Company Service Bulletin DC-8 SB 52-78, dated May 5, 1975, within 12 months after the effective date of this AD, inspect, lubricate, replace as necessary, and seal the cargo door latch spool fitting attach bolts in accordance with a method approved by the Chief, Los Angeles Area Aircraft Certification Office. (NOTE: Accomplishment of the instructions in Figure 1 of Douglas Aircraft Company Service Bulletin DC-8 SB 52-82, dated October 28, 1980, has been approved as a means of compliance with this requirement.) \n\n\tB.\tFor airplanes modified per Douglas Aircraft Company Service Bulletin DC-8 SB52-78, within 24 months after the effective date of this AD, inspect, lubricate, replace as necessary, and seal the cargo door latch spool fitting attach bolts in accordance with a method approved by the Chief, Los Angeles Area Aircraft Certification Office. (NOTE: Accomplishment of the instructions in Part II, Group II, Paragraph C of DC-8 SB 52-82 has been approved as a means of compliance with this requirement.) \n\n\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes unpressurized to a base for the accomplishment of inspections/modifications required by this AD. \n\n\tD.\tAlternative inspections, modifications, or other actions which provide an equivalent level of safety may be used when approved by the Chief, Los Angeles Area Aircraft Certification Office, FAA Northwest Region. \n\n\tThis amendment becomes effective April 1, 1981.
2009-07-12: The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CF34-1A, -3A, -3A1, -3A2, -3B, and -3B1 turbofan engines with high-pressure (HP) rotor 4-step air balance piston stationary seals (4-step seals), part numbers (P/Ns) 4923T54G01, 6019T90G03, 6037T99G01, 6037T99G02, and 6037T99G03, installed. This AD requires removing the 4-step seals and incorporating an 8-step seal at the next piece-part exposure. This AD results from the investigation of an airplane accident. Both engines experienced high-altitude flameout. Rotation of the HP rotors was not maintained during descent and the engines could not be restarted. We are issuing this AD to prevent the inability to restart both engines after flameout due to excessive friction of the 4-step seal, which could result in subsequent forced landing of the airplane.
64-19-04: 64-19-04 GENERAL DYNAMICS: Amdt. 783 Part 507 Federal Register August 7, 1964. Applies to Model 240 Series Aircraft. Compliance required within 1,000 hours' time in service after the effective date of this AD, unless already accomplished. A fault in an unprotected cabin supercharger disconnect circuit caused an electrical fire in the cabin pressurization console on the copilot's side. To prevent recurrence of this incident provide the following circuit protection: Modify the aircraft fire extinguisher circuits, cabin pressure dump solenoid circuit and emergency compressor shutoff valve circuit to provide circuit protection and incorporate an alternate emergency power circuit and a normally-off test light in accordance with Convair Service Engineering Report No. 240-24 dated January 3, 1964, with revision "A" dated March 9, 1964, or an FAA Western Region Engineering approved equivalent. (Convair Service Engineering Report No. 240-24 pertains to this same subject.) This directive effective September 7, 1964.
2020-19-05: The FAA is adopting a new airworthiness directive (AD) for certain Bell Helicopter Textron Canada Limited (Bell) Model 505 helicopters. This AD requires inspecting each swashplate assembly bearing (bearing), and depending on the inspection results, removing the bearing from service. This AD was prompted by a report of a bearing that migrated out of the swashplate inner ring. The actions of this AD are intended to address an unsafe condition on these products.
79-06-03: 79-06-03 GULFSTREAM AMERICAN (formerly Grumman American Aviation Corporation): Amendment 39-3437. Applies to Model G-159, all serial numbers; and to Model G-1159, serial numbers 1 through 238 and 775, certificated in all categories. Compliance is required prior to further flight, unless already accomplished. To prevent a potential hazard caused by inability to discharge the engine or APU fire extinguisher bottles, accomplish the following: (1) Inspect the cartridge terminals on each aircraft engine and APU fire extinguisher bottle (container) for the presence of electrical shunts. Shunts are installed for safety in shipping and handling and inadvertently may have been left installed. (2) Remove any electrical shunts found on the cartridge terminals, using procedures in the applicable aircraft maintenance manual. Gulfstream American Alert Customer Bulletins No. 11 for Model G-159, and No. 17 for Model G-1159, both dated February 16, 1979, pertain to this subject. This amendment is effective April 2, 1979.
2003-20-14: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727-200 series airplanes, that requires installation of four lanyards on the forward access panel/ door. This action is necessary to prevent the forward ceiling access panel/door from falling down and blocking the aisle, which would impede evacuation in an emergency. This action is intended to address the identified unsafe condition.
78-26-05: 78-26-05 PIPER: Amendment 39-3377. Applies to Piper Model PA-36-285 and PA-36-300, Serial Nos. 36-7360001 thru 36-7760123, 36-7760125 thru 36-7860001, 36-7860003, 36-7860007, 36-7860010 thru 36-7860015 36-7860017 thru 36-7860019, 36-7860021 thru 36- 7860024, 36-7860027 thru 36-7860031, 36-7860034, 36-7860036, 36-7860041, 36-7860043 thru 36-7860045, 36-7860047, 36-7860049 thru 36-7860051, 36-7860061 thru 36-7860063, 36- 7860069, 36-7860071, 36-7860073 thru 36-7860079, 36-7860081 thru 36-7860083, 36-7860086 thru 36-7860114 and 36-7860116 and Model PA-36-375, Serial Nos. 36-7802002 thru 36-7802019, 36-7802021 thru 36-7802023, 36-7802025 thru 36-7802029, 36-7802031, 36-7802040 thru 36-7802042 and 36-7802049 certificated in all categories. To prevent hazards in flight associated with the seizing of rod end bearings in the elevator and aileron control systems, accomplish the following: (a) Within the next ten hours in service from the effective date of this AD or upon the attainment of 50 hours total time in service whichever is later, unless previously accomplished within the previous 50 hours, and at intervals not to exceed 50 hours in service from the last inspection, inspect and replace the rod end bearings in the elevator and aileron system controls in accordance with the "Instructions Section - Paragraphs 1 thru 5" of Piper Service Bulletin No. 608 dated July 11, 1975, or equivalent. (b) Equivalent inspections and parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (c) Upon the installation of Heim MSS-3D, -4D and -5D rod end bearings for Piper part numbers 452633, 452590 and 452645, respectively, compliance with the inspection requirements of (a) may be canceled. (d) Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region may adjust the inspection intervals specified in this AD.This amendment is effective December 26, 1978.