Results
2001-24-14: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 series airplanes; C-9 airplanes; and Model DC-9-81, -82, -83, and -87 series airplanes, that requires an inspection of the power feeder bus cables of the auxiliary power unit (APU) for overheat damage between certain fuselage stations; and corrective action(s), if necessary. This action is necessary to prevent loose terminal stud connections and consequent damage to the small copper terminals, which could result in overheating of the wires at the terminal strip. Such overheating could cause an electrical failure and could result in smoke and fire in the electrical/electronic compartment. This action is intended to address the identified unsafe condition.
2001-24-19: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 series airplanes; C-9 airplanes; Model DC-9-81, -82, -83, and -87 series airplanes; and Model MD-88 airplanes, that requires an inspection to detect chafing or overheat damage of the electrical wires located at fuselage station Y=110.000 bulkhead of the lower nose left tunnel; and corrective actions, if necessary. This AD also requires replacing the external power ground stud with a new ground stud using new attaching parts, torquing new attachments, and installing a nameplate. This action is necessary to prevent loose external power ground wires, which could cause arcing and overheated wire insulation and consequent smoke/fire in the cockpit. This action is intended to address the identified unsafe condition.\n\n\nDATES: Effective January 16 2002. The incorporation by reference of certain publications listed in the regulations is approved bythe Director of the Federal Register as of January 16, 2002.
52-01-06: 52-01-06 BELL: (Applies to All Model 47 series Helicopters Having Covered Tail Booms. Compliance required at next 300-hour overhaul, but not later than March 1, 1952. To prevent the main rotor striking the tail boom as a result of boom deflection when yawing at high forward speed, install the 47-706-211-1 or -2 spoiler on the tail boom. (Note: Spoiler must not be installed on any helicopter having an uncovered tail boom.) (Bell Service Bulletin No. 81 covers this same subject.)
2017-13-10: We are superseding Airworthiness Directive (AD) 2003-18-06, which applied to certain Airbus Model A319-131 and -132 airplanes; Model A320-231, -232, and -233 airplanes; and Model A321-131 and -231 airplanes. AD 2003-18-06 required installing new anti-swivel plates and weights on the engine fan cowl door (FCD) latches and a new cowl door hold-open device. This AD retains the previous actions and requires modifying the engine FCDs, installing placards, and re-identifying the FCDs. This AD also adds airplanes to the applicability. This AD was prompted by reports of additional engine FCD in-flight losses, and a new FCD front latch and keeper assembly that has been developed to address this unsafe condition. We are issuing this AD to address the unsafe condition on these products.
95-15-13: This amendment adopts a new airworthiness directive (AD) that applies to Jetstream Aircraft Limited (JAL) Jetstream Models 3101 and 3201 airplanes. This action requires inspecting the main passenger/crew door locking mechanism to ensure that a taper pin is installed, installing a taper pin if not already installed, and modifying the passenger door warning system. The actions specified by this AD are intended to prevent the inability to open the passenger/crew door or failure of the passenger door warning system, which could result in passenger injury if emergency evacuation is needed.
77-14-18: 77-14-18 SIAI-MARCHETTI: Amendment 39-2968. Applies to F.260 and F.260B airplanes, Serial Numbers 101 thru 125, 2-26 thru 2-61, 3-76, 3-77, 3-78, 3-80, 3-84, 502, 10-09, and 20-01, certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent structural failure and possible loss of airplane control due to fatigue cracks surrounding the control surface hinge bracket attachment holes, accomplish the following: (a) Comply with paragraph (c) of this AD in accordance with the following schedule: (1) For airplanes with 1000 or less hours time in service on the effective date of this AD, within the next 25 hours time in service unless accomplished within the past 475 hours time in service, and thereafter in accordance with subparagraph (3) of this paragraph. (2) For airplanes with more than 1000 hours time in service on the effective date of this AD, within the next 10 hours time in service, unless accomplished within the past 190 hours time in service, and thereafter in accordance with subparagraph (3) of this paragraph. (3) Continue to comply with paragraph (c) of this AD at intervals not to exceed 500 hours time in service until reaching 1000 hours total time in service and thereafter at intervals not to exceed 200 hours time in service. (b) The inspections required by paragraph (c) of this AD may be terminated - (1) With respect to individual affected areas upon compliance with paragraph (d) of this AD; or (2) Upon accomplishment of paragraph (e) of this AD. (c) Inspect the areas surrounding the control surfaces hinge bracket attachment holes for cracks using dye penetrant in accordance with - (1) SIAI Marchetti Mandatory Service Bulletins listed in paragraph (f) of this AD; (2) SIAI Marchetti Mandatory Service Bulletin S.B. No. 260B16 dated April 2, 1976; or (3) An FAA-approved equivalent of bulletins specified in paragraph (c)(1) and (c)(2) of this AD. (d) If a crack is found during the inspection required by paragraph (c) of this AD, before further flight, modify and repair the affected area in accordance with appropriate SIAI Marchetti Mandatory Service Bulletin listed in paragraph (f) of this AD, or an FAA-approved equivalent. (e) For areas where no cracks are found as a result of any inspection required by this AD, within the next 1,000 hours time in service after the effective date of this AD, perform the modifications and repairs specified in the SIAI Marchetti Mandatory Service Bulletins listed in paragraph (f) of this (AD), or FAA- approved equivalents. (f) The applicable areas and Service Bulletins are as follows: Affected Area Applicable Service Bulletin (1) Wing Rear Spar in the Flaps and Aileron Hinge Bracket Area S.B. 260B21 dated September 24, 1976. (2) Flaps Hinge Bracket Attachment Area S.B. 260B22 dated September 24, 1976. (3) Aileron Hinge Bracket Attachment Area S.B. 260B23 dated September 24, 1976. (4) Horizontal Stabilizer (Empennage) Rear Spar Hinge Bracket Attachment Area S.B. 260B24 dated September 24, 1976. (5) Rudder Spar Upper Hinge Bracket Attachment Area S.B. 260B25 dated September 24, 1976. (6) Elevator Outboard Hinge Bracket Attachment Area S.B. 260B26 dated September 24, 1976. (7) Horizontal Stabilizer Outboard Hinge Bracket Attachment Area S.B. 260B27 dated September 24, 1976. This amendment becomes effective July 28, 1977.
2001-24-24: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10 and -30 series airplanes, that requires an inspection of the power feeder cable for evidence of chafing, and repair of any chafed power feeder cable. This amendment also requires replacement of the wiring support clip (standoff) of the power feeder cable with a new, improved wiring support clip. This action is necessary to prevent chafing and arcing of the power feeder cable and adjacent airplane structure and system components, and consequent smoke/fire in an engine nacelle. This action is intended to address the identified unsafe condition.
2017-13-11: We are adopting a new airworthiness directive (AD) for all Model G-IV airplanes. This AD was prompted by a report indicating that the G-IV gust lock system allows more throttle travel than was intended and could allow the throttle to be advanced to reach take-off thrust. This AD requires modification of the gust lock system, and a revision of the maintenance or inspection program to incorporate functional tests. We are issuing this AD to address the unsafe condition on these products.
2010-26-04: We are adopting a new airworthiness directive (AD) for the products listed above that are equipped with Thielert Aircraft Engine GmbH (TAE) Engine Model TAE-125-01 installed per Supplemental Type Certificate (STC) No. SA03303AT. This AD requires installing a full authority digital engine control (FADEC) backup battery, replacing the supplement pilot's operating handbook and FAA approved airplane flight manual, and revising the limitations section of the supplement airplane maintenance manual. This AD was prompted by an incident where an airplane experienced an in-flight engine shutdown caused by a momentary loss of electrical power to the FADEC. We are issuing this AD to prevent interruption of electrical power to the FADEC, which could result in an uncommanded engine shutdown. This failure could lead to a loss of engine power.
2001-24-18: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -30, and -40 series airplanes and C-9 airplanes, that requires revising the wiring of the sidewall lights in the forward and aft passenger compartment. The actions specified by this AD are intended to prevent the control switch of the cabin sidewall lights on the forward attendant's panel from overheating, which could result in shorting of the dim, bright, and power terminals, and consequent smoke/fire in the passenger compartment. This action is intended to address the identified unsafe condition.