Results
98-06-39: This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model AS 332C, L, L1, and L2 helicopters. This action requires determining the thickness of the shim washers, inspecting certain cockpit door hinge tenons (hinge tenons) for cracks, and if a crack is found, replacing the hinge tenon with an airworthy hinge tenon. This amendment is prompted by several reports of cracked hinge tenons due to improper shimming. The actions specified in this AD are intended to detect cracks in the hinge tenons due to unintended loading of the improperly shimmed tenons caused by closing the door, which may lead to separation of the door from the helicopter, impact with the main rotor or tail rotor system, and subsequent loss of control of the helicopter.
78-11-06: 78-11-06 BEECH: Amendment 39-3226. Applies to Model 65-A90, B90 and C90 (Serial Numbers LJ-114 through LJ-705), and Model E90 (Serial Numbers LW-1 through LW-141) airplanes incorporating Beechcraft H-14 autopilot installations with a 13.5 inch diameter elevator servo bellcrank. To preclude possible failure of the elevator control cable, unless already accomplished. A) Before the next flight, except for those airplanes previously modified in accordance with Beech Modification Kit Number 90-9067-1S, open the aft fuselage belly access door and locate the autopilot elevator servo bellcrank at F.S. 319.00, located to the left of centerline. Measure the bellcrank and if it measures 10 inches or less no further action is required. If the bellcrank measures 13.5 inches or larger (groove to groove), visually inspect the primary elevator control cable, the pulley bracket at F.S. 340.00, the autopilot servo cable, and autopilot bellcrank in accordance with Beech Service Instructions No. 0988, or later approved revisions. If there is no evidence of cable rubbing or damage to the airplane, no further immediate action is required. 1. If rubbing of the elevator cable is noted, but no damage has occurred. a. Disconnect and remove the autopilot servo cable from the airplane. b. Install a locally fabricated placard in plain view of the pilot indicating "AUTOPILOT INOPERATIVE". 2. If fraying of the elevator cable or other damage is noted: a. Replace the elevator cable and repair or replace any other damaged parts. b. Accomplish paragraphs A)1.a. and 1.b. B) If not previously accomplished, on or before September 1, 1978, modify the servo mount of any Beechcraft H-14 elevator autopilot servo having a 13.5 inch diameter or larger bellcrank in accordance with Beech Modification Kit Number 90-9067-1S, or later approved revisions. Upon the completion of this modification any autopilot made inoperative under paragraphs A)1. orA)2. of this AD may be returned to service and the "AUTOPILOT INOPERATIVE" placard removed. C) Aircraft may be flown in accordance with 21.197 to a base where the inspection required by this AD can be accomplished, after coordination with the Chief, Engineering and Manufacturing Branch, FAA, Central Region. D) 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 June 8, 1978, to all persons except those to whom it has already been made effective by air mail letter from the FAA dated May 4, 1978.
2011-19-01 R1: We are revising an existing airworthiness directive (AD) that applies to all Airbus Model A318, A319, A320, and A321 series airplanes. The existing AD currently requires revising the airplane flight manual (AFM) to include a procedure intended to address the unsafe condition, an inspection of the firewall connector for signs of arcing if an integrated drive generator (IDG) (or generator (GEN)) was shut down in-flight automatically or using the AFM procedure, and corrective action if necessary; and provides an optional terminating action for certain AFM revision and inspections. This AD was prompted by the potential for an inadvertent error by flightcrew to use the IDG switch instead of the GEN switch when doing the AFM display unit failure procedure required by the existing AD. This AD retains the actions required by the existing AD and clarifies certain terminology. We are issuing this AD to prevent transient loss of certain systems, which could result in the reduced abilityof the flightcrew to cope with adverse flight conditions.
2006-23-05: The FAA is adopting a new airworthiness directive (AD) for all Cessna Model 750 airplanes. This AD requires inspecting the inboard- hinge brackets of the left and right elevators for cracking, and doing related investigative and corrective actions if necessary. This AD results from a report of cracking found on the elevator inboard-hinge brackets. We are issuing this AD to detect and correct cracking of the elevator inboard-hinge brackets, which could result in structural failure of the elevators and consequent loss of control of the airplane.
77-08-07: 77-08-07 MESSERSCHMITT-BOLKOW-BLOHM (MBB): Amendment 39-2880. Applies to Model BO-105A and BO-105C helicopters, serial numbers S101 through S200, certificated in all categories, that incorporate external load hook assembly P/N 105-80322. Compliance is required as indicated, unless already accomplished. To prevent the possible inability to release an external load, accomplish the following: (a) Within the next 5 hours time in service after the effective date of this AD, either - (1) Install an operating limitation placard on the instrument panel in full view of the pilot, setting forth the following limitation "EXTERNAL LOAD OPERATIONS PROHIBITED"; or (2) Replace wire bundle 22VB, P/N 105-98327, with new bundle, P/N 105- 98326, and change the wiring connection of the associated connector plug 5MDA in accordance with subparagraph 2B of MBB Service Bulletin No. 80-21, dated July 25, 1975, or equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, c/o American Embassy, A.P.O. New York, N.Y. 09667. (b) The operating limitation placard required by paragraph (a)(1) of this AD may be removed upon compliance with paragraph (a)(2) of this AD. This amendment becomes effective May 6, 1977.
98-06-26: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires repetitive inspections to detect corrosion in the wheel axles of the main landing gear (MLG) sliding members; and rework of any corroded areas, an inspection to detect cracks in the wheel axles, and replacement of any cracked sliding member. This AD provides for interim actions that may be accomplished in lieu of the repetitive inspections. This AD also requires eventual modifications of the main wheel brake units and the MLG sliding members; when accomplished, these modifications terminate the repetitive inspections and interim actions. This amendment is prompted by a report of failure of an MLG wheel axle during push back of an in-service airplane from the terminal. The actions specified by this AD are intended to prevent failure of the MLG wheel axle due to problems associated with corrosion and cracking.
81-06-06: 81-06-06 BRITISH AEROSPACE: Amendment 39-4065. Applies to Model HS/DH/BH- 125 airplanes series -3A/R, -3A/RA, and -3A/RA with British Aerospace Modification 25/2600 installed; series -400A and -400A with British Aerospace Modification 25/2550 or STC SA3870WE installed; and series -600A and -600A with British Aerospace Modification 25/2468 installed, certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent restricted movement of the flap control unit input lever and chafing of the left engine fuel line due to possible interferences, accomplish the following: (a) Within 50 hours time in service after the effective date of this AD, inspect: (1) For chafing of the left engine fuel feed line; and (2) For recommended clearance between the fuel feed line and the flap control unit input lever in accordance with paragraph 2A(1), (2), and (3) of the Accomplishment Instructions of British Aerospace Service Bulletin28-69, Revision 1, dated June 25, 1979 (hereinafter referred to as the service bulletin) or an equivalent approved by the Chief, Aircraft Certification Staff, Federal Aviation Administration, Europe, Africa, and Middle East Office, Brussels, Belgium. (b) If as a result of the inspections required in paragraph (a) of this AD - (1) Chafing or other damage to the fuel line is found, before further flight, except that aircraft may be flown in accordance with FAR Section 21.197 to a base where the work can be performed, replace the fuel line with a serviceable fuel line of the same P/N. (2) Clearance between the engine fuel feed line and the flap control unit input lever is found to be less than 0.15 inches, before further flight, increase the clearance in accordance with paragraph 2A(4) of the service bulletin. (c) Upon completion of the actions required in paragraphs (a) and (b) of this AD, return the aircraft to service in accordance with paragraphs 2A(5) and 2A(6)of the service bulletin. This amendment becomes effective March 26, 1981.
2012-15-10: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-400 and 747-400D series airplanes. This AD was prompted by a report of an in-flight multi-power system loss of the 1, 2, and 3 alternating current electrical power systems located in the main equipment center (MEC). This AD requires installing aluminum gutter reinforcing brackets to the forward and aft drip shield gutters of the MEC; and adding a reinforcing fiberglass overcoat to the top surface of the MEC drip shield, including an inspection for cracking and holes in the MEC drip shield, and corrective actions if necessary. This AD also provides for an option to install an MEC drip shield drain system, which, if accomplished, would extend the compliance time for adding the reinforcing fiberglass overcoat to the top surface of the MEC drip shield. We are issuing this AD to prevent water penetration into the MEC, which could result in the loss of flight critical systems.
2010-10-18: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Investigation of a recent high altitude loss of cabin pressurization on a BD-100-1A10 aircraft determined that it was caused by a partial blockage of a safety valve cabin pressure- sensing port, in conjunction with a dormant failure/leakage of the safety valve manometric capsule. The blockage, caused by accumulation of lint/dust on the grid of the port plug, did not allow sufficient airflow through the cabin pressure-sensing port to compensate for the rate of leakage from the manometric capsule, resulting in the opening of the safety valve. It was also determined that failure of the manometric capsule alone would not result in the opening of the safety valve. * * * * * The unsafe condition is possible loss of cabin pressure caused by the opening of the safety valve. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2012-15-11: We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by a report that a passenger oxygen pipe at frame 10 was chafing against the forward lavatory rear structure, raising the risk of the oxygen pipe developing a crack. This AD requires modifying the routing of and, if necessary, replacing, the oxygen pipe. We are issuing this AD to prevent rupture of the oxygen pipe which, in case of a cabin depressurization, would impair operation of the passenger oxygen distribution system.