Results
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.
98-06-30: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Raytheon (Beech) Model 400, 400A, 400T, MU-300, MU-300-10 airplanes, that currently requires replacement of outflow/safety valves with serviceable valves. This amendment revises the applicability of the existing AD to add an airplane model and to remove other airplanes, as well as to identify the serial numbers of affected airplanes. The actions specified by this AD are intended to prevent cracking and consequent failure of the outflow/safety valves, which could result in rapid decompression of the airplane.
90-02-07: 90-02-07 AEROSPATIALE: Amendment 39-6466. Docket No. 89-NM-266-AD. Applicability: Model ATR42 series airplanes, Serial Numbers 003 through 100, certificated in any category. Compliance: Required within 30 days after the effective date of this AD, unless previously accomplished; and thereafter, compliance is required immediately following any maintenance action which could result in mis-wiring and/or mis-plumbing. To detect incorrectly installed fire protection system plumbing and/or wiring, accomplish the following: A. Conduct an inspection of the right engine fire extinguishing system wiring and plumbing in accordance with the Aerospatiale All Operators Information Message DS/E 20/89, dated December 4, 1989. If any pipes or electrical connectors are improperly installed, prior to further flight, correct the installation in accordance with the Aerospatiale message. B. An alternate means of compliance or adjustment of the compliance time, which providesan 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 will either concur or comment and then send it to the 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 in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse Cedex 03, France. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6466, AD 90-02-07) becomes effective on January 23, 1990.