Results
2010-02-04: We are adopting a new airworthiness directive (AD) for certain Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD requires replacing the engine fuel shutoff valves for the left and right main tanks. This AD results from a report of a failed engine start, which was caused by an internally fractured engine fuel shutoff valve. We are issuing this AD to prevent the failure of the valve in the closed position, open position, or partially open position, which could result in engine fuel flow problems and possible uncontrolled fuel leak or fire.
94-11-07: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model BAC 1-11-200 and -400 series airplanes, that requires inspection of the landing gear brakes for wear, and replacement of the brakes if the wear limits prescribed in this amendment are not met. This amendment also requires that the specified maximum brake wear limits be incorporated into the FAA-approved maintenance inspection program. This amendment is prompted by an accident in which a transport category airplane executed a rejected takeoff (RTO) and was unable to stop on the runway due to worn brakes; and the subsequent review of allowable brake wear limits for all transport category airplanes. The actions specified by this AD are intended to prevent the loss of brake effectiveness during a high energy RTO.
2009-26-06: The FAA is superseding an existing airworthiness directive (AD) for Honeywell International Inc. ALF502 series and LF507 series turbofan engines with certain fuel manifold assemblies installed. That AD currently requires initial and repetitive on-wing eddy current or in-shop fluorescent penetrant inspections of certain part number (P/N) fuel manifold assemblies for cracks, and replacement of cracked fuel manifolds with serviceable manifolds. This AD continues to require inspecting those fuel manifolds for cracks, adds leak checks of certain additional P/N fuel manifolds, and specifies replacement of the affected manifolds as an optional terminating action in lieu of the repetitive inspections. This AD results from reports of fire in the engine nacelle. We are issuing this AD to detect cracks in certain fuel manifolds and fuel leaks from other fuel manifolds, which could result in a fire in the engine nacelle and a hazard to the aircraft.
96-19-04: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Fokker Model F28 Mark 1000, 2000, 3000, and 4000 series airplanes. This action requires a one-time inspection to detect cracks of the dimpled lap joints in the fuselage skin, and repair of cracked lap joints. This amendment is prompted by a report indicating that cracks were found at various locations in the outer skin of the dimpled longitudinal lap joints of the fuselage skin. The actions specified in this AD are intended to prevent such cracking, which could result in reduced structural integrity of the fuselage and/or rapid decompression of the airplane.
78-18-04: 78-18-04 BENDIX: Amendment 39-3292. Applies to Bendix D-2000 and D-2200 series magnetos unless previously accomplished. To preclude the loss of ignition, accomplish the following, excepting paragraph (e), within the time specified below or 180 days after the effective date of this AD, whichever occurs first. (a) Rotor-Housing Interference Within the next 10 hours in service, for any of the following serial numbered magnetos, accomplish the, "Detailed Instructions", shown in Service Bulletin No. 590A or an approved equivalent. (1) Red nameplate magnetos exhibiting four hex. head socket cap screws as shown in Service Bulletin No. 590A, Figure 1, having S/N 5145 thru 11744, not prefixed by the letter "A" nor "R". (2) Blue nameplate magnetos exhibiting four hex. head socket cap screws as shown in Service Bulletin Figure 1, having S/N 701001 or below, not prefixed by the letter "A" nor "R". (b) Rear Bearing Overheating. Within the next 10 hours inservice, for any of the following serial numbered magnetos, accomplish the "Detailed Instructions", shown in Service Bulletin No. 600 or an approved equivalent. (1) Red nameplate magnetos, S/N 3001 thru 17509 (including those identified by an "A" or "R" preceding the serial number) not exhibiting the letter "B" stamped approximately in the center of the bottom line of the nameplate. (2) Red nameplate magnetos, S/N X2455 thru X2561 not exhibiting the letter "B" stamped approximately in the center of the bottom line of the nameplate. (3) Blue nameplate (Bendix remanufactured) magnetos, having S/N below 806001, not exhibiting the letter "B" stamped approximately in the center of the bottom line of the nameplate. (c) Capacitor Malfunction Within the next 25 hours in service for red nameplate magnetos below S/N 11744, accomplish Parts I and II of Service Bulletin No. 587 or an approved equivalent unless the stamped letter "S" appears on the nameplate in or nearthe lower right corner. On four cylinder versions, S/N 8618 thru 9823 and on six cylinder versions, S/N 7544 thru 9823, also accomplish Part III, or an approved equivalent. (d) Coil Retainer Plug Migration. Within the next 25 hours in service, for red nameplate magnetos below S/N 4400, accomplish the instructions of Part 1 "Detailed Inspection" procedure for threaded tapered plug, 10-382649, Paragraph Nos. 1 and 2, of Service Bulletin No. 584B or an approved equivalent. (e) Coil Retaining Devices Compliance with this paragraph is required at the expiration of 24 months after the effective date of this AD or the following specific periods whichever occurs first, unless previously accomplished. (1) On magnetos having less than 1800 hours in service since new or last overhaul on the effective date of this AD, accomplish Paragraph (e)(3) before accumulation of 2000 hours in service. (2) On magnetos having more than 1800 hours in service since new or lastoverhaul on the effective date of this AD, accomplish Paragraph (e)(3) within the next 200 hours in service. (3) Install Bendix Coil Securing Kit, P/N 10-382939 per Service Bulletin No. 584B, Part No. 2, "Detailed Housing Modification Procedure" or Part No. 3, "Detailed Disassembly and Detailed Reassembly Instructions" as specified in Part Nos. 2 or 3 "General Instructions", or an approved equivalent. (f) Equivalent inspections and procedures must be approved by the Chief of the Engineering & Manufacturing Branch, AEA-210, Federal Aviation Administration (FAA) Eastern Region. (g) As permitted by FAR 21.197 aircraft may be flown to a base where maintenance required by this Airworthiness Directive can be accomplished. This amendment supersedes AD 77-17-07. This amendment is effective September 9, 1978.
2010-01-11: 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: Excessive wear and tear of the backlash remover mechanism has been found several times on Goodrich Part Number (P/N) 23400-3B and P/N 23400-7 elevator booster control units (BCU), while corrosion has been found on some components in other BCU. The wear and tear may result in a (partly) blocked operation of the elevator system in the normal (hydraulic) mode, while any corrosion may result in deteriorated elevator control when the BCU is in MANUAL mode. * * * * * The unsafe condition is wear and tear, and corrosion of the backlash remover mechanism, which can cause a (partly) blocked operation of the elevator system in the normal (hydraulic) mode and deteriorated elevator control when the BCU is in MANUAL mode, which could result in loss of control of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
2009-26-15: 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: It has been found the possibility of some aluminum fasteners having been installed instead of titanium ones at bulkhead 1 of the LH (left-hand) and RH (right-hand) pylons of some [Embraer ERJ 170 and] Embraer ERJ 190 aircraft models. * * * * * * * * The unsafe condition for Model 170 airplanes is structural damage in the case of bird impact in the region of bulkhead 1 of the pylons, which could adversely affect continued safe flight and landing. The unsafe condition for Model 190 airplanes is damage to the hydraulic lines and electrical generator power cables in the case of bird impact in the region of bulkhead 1 of the pylons, which might lead to presence of fire without indication to the flightcrew. We are issuing this AD to require actions to correct the unsafe condition on these products.
2008-10-09 R1: The FAA is revising an existing airworthiness directive (AD), which applies to all Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. That AD currently requires revising the FAA-approved maintenance program to incorporate new airworthiness limitations (AWLs) for fuel tank systems to satisfy Special Federal Aviation Regulation No. 88 requirements. That AD also requires an initial inspection to phase in certain repetitive AWL inspections, and repair if necessary. This AD clarifies the intended effect of the AD on spare and on-airplane fuel tank system components. That AD results from a design review of the fuel tank system. We are issuing this AD to prevent the potential for ignition sources inside fuel tanks caused by latent failures, alterations, repairs, or maintenance actions, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
91-11-11: 91-11-11 SHORT BROTHERS: Amendment 39-7009. Docket No. 91-NM-11-AD. Applicability: Model SD3-60 series airplanes, equipped with PT6A-67R engines with Fuel Control Unit (FCU), Part Number (P/N) 3037319, certificated in any category. Compliance: Required within 30 days after the effective date of this AD, unless previously accomplished. To prevent the pilot from inadvertently selecting propeller pitch settings below the flight idle setting while in flight, thereby adversely affecting airplane controllability, accomplish the following: A. Shorten the existing ground/air lever spool spindle P/N SD3-47-1130xA, in accordance with Shorts Service Bulletin SD360-76-11, dated October 1990. NOTE: This service bulletin references Pratt and Whitney Service Bulletin No. 14017, Revision 1, dated August 16, 1989, for additional instructions. B. An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may 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 documents from the manufacturer may obtain copies upon request to Short Brothers, PLC, 2011 Crystal Drive, Suite 713, Arlington, Virginia 22202-3719. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-7009, AD 91-11-11) becomes effective on July 1, 1991.
2010-02-02: 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: Several occurrences of untimely radio-altimeter lock-up have been reported, where the failed radio-altimeter indicated a negative distance to the ground despite the aircraft was flying at medium or high altitude. A locked radio-altimeter 1 leads to untimely inhibition of warnings that could be displayed along with certain abnormal conditions while the avionic system switches into landing mode during altitude cruise. * * * * * [Untimely radio-altimeter lock-up] may cause the crew to be unaware of possible system failures that could require urgent crew's actions. * * * * * This AD requires actions that are intended to address the unsafe condition described in the MCAI.