Results
91-03-10: 91-03-10 CASA: Amendment 39-6883. Docket No. 90-NM-17-AD. Applicability: Model C-212 series airplanes, certificated in any category. Compliance: Required within 60 days after the effective date of this AD, unless previously accomplished. To prevent reduced controllability of the airplane, accomplish the following: A. Modify the propeller speed and pitch control system so that the control cannot be moved into reverse thrust while in flight, and so that the propeller pitch settings cannot be adjusted for ground operation while in flight, in accordance with CASA Service Bulletin 212-76-07, dated July 27, 1990, or in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. B. An alternate means 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 submitted directly to the Manager, Standardization Branch, ANM- 113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence 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 Construcciones Aeronauticas S.A., Getafe, Madrid, Spain. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. Airworthiness Directive 91-03-10 supersedes AD 90-04-11. Amendment 39-6508. This amendment (39-6883, AD 91-03-10) becomes effective on March 11, 1991.
2010-20-22: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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: Following a review of operational data of the Tay 651-54 engine, it has been found that the actual stress levels in the Tay 651-54 engine High Pressure Compressor (HPC) stages 1, 3, 6, 7 and 12 discs were higher than those originally assumed and therefore the approved lives needed to be reduced. We are issuing this AD to prevent HPC stages 1, 3, 6, 7, and 12 discs from exceeding the approved reduced life limits, which could result in an uncontained failure of a disc and damage to the airplane.
2010-20-16: 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: * * * * * Two cases of complete nose landing gear (NLG) shock absorber bolts failure were reported to the manufacturer. In both cases, the crew was unable to retract the gear and was forced to an In Flight Turn Back. In one case, the aircraft experienced a low speed runway excursion. The root cause of the bolts failure has been identified being due to a bolt(s) over-torque. The investigation has highlighted that the design of the NLG shock absorber was not tolerant to the over-torque, and an inspection plan has been developed to track any NLG shock absorber-to-main barrel attachment bolts status. * * * * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
91-14-11: 91-14-11 BRITISH AEROSPACE: Amendment 39-7052. Docket No. 91-NM-37-AD. Applicability: Model ATP series airplanes, on which Modification (c)AC11431 has not been accomplished, certificated in any category. Compliance: Required within 60 days after the effective date of this AD, unless previously accomplished. To prevent loss of the main landing gear (MLG) wheel from the axle and reduced controllability of the airplane on takeoff or landing, accomplish the following: A. Install a new axle washer and a new axle nut on all MLG's [Modification (c)AC11431], in accordance with Dowty Aerospace Service Bulletin 200-32-137, dated November 6, 1990. NOTE: British Aerospace Service Bulletin ATP-32-28, dated November 6, 1990, references the Dowty Aerospace Service Bulletin for modification 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. D. The installation requirements shall be done in accordance with Dowty Aerospace Service Bulletin 200-32-137, dated November 6, 1990. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041-0414. Copies may be inspected at the FAA, Transport Airplane Directorate, Renton, Washington; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. This amendment (39-7052, AD 91-14-11) becomes effective on August 6, 1991.
2010-20-13: We are adopting a new airworthiness directive (AD) for certain Model DC-10-30, DC-10-30F, DC-10-30F (KC-10A and KDC-10), DC-10-40, DC- 10-40F, and MD-10-30F airplanes. This AD requires doing a one-time inspection of the wire bundles to determine if wires touch the upper surface of the center upper auxiliary fuel tank, and marking the location if necessary; a one-time inspection for splices and damage of all wire bundles routed above the center upper auxiliary fuel tank; a one-time inspection for damage to the fuel vapor barrier seal and upper surface of the center upper auxiliary fuel tank; and corrective actions, if necessary. This AD also requires installing non-metallic barrier/shield sleeving to the wire harnesses, new clamps, new attaching hardware, and new extruded channels. This AD was prompted by fuel system reviews conducted by the manufacturer. We are issuing this AD to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
2010-20-24: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires incorporating changes to the electronic flight information system and the airplane flight manuals. This AD was prompted by reports of uncommanded changes to the communications radio frequency, altitude preselect, and/or transponder codes. We are issuing this AD to correct faulty integration of hardware and software, which could result in unannunciated, uncommanded changes in communications radio frequency, transponder codes, and altitude preselect settings. These uncommanded changes could result in loss of communication with air traffic control due to improper communications frequency, autopilot level off at the incorrect altitude, or air traffic control loss of proper tracking of the aircraft.
91-14-18: 91-14-18 BRITISH AEROSPACE: Amendment 39-7059. Docket No. 91-NM-42-AD. Applicability: All Viscount Model 744, 745D, and 810 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent reduced structural integrity of the wings, accomplish the following: A. Within 180 days after the effective date of this AD, and thereafter at intervals not to exceed 180 days, perform an eddy current inspection to detect corrosion along the total length of the top surface of the left and right wing spar upper boom in accordance with British Aerospace Preliminary Technical Leaflet (PTL) No. 321, Issue 1, dated January 13, 1989, or PTL No. 190, Issue 1, dated January 13, 1989, as applicable. B. If corrosion is found, prior to further flight, repair in accordance with PTL No. 321, Issue 1, dated January 13, 1989, or PTL No. 190, Issue 1, dated January 13, 1989, as appropriate; or in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. C. 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. D. 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. E. The inspections and repair requirements shall be done in accordance with British Aerospace Preliminary Technical Leaflet (PTL) No. 321, Issue 1, dated January 13, 1989, or PTL No. 190, Issue 1, dated January 13, 1989, as applicable. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041-0414. Copies may be inspected at the FAA, Transport Airplane Directorate, Renton, Washington; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. This amendment (39-7059, AD 91-14-18) becomes effective on August 6, 1991.
96-04-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A340 series airplanes. This action requires repetitive inspections to detect corrosion and cracking of the shortening mechanism pins in the main landing gear (MLG), and repair or replacement, if necessary. It also requires replacement of the shortening mechanism pin and retraction mechanism pins; the forward pintle pin; the shortening mechanism bellcrank pin; and the bellcrank subassembly of the shortening mechanism. This amendment is prompted by reports of failure of the shortening mechanism pins due to improper grinding of the chrome plating during manufacture, which led to the initiation of stress corrosion and cracks. The actions specified in this AD are intended to prevent failure of these pins, which could lead to a significant reduction of the shock absorber capability or damage to various components of the MLG, and eventually could lead to the failure of the MLG.
77-18-04: 77-18-04 BEECH: Amendment 39-3028. Applies to Models C90 (serial numbers LJ-689 through LJ-713), E90 (serial numbers LW-167 through LW-216), A100 (serial numbers B-213 through B-232), B100 (serial numbers BE-10 through BE-22), Model 200 (serial numbers BB- 175 through BB-185, BB-187 through BB-193, BB-195 through BB-198, BB-200 through BB- 202, and BB-204 through BB-223), and Model 200T (serial numbers BT-1 and BT-2) airplane certificated in all categories. Compliance: Required as indicated unless already accomplished. To assure proper locking of the cabin door and to prevent possible incidents involving loss of cabin pressurization, within the next 25 hours time-in-service after the effective date of this AD, accomplish the following in accordance with Beechcraft Service Instructions No. 0914 or later approved revisions and instructions contained in the applicable airplane maintenance manual: A. Visually inspect the cabin door latch hooks and pins for proper engagement and adjustment, check the door latch mechanism for over center position when locked, and adjust latch hooks, pins and/or door latch mechanism if necessary. B. Any equivalent means of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective on September 12, 1977.
51-24-01: 51-24-01 LYCOMING: Applies to All Lycoming GO-435-C2 Engines Serially Numbered 1815-11 and Below Not Having the Letter "P" Stamped on the Upper Right-hand Corner of Each Cylinder Rocker Box and Installed in Navion Model B Aircraft. To be accomplished by June 1, 1952 or next overhaul, whichever occurs first. To prevent loosening of the exhaust valve seats in Lycoming GO-435-C2 engines installed in Navion Model B airplanes, the exhaust valve seats are to be peened in the cylinder head. The cylinders must be removed from the engine for this operation. When peening is accomplished, stamp "P" 1/8 inch high on upper right-hand corner of cylinder rocker box flange face near exhaust push rod. (Lycoming Service Bulletin No. 145 also covers this subject.