Results
2014-17-03: We are adopting a new airworthiness directive (AD) for certain Technify Motors GmbH (type certificate previously held by Thielert Aircraft Engines GmbH) TAE 125-02-99 and TAE 125-02-114 reciprocating engines. This AD requires removal of each high-pressure (HP) fuel pump before 300 flight hours (FHs) in service or within 55 FHs after the effective date of the AD, whichever occurs later. This AD was prompted by in-flight shutdowns on airplanes with TAE 125-02 engines. We are issuing this AD to prevent failure of the HP fuel pump, which could result in damage to the engine and damage to the airplane.
2000-02-31: This amendment adopts a new airworthiness directive (AD) that applies to certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. This AD requires replacing the stick pusher capstan and the stick pusher servo with parts of improved design. The AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to prevent improper operation of the stick pusher system caused by the existing design configuration, which could result in loss of control of the airplane during a stall.
2000-02-26: This document adopts a new airworthiness directive (AD) that applies to all Harbin Aircraft Manufacturing Corporation (Harbin) Model Y12 IV airplanes. This AD requires you to revise the Airplane Flight Manual (AFM) to include requirements for activating the airframe pneumatic deicing boots. This AD is the result of reports of in-flight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to assure that flightcrews have the information necessary to activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. Without this information, flightcrews could experience reduced controllability of the aircraft due to adverse a\nrodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
2014-16-28: We are adopting a new airworthiness directive (AD) for certain Empresa Brasileira de Aeronautica S.A. (Embraer) Model EMB-135BJ airplanes. This AD was prompted by reports of failure of the bolts that connect the cockpit windshield center-post to the forward fuselage. This AD requires repetitive detailed inspections to detect discrepancies on the attaching parts of the cockpit windshield center- post; checking whether the bolts are tightened, if applicable; and modifying parts, including inspecting for and repairing damage. We are issuing this AD to prevent failed bolts and failed attaching parts of the cockpit windshield center-post, which could lead to loss of structural integrity of the airplane.
53-24-03: 53-24-03 MOONEY: Applies to All Model M-18L Aircraft Which Have Not Had the Landing Gear Bellcrank Cover Installed. Compliance required by February 28, 1954. In order to prevent baggage from jamming or fouling the landing gear retraction bellcrank P/N 35-1, install bellcrank covers, P/N 1028-1 with installing angles P/N 1028-2. (Mooney Service Bulletin No. 12 covers this same subject.)
2000-02-27: This document adopts a new airworthiness directive (AD) that applies to all Empresa Brasileira de Aeronautica S.A. (Embraer) Models EMB-110P1 and EMB-110P2 airplanes. This AD requires you to revise the Airplane Flight Manual (AFM) to include requirements for activating the airframe pneumatic deicing boots. This AD is the result of reports of in-flight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to assure that flightcrews have the information necessary to activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. Without this information, flightcrews could experience reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
98-11-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300, A310, and A300-600 series airplanes, that requires replacement of the non-return valves located in the engine fuel feed lines on the outer fuel tank with new return valves; and, for certain airplanes, replacement of the inner tank booster pump canisters with modified canisters. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent sticking of non-return valves located in the fuel system, which could result in an internal fuel transfer from the center tank to the inner or outer tank. Such a transfer of fuel could lead to fuel spillage overboard through the vent system, and consequent insufficient fuel for the airplane to reach its flight destination.
91-26-01: 91-26-01 BRITISH AEROSPACE: Amendment 39-8112. Docket No. 91-NM-117-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 controllability of the airplane, accomplish the following: (a) Within 180 days after the effective date of this AD, and thereafter at intervals not to exceed 4 years, perform a visual inspection of the elevators to detect corrosion of the mild steel balance weights and of the forward face of the leading edge members in accordance with British Aerospace Preliminary Technical Leaflet (PTL) No. 324 (for Viscount Model 744 and 745D series airplanes), Issue 1, or PTL No. 193 (for Viscount Model 810 series airplanes), Issue 1, both dated February 10, 1990, as applicable. (1) If corrosion is found in the mild steel balance weights, prior to further flight, repair in accordance with the applicable PTL.(2) If corrosion is found in the forward face of the leading edge members, prior to further flight, repair in accordance with the applicable PTL. If corrosion exceeds the limits specified in the PTL, prior to further flight, replace the members in accordance with the PTL. (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 inspection and repair requirements shall be done in accordance with British Aerospace Preliminary Technical Leaflet (PTL) No. 324 (for Viscount Model 744 and 745D series airplanes) Issue 1, dated February 10, 1990; or PTL No. 193 (for Viscount Model 810 series airplanes), Issue 1, dated February 10, 1990; 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. (e) This amendment (39-8112, AD 91-26-01) becomes effective on March 23, 1992.
75-16-12: 75-16-12 BRITISH AIRCRAFT CORPORATION: Amendment 39-2285. Applies to Model BAC 1-11 200 and 400 Series Airplanes Equipped with AiResearch Model GTCP-85-115, -115C, -115K, or -115CK Auxiliary Power Units (APU). Compliance is required as indicated. To prevent possible overheat damage of the rear fuselage tail cone structure due to fire resulting from an APU or jet pipe assembly failure, accomplish the following: (a) Check the condition of the APU turbine bearing seals either - (1) In accordance with an oil sampling analysis program that detects progressive deterioration of the bearing seals and that must be approved by an FAA maintenance inspector within the nest 25 APU hours' time in service after the effective date of this AD; or (2) In accordance with paragraphs 2.2.1, 2.2.2, and 2.2.3, BAC 1-11 Alert Service Bulletin No. 49-A-PM 4714, Issue 4, dated March 8, 1971, or an FAA-approved equivalent, within the next 25 APU hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 25 APU hours' time in service from the last inspection. (b) If a defective turbine bearing seal is found during a check required by paragraph (a), before further flight, either - (1) Repair the APU in accordance with the applicable AiResearch Maintenance Manual or an FAA-approved equivalent; or (2) Mechanically disconnect the APU so that it is not possible to operate the APU on the ground or in flight and install a placard in the cockpit in clear view of the pilot stating that the APU is not to be operated. (c) Within the next 1,000 APU hours' time in service after the effective date of this AD, unless already accomplished, either - (1) Mechanically disconnect the APU so that it is not possible to operate the APU on the ground or in flight and install a placard on the APU cockpit controls stating that the APU is not to be operated; or (2) Modify the APU installation and tail cone assembly to provide ameans that automatically shuts down the APU when an overheat condition occurs, as follows: (i) For airplanes equipped with a premodification PM 3520 tail cone installation, modify the APU installation and tail cone assembly in accordance with BAC 1-11 Service Bulletin No. 49-PM 4714, Part 1, Revision 1, dated November 9, 1970, and Parts 2(a), (b), and (d), dated November 16, 1970, or an FAA- approved equivalent. (ii) For airplanes equipped with a post-modification PM 3520 tail cone installation, modify the APU installation and tail cone assembly in accordance with BAC 1- 11 Service Bulletin No. 49-PM-4714, Part 1, Revision 1, dated November 9, 1970, and Parts 2(a), (b), (c), and (d), dated November 16, 1970, or an FAA- approved equivalent. (d) The checks required by paragraph (a) may be discontinued after the APU has been disconnected in accordance with subparagraph (b)(2), or subparagraph (c)(1) or after the modification specified in subparagraph (c)(2) has been accomplished. (e) Placards installed in accordance with subparagraph (b)(2), or subparagraph (c)(1) may be removed after the modification specified in subparagraph (c)(2) has been accomplished. (f) The checks required by paragraph (e) constitute preventive maintenance under FAR 43. This amendment becomes effective August 28, 1975.
2014-17-04: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by reports that elevator power control unit (PCU) shear pins may fail prematurely. This AD requires repetitive replacement of the elevator PCU shear pins. We are issuing this AD to prevent premature elevator PCU shear pin failure. If all pins fail on one elevator, the elevator surface would become inoperative, which could reduce the controllability of the airplane and could result in a loss of redundancy for flutter prevention.