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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.
2000-02-23: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9, DC-9-80, and C-9 (military) series airplanes, and Model MD-88 airplanes, that requires a one-time inspection to determine the type of engine ignition switch installed in the hinged forward overhead switch panel, and replacement of certain rotary ignition switches with new design rotary ignition switches. This amendment is prompted by reports of smoke in the flight compartment during engine ignition selection. The actions specified by this AD are intended to prevent an internal electrical short in the engine ignition switch, which could result in smoke in the flight compartment.
87-02-02: 87-02-02 FAIRCHILD AIRCRAFT CORPORATION: Amendment 39-5518. Applies to Models SA 226-T, SA 226-T(B), SA 226-AT, SA 226-TC, SA 227-TT, SA 227-AT, and SA 227-AC (all serial numbers) airplanes certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent possible primary control system cable failures, accomplish the following: (a) For airplanes with 10,000 or more hours time-in-service (TIS) on the effective date of this AD, within the next 150 hours TIS after the effective date of this AD and each 400 hours TIS thereafter, inspect control cables in accordance with paragraph (a)(1) of this AD or, within the next 150 hours TIS and each 10,000 hours TIS thereafter, replace control cables in accordance with paragraph (a)(2) of this AD: (1) Inspect all elevator, rudder, aileron and aileron to rudder interconnect primary control cables, including cables that are routed inside the control column, as follows: (A) Gain access to control cables in accordance with appropriate maintenance instructions. (B) Release tension on each cable. (C) Pass a cloth along the entire length of each cable to clean the cable for visual inspection and to detect broken wires. Visually inspect the entire length for broken wires and general condition. Rotate the cable 180 degrees where the cable contacts any pulley/fairlead or pressure seal, birdcage cable (slightly untwist), and visually inspect for wear/broken wires and for general condition 24 inches either side of contact area when the controls are in the neutral position. (D) Prior to further flight, replace with a new cable any cable found to have any one of the following conditions: (i) More than three (3) broken wires within any one-foot section of the cable (any wire worn more than one-half its diameter is considered broken), or (ii) More than one (1) one-foot section with three broken wires, or(iii) Cables whose total number of broken wires exceeds the total number of feet in length of that cable, or (iv) More than six (6) wires worn not more than one-half of the wire diameter in any one-inch length of cable. (E) In cases where discrepant cables have been found, prior to further flight, inspect the condition of the associated fairleads/pressure seals or pulleys in accordance with appropriate maintenance instructions and replace any unserviceable components as required. (F) Prior to returning the airplane to service, reset cable tensions, rerig primary control systems, reassemble the airplane and verify proper control systems operation, all in accordance with appropriate maintenance instructions, and make an appropriate maintenance record entry. (2) Remove and replace all elevator, rudder, aileron and aileron to rudder interconnect primary control cables with new cables in accordance with appropriate maintenance instructions. Prior to returning the airplane to service, reset cable tensions, rerig primary control systems, reassemble the airplane and verify proper control systems operations, all in accordance with appropriate maintenance instructions, and make an appropriate maintenance record entry. (b) For airplanes with less than 10,000 hours TIS on the effective date of this AD, prior to the accumulation of 10,150 hours TIS and each 400 hours TIS thereafter, inspect control cables in accordance with paragraph (a)(1) of this AD or, prior to the accumulation of 10,150 hours TIS and each 10,000 hours TIS thereafter, replace control cables in accordance with paragraph (a)(2) of this AD. (c) Paragraphs (a) and (b) of this AD do not restrict compliance to one alternative (repetitive inspections or replacement at specified intervals) exclusive of the other, but may be complied with interchangeably provided the inspection/replacement intervals are complied with. (d) Operators who have kept recordsof hours TIS on all individual control cables in an airplane may substitute these records in lieu of airplane hours TIS for determining the compliance times in this AD. (e) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (f) An equivalent method of compliance with this AD may be used when approved by the Manager, Airplane Certification Branch, ASW-150, Southwest Regional Office, FAA, Fort Worth, Texas 76101; Telephone (817) 624-5150. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Fairchild Aircraft Corporation, P.O. Box 32486, San Antonio, Texas 78284; or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on January 27, 1987.