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87-04-24: 87-04-24 BEECH AIRCRAFT CORPORATION: Amendment 39-5599. Applies to the following Beech airplanes certificated in any category. \n\n\nMODEL\nSERIAL NUMBERS S/N\nREFERENCE SERVICE \nINSTRUCTION NO.\n65-A90, B90,\nLJ-114 thru LJ-1139;\nBeechcraft Mandatory \nC90, C90A;\n\nService Instruction\nE90;\nLW-1 thru LW-347;\nNo. 2028, Rev. III,\nF90;\nLA-2 thru LA-236\nrevised February 1987\n200, B200;\nBB-2; BB-6 thru BB-1211; \nBB-1213 thru BB-1253; \nBB-1255 thru BB-1261; \nBB-1263 thru BB-1267;\n\n200C, B200C;\nBL-1 thru BL-112 and \nBL-124 thru BL-127;\n\n200CT, B200CT;\nBN-1 thru BN-4;\n\n200T, B200T\nBT-1 thru BT-31; \n\n300\nFA-1 thru FA-38 and \nFA-40 thru FA-50\n\n1900\nUA-1 thru UA-3\n\n1900C\nUB-1 thru UB-62\n\nH90 (T-44A)\nLL-1 thru LL-18,\nLL-20 thru LL-31,\nLL-33 thru LL-40,\nLL-42 thru LL-48, and \nLL-50 thru LL-61\nBeech T-44A Service\nInstructions No. \nT-44A-0058, Rev. 1 \nA200 (C-12A)\nBD-1 thru BD-30;\nBeech C-12 Service\nA200 (C-12C)\nBC-1 thru BC-75;\nInstructions No.A200CT (C-12D)\nBP-1, BP-22, BP-24 thru BP-39; \nBP-40 and BP-45;\nC-12-0103, Rev. 1\nA200CT (RC-12D)\nGR-1 thru GR-13;\n\nA200CT (RC-12G)\nFC-1 thru FC-3; \n\nA200CT (FWC-12D)\nBP-7 thru BP-11; \n\nA200C (UC-12B)\nBJ-1 thru BJ-66\n\nA200CT (C-12D)\nBP-46 thru BP-51;\nBeech C-12 Service\nA200CT (C-12F)\nBP-52 thru BP-63;\nInstructions No.\nB200C (C-12F)\nBL-73 thru BL-112 and\nBL-118 thru BL-123; \nC-12-0112\n65-A90-1 (U-21A)\nLM-1 thru LM-63,\nLM-65, LM-67 thru LLM-69, \nLM-71 thru LM-107, \nand LM-112 thru LM-124;\nBeech U-21 Service \nInstruction No.\nU-21-0002, Rev. 1\n65-A90-1 (JU-21A)\nLM-64, LM-66, LM-70;\n\n65-A90-1 (U-21G)\nLM-125 thru LM-141; \n\n5-A90-1 (RU-21A)\nLM-108 thru LM-111;\n\n6 65-A90-2 (RU-21B)\nLS-1 thru LS-3;\n\n65-A90-3 (RU-21C)\nLT-1 and LT-2;\n\n65-A90-4 (RU-21H)\nLU-1 thru LU-16 \n\n\n\tCompliance: Required as indicated after the effective date of this AD, unless previously accomplished. \n\n\tTo preclude malfunction of the elevator trim cable system, accomplish the following: \n\n\t(a)\tWithin the next 10 hours time-in-service, perform the following: \n\n\t\t(1)\tFor Models 65-A90, B90, C90, C90A airplanes (S/N LJ-114 thru LJ-1110), and Model E90 airplanes (S/N LW-1 thru LW-347), which have complied with AD 86-20- 03, paragraph (b), and for Models C90A airplanes (S/N LJ-1111 thru LJ-1139), which have a redesigned elevator trim cable system installed at the Beech factory without moisture protection; modify the elevator trim system in accordance with Part IV of Beechcraft Service Bulletin No. 2028, Rev. III, dated February 1987. \n\n\t\t(2)\tFor Models F90 airplanes (S/N LA-2 and LA-235); Models 200 and B200 airplanes (S/N BB-2, BB-6 thru BB-1211 and BB-1213 thru BB-1217); and for Models 200C and B200C airplanes (S/N BL-1 thru BL-112 and BL-124); and for Models 200CT and B200CT airplanes (S/N BN-1 thru BN-4); and for Models 200T and B200T airplanes (S/N BT-1 thru BT-30), which have complied with AD 86-20-03, paragraph (b), and for Models F90 airplane (S/N LA-236); and for Models 200 and B200 airplanes (S/N BB-1218 thru BB-1253, BB-1255 thru BB-1261, BB-1263 thru BB-1267); and for Models B200C airplanes (S/N BL-125 thru BL-127); and for Models B200T airplane (S/N BT-31), which have a redesigned elevator trim cable system installed at the Beech factory without moisture protection; modify the elevator trim system in accordance with Part V of Beechcraft Service Bulletin No. 2028, Rev. III, dated February 1987. \n\n\t\t(3)\tFor Models 1900 airplanes (S/N UA-1 thru UA-3) and for Models 1900C airplanes (S/N UB-1 thru UB-44), which have complied with AD 86-20-03, paragraph (b), and for Models 1900C airplanes (S/N UB-45 thru UB-62), which have a redesigned elevator trim cable system installed at the Beech factory without moisture protection; modify the elevator trim system in accordance with Part VI of Beechcraft Service Bulletin No. 2028, Rev. III, dated February 1987. \n\n\t(b)\tFor those airplanes that have not been modified in accordancewith paragraph (b) of AD 86-20-03, within the next 25 hours time-in-service, accomplish the following: \n\n\t\t(1)\tCheck the operation of the elevator trim system and mark the elevator trim indicator scale in accordance with Part I or Part II of Beech Service Bulletin No. 2028, Rev. III, dated February 1987. \n\n\t\t(2)\tFor Models 65-A90, B90, C90, C90A, and E90 airplanes, mark the elevator trim tab push rods in accordance with Part I or Part II of Beech Service Bulletin No. 2028, Rev. III, dated February 1987. \n\n\tNOTE: The following airplanes have been previously marked by the manufacturer per paragraphs (a)(1) and (a)(2) of AD 86-20-03: Models C90A (S/N LJ-1077 thru LJ-1110), F90 (S/N LA-223 thru LA-235), B200 (S/N BB-1193 thru BB-1217), B200C (S/N BL-72 thru BL-112 and BL-124), 300 (S/N FA-1 thru FA-38 and FA-40 thru FA-50), 1900 (S/N UA-1 thru UA-3), and 1900C (S/N UB-9 thru UB-44). \n\n\t\t(3)\tPlace the Elevator Trim System Preflight Check Procedure, shown in Attachment 1 of this AD, in the Limitations Section of the FAA Approved Flight Manual for the Models 65-A90, B90, C90, E90, and 200T/200CT airplanes; and the Limitations Section of the Pilot's Operating Handbook and the FAA Approved Airplane Flight Manual for the Models C90, C90A, F90, 200/200C, B200/B200C, B200T, B200CT, 300, and 1900/1900C airplanes. \n\n\t(c)\tPrior to May 15, 1987, modify the elevator trim system on all airplanes which have not complied with the requirements of paragraph (a) of this AD, in accordance with Part III of Beechcraft Service Bulletin No. 2028, Rev. III, dated February 1987. \n\n\t(d)\tCompliance with paragraph (b) of this AD is no longer necessary after the modification required in paragraph (c) of this AD is accomplished. \n\n\t(e)\tAirplanes may be flown in accordance with FAR 21.197 to a location where the AD may be accomplished. \n\n\t(f)\tAn equivalent means of compliance with this AD may be used, if approved by the Manager, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid- Continent Airport, Wichita, Kansas 67209; Telephone (316) 946-4400. \n\n\tAll persons affected by this directive may obtain copies of the document(s) referred to herein upon request to Beechcraft Aero and Aviation Centers or Beech Aircraft Corporation, Commercial Service Department 52, P.O. Box 85, Wichita, Kansas 67201-0085; or may examine copies of the document(s) referred to herein at the FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. \n\n\tThis AD supersedes AD 86-20-03, Amendment 39-5413. \n\n\tThis amendment becomes effective on April 14, 1987, to all persons except those to whom it has already been made effective by priority letter from the FAA dated February 23, 1987, and is identified as AD 87-04-24. \n\nATTACHMENT 1 - 87-04-24 \n\nOPERATING LIMITATION: \n\n\tThe Elevator Trim System Preflight check procedure, as defined below, must be conducted prior to each flight. \n\n\tTo verify that the elevator trim cable is not fouled or disengaged from the cable drum, the following Elevator Trim System Preflight Check is required prior to each flight of the Beech Model 65-A90, B90, C90, C90A, E90, F90, 200, B200, 200C, B200C, 200CT, B200CT, 200T, B200T, 300, 1900 and 1900C airplanes: \n\nCOCKPIT \n\n\t1.\tControl Locks - REMOVE \n\n\t2.\tElevator Trim: \n\n\t\ta.\tAll airplanes except 1900/1900C - SET TO "O" UNITS \n\n\t\tb.\t1900/1900C airplanes - SET TWO UNITS NOSE UP CAUTION \n\n\t\t\tThe elevator trim system must not be forced past the limits which are indicated on the elevator trim indicator scale either manually, electrically (except Model 300) or by action of the autopilot (except Model 300). \n\nTAIL SECTION \n\n\t1.\tElevator Trim Tab \n\n\t\ta.\tVERIFY "O" (NEUTRAL) POSITION \n\n\t2.\tOn Model 65-A90, B90, C90, C90A and E90 airplanes, the elevator trim tab "O" (neutral) position is determined by observing that the alignment marks on the elevator trim tab pushrods align with the alignment marks on the elevator (See Figure 1 or 2 below), when the elevator is resting against the downstops. \n\n\t3.\tOn Model F90, 200 Series, 300 and 1900/1900C airplanes, the elevator trim tab "O" (neutral) position is determined by observing that the trailing edge of the elevator trim tab aligns with the trailing edge of the elevator, when the elevator, when the elevator is resting against the downstops.\n\n WARNING \n\n\tThe above Preflight Inspection check MUST be repeated prior to take-off if the elevator trim is allowed to reach limit travel at any time prior to take-off as a result of MANUAL, ELECTRICAL (except Model 300) OR AUTOPILOT (except Model 300) OPERATION of the trim system.
99-18-21: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires a one-time inspection of the propeller de-ice system to verify the proper functioning of the engine indication and crew alert system (EICAS) for the de-ice system; and corrective action, if necessary. 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 failure of the EICAS to provide a warning to the flightcrew in the event of failure of the propeller de-ice system, which could result in damage to the airplane and consequent loss of controllability of the airplane.
2019-07-10: We are adopting a new airworthiness directive (AD) for Northrop Grumman LITEF GmbH LCR-100 Attitude and Heading Reference System (AHRS) units installed on various aircraft. This AD requires removing certain LCR-100 AHRS units from service. This AD was prompted by test results showing loss of or invalid data. The actions of this AD are intended to prevent an unsafe condition on these products.
2019-07-06: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by a report that certain split ball bearings used in main landing gear (MLG) side brace actuator assemblies are manufactured from material that does not meet the required material properties. This AD requires an inspection of the left and right MLG side brace actuator assemblies and, if necessary, replacement of the split ball bearings. We are issuing this AD to address the unsafe condition on these products.
89-03-15: 89-03-15 DORNIER: Amendment 39-6130. Applicability: Models Do28 D and Do28 D-1 (all serial numbers) airplanes certificated in any category. Compliance: Required within the next 100 hours time-in-service and every 100 hours time-in-service thereafter after the effective date of this AD, unless already accomplished. To preclude the loss of the horizontal tail, accomplish the following: (a) Visually inspect in accordance with Dornier Service Bulletin No. 1110-3204, dated April 15, 1988, as follows: (1) Inspect the rivet connections between the left hand and right hand horizontal tail bearing fittings and the lateral skins for loose rivets. If loose rivets are found, before further flight replace the loose rivets in accordance with Dornier Service Bulletin No. 1110-3204, and (2) Inspect the rear fuselage frame 10420 and the corner gusset for cracks. If cracks are detected, before further flight repair as follows: (i) For cracks less than 25mm (.98 inch), stop drill the crack in accordance with Dornier Service Bulletin No. 1110-3204. (ii) For cracks 25mm or longer (.98 inch or more), repair the airplane in accordance with instructions from Dornier approved by the Manager, Aircraft Certification Staff, AEU-100. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, B-1000 Brussels, Belgium. All persons affected by this directive may obtain a copy of the document referred to herein upon request to Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, B-1000 Brussels, Belgium; or Dornier GmbH, P.O. Box 2160, D- 8000 Munchen 66, Federal Republic of Germany; or may examine this document at the FAA, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment (39-6130, AD 89-03-15) becomes effective on March 3, 1989.
94-25-03: This amendment adopts a new airworthiness directive (AD) that is applicable to all Fokker Model F28 series airplanes. This action requires a revision to the Airplane Flight Manual that prohibits takeoff in certain icing conditions unless either a tactile inspection is performed or specific takeoff procedures are followed. This amendment is prompted by several accidents in which Fokker Model F28 series airplanes lost aerodynamic lift when attempting takeoff with ice contamination on their wings. The actions specified in this AD are intended to prevent degradation of aerodynamic lift during takeoff when icing conditions exist.
87-12-06: 87-12-06 SIKORSKY AIRCRAFT: Amendment 39-5602. Applies to all Model S-76A/B series helicopters, certified in all categories. Compliance is required within the next 25 hours' time in service unless already accomplished. To prevent possible loss of electrical power due to DC generator ground failure, accomplish the following: (a) Perform inspection to determine the wiring configuration and connections of the GCU. Inspect the ground and power path connections of both generators for corrosion and proper torque, and inspect the ground connections of the GCU to determine their configuration. Modify and repair, as necessary. Accomplish these inspections and modifications in accordance with the Sikorsky Alert Service Bulletin, ASB-76-24-8, dated January 30, 1987. (b) Upon request, with substantiating data, an alternate means of compliance which provides an equivalent level of safety or adjustment in the compliance time may be used when approved by the Manager, Boston Aircraft Certification Office, Aircraft Certification Division, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, MA 01803. These procedures shall be accomplished in accordance with Sikorsky ASB-76-24-8, dated January 30, 1987. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a)(1). Copies may be obtained from Sikorsky Aircraft, 6900 North Main Street, Stratford, Connecticut 06601-1381. Copies may be inspected at the Office of the Regional Counsel, FAA, Southwest Region, 4400 Blue Mound Road, Fort Worth, Texas, or at the Office of the Federal Register, 1100 L Street, NW., Room 8401, Washington, D.C. This amendment becomes effective June 10, 1987.
2019-07-09: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) Trent 1000-A2, Trent 1000-AE2, Trent 1000-C2, Trent 1000-CE2, Trent 1000-D2, Trent 1000-E2, Trent 1000-G2, Trent 1000-H2, Trent 1000-J2, Trent 1000-K2, and Trent 1000-L2 model turbofan engines. This AD was prompted by reports of intermediate-pressure compressor (IPC) rotor seal failures. This AD requires initial and repetitive on-wing borescope inspections (BSIs) of affected IPC rotor seals and removing any cracked parts from service. We are issuing this AD to address the unsafe condition on these products.
2000-02-39: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A300 series airplanes. This action requires either a one-time ultrasonic inspection, or repetitive visual inspections and eventual ultrasonic inspection, to detect cracking of the longitudinal skin splice above the mid-passenger door panels, and corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to detect and correct cracking of the longitudinal skin splice above the mid-passenger door panels, which could result in reduced structural integrity of the fuselage pressure vessel.
86-08-02: 86-08-02 BOEING: Amendment 39-5288. Applies to all Model 747 series airplanes through line number 625, certificated in any category. To prevent structural failure of the vertical fin in the event of failure of the aft pressure bulkhead, accomplish the following within 6 months after the effective date of this AD, unless already accomplished: \n\n\tA.\tInstall the vertical fin access cover in accordance with Boeing Service Bulletin 747-53A2264, dated November 25, 1985, or later FAA-approved revisions. \n\n\tB.\tAn 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, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the modifications required by this AD. \n\n\tAll persons affected by this proposal who have not already received the appropriate service document from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124-2207. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective May 19, 1986.