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89-15-04: 89-15-04 BOEING: Amendment 39-6250. \n\tApplicability: Model 757-200 series airplanes through line number 164, equipped with Pratt and Whitney PW2000 engines, certificated in any category. \n\tCompliance: Required within one year after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent engine in-flight shutdown and engine damage, due to loss of engine oil resulting from cracked oil pressure indicator tube assemblies, accomplish the following: \n\n\tA.\tRemove five oil pressure indication system tube assemblies and replace them with flexible hose assemblies, in accordance with Boeing Service Bulletin 757-79-0005, dated May 26, 1988. \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\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tC.\tSpecial 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. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6250, AD 89-15-04) becomes effective on July 24, 1989.
98-22-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires repetitive inspections to detect fatigue cracking of the lower surface panel on the wing center box; and repair, if necessary. This amendment also requires modification of the lower surface panel on the wing center box, which constitutes terminating action for the repetitive inspections. 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 fatigue cracking of the lower surface panel on the wing center box, which could result in reduced structural integrity of the airplane.
2019-03-29: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by an incident of uncommanded nose wheel steering (NWS) in-service; subsequent investigation revealed that the steering selector valve (SSV) is susceptible to jamming in the open position due to particulate contamination of the hydraulic system. This AD requires modifying the left-hand hydraulic system of the NWS control system and, for certain airplanes, torqueing the [[Page 18705]] fittings on a certain tube assembly. We are issuing this AD to address the unsafe condition on these products.
2006-18-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB-Fairchild SF340A (SAAB/SF340A) and SAAB 340B airplanes, that requires modification and repetitive inspections of the hot detection system of the tail pipe harness of the engine nacelles. The actions specified by this AD are intended to prevent false warning indications to the flightcrew from the hot detection system due to discrepancies of the harness, which could result in an unnecessary aborted takeoff on the ground or in-flight engine shutdowns. This action is intended to address the identified unsafe condition.
87-08-09: 87-08-09 AIRBUS INDUSTRIE, BOEING, BRITISH AEROSPACE, LOCKHEED, AND MCDONNELL DOUGLAS: Amendment 39-5613. Applies to Airbus Industries Models A300 and A310; Boeing Models 707, 720, 727, 737, 747, 757, and 767; British Aerospace Models BAe 146 and BAC 1-11; Lockheed Model L-1011; and McDonnell Douglas Models DC-8, DC-9 (includes MD-80 series), and DC-10; certificated in any category.\n\n\tTo eliminate the possibility of a chemical reaction between atmospheric oxygen and volatile gases from the tire inner liner producing a tire explosion, accomplish the following, unless already accomplished:\n\n\tA.\tWithin 180 days after the effective date of this AD, to ensure that all aircraft tires mounted on braked wheels do not contain more than 5 percent oxygen by volume, accomplish paragraph 1. or 2., below. Either of these procedures is acceptable, or they may be used together:\n\n\t\t1.\tInstall a placard, either in each wheel well or on or near each landing gear strut incorporating braked wheels, and in a location so as to be easily seen and readable by a person performing routine tire servicing. This placard shall state "INFLATE TIRES WITH NITROGEN ONLY." The words "SERVICE" or "FILL" may be substituted for the word "INFLATE".\n\n\t\t2.\tIncorporate into the FAA-approved maintenance program procedures that include the following items: \n\n\t\t\ta.\tOn braked wheels, install only tires that have been inflated with dry nitrogen or other gases shown to be inert such that the gas mixture does not exceed 5 percent oxygen by volume.\n\n\t\t\tb.\tTires on braked wheels may be serviced with air at remote locations where dry nitrogen is not available, provided that:\n\n\t\t\ti.\tthe oxygen content does not exceed 5 percent by volume; or\n\n\t\t\tii.\twithin the next 15 hours time-in-service, the tire must be purged of air and inflated with dry nitrogen so that the oxygen does not exceed 5 percent by volume.\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 (Airbus Industrie, Boeing, and British Aerospace models); or the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region (Lockheed and McDonnell Douglas models).\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 modification required by this AD.\n\n\tThis Amendment becomes effective June 1, 1987.
98-19-18: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A310, A300-600, and A320 series airplanes, that currently requires inspections to verify proper installation of the grill over the air extraction duct of the lavatory and to detect blockages in the air extraction duct of the lavatory, and correction of any discrepancies. This amendment adds a requirement for modification of the grill of the air extraction duct, which, when accomplished, terminates the repetitive inspections. This amendment also expands the applicability of the existing AD to include additional airplanes. 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 obstructions in the air extraction system of the lavatory, which may result in the failure of the smoke detection system to detect smoke in the lavatories.
2019-06-13: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 787 series airplanes. This AD was prompted by reports of hydraulic leakage caused by damage to aileron and elevator actuators from lightning strikes. This AD requires an inspection or records check to inspect for certain parts, detailed inspections of aileron and elevator power control units (PCUs), and applicable on- condition actions. We are issuing this AD to address the unsafe condition on these products.
87-07-04: 87-07-04 MCDONNELL DOUGLAS: Amendment 39-5586. Applies to McDonnell Douglas Model DC-10-10, -10F, -15, -30, -30F, and KC-10A (Military) airplanes, certificated in any category. \n\n\tCompliance required as indicated, unless previously accomplished. \n\n\tTo prevent structural damage to the airplane due to engine core cowl door separation, accomplish the following: \n\n\tA.\tWithin eighteen months after the effective date of this AD, modify the engine core cowl doors by installing a secondary retention system for the engine core cowl doors in accordance with the Accomplishment Instructions of McDonnell Douglas Model DC-10 Service Bulletin 71-142, dated September 26, 1986, or later FAA-approved revision; or in accordance with data approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tB.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles 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 the airplane to a base for accomplish of modifications required by this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-L65 (54-60). These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. \n\n\tThis Amendment becomes effective April 27, 1987.
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.