Results
99-26-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 050 series airplanes. This action requires a one-time inspection to verify the tension values of the aileron control cables of the left- and right-hand wings, and corrective actions, if necessary. This action also requires either replacement of the aileron control cables with new, improved aileron control cables, or replacement of the aileron control cables with new, improved aileron control cables and modification of the pulley bracket on the rear face of the bulkhead at frame station 3100. The FAA is issuing this AD in response to mandatory continuing airworthiness information issued by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent interference between the turnbuckles of the aileron control cables and the lightening holes, which could result in binding of the aileron control cables and consequent reduced controllability of the airplane.
2013-17-04: We are adopting a new airworthiness directive (AD) for various aircraft equipped with Rotax Aircraft Engines 912 A Series Engine. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as oil leaks in the intake channel in the area of the valve guide on some cylinder heads could increase the oil consumption and result in engine stoppage. We are issuing this AD to require actions to address the unsafe condition on these products.
2022-21-11: The FAA is adopting a new airworthiness directive (AD) for certain Bell Textron Inc. Model 204B, 205A, and 205A-1 helicopters and various restricted category helicopters. This AD was prompted by a report of cracked main rotor blades (MRBs). This AD requires repetitive inspections of each MRB and removing any cracked MRB from service. The FAA is issuing this AD to address the unsafe condition on these products.
78-19-01: 78-19-01 ROLLS-ROYCE LIMITED (Formerly Rolls-Royce (1971) Limited): Amendment 39-3297. Applies to Model RB-211-22B engines which have high pressure turbine discs, part number and serial number as indicated, installed. Compliance is required as indicated, unless already accomplished. To ensure adequate life limit margin for, and to prevent failure of the high pressure turbine discs listed herein, accomplish the following: (a) Permanently remove from service the following high pressure turbine discs before or upon reaching the flight cycle life limit shown. Part No. Serial No. Revised Life Limit Flight cycles LK48423 CQDY 107 2900 LK48423 CQDY 140 2900 LK48423 CQDY 130 2900 LK48423 CQDY 133 2900 LK48423 CQDY 134 2900 LK48423 CQDY 233 2900 LK53204 CQDY 334 4350 LK53204 CQDY 345 4350 LK53204 CQDY 389 4350 LK53204 CQDY 417 3500 LK53204 CQDY 419 4350 LK53204 CQDY 426 4350 LK53204 CQDY 427 3500 LK53204 CQDY 436 2500 LK53204 CQDY 449 4350 LK53204 CQDY 540 4350 LK53204 CQDY 578 3000 LK53204 CQDY 579 3000 LK53204 CQDY 581 4350 LK53204 CQDY 583 3500 LK69209 A2 CQDY 592 4350 LK53204 CQDY 624 2900 LK53204 CQDY 625 4350 LK53204 CQDY 627 3500 LK53204 CQDY 630 3600 LK53204 CQDY 631 4350 LK53204 CQDY 655 3500 LK53204 CQDY 702 4350 LK53204 CQDY 703 3500 LK53204 CQDY 712 4350 LK53204 CQDY 730 3500 LK69209 CQDY 740 4350 LK62143 CQDY 757 2250 LK53204 CQDY 770 4350 LK53204 CQDY 771 4350 LK53204 CQDY 805 2400 LK58998 CQDY 958 2250 LK58998 CQDY 964 2250 LK53204 CQDY 965 2250 LK58998 CQDY 976 2250 LK58998 CQDY 989 2250 LK69213 CQDY 996 4360 LK58998 CQDY 998 2250 LK58998 CQDY 1002 1200 LK58998 CQDY 1037 2250 LK58998 CQDY 1076 2250 LK58998 CQDY 1140 2250 NOTE: Rolls-Royce Limited Service Bulletin RB.211-72-4300, Revision 3, dated May 12, 1978, pertains to this same subject. (b) Permanently remove from service the following high pressure turbine discs before or upon reaching 2900 flight cycles: Part No. Serial No. LK53203 CQDY 241 LK48424 CQDY 242 LK53203 CQDY 257 LK53195 CQDY 309 LK53204 CQDY 428 LK53204 CQDY 657 LK53204 CQDY 678 LK53204 CQDY 697 LK53204 CQDY 773 LK53204 CQDY 951 LK69210 CQDY 1227 LK69210 CQDY 1419 NOTE: Rolls-Royce Limited Service Bulletin RB.211-72-4304, Revision 2, dated June 3, 1977, pertains to this same subject. (c) In accordance with the provisions of FAR 21.197 and FAR 21.199 the aircraft may be flown to a base where the disc removals required by this AD may be performed. NOTE: For the purpose of this AD a flight cycle is considered to be an operating sequence consisting of engine starting, takeoff operation, landing and engine shutdown. This amendment becomes effectiveSeptember 25, 1978.
2022-18-11: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 777 airplanes. This AD was prompted by a report of a crack found in a front spar lower chord undergoing an underwing longeron replacement. This AD requires repetitive inspections for cracking of the left and right side ring chords, repair angles, front spar lower chords, and front spar webs (depending on configuration) common to the underwing longeron located at station (STA) 1035; modification of the front spar lower chord for some airplanes; repetitive post-modification inspections; and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2004-20-10: The FAA adopts a new airworthiness directive (AD) for all Valentin GmbH & Co. Taifun 17E sailplanes. This AD requires you to do an operational check of the front wing-locking mechanism left and right, inspect stop key movement, inspect wing and fuselage side root ribs, inspect the wing side shear force fittings, and take any corrective actions that may be required. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to detect and correct malfunction of wing-locking mechanism, which could result in failure of the wing-locking mechanism disengagement. This failure could lead to unlocking of wing in flight and consequent loss of control of the sailplane.
2022-19-04: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-2C series airplanes. This AD was prompted by a report that insufficient clearance was found between the right stabilizer trim shut-off control wire (bundle W0589) and an elevator control cable. This AD requires a one-time inspection for insufficient clearance between the elevator control cable and wire bundle W0589 on the airplane's left crown, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2013-17-03: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200 and -300 series airplanes; Model A340-200 and - 300 series airplanes; and Model A340-541 and -642 airplanes. This final rule was prompted by reports of wing tip brakes (WTBs) losing their braking function in service due to heavy wear on the brake discs. WTBs are designed to stop and hold the mechanical transmission of slats and flaps in certain failure cases. This final rule requires repetitive operational tests of certain WTB pressure-off-brakes (POBs) for performance on the flap and slat systems, and replacement of any affected WTB with a new or serviceable part if the test fails. This final rule also requires eventual replacement of all affected WTBs with a new part, which terminates the repetitive tests. We are issuing this final rule to prevent loss of the WTB braking function, and consequent inability of the flap or slat system to be stopped and held in [[Page 53636]] position during operation, which could result in loss of control of the airplane.
2004-20-14: This amendment supersedes an existing airworthiness directive (AD), applicable to all Airbus Model A300 B4 series airplanes and all Airbus Model A300-600 series airplanes. That AD currently requires a one-time high frequency eddy current inspection to detect cracking of the splice fitting at fuselage frame (FR) 47 between stringers 24 and 25; and corrective actions if necessary. This amendment requires new repetitive inspections of an expanded area and adds airplanes to the applicability in the existing AD. The actions specified by this AD are intended to detect and correct cracking of the splice fitting at fuselage FR 47, which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
77-21-07: 77-21-07 MESSERSCHMITT-BOLKOW-BLOHM (MBB): Amendment 39-3061. Applies to Model BO-105A and BO-105C helicopters, Serial Number V4 through V10, and S1 through S160, certificated in all categories. Compliance required within the next 600 hours time in service after the effective date of this AD, unless already accomplished. Remove socket connections 1 VED and 1 VEE from main relay box, remove plugs 110 VVa and 210 VVa together with associated receptacles and wiring bundles, and install generator wiring assembly, in accordance with subparagraph 2B of MBB Service Bulletin No. 90-11 dated April 17, 1975, or an FAA-approved equivalent. This amendment becomes effective November 14, 1977.
2022-19-13: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters. This AD was prompted by the identification of certain parts needing maintenance actions, including life limits and maintenance tasks. This AD requires incorporating into existing maintenance records requirements (airworthiness limitations), as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2022-20-06: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A320-251N, -253N, and -271N airplanes; and Model A321-251N, -253N, -271N, and -272N airplanes. This AD was prompted by the failure of an electronic centralized aircraft monitor (ECAM) warning to be triggered during heating of several sensing elements of the over-heat detection system (OHDS) loop sequentially during flight test operation procedures. This AD requires revising the existing airplane flight manual (AFM) with an AFM Temporary Revision (TR) to provide procedures to operate the airplane without functioning bleed leak detection; revising the operator's existing FAA-approved minimum equipment list (MEL); and modifying the electrical connections of the bleed monitoring computers (BMCs), which allows for the removal of the AFM TR and the MEL revision; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2022-19-01: The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) GEnx-2B67/P model turbofan engines. This AD was prompted by the detection of an iron inclusion in a forging, which may reduce the fatigue life of certain low-pressure turbine rotor (LPTR) stage 4 disks and LPTR stage 6 disks. This AD requires the removal of certain LPTR stage 4 disks and LPTR stage 6 disks from service and replacement with parts eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
2004-20-11: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A300 B2 and B4 series airplanes; and certain Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes; and Model C4-605R Variant F airplanes (collectively called A300-600). This AD requires an inspection of the skin panels of the wing slats for damage and certain repairs, and applicable related investigative/corrective actions if necessary. This AD is prompted by the results of an engineering evaluation that revealed that several repairs and some allowable damage limits specified in the structural repair manuals do not provide adequate static and/or fatigue strength for repaired wing slats. We are issuing this AD to find and fix previously done repairs of the wing slats that have inadequate static and/or fatigue strength, which, if not corrected, could result in loss of the slats and consequent reduced controllability of the airplane.
2013-16-22: We are adopting a new airworthiness directive (AD) for certain Embraer S.A. Model ERJ 170 and ERJ 190 airplanes. This AD was prompted by reports of chafing between the auxiliary power unit (APU) electronic starter controller (ESC) power cables and the airplane tail cone firewall. This AD requires a detailed inspection for damage to the insulation and inner conductors of the APU ESC power cables, installing a new grommet support in the tail cone firewall, and corrective actions if necessary. We are issuing this AD to detect and correct damage to the APU ESC power cable harness, which if not corrected, could result in reduced structural integrity of the fuselage and empennage in the event of fire penetration through the firewall.
2013-14-08: We are adopting a new airworthiness directive (AD) for all Austro Engine GmbH model E4 engines. This AD requires removing from service certain part number waste gate controllers. This AD was prompted by several reports of power loss events due to fracture of the waste gate controller lever. We are issuing this AD to prevent engine power loss or in-flight shutdown, which could result in loss of control and damage to the airplane.
2022-19-08: The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Model SA341G and SA342J helicopters. This AD was prompted by a report of manufacturing defects on multiple tail rotor blades (TRBs). This AD requires visually inspecting certain part- numbered TRBs for the presence of a linear indication; and depending on the inspection results, fluorescent penetrant inspecting the TRB and further corrective actions if necessary. This AD also prohibits installing an affected TRB unless certain requirements have been met, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
96-23-19: This amendment adopts a new airworthiness directive (AD) that applies to certain Air Tractor, Inc. (Air Tractor) Models AT-300, AT-400, and AT-500 series airplanes. This AD requires installing both a new flap actuator overtravel stop and a roll pin through the overtravel stop and jack screw. This AD results from incidents where the flap actuator overtravel stop nut disengaged from the jack screw. The flap pushrod pressed against the aileron pushrod, which caused difficulty in moving the ailerons. The actions specified by this AD are intended to prevent interference between the flap pushrod and the aileron pushrod caused by the flap actuator overtravel nut disengaging, which could result in loss of aileron control.
90-20-06: 90-20-06 BOEING: Amendment 39-6748. Docket No. 90-NM-89-AD. \n\n\tApplicability: Model 757 series airplanes, equipped with Arkwin Industries Incorporated part number (P/N) 1211233-005 ram air turbine deployment actuators with serial numbers 213 through 285, certificated in any category. \n\n\tCompliance: Required within the next 3,000 hours time-in-service after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent loss of hydraulic power due to failure of the ram air turbine to deploy in the event of dual engine failure, accomplish the following: \n\n\tA.\tReplace the ram air turbine deployment actuator in accordance with Arkwin Industries Incorporated Service Bulletin 1211233-29-02, dated July 25, 1989. \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 (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be submitted directly to the Manager, Seattle ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Seattle ACO. \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 Airplane Group, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. \n\n\tThis amendment (39-6748, AD 90-20-06) becomes effective on October 29, 1990.
2004-20-15: This amendment supersedes an existing airworthiness directive (AD), applicable to all Dornier Model 328-100 series airplanes, that currently requires certain revisions to the airplane flight manual, replacement of certain de-icing boots in the air intake duct assemblies of the engine with re-designed units, repetitive inspections of the boots to find discrepancies, and corrective action if necessary. This amendment also requires modification of the engine air inlet de-icing system. This action extends the repetitive inspection interval required by the existing AD, and adds repetitive debonding/delamination and leakage inspections of the de-icing boots, and corrective action if necessary. Initiation of the extended repetitive inspections and new repetitive inspections ends the repetitive inspections required by the existing AD. The actions specified by this AD are intended to prevent engine malfunction due to failure of the engine air inlet de-icing system, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2022-18-12: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-841 and -941 airplanes. This AD was prompted by a report of erroneous electronic centralized airplane monitoring (ECAM) warnings for low engine oil pressure, which can lead to a commanded shutdown of an engine. This AD requires installing serviceable engine electronic control (EEC) software or EEC units having the serviceable software, limiting certain parts installation configurations, and prior or concurrent modification of EEC software, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
90-16-05: 90-16-05 MCDONNELL DOUGLAS: Amendment 39-6614. Docket No. 89-NM-196-AD. \n\n\tApplicability: Model DC-8 series airplanes, as listed in McDonnell Douglas Report No. MDC K1579, Revision A, dated March 1, 1990, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent structural failure, accomplish the following: \n\n\tA.\tWithin one repetitive inspection interval specified in the service bulletins listed in Table 2.1 of "DC-8 Aging Aircraft Service Action Requirements Document", McDonnell Douglas Report MDC K1579, Revision A, dated March 1, 1990 (hereinafter referred to as "The Document") after the effective date of this AD, or at the inspection threshold specified in McDonnell Douglas Report No. MDC K1579, Revision A, dated March 1, 1990, whichever is later (unless currently being accomplished), begin performing inspections for cracks in accordance with the service bulletins listed in Table 2.1 of The Document. Repeat these inspections at intervals specified in the applicable service bulletins listed in Table 2.1 of The Document. \n\n\t\t1.\tIf cracks are found during any inspection, prior to further flight, either accomplish the terminating modification in accordance with the applicable service bulletin, or repair in accordance with data approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: Detection of discrepancies other than cracking necessitates appropriate corrective action in accordance with the provisions of Part 43 of the Federal Aviation Regulations (FAR). \n\n\t\t2.\tModification in accordance with paragraph B. of this AD terminates individual inspection requirements of the applicable service bulletin. \n\n\tB.\tExcept as provided below, prior to reaching the incorporation thresholds listed in The Document or within 4 years after the effective date of this AD, whichever occurs later, accomplish the structural modifications in accordance withthe service bulletins listed in The Document. Modifications whose time for accomplishment is specified in The Document by a calendar date must be accomplished by that date in lieu of the 4 years specified in this paragraph. \n\n\tNOTE: The modification required by this paragraph does not terminate the inspection requirements of any other AD unless that AD specifies that any such modification constitutes terminating action for the inspection requirements. \n\n\tC.\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, Los Angeles 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, Los Angeles Aircraft Certification Office. \n\n\tD.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 tooperate airplanes to a base in order to comply with the requirements of this AD. \n\n\tThe inspections and modifications shall be done in accordance with "DC-8 Aging Aircraft Service Action Requirements Document," McDonnell Douglas Report MDC K1579, Revision A, dated March 1, 1990, which incorporates the following list of effective pages: \n\n\nPage Number\t\t\nRevision\nDate \ni\t \n A\t\nMarch 1, 1990 \nii\t\nOriginal\t\nSeptember 12, 1989 \niii - vii\t \t\nA\nMarch 1, 1990 \n1 - 4\t\nOriginal\t\nSeptember 12, 1989 \n5 - 12\t \t\n A\nMarch 1, 1990 \n13\t\nOriginal\t\nSeptember 12, 1989 \n14 - 18\t \t\n A\nMarch 1, 1990 \n19\t \n Original\t\nSeptember 12, 1989 \n20 - 21\t \n A\t\nMarch 1, 1990 \n\t\t\t\t\nThis 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 McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846-0001, Attention: Director, Publication and Training, C1-750 (54-60). Copies may be inspected at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington; or at the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California; or at the Office of the Federal Register, 1100 L Street, N.W., Room 8301, Washington, D.C. \n\n\tThis amendment (39-6614, AD 90-16-05) becomes effective on September 10, 1990.
91-10-01: 91-10-01 COLLINS: Amendment 39-8002. Docket No. 91-CE-42-AD. \n\n\tApplicability: All aircraft equipped with the Traffic Alert and Collision Avoidance (TCAS) II (or 94) systems that are installed in, but not limited to, the following aircraft, certificated in any category: Boeing 727, 727C, 727-100/100C/200/200F airplanes; Boeing 747-100, 200, SR, SP airplanes; McDonnell Douglas DC9-81/82/83/87 and MD-88 airplanes; Aerospatialle ATR42-200/300 airplanes; Lockheed L1011-385-1 airplanes; DeHavilland DHC-7 airplanes; Saab SF340A/B airplanes; and Shorts Brothers SD3-60 airplanes. \n\n\tCompliance: Required as indicated, unless already accomplished. \n\n\tTo prevent altitude deviations, which could result in unnecessary pilot/controller communication and controller distraction, accomplish the following: \n\n\t(a)\tWithin the next 25 hours time-in-service (TIS) after the effective date of this AD, unless already accomplished (priority letter AD 91-10-01), accomplish the following: \n\n\t\t(1)\tPull and band the circuit breaker that applies electrical power to the TCAS II (or 94) system. \n\n\t\t(2)\tFabricate a placard with the following words in 1/8 inch high letters: "TCAS II Inoperative" or "TCAS 94 Inoperative" as appropriate. Install this placard adjacent to the TCAS control unit within the pilot's clear view and operate the aircraft accordingly. \n\n\t(b)\tReactivation of the TCAS II (or 94) system must be accomplished after modification of the Collins TTR-920 Computer in accordance with Collins Service Bulletin (SB) C, dated April 24, 1991, or No. 7, dated April 4, 1991, whichever is applicable, or Collins SB C, Revision 1, or SB No. 7, Revision 1, both dated May 20, 1991, whichever is applicable. This reactivation must be accomplished in accordance with a schedule acceptable to the administrator. \n\n\t(c)\tWithin the next 30 days after the effective date of this AD, unless already accomplished (priority letter AD 91-10-01), the airlines operating the aircraft affectedby this AD must submit to the FAA for approval, a schedule for reactivation of the TCAS II (or 94) system. \n\n\t(d)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate aircraft to a location where the requirements of this AD can be accomplished. \n\n\t(e)\tAn alternative method of compliance or adjustment of the compliance times that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita Aircraft Certification Office. \n\n\t(f)\tThe modification required by this AD shall be done in accordance with Collins Service Bulletin (SB) C, dated April 24, 1991, or Collins SB No. 7, dated April 4, 1991, whichever is applicable; or whichever of the following two revised service bulletins that is applicable: SB C, Revision 1, which incorporates the following pages: \n\n\nPages\nIssue Level\nDate\n4 and 5\nRevision 1\nMay 20, 1991\n1, 2, 3 and 6\nOriginal\nApril 24, 1991\n\nor Collins SB No. 7, Revision 1, which incorporates the following pages:\n\n\nPages\nIssue Level\nDate\n1, 4 and 8\nRevision 1\nMay 20, 1991\n2, 3, 5, 6, 7, and 9 through 34\nOriginal\nApril 4, 1991 \n\nThis 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 Rockwell International, Avionics Group, 400 Collins Road, NE; Cedar Rapids, Iowa 52498. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW, Room 8401, Washington, DC. \n\n\t(g)\tThis amendment (39-8002) supersedes Priority Letter AD 91-10-01. \n\n\t(h)\tThis amendment (39-8002, AD 91-10-01) becomes effective on March 10, 1992.
99-25-03: This amendment supersedes two airworthiness directives (ADs) that apply to International Aero Engines AG (IAE) V2500-A1 series turbofan engines. The first superseded AD, AD 98-20-18, currently requires removal from service of affected high pressure turbine (HPT) disks, identified by part number and serial number in the applicability paragraph of that AD, and replacement with a serviceable part. The second superseded AD, AD 99-05-05, requires initial and repetitive inspections of certain HPT stage 1 and stage 2 disks utilizing an improved ultrasonic method when the disks are exposed during a normal shop visit, and if a subsurface anomaly is found, removal from service and replacement with a serviceable part. This supersedure requires the initial inspection mandated by AD 99-05-05 to be completed at the next shop visit regardless of the planned maintenance or the reason for shop removal. The repetitive inspection interval is redefined to eliminate the cyclic limit and thusbe less restrictive. This superseding action is prompted by results from investigations subsequent to the publication of AD 98-20-18 that have revealed that the HPT disks affected by that AD are part of the population addressed by AD 99-05-05. These HPT disks can be safely reintroduced into service after completing the initial inspection requirements mandated by this proposed AD. This supersedure is also prompted by further analysis that indicates a reduction in risk if the initial inspection required by AD 99-05-05 is completed sooner and the subsequent required inspections can be redefined to eliminate the cyclic limit, thereby creating less burden on operators. The actions specified by this AD are intended to prevent HPT disk fracture, which could result in an uncontained engine failure and damage to the airplane.
92-14-04: 92-14-04 FOKKER: Amendment 39-8286. Docket No. 91-NM-211-AD. Applicability: Model F-28 Mark 0100 series airplanes; serial numbers 11244, 11245, 11250 through 11256, inclusive, and 11268 through 11273, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural capability of the vertical stabilizer, accomplish the following: (a) For airplanes having serial numbers 11244, and 11250 through 11256, inclusive: Prior to the accumulation of 6,500 landings, or within 60 days after the effective date of this AD, whichever occurs later, disassemble the vertical stabilizer in accordance with Part 1, Steps A. through C., of Fokker Service Bulletin SBF100-55-011, dated October 1, 1991. (1) For airplanes that have accumulated 3,000 or fewer landings at the time the airplane is disassembled to comply with paragraph (a) of this AD, modify the vertical stabilizer, in accordance with Part 1, Steps E. through G., of the service bulletin. (2) For airplanes that have accumulated more than 3,000 landings at the time the airplane is disassembled to comply with paragraph (a) of this AD, inspect the rivet holes for cracks, in accordance with Part 1, Step D., of the service bulletin. (i) If no cracks are found, or if cracks are found that are less than 0.8 mm in length, modify the vertical stabilizer, in accordance with Part 1, Steps E. through G., of the service bulletin. (ii) If any crack is found that is 0.8 mm or longer, prior to further flight, repair in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (b) For airplanes having serial numbers 11245, and 11268 through 11273, inclusive: Prior to the accumulation of 6,500 landings, or within 60 days after the effective date of this AD, whichever occurs later, disassemble the vertical stabilizer in accordance with Part 2, Steps A. through C., of Fokker Service Bulletin SBF100-55-011, dated October 1, 1991. (1) For airplanes that have accumulated 3,000 or fewer landings at the time the airplane is disassembled to comply with paragraph (b) of this AD, modify the vertical stabilizer, in accordance with Part 2, Steps E. through G., of the service bulletin. (2) For airplanes that have accumulated more than 3,000 landings at the time the airplane is disassembled to comply with paragraph (b) of this AD, inspect the rivet holes for cracks, in accordance with Part 2, Step D., of the service bulletin. (i) If no cracks are found, or if cracks are found that are less than 0.8 mm in length, modify the vertical stabilizer, in accordance with Part 2, Steps E. through G., of the service bulletin. (ii) If any crack is found that is 0.8 mm or longer, prior to further flight, repair 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. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Standardization Branch. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (e) The inspections and modifications shall be done in accordance with Fokker Service Bulletin SBF100-55-011, dated October 1, 1991. 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 Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. (f) This amendment becomes effective on August 18, 1992.