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89-04-06 R1: 89-04-06 R1 FOKKER: Amendment 39-6143 as revised by Amendment 39-6405. Applicability: Model F-27 series airplanes, Serial Numbers 10102 through 10307, 10308 through 10340, and 10342 through 10360, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent engine separation and subsequent structural damage to the airplane aft of the engine, accomplish the following: A. For airplanes listed in Fokker Service Bulletin F27/54-44, dated July 7, 1988: Within 60 days after March 28, 1989 (the effective date of AD 89-04-06, Amendment 39-6143), inspect both the right and left upper nacelle brace struts, in accordance with Fokker Service Bulletin F27/54-44, dated July 7, 1988. If any brace strut is found with a self-tapping screw, prior to the accumulation of 30,000 landings on the strut, or within the next 500 landings from May 27, 1989, whichever occurs later, replace the brace strut in accordance with the referenced service bulletin. B. For airplanes Serial Numbers 10308 through 10340 and 10342 through 10360: Within 60 days after the effective date of this amendment, inspect both the right and left upper nacelle brace struts, in accordance with Fokker Service Bulletin F27/54-44, Revision 1, dated May 19, 1989. If any brace strut is found with a self-tapping screw, prior to the accumulation of 30,000 landings on the strut, or within the next 500 landings after the effective date of this amendment, whichever occurs later, replace the brace strut in accordance with the referenced service bulletin. C. An 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, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: 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, Standardization Branch, ANM-113. D. 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. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Fokker Aircraft USA, Inc., 1199 N. Fairfax Street, Alexandria, Virginia 22314. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. The AD revises Amendment 39-6143, AD 89-04-06, which became effective on March 28, 1989. This amendment (39-6405, AD 89-04-06 R1) becomes effective on January 3, 1990.
2020-20-08: The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS332C, AS332C1, AS332L, AS332L1, AS332L2, and EC225LP helicopters. This AD requires, depending on helicopter configuration, installing skived polytetrafluoroethylene tape (PTFE tape) or removing PTFE tape and replacing window seals. This AD also prohibits the installation of a jettisonable cabin window unless the applicable requirements are accomplished. This AD was prompted by a report of excessive friction between the window seal and the helicopter airframe. The actions of this AD are intended to address an unsafe condition on these products.
59-06-01: 59-06-01 AERO COMMANDER: Applies to Model 500, Serial Numbers 618 Through 724 Except 700 and 718. Compliance required as indicated. I. Inspection. Within the next five hours of flight unless previously accomplished, inspect each elevator front spar in the area of the outboard hinge brackets for cracks. The elevator outboard hinge brackets must be removed for this inspection. If no cracks are found, the horizontal stabilizer must be modified as outlined in Item II. If any cracks are found in the elevator front spar, the spar must be reworked as outlined in Item III and the horizontal stabilizer must be modified as outlined in Item II. II. Modification. The horizontal stabilizer will be modified by installation of lead weights on the horizontal stabilizer front spars by incorporating Aero Design Company Kit No. Service Bulletin 57 or an equivalent approved modification. Modification of aircraft without elevator spar cracks will be accomplished within 25 flight hours, but not later than May 1, 1959. Modification of aircraft with elevator spar cracks will be accomplished immediately. III. Rework. If cracks are present, contact the Service Department, Aero Design and Engineering Company, Post Office Box 118, Bethany, Oklahoma, for rework of the elevator front spars. (Modification instructions are contained in Aero Design Service Bulletin No. 57. Rework of the elevator front spars is covered by Aero Design Salvage E.O. No. 5440000.) This Airworthiness Directive supersedes the FAA telegraphic instruction of March 12, 1959.
72-07-08: 72-07-08 GRUMMAN: Amdt. 39-1419. Applies to all Model G-159 Airplanes certificated in all categories. Compliance required as indicated unless already accomplished. To prevent jamming of the main landing gear drag brace assembly, P/N 159L10003, accomplish the following: (a) For airplanes having been inspected and modified, if necessary, in accordance with Grumman Customer Bulletin Number 99 or 217 within the last 50 hours time in service, comply with paragraph (e) below within the next 50 hours time in service after the effective date of this AD. (b) For all airplanes incorporating a new drag brace lower bearing, P/N 159LM10011-3 or -5, within the last 100 hours time in service, comply with paragraph (e) below within the next 15 hours time in service after the effective date of this AD. (c) Airplanes having been inspected and modified, if necessary, in accordance with Grumman Customer Bulletin 217A have met the requirements of this AD. (d) All airplanes that do not meet the requirements set forth in paragraphs (a), (b), or (c) above, must comply with paragraph (e) below within the next 15 hours time in service after the effective date of this AD. (e) (1) Inspect the following areas of the main landing gear drag brace assembly in accordance with Grumman Customer Bulletin 217A dated February 18, 1972 or later FAA approved revision: (a) Inner cylinder, P/N 159LM10001, for wear and galling; (b) The lower bearing, P/N 159LM10011, for wear and proper wall thickness; (c) The down lock, P/N 159LM10007, for the presence of a .030 + 010 inch radius on the 2.735 inch major diameter. (2) If bearing wear or improper wall thickness is found, before further flight, replace with a P/N 159LM10011-7 bearing. (3) If the down lock radius is absent, or if wear or galling of the inner cylinder is noted, before further flight, rework in accordance with Grumman Customer Bulletin 217A. (f) Airplanes requiring any action under sub-paragraph (e)(2) or (e)(3) above, may be flown with the landing gear in the down and locked position in accordance with FAR 21.197 to a base where the repair or modification can be accomplished. This amendment becomes effective March 30, 1972.
2020-22-12: The FAA is adopting a new airworthiness directive (AD) for certain Polskie Zaklady Lotnicze Sp. z o.o. Model PZL M28 05 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as defective thermo-shrinkable tubes installed on the electrical harnesses located in the fuel tanks. This AD requires a one-time inspection of the electrical harnesses located in the fuel tanks and, depending on findings, replacement of the affected harness. The FAA is issuing this AD to address the unsafe condition on these products.
2006-12-06: The FAA is adopting a new airworthiness directive (AD) for certain Boeing transport category airplanes. This AD requires inspecting to determine if certain galleys and closets are installed, and replacing the spiral wire wrapping of the electrical cables of the galleys and closets with new spiral wire wrapping if necessary. This AD results from testing and reports from the manufacturer indicating unacceptable flammability properties of wire wrapping installed in certain galleys and closets. We are issuing this AD to prevent fire propagation or smoke in the cabin area due to electrical arcing or sparking and ignition of the spiral wire wrapping.
2006-11-17: This amendment adopts a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model AS350B, BA, B1, B2, B3, C, D, and D1 helicopters that have a Geneva Aviation, Inc. (Geneva) P132 console (console) installed. This AD requires installing right and left side Geneva cyclic control sticks and modifying the cyclic grips and the co- pilot cyclic stand (receptacle). This amendment is prompted by reports that pilots had restricted cyclic stick travel when using Eurocopter factory-installed cyclic sticks in a helicopter modified under a certain Supplemental Type Certificate (STC) for the installation of a Geneva P132 console. The actions specified by this AD are intended to prevent restricting full lateral movement of the cyclic control during high lateral center of gravity (CG) load operations in high cross winds and during slope takeoffs or landings and subsequent loss of control of the helicopter.
73-13-06: 73-13-06 HAWKER SIDDELEY: Amdt. 39-1671. Applies to Hawker Siddeley deHavilland Model DH-114 "Heron" Airplanes, having Modifications 496 installed. Compliance is required as indicated. To prevent possible inadvertent actuation of aileron and rudder trim in a direction other than that desired and to prevent possible interference by the aileron trim jack with the aileron when in its full down position, accomplish the following: Prior to September 21, 1973, unless already accomplished, incorporate Hawker Siddeley Modifications Nos. 1006 and 1053, or FAA-approved equivalents. This amendment becomes effective June 23, 1973.
95-19-13: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model BAe 146-100A, -200A, and -300A airplanes, that requires repetitive inspections for cracking of fuselage frame 29, and repair, if necessary. This amendment is prompted by testing that revealed fatigue cracking in the web and inboard flange of frame 29. The actions specified by this AD are intended to prevent reduced structural integrity of the fuselage due to fatigue cracking in frame 29.
2018-11-10: We are superseding Airworthiness Directive (AD) 2017-01-07, which applied to all Dassault Aviation Model FAN JET FALCON airplanes; Model FAN JET FALCON SERIES C, D, E, F, and G airplanes; Model MYSTERE- FALCON 200 airplanes; Model MYSTERE-FALCON 20-C5, 20-D5, 20-E5, and 20- F5 airplanes; and Model MYSTERE-FALCON 50 airplanes. AD 2017-01-07 required a functional test or check of the main entry door closure and warning system, and applicable door closing inspections, adjustments, operational tests, and corrective actions if necessary. This AD requires repetitive door closing inspections, adjustments, operational tests, and corrective actions if necessary. This AD was prompted by a report indicating that during approach for landing, the main entry door detached from an airplane. We are issuing this AD to address the unsafe condition on these products.
2018-11-03: We are adopting a new airworthiness directive (AD) Airbus Helicopters Model SA-365C, SA-365C1, and SA-365C2 helicopters. This AD requires establishing a life limit of 2,000 hours time-in-service (TIS) for the Starflex star/mast connecting bolt (bolt) and removing from service each bolt that exceeds its life limit. This AD is prompted by the discovery that the bolt's life limit was not included in helicopter maintenance records. The actions of this AD are intended to prevent an unsafe condition on these products.
2006-11-14: This amendment adopts a new airworthiness directive (AD) for the specified Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters. This action requires inspecting each main transmission assembly mounting bolt (bolt) for wear or corrosion, and if wear or corrosion is found, replacing the bolt, bolt barrel nut, and cage. This amendment is prompted by a report of a failure of a bolt that was discovered during a routine maintenance inspection. The actions specified in this AD are intended to prevent failure of a bolt, which could result in loss of support of the main transmission and subsequent loss of control of the helicopter.
2006-11-15: The FAA is adopting a new airworthiness directive (AD) for all EMBRAER Model ERJ 170 and Model ERJ 190 airplanes. This AD requires revising the Limitations section of the airplane flight manual to prohibit the flightcrew from moving the throttle into the forward thrust range immediately after applying the thrust reverser. This AD results from a report that, during landing, the thrust reverser may not re-stow completely if the throttle lever is moved into the forward thrust range immediately after the thrust reverser is applied. We are issuing this AD to prevent the flightcrew from performing a takeoff with a partially deployed thrust reverser, which could result in reduced controllability of the airplane.
47-06-06: 47-06-06 GLOBE: (Was Mandatory Note 9 of AD-766-5.) Applies to Models GC-1A and GC-1B Aircraft Serial Numbers 3 to 408 Inclusive; 1001 to 1460 Inclusive; and 2001 to 2329 Inclusive. Compliance required prior to April 1, 1947. Cut off the egress end of the engine breather line to terminate the line 1-inch above the grill opening. This will prevent clogging of the line due to formation of ice during cold weather operation or the entry of foreign matter caused by the propeller blast. (Globe Customer Service Maintenance Bulletin No. 11 covers this same subject.)
2020-21-23: The FAA is adopting a new airworthiness directive (AD) for Pilatus Aircraft Ltd. Models PC-12, PC-12/45, PC-12/47, and PC-12/47E airplanes. This AD was prompted by 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 improperly manufactured horizontal stabilizer rear attachment bolts. If not corrected, this could lead to fatigue failure of the bolts and loss of airplane control. The FAA is issuing this AD to address the unsafe condition on these products.
68-19-01: 68-19-01 SIAI-MARCHETTI: Amendment 39-653. Applies to Model S.205-22/R airplanes, Serial Nos. 213, 370, 371, 372, 373, 374, 378, 379, 380, 381, 382, 384, 385, 387, 388, 389, 390, 392, 393, 394, 395, 396, 398, 4-124, 4-125. Compliance required within the next 100 hours' time in service after the effective date of this AD unless already accomplished. Modify the limitation markings on the suction gage instrument, Siai P/N NS5F017, located on the right side of the instrument panel, by marking a green arc in the range from 4 inches Hg. to 5 inches Hg. and a red radial line at 5 inches Hg. and adjust the instrument's suction relief valve so that the suction gage reading is 4.5 + 0.1 inches Hg. at 2200 r.p.m., in accordance with Siai-Marchetti Service Bulletin No. 205B21 dated May 6, 1968, or later RAI-approved issue, or an FAA-approved equivalent. Check to insure that the suction gage reading does not exceed 5 inches Hg. at maximum engine r.p.m. This amendment becomes effectiveOctober 11, 1968.
2006-11-11: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 757 series airplanes. That AD currently requires revising the Airworthiness Limitations section of the maintenance manual (757 Airworthiness Limitations Instructions (ALI)) to incorporate certain inspections and compliance times to detect fatigue cracking of principal structural elements (PSEs). This new AD requires incorporating a new revision to the Airworthiness Limitations section of the Instructions of Continued Airworthiness to mandate certain repetitive inspections for fatigue cracking of PSEs, and adds airplanes to the applicability in the existing AD. This AD results from a new revision to the ALI. We are issuing this AD to ensure that fatigue cracking of various PSEs is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes.
97-02-04: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300, A300-600, A310, and A320 series airplanes, that currently requires an inspection of the landing gear brakes for wear, and replacement if the specified wear limits are not met. That AD also requires incorporation of the specified wear limits into the FAA-approved maintenance inspection program. This amendment requires that certain wear limits that are dependent on brake stack weight be used in conjunction with specified brake stack weights, and that maximum allowable brake wear limits for additional brake units be incorporated into the FAA-approved maintenance program. This amendment is prompted by a report that some brakes that are subject to the requirements of the existing AD have not been removed from service and by the determination of the maximum allowable brake wear limits for additional brake unit part numbers. The actions specified by this AD are intended to prevent the loss of brake effectiveness during a high energy rejected takeoff.
2018-11-07: We are adopting a new airworthiness directive (AD) for all Saab AB, Saab Aeronautics Model SAAB 2000 airplanes. This AD requires a one-time inspection of the aileron bellcrank support brackets and a thickness measurement of the affected lug attaching the support bracket; repetitive inspections of the affected aileron bellcrank support brackets; and corrective actions if necessary. This AD also provides an optional terminating action for the repetitive inspections. This AD was prompted by the identification of a manufacturing defect on certain aileron bellcrank support brackets that resulted in the material thickness of the affected lug attaching the support bracket to the rear spar of the wing to be insufficient. We are issuing this AD to address the unsafe condition on these products.
2018-11-05: We are superseding Airworthiness Directive (AD) 2018-06-10 for certain Honda Aircraft Company LLC Model HA-420 airplanes. AD 2018-06- 10 required incorporating a temporary revision into the airplane flight manual and replacing faulty power brake valves upon condition. This AD retains the actions required in AD 2018-06-10 and adds airplanes to the Applicability section. This AD was prompted by an inadvertent mistake in the serial number applicability (both in the service bulletin and in the AD). We are issuing this AD to address the unsafe condition on these products by correcting the inadvertent serial number error.
90-12-01: 90-12-01 EMBRAER: Amendment 39-6740. Final Rule of priority letter. Docket No. 90-CE-31-AD. Applicability: Models EMB-110P1 and EMB-110P2 (all serial numbers) airplanes equipped with the 10 degree dihedral stabilizer (as original equipment or as an added modification per EMBRAER Service Bulletin 110-55-022), certificated in any category. Compliance: Required as indicated in the body of the AD, unless already accomplished. To prevent failure of the inboard elevator mass balance arms and possible extreme vibration or flutter, resulting in possible loss of the airplane, accomplish the following: (a) Within the next 10 hours time-in-service (TIS) after the effective date of this AD, dye-penetrant inspect for cracks the areas of the elevator balance weight arms indicated in EMBRAER Alert Service Bulletin 110-027-A088, dated May 10, 1990, and visually inspect for cracks the remaining areas of the arms using a 10x glass for both elevator balance weight arms (Part Number (P/N) 110-3012-01-01 (left) or 110-3012-01-07 (left), and 110-3012-01-06 (right) or 110-3012-01-12 (right)). (1) If any cracks are found, prior to further flight replace the cracked elevator balance weight arm with a modified arm (P/N 110-3012-01-13 (left) or 110-3012-01-14 (right)) or with an original arm (P/N 110-3012-01-01, 110-3012-01-06, 110-3012-01-07, or 110- 3012-01-12, as applicable) that has been shown to be free from cracks using a visual inspection with a 10x glass. (2) If no cracks are found, thereafter at intervals not to exceed 25 hours TIS, visually reinspect, using a 10x glass, the entire elevator balance weight arms for cracks. (3) The above repetitive inspections may be discontinued when the airplane is modified by the installation of modified balance weight arms (P/N 110-3012-01-13 (left) and 110-3012-01-14 (right)). (b) If not accomplished per paragraph (a) of this AD, within the next 1000 hours TIS after the effective date of this AD, replace both elevator balance weight arms, (P/N 110-3012-01-01 (left) or 110-3012-01-07 (left), and 110-3012-01-06 (right) or 110-3012- 01-12 (right)), with modified arms (P/N 110-3012-01-13 (left) and 110-3012-01-14 (right), as applicable). (c) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (d) An alternate method of compliance or adjustment of the initial or repetitive compliance times which provides an equivalent level of safety may be approved by the Manager, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. NOTE: The request should be forwarded through an FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. This amendment (39-6740, AD 90-12-01) becomes effective on October 15, 1990, as to all persons except those persons to whom it was made immediately effective by priority letter AD 90-12-01, issued June 1, 1990, which contained this amendment.
47-10-10: 47-10-10 LOCKHEED: (Was Mandatory Note 12 of AD-763-3.) Applies to All Model 49 Serials Up to and Including 2088. Compliance required immediately. Remove all soundproofing pads adjacent to and surrounding the voltage regulators. (LAC Service Bulletin 49/SB-171 covers this same subject.)
2006-11-12: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 767 airplanes. This AD requires repetitive measurements of the rudder and elevator freeplay, repetitive lubrication of rudder and elevator components, and related investigative/corrective actions if necessary. This AD results from reports of freeplay-induced vibration of the rudder and the elevator. The potential for vibration of the control surface should be avoided because the point of transition from vibration to divergent flutter is unknown. We are issuing this AD to prevent excessive vibration of the airframe during flight, which could result in loss of control of the airplane.
2020-22-03: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-200, -200 Freighter, and -300 series airplanes. This AD was prompted by a report that during a certification exercise, it was identified that there was a risk of an engine bleed system over- temperature, without the engine bleed valve closing; the associated engine bleed valve should automatically close. This AD requires revising the existing airplane flight manual (AFM) to incorporate procedures to be applied if an engine bleed over-temperature occurs when the associated engine bleed valve is jammed open, and provides for the optional embodiment of updated flight warning computer (FWC) software, which would terminate the AFM revision, as specified in a European Union Aviation Safety Agency (EASA), which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2000-03-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2000-NM-58-AD that was sent previously to all known U.S. owners and operators of McDonnell Douglas Model DC-9, Model MD-90-30, Model 717-200, and Model MD-88 airplanes by individual telegrams. This AD requires inspecting the general condition of the jackscrew assembly and the area around the jackscrew assembly to detect the presence of metal shavings and flakes. This action is prompted by a report from an operator that indicated two instances of metallic shavings in the vicinity of the jackscrew assembly and gimbal nut of the horizontal stabilizer. The actions specified by this AD are intended to prevent loss of pitch trim capability due to excessive wear of the jackscrew assembly of the horizontal stabilizer, which could result in loss of vertical control of the airplane.