Results
2021-07-06: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-2B16 (601-3A, 601-3R, and 604 Variants) airplanes. This AD was prompted by a determination that certain airplanes have outdated magnetic variation (MagVar) tables inside navigation systems. This AD requires revising the existing airplane flight manual (AFM) to update the Flight Management System (FMS) and Inertial Reference System (IRS) limitations. The FAA is issuing this AD to address the unsafe condition on these products.
76-17-07: 76-17-07 BOEING: Amendment 39-2706. Applies to Boeing Model 727-100 series airplanes certificated in all categories with static port heater circuits deactivated. Compliance required as indicated unless already accomplished. \n\tTo prevent the loss of altitude and airspeed reference due to a small amount of water freezing in the static port system, accomplish either of (1) or (2) below: \n\t(1)\tWithin the next 1,000 hours time in service after the effective date of this AD reactivate the static port heater circuits to the original FAA approved Boeing 727-100 configuration; or \n\t(2)\tWithin the next 2,000 hours time in service after the effective date of this AD replace the deactivated heater assembly, P/N 10-60723-1, with elbow fitting MS21908D6 in accordance with Boeing Service Bulletin 727-34-95 dated September 3, 1976, or later FAA approved service bulletins, and enlarge the static port sensing holes from .047 inch diameter to .125 inch diameter in accordance with Boeing ServiceBulletin 727-34-94 (to be released) or later FAA approved service bulletins. \n\tNotwithstanding the provisions of the above paragraph (1) the heater elements in one static system may be inoperative provided the aircraft is not flown in icing or precipitation conditions. \n\tBoeing 727-100 airplanes already incorporating Boeing Service Bulletin 727-25-42, Revision 1, dated March 4, 1968, with elbow fitting MS21908D6 and Boeing Service Bulletin 727-34-57 dated April 7, 1968, enlarging the static sense holes are in compliance with this AD. \n\tEquivalent modifications may be approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. \n\tThe manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). \n\tAll persons affected by this directive, who have not already received these documents from the manufacturer, may obtain copies upon request to Boeing Commercial Airplane Company, P. O. Box 3707, Seattle, Washington 98124. The documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington.\n \n\tThis amendment becomes effective October 1, 1976.
96-22-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Beech (Raytheon) Model BAe series 1000A and Model Hawker 1000 airplanes, that requires modifications of the thrust reversers. This amendment is prompted by a review of the certification analysis of the thrust reversers and by testing of the thrust reversers, which indicated that additional design features are necessary to prevent failure of the driver link and the inadvertent deployment of a thrust reverser during flight. The actions specified by this AD are intended to prevent inadvertent deployment of a thrust reverser during flight, which could result in reduced controllability of the airplane.
96-22-12: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Corporation (Raytheon) Models 1900C, 1900D, and 2000 airplanes. This action requires inspecting (one-time) the fuel filter assemblies to detect any bypass valve that is glued shut. If a bypass valve is glued shut, the AD requires replacing the associated fuel filter assembly. Three in-flight occurrences in which the low fuel pressure light illuminated prompted this action. In each of the instances, a bypass valve on the affected airplane engine was glued shut with anaerobic thread lock adhesive and when the fuel filter became clogged, proper fuel flow to the engine was not obtained. The actions specified by this AD are intended to prevent lack of fuel to the engine and eventual engine shutdown caused by a clogged fuel filter and a contaminated fuel filter bypass valve.
93-07-04: 93-07-04 BRITISH AEROSPACE: Amendment 39-8536. Docket 92-NM-189-AD. Applicability: Model ATP series airplanes; serial numbers 2001 through 2049, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent possible loss of integrity and security of the flap drive system, accomplish the following: (a) Within 14 days after the effective date of this AD, perform a one-time general visual inspection of the primary flap drive torque tubes to ensure that the four bolt and nut assemblies on the splined flanged-coupling assembly on the right gearbox drive at station 0 have split pins installed, in accordance with British Aerospace Service Bulletin ATP-27-55, dated August 14, 1992. (1) If split pins are installed, no further action is necessary. (2) If any split pin is missing, accomplish the requirements of both paragraphs (a)(2)(i) and (a)(2)(ii) of this AD: (i) Prior to further flight, check tighten each of the four bolts to 8 to 10 foot pounds torque. Repeat this check tightening thereafter at intervals not to exceed 14 days. (ii) Within 6 months after the effective date of this AD, install split pins in the bolt and nut assemblies in accordance with British Aerospace Service Bulletin ATP-27-55, dated August 14, 1992. Installation of these split pins constitutes terminating action for the inspections and check tightening requirements of this paragraph. (b) Installation of split pins in the bolt and nut assemblies in accordance with British Aerospace Service Bulletin ATP-27-55, dated August 14, 1992, constitutes terminating action for the requirements of paragraph (a) of this AD. (c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (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 inspection and installation shall be done in accordance with British Aerospace Service Bulletin ATP-27-55, dated August 14, 1992. 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 Jetstream Aircraft, Inc., Librarian for Service Bulletins, P.O. Box 16029, Dulles International Airport, Washington, DC 20041-6029. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on May 10, 1993.
2021-07-14: The FAA is adopting a new airworthiness directive (AD) for all Yabora Industria Aeronautica S.A. Model EMB-135 and EMB-145 airplanes. This AD was prompted by a report involving disconnection of a side arm strut from the right main landing gear (MLG); a subsequent investigation found that the side arm strut lower bearing was installed inverted on the airplane. This AD requires doing a general visual inspection of the right and left MLG to verify certain conditions and doing all applicable on-condition actions, as specified in an Agencia Nacional de Aviacao Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
91-23-12: 91-23-12 LOCKHEED: Amendment 39-8081. Docket No. 91-NM-77-AD. Applicability: Model L-1011 series airplanes, equipped with BFGoodrich brake part numbers identified in paragraph (a) of this AD, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent the loss of main landing gear braking effectiveness, accomplish the following: (a) Within 180 days after the effective date of this AD, inspect the brake part numbers shown below for wear. Any brake worn more than the maximum wear limit specified below must be replaced, prior to further flight, with a brake within this limit. Type Certificated Model Designation Common Model Designation Maximum GTOW Brake Part No. Maximum Wear Limit (inches) L-1011-385-1 (-1) 430,000 2-1195-1 2.10 (-1) 430,000 2-1195-5 2.10 (-1) 430,000 2-1195-6 2.10 (-1) 430,000 2-1195-7 2.10 (-1) 430,000 2-1195-8 2.10 (-1) 430,000 2-1367 3.00 (-1) 430,000 2-1367-1 3.00 (-1) 430,000 2-1367-2 3.00 (-40) 440,000 2-1195-1 2.10 (-40) 440,000 2-1195-5 2.10 (-40) 440,000 2-1195-6 2.10 (-40) 440,000 2-1195-7 2.10 (-40) 440,000 2-1195-8 2.10 (-40) 440,000 2-1367 3.00 (-40) 440,000 2-1367-1 3.00 (-40) 440,000 2-1367-2 3.00 (-50) 450,000 2-1367-3 2.60 (-50) 450,000 2-1367-4 2.60 (-50) 450,000 2-1367-5 2.60 L-1011-385-1-14 (-100,-150,-200) 466,000 2-1367-3 2.60 (-100,-150,-200) to 2-1367-4 2.60 (-100,-150,-200) 474,000 2-1367-5 2.60 (-250) 510,000 2-1367 3.00 (-250) 510,000 2-1367-1 3.00 (-250) 510,000 2-1367-2 3.00 L-1011-385-1-15 (-100,-150,-200) 466,000 2-1367-3 2.60 (-100,-150,-200) to 2-1367-4 2.60 (-100,-150,-200) 474,000 2-1367-5 2.60 (-250) 510,000 2-1367 3.00 (-250) 510,000 2-1367-1 3.00 (-250)510,000 2-1367-2 3.00 L-1011-385-3 (-500) 496,000 2-1367 3.00 (-500) to 2-1367-1 3.00 (-500) 516,000 2-1367-2 3.00 NOTE: Lockheed Service Bulletin 093-32-253, dated March 29, 1991, contains additional information concerning Model L-1011 brake configurations. (b) Within 180 days after the effective date of this AD, incorporate the maximum brake wear limits specified in paragraph (a) of this AD into the FAA-approved maintenance inspection program. (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, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Los Angeles ACO. (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. This amendment (39-8081, AD 91-23-12) becomes effective on December 9, 1991.
96-21-10: This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-60 SHERPA series airplanes, that requires revising the Airplane Flight Manual (AFM) to provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions, and to limit or prohibit the use of various flight control devices. This amendment is prompted by results of a review of the requirements for certification of the airplane in icing conditions, new information on the icing environment, and icing data provided currently to the flight crews. The actions specified by this AD are intended to minimize the potential hazards associated with operating the airplane in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
96-21-01: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 series airplanes, that requires either replacement or modification of the hydraulic damper assembly. This amendment is prompted by reports indicating that insufficient damping of the hydraulic shimmy damper in the main landing gear (MLG) can allow high torsional vibration to occur. The actions specified by this AD are intended to prevent such vibration, which can damage the MLG assembly and lead to its collapse.
93-04-02: 93-04-02 ROCKWELL INTERNATIONAL/COLLINS AVIATION DIVISION: Amendment 39-8504. Docket No. 93-CE-18-AD. Applicability: TDR-94D Mode S transponders, P/N CPN 622-9210-002, installed on, but not limited to the following, certificated in any category: Aerospatiale ATR-42 and ATR-72 series airplanes Saab 340A and 340B airplanes Short Model SD3-60 airplanes de Havilland DHC-7 and DHC-8 series airplanes British Aerospace ATP airplanes Gulfstream G-II, G-III, and G-IV series airplanes Dassault Mystere-Falcon 50, Mystere-Falcon 200, and Mystere-Falcon 900 airplanes Canadair Challenger CL-601 airplanes British Aerospace HS 125-700A airplanes Beechcraft 300 series airplanes Compliance: Required as indicated, unless already accomplished. To prevent a mid-air collision or a near-miss situation caused by failure of these Mode S transponders, accomplish the following: (a) Within the next 10 calendar days after theeffective date of this AD, fabricate a placard with the following words in letters at least 0.10-inch in height and install this placard within the pilot's clear view on the instrument panel: "OPERATION OF TCAS II IN ANY MODE OTHER THAN THE "TA ONLY" MODE IS PROHIBITED." (b) Within the next 6 calendar months after the effective date of this AD, modify the software of the Mode S transponders in accordance with the Accomplishment Instructions section of Collins Service Bulletin TDR-94/94D-34-6, Revision 2, dated September 21, 1992. The placard required by paragraph (a) of this AD is no longer required after this modification is incorporated. (c) If parts for the above modification are not available, the airplane operator may comply with the placard requirement of paragraph (a) of this AD until the modification is incorporated based upon a schedule established by the manufacturer through the Atlanta Aircraft Certification Office. (d) Special flight permits may be issuedin 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) An alternative method of compliance or adjustment of the compliance times that provides an equivalent level of safety may be approved by the Manager, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta Aircraft Certification Office. (f) The modification required by this AD shall be done in accordance with Collins Service Bulletin TDR-94/94D-34-6, Revision 2, dated September 21, 1992. 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 Rockwell International/Collins General Aviation Division, 1100 West Hibiscus Boulevard, Melbourne, Florida 32901. 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, 800 North Capitol Street, NW., 7th Floor, suite 700, Washington, DC. (g) This amendment becomes effective on March 26, 1993.
2021-07-03: The FAA is superseding Airworthiness Directive (AD) 2015-05- 03, which applied to certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. AD 2015-05-03 required revising the existing maintenance or inspection program, as applicable, to incorporate new or revised maintenance requirements and airworthiness limitations, and incorporating structural repairs and modifications to preclude widespread fatigue damage (WFD). This AD continues to require the actions specified in AD 2015-05-03. This AD also requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, and incorporating additional structural repairs and modifications to preclude WFD. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary, as well as the corresponding structural repairs and modifications to preclude WFD. The FAA is issuing this AD to addressthe unsafe condition on these products.
2005-18-01: The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CT7-5A2, -5A3, -7A, -7A1, -9B, -9B1, and -9B2 turboprop engines, with stage 2 turbine aft cooling plate, part number (P/N) 6064T07P01, 6064T07P02, 6064T07P05, or 6068T36P01 installed. This AD requires a onetime eddy current inspection (ECI) of certain P/N stage 2 turbine aft cooling plate boltholes. This AD results from reports of six stage 2 turbine aft cooling plates found cracked during inspection. We are issuing this AD to prevent stage 2 aft cooling plate separation, resulting in uncontained engine failure and damage to the airplane.
78-17-04: 78-17-04 GENERAL DYNAMICS: Amendment 39-3283. Applies to all Model 340 and 440 series and C-131E airplanes in passenger configuration, including those modified for turbopropeller power, certificated in all categories. To insure that the passenger emergency escape window release handle access door can be opened, accomplish the following: (a) Within the next 10 hours time in service from the effective date of this AD unless already modified in accordance with paragraph (c) or (d), check each passenger emergency escape window release handle cover assembly to assure that the release handle access door swings open without restriction. If the release handle access door cannot be opened, modify the cover assembly per General Dynamics Alert Service Bulletin 640(340D)-25-A10 dated July 12, 1978 prior to the next flight. (b) Repeat the checks specified in (1) on all unreworked cover assemblies prior to first flight of each day pending accomplishment of the rework defined in General Dynamics Alert Service Bulletin 640(340D)-25-A10 dated July 12, 1978. (c) Within 30 days or 50 hours time in service, whichever occurs earlier from the effective date of this AD, accomplish the rework defined in the General Dynamics Service Bulletin noted in paragraph (b) at which time checks required by this AD may be discontinued. (d) Alternate methods of insuring that the release handle access door can be opened may be used if approved by the Chief, Aircraft Engineering Division, FAA, Western Region. (e) The checks specified in this AD may be performed by flight crew personnel. (f) Record the accomplishment of check in a record maintained by the operator. This amendment becomes effective September 5, 1978.
92-06-12: 92-06-12 BELL HELICOPTER TEXTRON, INC.: Amendment 39-8192. Docket No. 90-ASW-48. Applicability: All Model 206A, 206B, 206L, 206L-1, and 206L-3 helicopters, certificated in any category, with the main transmission sungear, part number (P/N) 206-040-662-101, installed. Compliance: Required as indicated, unless already accomplished. To prevent premature wear of the sungear and mating spur gears which could result in transmission failure, accomplish the following: (a) At the next inspection interval for the main transmission sungear, P/N 206-040-662-101, but no later than 1,500 hours' time in service after the effective date of this AD, remove and replace sungears which have the following serial numbers: SD-0005 SD-0010 SD-0020 SD-0022 SD-0023 SD-0024 SD-0025 SD-0026 SD-0027 SD-0031 SD-0033 SD-0034 SD-0035 SD-0036 SD-0037 SD-0039 SD-0040 SD-0043 SD-0044 SD-0046 SD-0054 SD-0055 SD-0057 SD-0060 SD-0062 SD-0065 SD-0066 SD-0067 SD-0068 SD-0069 SD-0071 (b) In conjunction with (a), inspect the pinion spur gears which mate with the above listed sungears for micro pitting or hardlines in the gear teeth due to the insufficient tip relief, or improper tooth profile of the sungear. Determine if wear or damage is within specified limits according to the applicable BHTI maintenance, repair and overhaul manuals. (c) If wear or damage exceeds the specified limits, remove and replace the affected spur gears with serviceable parts before further flight. (d) An alternative method of compliance or adjustment of the compliance times which provides an acceptable level of safety may be used if approved by the Manager, Rotorcraft Certification Office, ASW-170, Rotorcraft Directorate, Aircraft Certification Service, FAA, Fort Worth, Texas, 76193-0170. (e) Bell Helicopter Textron, Inc., Alert Service Bulletins No. 206-90-56, Rev. A, dated 1/15/91 or 206L-90-69, Rev. A, dated 1/15/91, as applicable, provide an acceptable, alternate means of compliance with this AD. (f) This amendment becomes effective on April 13, 1992.
96-20-05: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 767 series airplanes, that requires repetitive operational tests to verify proper deployment of the ram air turbine (RAT), and replacement of the rotary actuator motor with a new or serviceable rotary actuator motor, if necessary. This amendment is prompted by reports of corroded rotary actuator motors of the RAT found on in-service airplanes. The actions specified by this AD are intended to ensure that the RAT actuator motor is not corroded to the point where it may result in the failure of the RAT to deploy and subsequently result in loss of emergency hydraulic power to the flight controls in the event that power is lost in both engines.
2021-07-04: The FAA is adopting a new airworthiness directive (AD) for all ATR-GIE Avions de Transport Regional Model ATR42 airplanes and Model ATR72 airplanes. This AD was prompted by in-service data, which revealed that the minimum operating airspeeds in severe icing conditions, computed to provide adequate stall margins, do not provide sufficient margins to stall speeds at high bank angle while exiting severe icing conditions. This AD requires revising the existing aircraft flight manual (AFM) and applicable corresponding operational procedures to provide emergency procedures and limitations for operating in severe icing conditions, 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.
92-24-04: 92-24-04 BOEING: Amendment 39-8409. Docket No. 92-NM-103-AD. \n\n\tApplicability: Model 737-300, -400, and -500 series airplanes; as listed in Boeing Alert Service Bulletin 737-78A1055, dated April 2, 1992, certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo prevent uncommanded deployment of the thrust reverser, accomplish the following: \n\t(a)\tWithin 12 months after the effective date of this AD, modify the engine thrust reverser control system, in accordance with Boeing Alert Service Bulletin 737-78A1055, dated April 2, 1992. \n\n\t(b)\tAn 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, Seattle Aircraft Certification Office (ACO), 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, Seattle ACO.\n \n\tNOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Seattle ACO. \n\n\t(c)\tSpecial 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. \n\n\t(d)\tThe modification shall be done in accordance with Boeing Alert Service Bulletin 737-78A1055, dated April 2, 1992. 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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124-2207. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. \n\n\t(e)\tThis amendment becomes effective on December 14, 1992.
96-19-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Gates Learjet Model 35 and 36 series airplanes that have been modified in accordance with Raisbeck Supplemental Type Certificate (STC) SA766NW, that requires a reduction of the maximum operating limit speed on the affected airplanes to prevent encountering certain potentially hazardous conditions. This amendment is prompted by reports of incidents of aileron buffet or buzz experienced during high speed cruise. The actions specified by this AD are intended to prevent aileron buffet or buzz conditions, which can result in the deterioration of the aircraft lateral control system characteristics to an unacceptable level.
2004-03-24: This amendment adopts a new airworthiness directive (AD) that is applicable to all Airbus Model A330-200, A330-300, A340-200, and A340-300 series airplanes. This action requires a revision of the airplane flight manual to include procedures for a pre-flight elevator check before each flight, repetitive inspections for cracks of the attachment lugs of the mode selector valve position transducers on the elevator servocontrols, and corrective actions if necessary. This action is intended to advise the flightcrew of the potential for an undetected inoperative elevator, and of the action they must take to avoid this hazard. This action is necessary to ensure proper functioning of the elevator surfaces, and to detect and correct cracking of the attachment lugs, which could result in partial loss of elevator function and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
77-11-02: 77-11-02 MESSERSCHMITT-BOLKOW-BLOHM GmbH: Amendment 39-2912. Applies to Model BO-105 helicopters, certificated in all categories. Compliance is required as indicated. To prevent the possible failure of the main rotor hub quadruple nuts and the consequent loss of the main rotor, accomplish the following: (a) For main rotor hub quadruple nuts, P/N's 105-14101.19 and 105-14101.20 and associated bolts, P/N's 105-14101.22 and 105-14101.23, with more than 1,400 hours total time in service, within the next 100 hours time in service after the effective date of this AD, unless already accomplished within the last 200 hours time in service, and thereafter at intervals not to exceed 300 hours time in service from the last inspection, remove the quadruple nuts and associated bolts and inspect them for cracks using a magnaflux process, or an FAA-approved equivalent. (b) If a crack is found in a nut or bolt during any of the inspections required by this AD, before further flight, replace the cracked part with a serviceable part of the same part number. For parts installed as replacements, before the accumulation of 1,500 hours total time in service on the replacement parts and thereafter at intervals not to exceed 300 hours time in service from the last inspection, remove the replacement quadruple nuts and associated bolts and inspect them for cracks using a magnaflux process or an FAA-approved equivalent. (c) Before the accumulation of 2,400 hours total time in service on a quadruple nut or bolt specified in paragraph (a) of this AD, replace the quadruple nuts and associated bolts with serviceable nuts and bolts of the same part numbers and comply with paragraphs (a) and (b) of this AD for the replacement parts. (MBB Service Bulletin No. 10-18 dated July 18, 1975, covers this same subject.) This amendment becomes effective June 14, 1977.
2021-05-19: The FAA is adopting a new airworthiness directive (AD) for Sikorsky Aircraft Model S-61L, S-61N, S-61NM, and S-61R helicopters and Sikorsky Aircraft Corporation Model S-61A, S-61D, S-61E, and S-61V restricted category helicopters. This AD was prompted by the manufacturer determining that there may be arm assemblies in service that have accumulated 15,000 or more hours time-in-service (TIS), which exceeds the service life limit for this component. This AD requires reviewing the mixer unit component log card or equivalent record and, depending on the number of hours TIS, calculating the remaining life of the arm assembly or removing the arm assembly from service. The FAA is issuing this AD to address the unsafe condition on these products.
96-18-21: This amendment supersedes Airworthiness Directive (AD) 75-26-15, which currently requires repetitively inspecting the aileron mass balance clamp unit attachment for looseness on Pilatus Britten-Norman Ltd. (Pilatus Britten-Norman) BN-2A and BN2A MK. 111 series airplanes, and modifying the aileron and mass balance clamp unit if any looseness is found. The Federal Aviation Administration's policy on aging commuter-class aircraft is to eliminate or, in certain instances, reduce the number of certain repetitive short-interval inspections when improved parts or modifications are available. This action retains the repetitive inspections required by AD 75-26-15, and requires modifying the aileron and mass balance unit (at a certain time) as terminating action for the repetitive inspection requirement. The actions specified in this AD are intended to prevent failure of the aileron mass balance attachment, which could result in loss of control of the airplane.
77-07-07: 77-07-07\tAVCO LYCOMING: Amendment 39-2864 as amended by Amendment 39-3415. Applies to the O-320-H2AD series Lycoming engines Serial Numbers L-101-76 thru L-1049-76. \n\tCompliance required within 50 hours in service after the effective date of this AD, unless previously accomplished. \n\tTo prevent the incorrect installation of the P/N LW-14784 or the P/N LW-15481 oil level gage modify the P/N 75675 oil filler extension by installing a P/N LW-15498 perforated sleeve as follows: \n\t(a)\tRemove the P/N 75675 oil filler extension from the engine. \n\t(b)\tInsert the P/N LW-15498 perforated sleeve in the oil filler extension. Make certain that the flanged end rest evenly against the recessed surface below the threads inside of the oil filler extension. Locate and mark the perforated sleeve where it protrudes through the base of the oil filler extension. \n\t(c)\tAfter locating this position, remove the perforated sleeve from the oil filler extension and insert a length of 3/4 inch diameter steel rod into the sleeve. Place the steel rod and sleeve in a vise or other suitable holding device and with a narrow chisel cut the perforated sleeve as shown in figure 1 at the location marked per instructions of item (b) of this AD. \n\t(d)\tRemove the 3/4 inch diameter steel rod and install the perforated sleeve in the oil filler extension. Bend the chiseled section of the perforated sleeve at the seam to form a tab as shown in figure 2. \n\n\n\n\t(e)\tInstall the reworked oil filler extension and perforated sleeve in the engine, making certain that the P/N 70457 gasket is properly in place between the oil filler extension and the engine crankcase. Install either P/N LW-14784 or P/N LW-15481 oil level gage. Apply lockwire as required. \n\t(f)\tUpon submission of substantiating data through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the compliance time. \n\t(Note: AVCO Lycoming Service Bulletin No. 407A covers this subject). \n\tAmendment 39-2864 became effective April 11, 1977. \n\tThis amendment 39-3415 is effective February 20, 1979
78-12-10: 78-12-10 SHORT BROTHERS LIMITED: Amendment 39-3236. Applies to Model SD3-30 airplanes certificated in all categories. Compliance is required prior to the accumulation of 4000 landings or prior to accumulating 25 landings after the effective date of this AD, whichever occurs later, unless already accomplished, and thereafter at intervals not to exceed 4000 landings. To prevent failure of the rod end bearing of the nose wheel steering actuator, replace the rod end bearing, P/N MS 21242S8K, with a new part of the same part number in accordance with Section 10, "Accomplishment Instructions" of Menasco Manufacturing Service Bulletin 32-21, dated January 11, 1978, or an FAA approved equivalent. NOTE: Short Brothers Limited Service Bulletin SD3-32-37 covers this same subject. This amendment becomes effective June 26, 1978.
96-18-04: This amendment supersedes two existing airworthiness directives (AD), applicable to certain Boeing Model 737-300, -400, and -500 series airplanes, that currently require modification of the packing and slide containers of the escape slide, and repetitive inspections of the velcro girt retaining straps of the escape slides at the forward door. The existing AD's were prompted by reports of slide girt material interfering with the girt bar stowage brackets during door opening. This new amendment requires the installation of a new modification, which constitutes terminating action for the repetitive inspection requirements. The actions specified by this amendment are intended to prevent failure or interference of opening of the forward doors, which could delay or impede the evacuation of passengers during an emergency.