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76-22-10: 76-22-10 AVIONS MARCEL DASSAULT (AMD): Amendment 39-2766. Applies to Model Fan Jet Falcon (Falcon 20) airplanes, all series, certificated in all categories, with installed Messier/Hispano Main Landing Gear Actuating Cylinders P/N A23721 (L.H.) and A23722 (R.H.) serial numbers 1 through 807, 809 through 813, 816, 818, and 820 not modified in accordance with AMD Service Bulletin No. 529, dated September 5, 1975. Compliance is required as indicated. To prevent possible failure of main landing gear down-locks, accomplish the following: (a) Inspect the following actuating cylinders for corrosion in accordance with Messier Hispano Technical Instruction DME361-5, or an FAA-approved equivalent: (1) For S/N 1 through 699, within the next 50 hours time in service or three months, whichever occurs first, after the effective date of this AD, unless already accomplished within the preceding three months, and thereafter at intervals not to exceed six months from the dateof the last inspection. (2) For S/N 700 through 807, 809 through 813, 816, 818, and 820, within the next 200 hours time in service or four months, whichever occurs first, after the effective date of this AD, unless already accomplished within the preceding two months, and thereafter at intervals not to exceed six months from the date of the last inspection. (b) If the inspection required by paragraph (a) of this AD reveals the presence of a corrosion condition classified as "very corroded," in accordance with the classification criteria of paragraph 1.c. of AMD Service Bulletin No. 528, dated July 17, 1975 (Revision 2, February 19, 1976), or an FAA-approved equivalent, within the next three months after this inspection - (1) Replace the actuator with a serviceable part of the same part number and continue the periodic inspections specified in paragraph (a) of this AD; or (2) Modify the actuator in accordance with AMD Service Bulletin No. 529, dated September 5, 1975, or an FAA-approved equivalent. (c) The inspections required by paragraphs (a) and (b)(1) of this AD may be discontinued upon the incorporation of the modification specified in paragraph (b)(2) of this AD. This amendment becomes effective November 22, 1976.
96-09-05: This amendment adopts a new airworthiness directive (AD) that is applicable to Diamond Aircraft Industries (Diamond) Model DA 20-A1 airplanes. This action requires inspecting the aft wing cavities for manufacturing debris, removing any debris found, and modifying the aileron pushrod fairings to allow them to flex. Several reports of the aileron controls becoming blocked because of manufacturing debris getting jammed between the short aileron pushrod and the pushrod exit fairing on both left and right wings prompted this action. The actions specified by this AD are intended to prevent the aileron controls from becoming blocked causing jamming between the short aileron pushrod and the pushrod fairing exit, which, if not detected and corrected, could cause loss of control of the airplane.
96-20-01: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 777-200 series airplanes. This action requires a one-time inspection to determine the serial numbers of various switch modules on the overhead panel and control stand, and replacement of switch modules with new improved modules. This AD also requires repetitive tests of the cargo fire extinguishing system, and one-time tests of the fuel crossfeed valve, pack, trim air, and alternate flap control switches; and repair or replacement of switch modules with new improved modules, if necessary. This amendment is prompted by a report indicating that the flight crew received a warning of fire in the forward cargo compartment during flight; later inspection revealed that the metered fire bottles failed to discharge due to suspected contamination of the arming switch contacts of the cargo fire extinguishing system. The actions specified in this AD are intended to minimize contamination of the switch contacts and consequent failure of the switches, which, if not corrected, could result in inability of the flight crew to activate the cargo fire extinguishing, fuel, air conditioning, and alternate flap systems.
2022-16-01: The FAA is superseding Airworthiness Directive (AD) 2022-08- 07, which applied to all Embraer S.A. Model ERJ 170-100 STD, -100 LR, - 100 SU, and -100 SE airplanes; Model ERJ 170-200 STD, -200 LR, and -200 SU airplanes; Model ERJ 190-100 STD, -100 LR, -100 IGW, and -100 ECJ airplanes; and Model ERJ 190-200 STD, -200 LR, and -200 IGW airplanes. AD 2022-08-07 required determining if certain NORDAM passenger windows are installed, inspecting affected parts for cracks, and replacing cracked parts. AD 2022-08-07 also required repetitive inspections of uncracked affected parts until all affected parts are replaced. This AD was prompted by a determination that additional airplanes are affected by the unsafe condition identified in AD 2022-08-07. This AD retains certain requirements of AD 2022-08-07, revises the applicability of AD 2022-08-07 to include the affected parts for clarification, and adds a certain airplane model to the applicability. This AD also prohibits the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
2013-05-11: We are superseding an existing airworthiness directive (AD) for certain Airbus Model A318, A319, A320, and A321 series airplanes. That AD currently requires one-time and repetitive inspections of specific areas and, when necessary, corrective actions for those rudders where production rework has been identified. This new AD adds airplanes with certain rudders to the AD applicability; changes an inspection type for certain reinforced rudder areas; requires pre- inspections and repairs if needed; and requires permanent restoration of vacuum loss holes. This AD also requires additional inspections for certain rudders and repair if needed, and requires replacement of certain rudders with new rudders. This AD was prompted by reports of surface defects on rudders that were the result of debonding between the skin and honeycomb core. We are issuing this AD to detect and correct extended de-bonding, which might degrade the structural integrity of the rudder. The loss of the rudder leads to degradation of the handling qualities and reduces the controllability of the airplane.
95-24-12: This amendment adopts a new airworthiness directive (AD) that applies to Jetstream Aircraft Limited (JAL) Model 3201 airplanes. This action requires repetitively inspecting the main landing gear (MLG) bay forward lower edge wing skin structure for cracks, replacing any cracked doubler with a joggled doubler of improved design to reinforce the area and prevent future cracking, and eventually incorporating these doublers on all affected airplanes. Cracking found at the MLG bay forward lower edge wing skin structure during fatigue testing of the JAL Model 3201 prompted this action. The actions specified by this AD are intended to prevent the MLG bay forward lower edge wing skin structure from cracking, which, if not detected and corrected, could cause failure of the wing structure and loss of control of the airplane.
2022-12-10: The FAA is adopting a new airworthiness directive (AD) for all Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by a report of a weak point identified in the Falcon 7X 'EASy' avionics architecture, which, coupled with theoretical generic input/output (I/ O) card failure, could lead to misleading data on display units. This AD requires revising the existing airplane flight manual (AFM) to provide emergency procedures for inconsistent or unreliable flight data and emergency and abnormal operations procedures for the GEN I/O internal module failure, and revising the operator's existing FAA- approved minimum equipment list (MEL) items for the multi-function probe heating, air data, and inertial reference systems, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also requires revising the existing AFM to incorporate additional information in the emergency procedures. The FAA is issuing this AD to address the unsafe condition on these products.
2022-12-11: The FAA is adopting a new airworthiness directive (AD) for certain Embraer S.A. Model ERJ 190-100 ECJ airplanes. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary and that some life limits on some components used on the main landing gear (MLG) may not be properly controlled, due to interchanging those parts between airplane models with different operational loads during repair or overhaul. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations; reviewing maintenance records of the MLG assemblies to determine if any life-limited item has been replaced and reporting those findings; and re-identifying the MLG assemblies and certain components; as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. This AD also prohibits installing certain part numbers. The FAA is issuing this AD to address the unsafe condition on these products.
2004-18-04: The FAA is adopting a new airworthiness directive (AD) for all McDonnell Douglas MD-10-10F, MD-10-30F, MD-11, MD-11F, and 717-200 airplanes. This AD requires a revision to the Limitations section of the Airplane Flight Manual (AFM) to prohibit use of the flight management system (FMS) profile (PROF) mode for descent and/or approach operations unless certain conditions are met. This AD is promoted by a report of two violations of the selected flight control panel (FCP) altitude during FMS PROF descents. We are issuing this AD to prevent, under certain conditions during the FMS PROF descent, the uncommanded descent of an airplane below the selected level-off altitude, which could result in an unacceptable reduction in the separation between the airplane and nearby air traffic or terrain.
92-25-05: 92-25-05 BRITISH AEROSPACE: Amendment 39-8420. Docket No. 91-NM-269-AD. Applicability: All Model ATP series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent structural failure of certain brake torque plates and accompanying brake failure, accomplish the following: (a) Within 400 landings after the effective date of this AD, revise the FAA-approved Mandatory Life Limitations (Airframe) Section, Chapter 5, Section 05-10-11, Table 1, page 4, of the British Aerospace ATP Aircraft Maintenance Manual, by deleting the existing life limitations for brake torque plates, part numbers AHA 1777 and AHA 1650, and adding the component life limitations listed in Table 1 below. The Maintenance Manual revision may be accomplished by inserting a copy of this AD into the Mandatory Life Limitations (Airframe) Section of the ATP Aircraft Maintenance Manual. Once this revised page of the Maintenance Manual is available from British Aerospace and is inserted into the Maintenance Manual, the copy of this AD may be removed. TABLE 1 continued MSI/SSI ITEM DESCRIPTION PART NUMBER LIFE LIMITATION 32-42-00-022 Brake torque plate (Post Dunlop Mod 2541) AHM8857 Assembly AHA 1777 14,500 landings 32-42-00-022 Brake torque plate (Pre Dunlop Mod 2541) AHM8857 Assembly AHA 1650 10,000 landings (b) 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, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, 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. (c) 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. (d) This amendment becomes effective on December 22, 1992.
2022-14-14: The FAA is adopting a new airworthiness directive (AD) for all Alexander Schleicher GmbH & Co. Segelflugzeugbau Model ASW-15 gliders. 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 identifies the unsafe condition as wing root damage. This AD requires repetitively inspecting the wing root ribs for cracks, looseness, and damage and replacing any root rib with a crack, a loose rib or lift pin bushing, or any damage. The FAA is issuing this AD to address the unsafe condition on these products.
2013-11-07: We are adopting a new airworthiness directive (AD) for certain Embraer S.A. Model ERJ 190 airplanes. This AD was prompted by reports of cracks on the side stay of the main landing gear (MLG). This AD requires repetitive measurements of the left-hand (LH) and right-hand (RH) MLG side stay support fitting to detect bushing migration, and eventual replacement of the bushing; and a detailed inspection for damage on the LH and RH MLG side stay support assembly, and related investigative and corrective actions if necessary. We are issuing this AD to prevent excessive bearing friction, which might compromise the MLG free fall extension and cause fatigue cracking on the MLG side stay and on its support assembly, resulting in reduced structural integrity of the MLG.
2013-11-13: We are adopting a new airworthiness directive (AD) for all Rolls-Royce plc (RR) Viper Mk. 601-22 turbojet engines. This AD requires reducing the life of certain critical parts. This AD was prompted by a review carried out by RR of the lives of these parts. We are issuing this AD to prevent failure of life-limited parts, damage to the engine, and damage to the airplane.
97-02-21: This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-120 series airplanes, that requires repetitive inspections to detect cracks in the wing rib-to-skin support brackets (shear clips), and replacement of cracked brackets with new or serviceable brackets. This amendment also requires the eventual replacement of certain brackets with new brackets, which terminates the requirement for the inspections. This amendment is prompted by reports of cracks in certain wing rib-to-skin support brackets in both the lower and upper skin of the wings. The actions specified by this AD are intended to prevent cracking of those support brackets, which can subsequently lead to the loosening of the rivets in the wing skin, leakage of fuel through the rivet holes, and, ultimately, the reduction of the structural integrity of the wing.
2004-19-02: This amendment adopts a new airworthiness directive (AD), applicable to all Dassault Model Fan Jet Falcon series airplanes and Model Mystere-Falcon 20 series airplanes, that requires inspecting and testing for fatigue cracking due to stress corrosion in the vertical posts of the window frames in the flight compartment. This action is necessary to prevent fatigue cracking of the window frames, which could result in rapid depressurization of the fuselage and consequent reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
2013-11-06: We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model Mystere-Falcon 900 and Falcon 900EX airplanes. This AD was prompted by reports of chafing between the tail strobe power supply and a hydraulic line. This AD requires modifying the tail strobe power supply wire routing. We are issuing this AD to prevent chafing between the tail strobe power supply and a hydraulic line, which could result in hydraulic fluid leakage and possible fire due to arcing, and consequent loss of control of the airplane due to structural failure of the tail.
2022-14-13: The FAA is superseding Airworthiness Directive (AD) 2015-07- 05, which applied to all BAE Systems (Operations) Limited Model BAe 146 series airplanes and Model Avro 146-RJ series airplanes. AD 2015-07-05 required repetitive external eddy current inspections on the aft skin lap joints of the rear fuselage for cracking, corrosion, and other defects, and repair if necessary. This AD continues to require the actions in AD 2015-07-05, at certain revised compliance times, and also requires repetitive low frequency eddy current (LFEC) inspections for any cracking, corrosion, and other defects in the aft skin lap joints of the rear fuselage and in the fuselage skin panels, and repair if necessary. This AD was prompted by a report of a pressurization problem on an airplane during climb-out; a subsequent investigation showed a crack in the fuselage skin; and that repetitive LFEC inspections in the rear fuselage aft skin lap joints and in the fuselage skin panels are necessary. Certain compliance times must also be revised. The FAA is issuing this AD to address the unsafe condition on these products.
91-20-08: 91-20-08 BEECH: Amendment 39-8042. Docket No. 91-CE-13-AD. Applicability: The following model and serial number airplanes that are equipped with an optional fresh air blower, certificated in any category: Model Serial Numbers F33A CE-941 through CE-1555 F33C CJ-156 through CJ-179 V35B D-10348, and D-10364 through D- 10403 A36 E-1809 through E-2592 A36TC and B36TC EA-192 through EA-514 Compliance: Required within the next 50 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent fresh air blower housing failure, which could lead to blower impingement on the flight control cables located below the blower and possible loss of control of the airplane, accomplish the following: (a) Inspect and modify as required the attachment of the fresh air blower housing in accordance with the instructions and the criteria contained in Beech Service Bulletin No. 2380, revised April 1991. (b) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a location where the requirements of this AD can be accomplished. (c) An alternative method of compliance or adjustment of the compliance time 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. (d) The inspection and modification required by this AD shall be done in accordance with Beech Service Bulletin No. 2380, revised April 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 the Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085. 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. This amendment (39-8042, AD 91-20-08) becomes effective on October 31, 1991.
67-15-01: 67-15-01 BRITISH AIRCRAFT: Amdt 39-401 Part 39 Federal Register April 18, 1967. Applies to Model BAC 1-11 200 and 400 Series Airplanes. Compliance required as indicated, unless already accomplished. To prevent failure of the link pin, P/N AB 21-6503, installed between the stabilizer pivot lower link assembly and the fin, accomplish the following: (a) Within the next 200 landings for airplanes with 800 or more landings, and before the expiration of 1,000 landings for airplanes with less than 800 landings, remove P/N AB 21- 6503 from service, and replace with a new P/N AB 21-6679. (b) After each installation of a new P/N AB 21-6679, conduct a check of the adjustment and torque loading of the horizontal stabilizer side load transfer mechanism and stabilizer link assembly center pivot in accordance with BAC 1-11 Alert Service Bulletin 55-A- PM 2706, Issue 1, dated November 16, 1966, or later ARB-approved issue. (c) For the purpose of complying with this AD, subjectto acceptance by the assigned FAA maintenance inspector, the number of landings may be determined by dividing each airplane's hours' time in service by the operator's fleet average time from takeoff to landing for the airplane type. This directive effective May 18, 1967.
2004-18-14: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A330 and A340-200 and -300 series airplanes, that currently requires revising the Limitations Section of the airplane flight manual (AFM) to ensure that the flightcrew is advised of the proper procedures in the event of uncommanded movement of a spoiler during flight. This amendment adds inspections of the function of the pressure relief valves of each spoiler servo control (SSC), and corrective action if necessary. This new AD also mandates eventual modification of the SSCs, which terminates the AFM revision in the existing AD. The actions specified by this AD are intended to prevent uncommanded movement of a spoiler during flight, which could result in reduced controllability of the airplane and consequent significant increased fuel consumption during flight, which could necessitate an in-flight turn-back or diversion to an unscheduled airport destination. This action is intended to address the identified unsafe condition.
2013-09-11: We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company Model 500, 501, 550, 551, S550, 560, 560XL, and 650 airplanes. This AD was prompted by multiple reports of smoke and/or fire in the tailcone caused by sparking due to excessive wear of the brushes in the air conditioning (A/C) motor. This AD requires inspecting to determine if certain A/C compressor motors are installed and to determine the accumulated hours on certain A/C drive motor assemblies; repetitive replacement of the brushes in the drive motor assembly, or, as an option to the brush replacement, deactivation of the A/C system and placard installation; and return of replaced brushes to Cessna. We are issuing this AD to prevent the brushes in the A/C motor from wearing down beyond their limits, which could result in the rivet in the brush contacting the commutator causing sparks and consequent fire and/or smoke in the tailcone with no means to detect or extinguish the fire and/or smoke.
2022-15-03: The FAA is superseding Airworthiness Directive (AD) 2021-14-06 for all Pratt & Whitney (PW) PW1519G, PW1521G, PW1521G-3, PW1521GA, PW1524G, PW1524G-3, PW1525G, PW1525G-3, PW1919G, PW1921G, PW1922G, PW1923G, and PW1923G-A model turbofan engines. AD 2021-14-06 required repetitive borescope inspections (BSI) of certain low-pressure compressor (LPC) rotor 1 (R1) until replacement of electronic engine control (EEC) full authority digital electronic control (FADEC) software with updated software. AD 2021-14-06 also required a BSI after installation of the updated EEC FADEC software if certain Onboard Maintenance Message fault codes are displayed and meet specified criteria. AD 2021-14-06 also required, depending on the results of the BSI, replacement of the LPC R1. Since the FAA issued AD 2021-14-06, the manufacturer redesigned the compressor intermediate case (CIC) assembly to incorporate a shortened bleed duct configuration and updated the EEC FADEC software. This AD continues to require repetitive BSI of certain LPC R1s until replacement of EEC FADEC software with updated software and also a BSI after installation of the updated EEC FADEC software if certain Onboard Maintenance Message fault codes are displayed and meet specified criteria. This AD continues to require, depending on the results of the BSI, replacement of the LPC R1. This AD also requires removal and replacement of the existing CIC assembly with a CIC assembly eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
2004-18-13: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300 B2 and B4 series airplanes, and Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622R, C4- 605R Variant F, and F4-605R airplanes, that currently requires a one- time inspection for cracking of the gantry lower flanges in the main landing gear (MLG) bay area; and repair, if necessary. This amendment removes an airplane model from the applicability. This amendment, for certain airplanes, retains the one-time inspection for cracking of the gantry lower flanges and repair, if necessary. For other airplanes, this amendment adds repetitive inspections of the gantry lower flanges; repair, if necessary; and reinforcement of the left-hand and right-hand gantry. The actions specified by this AD are intended to detect and correct cracking of the gantry lower flanges in the MLG bay area, which could result in decompression of the airplane. This action is intended to address the identified unsafe condition. DATES: Effective October 19, 2004. The incorporation by reference of Airbus Service Bulletin A300-53- 6128, dated March 5, 2001, as listed in the regulations, is approved by the Director of the Federal Register as of October 19, 2004. The incorporation by reference of Airbus All Operators Telex (AOT) 53-11, dated October 13, 1997, as listed in the regulations, was approved previously by the Director of the Federal Register as of July 30, 1998 (63 FR 34589, June 25, 1998).
2013-10-05: We are adopting a new airworthiness directive (AD) for Eurocopter Deutschland GmbH (ECD) Model MBB-BK 117 C-2 helicopters. This AD requires revising the operating limitations to prohibit flights under instrument flight rules (IFR) or under night visual flight rules (VFR) when the autotrim is inoperative. The actions of this AD are intended to prevent a workload situation whereby stabilizing the helicopter in flight would be difficult if not impossible, resulting in possible loss of helicopter control.
2013-10-01: We are adopting a new airworthiness directive (AD) for a certain Spectrolab Nightsun XP Searchlight Assembly (searchlight) installed on, but not limited to Agusta S.p.A. (Agusta) Model AB139 and Model AW139 helicopters, Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters, and Eurocopter Deutschland GmbH (Eurocopter) Model EC135 and Model MBB-BK 117 C-2 helicopters. This AD requires, before further flight, inserting information into the Normal Procedures section of the Rotorcraft Flight Manual (RFM), a daily check of the searchlight, and at a specified time interval or if certain conditions are found, modifying any affected searchlight gimbal assembly. This AD was prompted by a report of a searchlight vibrating and an investigation that revealed that the gimbal azimuth top nut was loose. A loose nut, if not detected and corrected, could result in a gap between the rubber edging of the top shroud and the gimbal frame, leading to degradation of pointing accuracy andstability performance of the searchlight and excessive vibration. If the nut were to entirely disengage, the searchlight could disconnect partially or totally from the helicopter, resulting in damage to the helicopter and injury to persons on the ground. The actions of this AD are intended to ensure that the searchlight remains firmly attached to the helicopter.