Results
2005-17-06: The FAA is adopting a new airworthiness directive (AD) for Turbomeca Artouste III series turboshaft engines. This AD requires modification of the engine air intake assembly. This AD results from a report of an in-flight shutdown and subsequent loss of control of the helicopter due to ice ingestion into the engine. We are issuing this AD to prevent ice ingestion into the engine, which could lead to an in- flight shutdown and subsequent loss of control of the helicopter.
97-22-01: This amendment adopts a new airworthiness directive that applies to Pilatus Britten-Norman Ltd. (Pilatus Britten-Norman) BN-2A, BN-2B, and BN-2T series airplanes. This AD requires repetitively inspecting the junction of the torque link lug and upper case of the main landing gear (MLG) torque link assemblies for cracks, and replacing any MLG torque link assembly with a Modification A39 MLG torque link assembly, either immediately when cracks are found or after a certain period of time if cracks are not found. Replacing all MLG torque link assemblies with Modification A39 MLG torque link assemblies eliminates the need for the repetitive inspections. These repetitive inspections are currently required by AD 86-07-02 for the BN-2A, BN-2B, and BN-2T series airplanes, as well as the BN2A MK. 111 series airplanes. There are no improved design parts for the BN2A MK. 111 series airplanes. The Federal Aviation Administration (FAA) is issuing in a separate action a revision to AD 86-07-02 to retain the repetitive inspection and replacement (if necessary) requirements for the BN2A MK. 111 series airplanes. The actions specified in this AD are intended to prevent failure of the main landing gear caused by cracks in the torque link area, which could lead to loss of control of the airplane during landing operations.
97-21-15: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model Avro 146-RJ series airplanes, that requires a modification of the electrical system in the equipment bay area by replacing certain cables, clamps, and fairleads with new components. This amendment is prompted by a report indicating that the incorrect size of electrical cables were used in the generator feeder circuit to certain busbars from the generator contactors. As a result, the electrical cables are not compatible with generator rating requirements and can overheat. The actions specified by this AD are intended to prevent possible overheating of electrical generator feeder cables and consequent damage, which could lead to possible fire or the loss of essential electrical systems.
2005-20-24: The FAA adopts a new airworthiness directive (AD) for certain SOCATA--Groupe AEROSPATIALE (SOCATA) Model TBM 700 airplanes. This AD requires you to inspect the fuselage skin in the VHF1 antenna mounting area for cracks and loose rivets. This AD also requires you to modify the area if you find cracks or loose rivets. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. We are issuing this AD to detect and correct cracks in the fuselage skin, which could result in loss of aircraft pressurization. Loss of aircraft pressurization could lead to flight crew incapacitation.
2016-22-14: Hydraulic tube
2001-26-12: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747-100, 747-200, 747-300, and 747SR series airplanes powered by General Electric CF6-45/50 or Pratt & Whitney JT9D-70 series engines, that currently requires a detailed visual inspection of the outboard diagonal brace for heat damage and cracking; and follow-on repetitive inspections and corrective actions, if necessary. This amendment requires accomplishment of the previously optional replacement of any existing sealant with heat-resistant sealant as terminating action for the repetitive inspections required by this AD. This amendment is prompted by reports of heat damage to the forward end of the diagonal brace after accomplishment of a previous strut and wing modification. The actions specified by this AD are intended to prevent heat damage to the diagonal brace, which could cause cracking, fracture, and possible loss of the diagonal brace load path and consequent separation of the strut and engine from the airplane.
97-21-13: This amendment adopts a new airworthiness directive (AD), applicable to all Lockheed Model 382 series airplanes, that requires revising the Airplane Flight Manual (AFM) to prohibit the positioning of the power levers below the flight idle stop, and to provide a statement of the consequences of positioning the power levers below the flight idle stop. This amendment is prompted by incidents and accidents involving airplanes equipped with turboprop engines in which the propeller beta was used improperly during flight. The actions specified by this AD are intended to prevent loss of airplane controllability, or engine overspeed and consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
83-04-06: 83-04-06 BRITISH AEROSPACE, AIRCRAFT GROUP, SCOTTISH DIVISION: Amendment 39-4574. Applies to Model B.121 series airplanes (all serial numbers) certificated in any category. COMPLIANCE: Required as indicated unless already accomplished. To preclude failure of the engine mounting structure, within the next 100 hours time-in- service after the effective date of this AD or upon accumulating 1000 hours time-in-service, whichever occurs later, and thereafter at intervals not to exceed 50 hours time-in-service from the last inspection, accomplish the following: (a) Visually inspect the engine mounting structure for cracks in accordance with the "Action" Section of British Aerospace, Aircraft Group, Scottish Division, Service Bulletin Number B121/81, Issue 2, dated December 3, 1980, or an FAA approved equivalent. (b) If a crack is found in the engine mounting structure, prior to further flight, repair or replace the engine mount in accordance with instructions providedby British Aerospace, Dulles International Airport, Washington, D.C., phone 703-435-9100, and approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium. (c) The intervals between the repetitive inspections required by this AD may be adjusted up to 10 percent of the specified interval to allow accomplishing these inspections concurrent with other scheduled maintenance of the airplane. (d) Operators who have not kept records of hours time-in-service of the engine mounting structure must substitute airplane hours time-in-service in lieu thereof. (e) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. (f) An equivalent method of compliance with this AD if used must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. This amendment becomes effective on March 7, 1983.
86-23-52 R2: 86-23-52 R2 LOCKHEED CALIFORNIA COMPANY: Amendment 39-5605. Applies to Model L-1011-385 series airplanes certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent wing rear spar failure due to fatigue cracking, accomplish the following: A. Within 40 landings after the effective date of this AD, or prior to accumulation of 6,000 landings, whichever occurs later, unless already accomplished within the last 260 landings, and thereafter at intervals not to exceed 300 landings, inspect the wing rear spar in accordance with the ultrasonic inspection procedures specified in Section 2, Accomplishment Instructions of Lockheed Service Bulletin 093-57-A181, Revision 3, dated December 11, 1986, or later FAA- approved revision. Ultrasonic inspections accomplished in accordance with Lockheed Service Bulletin 093-57-A181, Revision 1, dated November 20, 1986, or Revision 2, dated November 26, 1986, prior to receipt of telegraphic AD T86-23-52 R1, satisfies the initial ultrasonic inspection requirements of this paragraph. B. If a crack is found, repair before further flight in a manner approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. C. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer, may obtain copies upon request to Lockheed-California Company, P. O. Box 551, Burbank, California 91520, Attention: Commercial Order Administration, Dept. 65-33, U-33, B-1. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. This Amendment becomes effective May 1, 1987, as to all persons, except those persons to whom it was made immediately effective by telegraphic AD T86-23-52-R1, issued December 18, 1986.
2005-17-08: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A321 series airplanes. This AD requires repetitive measurements for correct control rod gap of the hold-open mechanism of all emergency doors, and corrective actions if necessary. This AD also requires replacing the control rods with new, improved control rods, which would terminate the repetitive measurements. This AD results from a report that an operator found it impossible to lock emergency doors 2 and 3 in the open position. We are issuing this AD to prevent failure of the emergency doors to lock in the open position, which could interfere with passenger evacuation during an emergency.
97-19-18: This amendment supersedes an existing airworthiness directive (AD), applicable to AlliedSignal Inc. (formerly AiResearch and Garrett) TSCP700-4B and -5 Series Auxiliary Power Units (APUs), that currently requires restretching the first stage low pressure compressor (LPC) tie rods, or replacing affected disks at or before 8,000 cycles since new (CSN). This amendment requires removing from service affected disks, replacing them with serviceable parts, and establishing a life limit of 8,000 CSN for affected disks. This amendment is prompted by a report of a first stage LPC disk rim separation due to low cycle fatigue on an APU that had its tie rods restretched in accordance with the current AD. The actions specified by this AD are intended to prevent first stage LPC disk rim separation due to low cycle fatigue, which could result in an uncontained APU failure and damage to the aircraft.
2016-07-19: We are adopting a new airworthiness directive (AD) for certain Technify Motors GmbH (type certificate previously held by Thielert Aircraft Engines GmbH) TAE 125-02-99 and TAE 125-02-114 reciprocating engines. This AD requires removal of affected fuel feed pumps. This AD was prompted by reports of in-flight shutdowns on TAE 125-02 engines. We are issuing this AD to prevent failure of the fuel feed pump, damage to the engine, and damage to the airplane.
2001-26-14: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Dornier Model 328 series airplanes, that currently requires modification of certain Honeywell GP-300 guidance and display controllers. That AD was prompted by reports of smoke and fumes emitting from the Honeywell GP-300 guidance and display controller due to a defective light bulb; and a report of failure of the autopilot to disconnect manually. The actions specified by this AD are intended to prevent a defective light bulb from causing a short circuit that emits smoke and fumes into the cockpit; or causing damage to the circuit cards and various components, which may lock the autopilot into the engaged mode. Locking of the autopilot into the engaged mode could lead to the inability of the pilot to disconnect the autopilot, which could result in reduced controllability of the airplane. This amendment requires verification of proper installation of the modification, and repair, if necessary. The incorporation by reference of Honeywell Service Bulletin 7015327-22-4, dated March 31, 1997, as listed in the regulations, is approved by the Director of the Federal Register as of February 8, 2002. The incorporation by reference of Honeywell Service Bulletin 7015327-22-2, dated March 4, 1996, as listed in the regulations, was approved previously by the Director of the Federal Register as of June 26, 1996 (61 FR 29465, June 11, 1996).
2016-22-08: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Deutschland GmbH (Airbus Helicopters) Model MBB-BK 117 C-2 helicopters. This AD requires inspecting each terminal lug and replacing any lug that has discoloration, corrosion, incorrect crimping, or incorrect installation. This AD was prompted by the discovery that terminal lugs with incorrect crimping may have been installed on these helicopters. The actions of this AD are intended to detect incorrectly installed or crimped terminal lugs and prevent contact resistance and reduced gastightness between the wire and terminal lug, subsequent loss of electrical power, and an electrical fire.
97-20-04: This amendment adopts a new airworthiness directive (AD) that is applicable to Enstrom Helicopter Corporation (Enstrom) Model F-28A, 280 and certain serial-numbered F-28C and 280C helicopters. This action requires an inspection of the voltage control system and an owner/operator (pilot) cockpit check of the amperage of the electrical system. If certain Prestolite- manufactured components are installed, additional tests and actions are required before further flight and at each pre-flight run-up and annual inspection thereafter. A terminating action is provided by replacing the existing voltage control system with a transistorized system. This amendment is prompted by 14 reports of voltage control system problems, including one incident in which smoke emanated from the radio panel during flight, forcing the pilot to make an emergency landing. The actions specified in this AD are intended to prevent an electrical overload and a failure of the voltage regulator and over-voltage relay, that could result in an inflight fire, and subsequent forced landing of the helicopter.
97-19-13: This amendment supersedes an existing airworthiness directive (AD) 94-23-03, applicable to Pratt & Whitney (PW) JT8D-200 series turbofan engines, that currently requires installation and periodic inspection of temperature indicators installed on the No. 4 and 5 bearing compartment scavenge oil tube and performance of any necessary corrective action. This amendment requires the installation and periodic inspection of temperature indicators to all PW JT8D-200 series engines, including those incorporating the containment hardware specified in AD 93-23-10. This amendment is prompted by a report of an uncontained turbine failure due to a high pressure turbine (HPT) shaft fracture on an engine that had the containment hardware installed. The actions specified by this AD are intended to prevent fracture of the HPT shaft, which can result in uncontained release of engine fragments, engine fire, inflight engine shutdown, or possible aircraft damage. The incorporation by referenceof PW Alert Service Bulletin (ASB) No. 5944, Revision 2, dated June 8, 1992, was previously approved by the Director of the Federal Register as of January 4, 1995 (59 FR 61789). The incorporation by reference of PW ASB No. 5944, Revision 3, dated December 16, 1994, is approved by the Director of the Federal Register as of October 24, 1997.
77-06-05: 77-06-05 CESSNA: Amendment 39-2856. Applies to Model 340A (Serial Numbers 340A0040 thru 340A0225, 340A0229 and 340A0230) airplanes. To preclude a fire hazard that could result from oxygen coming in contact with an improper lubricant which may have been used in the assembly of the oxygen system, accomplish the following: A) Prior to further flight: 1. Deactivate the oxygen system by disconnecting the control cable at the oxygen regulator and safety the regulator control in the off position. 2. Install a temporary placard on the instrument panel in full view of the pilot which reads as follows: "OXYGEN INOPERATIVE" "DO NOT OPERATE ABOVE 23,500 FEET" and operate the airplane in accordance with the placard limitation. 3. Install a tag on the oxygen filler line assembly with wording that prohibits servicing of the oxygen system. B) Within the next 25 hours' time in service after the effective date of this AD, repair and clean the oxygen system in accordance with Cessna Service Letter ME77-3, dated February 16, 1977, or later approved revisions. When this paragraph has been accomplished, Paragraph A is no longer applicable. C) Airplanes may be flown in accordance with FAR 21.197 to a location where Paragraph A may be accomplished. D) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This Amendment becomes effective March 31, 1977, to all persons except those to whom it was made effective earlier by air mail letters dated March 3, 1977, which were sent to the owners of Cessna Model 340A airplanes.
76-19-03: 76-19-03 HUGHES HELICOPTERS: Amendment 39-2725. Applies to Hughes Model 369H, 369HS, 369HE and 369HM helicopters, certificated in all categories, equipped with shock mounted stabilizer strut assembly P/N 369A2001-601. Compliance required as indicated unless already accomplished. To prevent fatigue failures of the damper plunger which could result in the loss of the stabilizer strut and possible contact with the tail rotor, accomplish the following: (a) Within 25 hours time in service after the effective date of this AD, disassemble the stabilizer strut P/N 369A2001-601 and determine if the damper plunger P/N 369A2130 or P/N 369A2130-3 has cut threads in accordance with Hughes Service Information Notice HN102.1 dated August 25, 1976 or later FAA-approved revision. (b) If the damper plunger is found to have cut threads during the inspection required by paragraph (a), before further flight, either replace the damper plunger with a damper plunger with rolled threads, or inspect the threaded area for cracks using the dye penetrant or magnetic particle inspection method. (1) If cracks are found, before further flight, replace the damper plunger with a damper plunger, P/N 369A2130 or P/N 369A2130-3, with rolled threads. (2) If cracks are not found, within 100 hours additional time in service after the inspection required by paragraph (a), replace the damper plunger with a damper plunger, P/N 369A2130 or P/N 369A2130-3, with rolled threads. (c) Equivalent inspection methods or alternate replacement parts may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. (d) Special flight permits may be issued in accordance with FAR's 21.197 and 21.199 to operate helicopters to a base for the accomplishment of the inspections required by this AD. This amendment becomes effective September 24, 1976.
91-03-12: 91-03-12 BELL HELICOPTER TEXTRON, INC. (BHTI): Amendment 39-6856. Docket No. 90-ASW-3. Applicability: All Model 206A, 206B, 206L, 206L-1, and 206L-3 helicopters equipped with emergency float bags, part numbers (P/N) 206-050-248-107, -109 and -111 manufactured prior to September 1, 1989. These float bags are used in BHTI emergency float kits 206-706-210 and 206-706-211. Compliance: Required within the next 100 hours' time in service after the effective date of this AD or upon installation of float bags from spares, unless already accomplished. To prevent unequal float inflation which could result in aircraft rollover and impede emergency egress after an emergency water landing, accomplish the following: (a) Inspect each float bag to determine if any square body, brass type inflation valves, P/N 222-336-101-19 or -23, are installed. If any of these valves are found, install an appropriate flow restrictor in accordance with the instructions in Appendix I of this AD for Models 206A and B, or Appendix II of this AD for Models 206L, L-1 and L-3, as applicable. (b) An alternative method of compliance, which provides an equivalent level of safety, may be used if approved by the Manager, Rotorcraft Certification Office, ASW-170, FAA Southwest Region, Fort Worth, Texas 76193-0170, telephone (817) 624-5170. (c) In accordance with FAR Sections 21.197 and 21.199, flight is permitted to a base where the requirements of this AD may be accomplished. NOTE: Appendix I, which is not reprinted in this AD, includes material from Bell Helicopter Textron, Inc., (BHTI) Alert Service Bulletin No. 206-89-49, and Appendix II, which is not reprinted in this AD, includes material from BHTI Alert Service Bulletin No. 206L-89-63, both dated October 10, 1989. A copy of the service bulletins may be obtained from BHTI, P.O. Box 482, Fort Worth, Texas 76101. This amendment (39-6856, AD 91-03-12) becomes effective on February 28, 1991.
2005-17-09: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747, 757, 767, and 777 series airplanes. That AD currently requires modifying certain drip shields located on the flight deck, and follow-on actions. This new AD removes certain airplanes that are included in the applicability statement of the existing AD, and requires modifying additional drip shields on the flight deck of certain other airplanes. This AD is prompted by a determination that certain airplanes have drip shields that are not adequately resistant to fire. We are issuing this AD to prevent potential ignition of the moisture barrier cover of the drip shield, which could propagate a small fire that results from an electrical arc, leading to a larger fire. \n\nDATES: This AD becomes effective September 27, 2005. \n\n\tThe incorporation by reference of certain publications listed in the AD is approved by the Director of the Federal Register as of September 27, 2005.On February 2, 2001 (65 FR 82901, December 29, 2000), the Director of the Federal Register approved the incorporation by reference of certain other publications listed in the AD.
2001-23-12 R1: This document revises an existing airworthiness directive (AD) that applies to certain Saab Model SAAB SF340A and SAAB 340B series airplanes. That AD currently requires a one-time review of records to determine whether an airplane has been repainted since its delivery from the factory; and a one-time inspection to detect damage associated with improper preparation for the repainting, and corrective action if necessary. The actions specified in that AD are intended to detect and correct damage to the aluminum skin of the airplane, which could result in a weakening of the structure of the airplane. This document corrects certain conditional requirements of the existing AD. The incorporation by reference of certain publications listed in the regulations was approved previously by the Director of the Federal Register as of December 31, 2001 (66 FR 58927, November 26, 2001).
2005-17-03: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD requires installing additional shielding of the hydraulic lines in the wing box area. This AD results from the determination that the additional hydraulic line shields will protect the lines from possible impact by tire debris if the tire tread fails. We are issuing this AD to prevent damage to the hydraulic lines and subsequent leakage from the two hydraulic systems, which could result in loss of braking capability on the affected side of the airplane, asymmetrical braking, and reduced directional control--particularly during a rejected takeoff.
76-19-01: 76-19-01 BRITISH AIRCRAFT CORPORATION: Amendment 39-2723. Applies to Viscount Model 744, 745D, and 810 Series airplanes, certificated in all categories. Compliance is required as indicated. To prevent possible failure of the elevator spring servo tab control mechanism, accomplish the following: (a) Replace the spigot bracket, P/N 70120-367, that attaches the elevator spring tab system bellcrank to the left elevator torque tube with a new bracket of the same part number as follows: (1) If neither paragraph (b) or (c) of AD 71-4-2 has been complied with prior to the effective date of this AD, replace the bracket within the next 100 hours time in service after the effective date of this AD or prior to the accumulation of 12,000 hours total time in service on the bracket, whichever occurs later. (2) If paragraph (b) or (c) of AD 71-4-2 has been complied with prior to the effective date of this AD, replace the bracket at the latest of the following:(i) Within the next 50 hours time in service after the effective date of this AD. (ii) Within 1000 hours time in service after complying with AD 71-4-2 if the bracket was not replaced in complying with that AD. (iii) Prior to the accumulation of 12,000 hours total time in service on the bracket. (3) After complying with paragraph (a)(1) or (a)(2) of this AD, as appropriate, continue to replace the brackets prior to the accumulation of 12,000 hours total time in service after installation. (b) Operators who have not kept records of total hours time in service on individual spigot brackets, P/N 70120-367, must substitute in lieu thereof the total hours time in service of the airplane. This supersedes Amendment 39-1154 (36 FR 2562), AD 71-4-2. This amendment becomes effective October 15, 1976.
2005-17-02: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 777-200 and -300 series airplanes. This AD requires inspecting the valve control and indication wire bundles of the fuel system of the wing rear spar for discrepancies, and corrective action if necessary. This AD is prompted by reports of six incidents of the wire bundles chafing against the rear spar stiffeners outside the fuel tank. We are issuing this AD to prevent this chafing, which could result in wire damage leading to a short circuit, subsequent ignition of flammable vapors, and possible uncontrollable fire during fueling or flight.
97-19-12: This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A,-11, -15, -17, and -17R series turbofan engines, that requires initial and repetitive fluorescent penetrant and eddy current inspections of 4th stage low pressure turbine (LPT) hubs for cracks, and, if necessary, replacement with serviceable parts. This amendment is prompted by a report of an uncontained 4th stage LPT blade release. The actions specified by this AD are intended to prevent a 4th stage LPT blade release due to hub cracking, which can result in an uncontained engine failure and damage to the aircraft.