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2014-16-20: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes. This AD was prompted by an analysis of the impacts of extended service goal activities on Airbus Model A300 series airplanes. This AD requires revising the maintenance or inspection program. We are issuing this AD to prevent failure of flight critical systems.
90-08-06: 90-08-06 AEROSPATIALE: Amendment 39-6566. Docket No. 89-NM-251-AD. Applicability: All Model ATR42 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent failure of the main landing gear wheel, due to cracked spokes, accomplish the following: A. For wheels with Loral Part Number (P/N) 5006856, 5006856-1, and 5006856-2, having serial numbers OCT83-001 through OCT86-377, with the exception of serial numbers OCT86-001 through OCT86 071: Within 7 days or 100 landings after the last inspection in accordance with AD 88-09-04, whichever occurs later, perform a visual inspection of the inboard wheel halves, with the airplane jacked, to detect cracks, in accordance with Loral Systems Group Service Bulletin ATR42-32-40-1, Revision 2, dated June 23, 1987. Repeat the inspection at intervals not to exceed 7 days or 100 landings, whichever occurs later. If a crack is detected, only one additional landing may be made after the detection of that crack before the cracked inboard wheel half must be replaced. B. For wheels with Loral Part Number (P/N) 5006856, 5006856-1, and 5006856-2, having serial numbers OCT83-001 through OCT86-377, with the exception of serial numbers OCT86-001 through OCT86-071: At each tire change, perform an eddy current inspection or other nondestructive test of the inboard wheel halves to detect cracks, in accordance with Loral Systems Group Service Bulletin ATR42-32-40-1, Revision 2, dated June 23, 1987. Replace any cracked inboard wheel half before further flight. NOTE: MLG wheels with Loral Part Number 5006856-2, serial numbers OCT86-001 through OCT86-071 and NOV86-072 through AUG87-376, are factory built new wheels, and are not subject to the repetitive inspection requirements of paragraphs A. and B., above. C. Replacement of inboard wheel halves with a new reinforced half wheel and replacement of the existing hub spacer with a modified hub spacer, in accordance with Aerospatiale Service Bulletin ATR42-32-0017, dated January 19, 1988, or Revision 1, dated May 20, 1988 (reference Loral Service Bulletin ATR42-32-40-4, dated July 15, 1987), constitutes terminating action for the repetitive inspection required by paragraphs A. and B., above. 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. E. 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 servicedocuments from the manufacturer may obtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. 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. This amendment supersedes Amendment 39-5907, AD 88-09-04. This amendment (39-6566, AD 90-08-06) becomes effective on May 11, 1990.
2000-02-17: This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce plc RB211 Trent 768-60, 772-60, and 772B-60 series turbofan engines. This action requires initial and repetitive visual inspections for flank wear on intermediate pressure turbine (IPT) shaft splines and intermediate pressure compressor (IPC) rear stub shaft splines. Components that show excessive flank wear must be replaced with serviceable parts. This amendment is prompted by reports of worn IPT shaft splines discovered at overhaul. The actions specified in this AD are intended to prevent IPT and IPC shaft spline flank wear, which could result in loss of drive between the IPT and IPC, leading to an IPT overspeed and possible disk burst, uncontained engine failure, and potential damage to the aircraft.
2014-16-10: We are superseding airworthiness directive (AD) 2013-12-01 for all Rolls-Royce plc (RR) model RB211 Trent 768-60, 772-60, and 772B-60 turbofan engines. AD 2013-12-01 required a one-time ultrasonic inspection (UI) of low-pressure (LP) compressor blades with more than 2,500 flight cycles since new or last inspection. This AD requires initial and repetitive UIs of the affected LP compressor blades. This AD was prompted by LP compressor blade partial airfoil release events. We are issuing this AD to prevent LP compressor blade airfoil separations, damage to the engine, and damage to the airplane.
2006-04-02: The FAA is adopting a new airworthiness directive (AD) for all EMBRAER Model EMB-135 airplanes; and Model EMB-145, -145ER, -145MR, - 145LR, -145XR, -145MP, and -145EP airplanes. This AD requires repetitive inspections of the pitot static heating relay K0057 for damage to the pin-type contacts, relay enclosure, and finishing material and corrective actions if necessary. This AD also requires doing a terminating modification, which ends the repetitive inspections. This AD results from a report of a burning drain hose and smoke caused by an overheated pitot static heating relay. We are issuing this AD to prevent over-heating of a certain pitot static heating relay, which could result in the burning of the windowsill drain hoses and consequent smoke or fire in the airplane cockpit.
2000-02-07: This amendment adopts a new airworthiness directive (AD), applicable to all Bombardier Model DHC-7-100 series airplanes, that requires repetitive high frequency eddy current inspections to detect cracks on the locking pin fittings of the baggage door and locking pin housings of the fuselage; repetitive detailed visual inspections to detect cracks of the inner door structure on all four door locking attachment fittings; and corrective actions, if necessary. In lieu of accomplishing the corrective actions, this amendment also provides a temporary option, for certain cases, for revising the Airplane Flight Manual (AFM), and installing a placard. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct fatigue cracking of the baggage door fittings and the support structure, which could result in structural failure, and consequent rapiddecompression of the airplane during flight.
86-08-05 R1: 86-08-05 R1 CFM INTERNATIONAL: Amendment 39-5281 as amended by Amendment 39-5339. Applies to CFM International (CFMI) CFM56-3/-3B series turbofan engines. Compliance is required within the next 80 hours time in service (TIS) after the effective date of this AD , unless already accomplished. To prevent engine shutdown from radial drive shaft disengagement, accomplish the following: Inspect oil distributor Part Number (P/N) 335-305-800-0 and spirolock P/N 649-363-137-0 in accordance with CFMI CFM56-3/-3B Service Bulletin (SB) 72-205 Revision 3, dated April 16, 1986, or FAA approved equivalent. However, the SB torque check increases from 50 inch-lbs. to 100 inch-lbs. and a minimum of 2 hours cool down time is required prior to inspection for the purpose of this AD. (a) If the oil distributor is loose and spirolock is serviceable, either re-inspect the spirolock for serviceability at intervals not to exceed 125 hours TIS since last inspection or replace the oil distributorin accordance with SB 72-205, Revision 3, and reinspect within 375 hours. (b) If the oil distributor is loose and spirolock is not serviceable, replace the spirolock prior to further flight and either reinspect the spirolock for serviceability within 250 hours TIS or replace the oil distributor and reinspect within 375 hours. (c) If the oil distributor is tight, reinspect within 375 hours. Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, Aircraft Certification Division, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Engine Certification Office, New England Region, may adjustthe compliance time specified in this AD. CFMI CFM56-3/-3B SB 72-205, Revision 3, dated April 16, 1986, identified and described in this document, is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received this document from the manufacturer may obtain copies upon request to CFM International, 1 Neumann Way, Cincinnati, Ohio 45215. This document also may be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Rules Docket Number 86-ANE-13, Room Number 311, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays. This amendment amends Amendment 39-5281 (44 FR 11034), AD 86-08-05, which became effective April 15, 1986. This Amendment 39-5339 becomes effective on July 7, 1986.
96-09-18: This amendment adopts a new airworthiness directive (AD), applicable to all Jetstream Model BAe ATP 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.
2014-16-14: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, and -900 series airplanes. This AD was prompted by reports in which a single, undetected, erroneous radio altimeter output caused the autothrottle to enter landing flare retard mode prematurely on approach. This AD requires removing certain autothrottle computers and installing a new or reworked autothrottle computer. We are issuing this AD to prevent a single, undetected, erroneous radio altimeter output from causing premature autothrottle landing flare retard and subsequent loss of automatic speed control, which could result in loss of control of the airplane.
93-05-11: 93-05-11 SCHWEIZER AIRCRAFT CORPORATION AND HUGHES HELICOPTERS, INC.: Amendment 39-8515. Docket No. 92-ASW-47. Applicability: Model 269A helicopters with fuel injected engines; all Model 269A-1 and 269B helicopters; and Model 269C helicopters, serial numbers (S/N) 0004 through 1480 and 1482 through 1486; equipped with an engine-driven fuel pump drain tube assembly (tube assembly), part number (P/N) 269A8326-95, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent a restriction to the movement of the engine throttle control linkage that could result in loss of control of engine power due to tube assembly interference, accomplish the following: (a) Within 5 hours time in service after the effective date of this AD, perform a one-time inspection of the length of the tube assembly, P/N 269A8326-95, in accordance with Part I of Schweizer Aircraft Corporation (Schweizer) Service Bulletin B-235.1, dated March 20, 1992 (SSB). If the tube assembly length is less than 7.50 inches, before next flight, install tube assembly, P/N 269A8326-235, with a clamp, P/N MS21333-98, in accordance with Part III of the SSB. (b) Within 5 hours time in service after the effective date of this AD, and thereafter at intervals not to exceed 25 hours time in service from the last check, check the tube assembly, P/N 269A8326-95, for security and clearance from the throttle linkage as follows: (1) Move the throttle linkage from fully open to fully closed and verify that the tube assembly is not loose and does not interfere with movement of the throttle linkage. (2) If the tube assembly interferes with movement of the throttle linkage, before next flight-- (i) Install tube assembly, P/N 269A8326-235, with a clamp, P/N MS21333-98, in accordance with Part III of the SSB; or (ii) Secure tube assembly, P/N 269A8326-95, in accordance with Part II b of the SSB and conduct repetitive checks as prescribed by this paragraph. (3) After the initial check, the repetitive check contained in this paragraph may be performed by the pilot and must be recorded in accordance with FAR 43.9. (c) Within 6 months after the effective date of this AD, replace the tube assembly, P/N 269A8326-95, with an improved tube assembly, P/N 269A8326-235, and clamp, P/N MS21333-98, in accordance with Part III of the SSB. (d) Installation of the improved tube assembly, P/N 269A8326-235, and clamp, P/N MS21333-98, constitutes terminating action for the requirements of this AD. (e) 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, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, New YorkAircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Manager, New York Aircraft Certification Office. (f) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the helicopter to a location where the requirements of this AD can be accomplished. (g) The inspections and modifications shall be done in accordance with Schweizer Service Bulletin B-235.1, dated March 20, 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 Schweizer Aircraft Corporation, P.O. Box 147, Elmira, New York 14902. Copies may be inspected at the FAA, Office of the Assistant Chief Counsel, 4400 Blue Mound Road, Bldg. 3B, Room 158, Fort Worth, Texas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (h) This amendment becomes effective May 25, 1993.
2000-02-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, equipped with ground spoiler actuators having part number 1059A0000-02, that requires removal of the gland attachment bolts of the ground spoiler actuator and replacement with new bolts installed with higher torque. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent hydraulic fluid leakage due to loose or broken gland attachment bolts, and consequent loss of the main hydraulic system.
87-25-01: 87-25-01 VALENTIN GmbH: Amendment 39-5762. Applies to Model Taifun 17E motor gliders certificated in any category. Compliance is required as indicated unless already accomplished. To prevent failure in the air brake, wheel brake, or rudder control systems, accomplish the following: (a) Within the next 10 hours time-in-service after the effective date of this AD and thereafter at intervals not to exceed 25 hours time-in-service after the last inspection, visually inspect the welded joints of the air brake actuating lever/torsion axle, actuating lever of brake cylinder/torsion axle, and pedal lever arms/pedal torsion axles, using a 5 power or greater magnifying glass, for cracks or deformation; reference Action 1 of Valentin TN No. 11/818, dated March 9, 1987. (b) If cracked or deformed parts are found during the inspection required by Paragraph (a) of this AD, before further flight, replace the damaged parts with serviceable parts of the same part number.(c) Within the next 10 hours time-in-service after the effective date of this AD, exchange Glider Flight Manual pages 36/37/40/46 for same pages, February 1987 edition, and Instructions for Continued Airworthiness page 64 for same page, February 1987 edition, in accordance with Action 2 of Valentin TN No. 11/818 dated March 9,1987. Upon request, an equivalent means of compliance with the requirements of this AD may be-approved by the Manager, Brussels Aircraft Certification Office, Europe, Africa and Middle East Office, FAA, c/o American Embassy, 15 Rue de Ia Loi B-1040 Brussels, Belgium, or the Manager, New York Aircraft Certification Office, Aircraft Certification Division, New England Region, FAA 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Brussels Aircraft Certification Office, or the Manager, New York Aircraft Certification Office, mayadjust the compliance time specified in this AD. Valentin TN No. 11/818, dated March 9, 1987; Glider Flight Manual pages 36/37/40/46, February 1987 edition; and Instructions for Continued Airworthiness page 64, February 1987 edition, identified and described in this document, are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Morris Aviation Ltd., Statesboro Airport, Box 718, Statesboro, Georgia 30458. These documents also may be examined at the Rules Docket, Office of the Regional Counsel, Room 311, FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, between the hours of 8:00 am. and 4:30p.m., Monday through Friday except federal holidays. This amendment becomes effective on December 3, 1987.
60-20-03: 60-20-03 LOCKHEED: Amdt. 202 Part 507 Federal Register September 28, 1960. Applies to All Model 188 Series Aircraft Serial Numbers 1002, 1004 Through 1102, 1104 Through 1126, 2001 Through 2014. Compliance required within 1,000 hours' time in service after September 28, 1960. Insufficient resistance to flammability of components of the AC Bus Transfer and Distribution Box has resulted in a fire. Temperatures within the AC Bus Transfer and Distribution Box and within the main electrical service center higher than that for which some of the equipment in these locations is designed contributes to over-temperature of the equipment. Accomplish those portions of Lockheed Electra Alert Service Bulletins 408 and 287, revision 1, summarized below or equivalent: (a) Within the AC Transfer and Distribution Box, replace the black vinyl covered flexible bus assemblies, which interconnect the circuit breakers, with jumpers made of MIL-W- 7139 wire. (b) Replace, with MIL-W-7139wire, all size 6, 8, 10 and 12 wires which route within and between sections of the AC Transfer and Distribution Box except power wires to propeller deice power relay. (c) Apply a fire retardant coating, Magna Coatings and Chemical Co. Laminar X- 500, to the exposed and accessible portion of the inside and outside of the following impregnated fiberglass boxes: AC Bus Transfer and Distribution Box and its covers; forward load center bus box and cover; forward load center circuit breaker shrouds; flap asymmetry control panel cover; hydraulic pump shroud boxes. (d) Replace, with molded melamine terminal blocks, the stepped terminal block assemblies which serve as busses in the three upper compartments of the AC Bus Transfer and Distribution Box. (e) Remove the short bus bars which serve as extensions for terminals T1 and T3 of relays No. 1 and No. 3. (f) Replace the bus bar assemblies on terminals T2 of relays 1 and 3 with a type which does not have plastic in compression.(g) Remove the short bus bars and terminal block assembly from terminals T1, T2 and T3 of relay No. 2. (h) Modify the terminal block assembly between the external power feeders and relay No. 6 to remove plastic in compression. (i) Within the AC Bus Transfer and Distribution Box, route the control wires for the generators separate from all power wires. (j) Relocate the essential bus alternate feeder circuit breaker to a housing to be attached to the left side of the AC Bus Transfer and Distribution Box. (k) Provide forced air cooling of the electrical load center by installing: two destratification fans; ducting from the fans to the AC Bus Transfer and Distribution Box; ducting and controller to regulate overboard dumping of heated air; ventilation holes in the AC Transfer and Distribution Box. Install a shield to cover hydraulic connectors between fuselage Stations 540 and 549.5. (The portions of Lockheed Electra Alert Service Bulletins 408 and 287, revision 1,not summarized above are also approved.) Revised December 8, 1960.
2014-16-09: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 707 airplanes, Model 720 and 720B series airplanes, Model 727 airplanes, and Model 737-100, -200, and -200C series airplanes. This AD was prompted by a report of a fire that originated near the first officer's area and caused extensive damage to the flight deck on a different airplane model. This AD requires replacing the low-pressure oxygen hoses with non-conductive low- pressure oxygen hoses in the flight compartment. We are issuing this AD to prevent electrical current from inadvertently passing through an internal, anti-collapse spring of the low-pressure oxygen hose, which can cause the low-pressure oxygen hose to melt or burn, leading to an oxygen-fed fire and/or smoke in the flight deck.
93-09-11: 93-09-11 BEECH: Amendment 39-8577. Docket 92-NM-240-AD. Applicability: Model 400A airplanes; serial numbers RK-2 through RK-33, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural integrity of the aft fuel filler tank installation, accomplish the following: (a) Within 200 hours time-in-service after the effective date of this AD, inspect the aft fuel filler tank installation to verify installation of attachment clips, part numbers 128-920021-61 and 128-920021-63, in accordance with Beechcraft Service Bulletin 2468, dated October 1992. (1) If the attachment clips are installed, no further action is required by this AD. (2) If no attachment clips are installed, prior to further flight, install the attachment clips in accordance with the service bulletin. (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, Wichita Aircraft Certification Office (ACO), FAA, Small 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, Wichita ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita ACO. (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) The inspection and installation shall be done in accordance with Beechcraft Service Bulletin 2468, dated October 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 Beech Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-0085. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Small Airplane Directorate, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on June 17, 1993.
2014-16-15: We are adopting a new airworthiness directive (AD) for certain Turbomeca S.A. Makila 2A and Makila 2A1 turboshaft engines. This AD requires initial and repetitive visual inspections, and replacement of the splines of the high-pressure (HP) fuel pump/metering valve and the module M01 drive gear, if necessary. This AD was prompted by the failure of two HP fuel pumps that resulted in engine in-flight shutdowns. We are issuing this AD to prevent failure of the HP fuel pump, which could lead to an in-flight shutdown, damage to the engine, and forced landing or accident.
2000-02-14: This amendment supersedes Airworthiness Directive (AD) 98-13-10, which currently requires repetitively inspecting all engine exhaust muffler end plates (four total) for cracks on all Cessna Aircraft Company (Cessna) Model 182S airplanes, and replacing any muffler where an end plate is found cracked. AD 98-13-10 also requires fabricating and installing a placard that specifies immediate inspection of all engine exhaust muffler end plates any time the engine backfires upon start-up. This AD is the result of Cessna developing an improved design exhaust system for the Model 182S airplanes. This AD retains the actions of AD 98-13-10 on all affected airplanes, and requires replacing the exhaust system with an improved design exhaust system within a certain period of time, as terminating action for those requirements retained from AD 98-13-10. This AD also limits the effectivity to exclude those airplanes manufactured with the improved design exhaust system. The actions specified by this AD are intended to detect and correct damage to the engine exhaust mufflers caused by cracking and the high stresses imposed on the attachment of the exhaust system at the area the firewall, which could result in exhaust gases entering the airplane cabin with consequent crew and passenger injury.
93-23-12: 93-23-12 LEARJET, INC.: Amendment 39-8748. Docket 93-NM-191-AD. Applicability: Model 60 airplanes having serial numbers 60-002 through 60-021, inclusive, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent overheating of the auxiliary cabin and cockpit heaters, which could potentially result in a fire, accomplish the following: (a) Within 10 flight hours after the effective date of this AD, deactivate the auxiliary cabin and cockpit heating systems; and install a placard stating, "Cabin and Cockpit Heat Inop" adjacent to the AUX HT Switch (S44) on the co-pilot's switch panel; in accordance with Learjet Alert Service Bulletin SB A60-21-1, dated November 1, 1993. (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, Wichita Aircraft Certification Office (ACO), FAA, Small 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, Wichita ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita ACO. (c) Special flight permits may be issued in accordance with section 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The deactivation and placard installation shall be done in accordance with Learjet Alert Service Bulletin SB A60-21-1, dated November 1, 1993. 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, as of December 15, 1993 (58 FR 63060, November 30, 1993). Copies may be obtained from Learjet, Inc., P.O. Box 7707, Wichita, Kansas 67277-7707. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Wichita ACO, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on December 15, 1993.
52-04-08: 52-04-08 MARTIN: Applies to All Models 202 and 202A Aircraft. Compliance required not later than May 1, 1952. Relocate the anti-icing heater controls to the main bus. (Trans World Airlines Engineering Order 5759 covers this same subject.)
93-07-08: 93-07-08 AEROSPATIALE: Amendment 39-8540. Docket 92-NM-128-AD. Applicability: Model ATR42-300 and -320 series airplanes and Model ATR72-100 and - 200 series airplanes, as listed in Aerospatiale Service Bulletins ATR42-55-0005, Revision 2, dated October 28, 1991, and ATR72-55-1001, Revision 2, dated October 28, 1991; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced controllability of the airplane, accomplish the following: (a) Within 30 days after the effective date of this AD, remove the cotter pins on the left and right elevator tab hinges; recheck the torque of the nuts; and install correct size cotter pins, in accordance with Aerospatiale Service Bulletin ATR42-55-0005, dated November 9, 1990, or Revision 1, dated May 28, 1991, or Revision 2, dated October 28, 1991 (for Model ATR42-300 and -320 series airplanes); or Aerospatiale Service Bulletin ATR72-55-1001, dated November 9, 1990, or Revision 1, dated April 10, 1991, or Revision 2, dated October 28, 1991 (for Model ATR72-100 and -200 series airplanes); as applicable. (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. 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) The removal and installation shall be done in accordance with the following Aerospatiale service bulletins, as applicable, which contain the specified effective pages: Service Bulletin Referenced and Date Page Number Revision Level Shown on Page Date Shown on Page ATR42-55-0005, November 9, 1990 1-7 Original November 9, 1990 ATR42-55-0005, Revision 1, May 28, 1991 1-3, 5, 7 4, 6 1 Original May 28, 1991 November 9, 1990 ATR42-55-0005, Revision 2, October 28, 1991 1-3, 4, 6 5, 7 2 Original 1 October 28, 1991 November 9, 1990 May 28, 1991 ATR72-55-1001, November 9, 1990 1-7 Original November 9, 1990 ATR72-55-1001, Revision 1, April 10, 1991 1-2, 5, 7 3-4, 6 1 Original April 10, 1991 November 9, 1990 ATR7-55-1001, Revision 2, October 28, 1991 1-2 3-4, 6 5, 7 2 Original 1 October 28, 1991 November 9, 1990 April 10, 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 Aerospatiale, 316 Routede Bayonne, 31060 Toulouse, Cedex 03, France. 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. (e) This amendment becomes effective on May 26, 1993.
2014-16-16: We are adopting a new airworthiness directive (AD) for all Embraer S.A. Model ERJ 190-100 STD, -100 LR, -100 ECJ, -100 IGW, -200 STD, -200 LR, and -200 IGW airplanes. This AD requires, for certain airplanes, retorquing and replacing the pylon outboard and inboard lower link fittings. For all airplanes, this AD requires repetitive retorquing of the pylon outboard and inboard lower link fittings. This AD was prompted by a report of a loose lower link assembly on the left and right pylons. We are issuing this AD to prevent loss of a shear pin on the pylon outboard and inboard lower link fittings, which could result in failure of the fitting and consequent separation of the engine from the wing.
2000-02-09: This amendment adopts a new airworthiness directive (AD) that is applicable to Agusta Model AB412 helicopters with certain rescue hoists installed. This action requires replacing the rescue hoist hook assembly retention pin (retention pin) and periodically inspecting the rescue hoist. This amendment is prompted by an incident in which a rescue hoist hook assembly separated from a helicopter due to a missing retention pin. The actions specified in this AD are intended to prevent separation of the rescue hoist hook assembly from the helicopter due to failure of the retention pin. Loss of the rescue hoist hook assembly could result in loss of the person on the rescue hoist. Also, with the loss of the weight of the hoist cable assembly, the rescue hoist cable could become entangled with a main rotor or tail rotor blade, and result in damage or separation of a rotor blade and subsequent loss of control of the helicopter.
70-15-18: 70-15-18 MITCHELL INDUSTRIES, INC., doing business as EDO-AIRE MITCHELL: Amendment 39-1046. Applies to the Mitchell Century II, Century III (Serial Numbers 624 and below) and Stabilizer, automatic pilot and automatic aileron stabilizer instruments, and to Piper AutoControl III, Altimatic III and AutoFlite automatic pilot and automatic aileron stabilizer instruments installed in various light aircraft in accordance with the following Supplemental Type Certificates: AIRCRAFT MAKE SUPPLEMENTAL TYPE CERTIFICATE NUMBERS Aero Commander SA680SW Beech SA617SW SA742SW SA755SW SA800SW SA638SW SA745SW SA761SW SA824SW SA651SW SA754SW SA767SW SA837SW Cessna SA603SW SA624SW SA668SW SA784SW (See also Wren) SA606SW SA637SW SA669SW SA789SW SA607SW SA658SW SA709SW SA795SW SA621SW SA667SW SA737SW SA829SW deHavilland (See Riley 400) Helio SA615SW Maule SA693SW Piper SA511SW SA540SW SA596SW SA757SW SA525SW SA566SWSA662SW SA822SW SA532SW SA576SW SA707SW SA862SW SA533SW SA581SW SA756SW SA921SW Riley 400 (deHavilland modified per STC's SA120SO, SE163SO and SA164SO) SA676SW Wren (Cessna modified per SA791SW STC No. SA485SW) Compliance required within the next 25 hours' time in service after the effective date of this AD, unless already accomplished. To prevent slippage of servo bridle cable clamps and resultant binding of the control system, accomplish the following: Remove Servo Bridle Cable Clamps, Mitchell P/N 42A173 or 42A184, as applicable, and replace with new Servo Bridle Cable Clamps, Mitchell P/N 42A173-1 or 42A184-1, as applicable, in accordance with the installation instructions in Mitchell Industries, Inc. Service Bulletin No. MB-1 dated 2-11-68, revised as Edo-Aire Mitchell Service Bulletin No. MB-1 dated 6-1-70, or later FAA approved revision, or in accordance with instructions approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration. The revised bulletin may be obtained from Edo-Aire Mitchell, P.O. Box 610, Mineral Wells, Texas 76067. This Amendment becomes effective August 31, 1970.
2022-18-14: The FAA is superseding Airworthiness Directive (AD) 2017-19- 13, AD 2018-24-04, and AD 2019-23-02, which applied to certain Airbus SAS Model A330-200 series, A330-200 Freighter series, and A330-300 series airplanes. ADs 2017-19-13, 2018-24-04, and 2019-23-02 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by the FAA's determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require the actions in AD 2019-23-02, adds airplanes to the applicability, and requires revising the existing maintenance or inspection program, as applicable, to incorporate additional new or more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2014-15-21: We are superseding Airworthiness Directive (AD) 2006-26-06 for certain The Boeing Company Model 777-200 and -300 series airplanes equipped with Rolls-Royce engines. AD 2006-26-06 required repetitive inspections to detect cracks of the outer V-blades of the thrust reverser, and corrective action if necessary. AD \n\n((Page 48025)) \n\n2006-26-06 also provided for an optional terminating action for the repetitive inspections. This new AD adds, for airplanes on which the optional terminating action is done, repetitive inspections for cracking in the outer V-blade fittings of the hinge beam and latch beam ends of each thrust reverser half, and replacement of an affected thrust reverser half if necessary. This new AD also adds airplanes to the applicability. This AD was prompted by reports of cracked outer V- blade fittings at the hinge beam end of Rolls-Royce engine thrust reversers, on airplanes on which the optional terminating action was done. We are issuing this AD to preventseparation of a thrust reverser from the airplane during normal reverse thrust or during a refused takeoff, which could result in unexpected thrust asymmetry and a possible runway excursion.