Results
99-27-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B4-203 series airplanes. This action requires repetitive inspections of the attachment bolts of the brake bar on the main landing gear (MLG) to detect missing or damaged bolts, and replacement with new bolts, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent detachment of the brake bar from the MLG strut, which could result in failure of the main landing gear to extend.
99-24-08: This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 737-100, - 200, -300, -400, and -500 series airplanes, that currently requires, for certain airplanes, repetitive replacements of the airplane battery with a new or reconditioned battery and replacement of the battery charger with a new or serviceable battery charger; performing repetitive tests to determine the condition of a certain diode of the Generator Control Units (GCU); and corrective actions, if necessary. This amendment adds, for certain other airplanes, a requirement for repetitive replacements of the airplane battery with a new or reconditioned battery, and clarifies a diode test requirement. This amendment is prompted by an incident during which all electrical power was lost due to a combination of a weak or depleted battery and the failure of a certain diode of the GCU. The actions specified in this AD are intended to prevent failure of all electrically powered airplane systems, which could result in the inability to continue safe flight and landing.
97-07-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes. This action requires the deactivation of the avionics ground refrigeration unit (GRU) of the air conditioning system until a modification of avionics ventilation circuit and the GRU is accomplished. This amendment is prompted by reports of water accumulation found in the Air Data/Inertial Reference Unit (ADIRU) trays of the avionics rack; the accumulation is the result of operation of the GRU in high ambient humidity. The actions specified in this AD are intended to prevent water accumulating in this area, which could result in the failure of the ADIRU and consequent loss of air data and navigational information to the flightcrew.
98-09-18: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Industrie Model A320 and A321 series airplanes, that requires replacement of two elevator aileron computers (ELAC) with ELAC s that contain new software. This amendment is prompted by a report indicating difficulty maintaining the intended flight path during landing in turbulent conditions. The actions specified by this AD are intended to prevent situations that could lead to reduced controllability of the airplane due to adverse airplane-pilot coupling characteristics.
98-11-23: This amendment adopts a new airworthiness directive (AD), applicable to certain CASA Model CN-235 series airplanes, that requires modification of certain fastener holes of the center wing. 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 fatigue cracking in this area, which could result in reduced structural integrity of the wing.
98-01-17: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires replacement of a capacitor of the main landing gear (MLG) circuitry with a new electrolytic capacitor having a tantalum casing. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent the failure of the landing gear to retract properly as a result of failure of a capacitor in the MLG circuitry and subsequent power interruption.
2000-02-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires repetitive inspections to detect broken fasteners and cracking of the forward edge frame for main entry door number 3, and repair, if necessary. This amendment is prompted by reports of fatigue cracks at the inner chord and web of the body station 1265 edge frame between stringers 23 and 27. The actions specified by this AD are intended to detect and correct such cracking, which could result in rapid depressurization of the airplane.
98-23-10: This amendment adopts a new airworthiness directive (AD) that applies to all Burkhart GROB Luft-und Raumfahrt GmbH (Grob) Model G 109B gliders. This AD requires inspecting the engine mounting frame for paint scratches and damage (abrasions, notches, or chafing); and repairing any paint scratches, and repairing or replacing any engine mounting frame that is found damaged. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to detect and correct damage to the engine mounting frame, which could result in failure of the engine mount structure with consequent loss of the engine.
2000-15-05: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, -10F, -15, -30, -30F (KC-10A and KDC-10 military), -40, and -40F series airplanes, that requires a one-time inspection of the wiring and wire bundles of the aft main avionics rack (MAR) to determine if the wires are damaged, or riding or chafing on structure, clamps, braces, standoffs, or clips, and to detect damaged or out of alignment rubber cushion inserts of the wiring clamps; and corrective actions, if necessary. This amendment is prompted by an incident in which the automatic and manual cargo door test in the cockpit was inoperative during dispatch of the airplane, due to wiring of the MAR chafing against clamps as a result of the wire bundles being installed improperly during production of the airplane. The actions specified by this AD are intended to ensure that the wires that route from the main wire bundles to the MAR and associated brackets, clamps, braces, standoffs, and clips are installed properly. Improper installation of such wiring and structure could cause chafing of the wires/wire bundles, which could result in electrical arcing, smoke, and possible fire in the MAR.
98-13-12 R1: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737, 747, 757, 767, and 777 series airplanes. This action requires a one-time inspection to detect discrepancies of the fasteners that connect the pushrods to the rudder pedal assemblies; and corrective actions, if necessary. This amendment is prompted by reports of loose and missing fasteners due to incorrect installation. The actions specified in this AD are intended to prevent loss of rudder control, jamming of the rudder system, uncommanded movement of the rudder system, and consequent reduced controllability of the airplane, due to loose or missing fasteners that connect the pushrods to the rudder pedal assemblies.
85-16-07: 85-16-07 MCDONNELL DOUGLAS: Amendment 39-5103. Applies to McDonnell Douglas Model DC-9 and C-9 (Military) series airplanes, certificated in any categories. Compliance required as indicated unless previously accomplished. \n\n\tTo assure the fire containment capability of the lavatory waste containers, accomplish the following: \n\n\tA.\tWithin 18 months after the effective date of this airworthiness directive (AD), modify the forward and/or aft lavatory waste containers in accordance with the Accomplishment Instructions of McDonnell Douglas DC-9 Service Bulletin 25-259, dated April 11, 1984, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tB.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tC.\tSpecial 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. \n\n\tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-750 (54-60). These documents also 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. \n\n\tThis amendment becomes effective August 26, 1985.
98-10-02: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace (Jetstream) Model 4101 airplanes, that requires replacement of certain wheel tie bolts with new bolts; and placing a life limit on these wheel tie bolts. 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 metal fatigue failure of the wheel tie bolts, which could result in a tire burst or loss of the main wheel/tire assembly, and consequent reduced controllability of the airplane.
99-21-20: This amendment adopts a new airworthiness directive (AD), applicable to certain Dassault Model Falcon 2000 series airplanes, that requires a detailed inspection for interference between the safety-lock hooks and upper cowls, and corrective action, if necessary. This amendment also requires modification of the attachment supports of the inner locking hooks; and a detailed inspection of the safety-lock hooks on the lower engine cowl for proper operation and for clearance between the outer edges of the upper and lower cowls; and corrective actions, if necessary. 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 unintended disengagement of the engine cowl hooks during ground maintenance, which could result in in-flight loss of an engine cowl from the airplane and possible damage to the airplane and persons or property on the ground.
98-06-35: This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model SA-366G1 helicopters. This action requires initial and repetitive inspections of the tail rotor blade Kevlar tie-bar (Kevlar tie-bar) for delaminations. This amendment is prompted by a report of delamination of a Kevlar tie-bar. The actions specified in this AD are intended to detect delaminations of the Kevlar tie-bar, that could result in loss of anti-torque function and subsequent loss of control of the helicopter.
98-03-17: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model HS 748 series airplanes. This action requires repetitive inspections to detect discrepancies of the gust locks of the flight control system, re-rigging of the gust lock system; and corrective action, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to detect and correct failure of the flight control gust lock system, which could result in reduced controllability of the airplane.
85-14-51 R2: 85-14-51 R2 BOEING OF CANADA, LTD., DE HAVILLAND DIVISION: Amendment 39- 5185 as amended by Amendment 39-5440, is further amended by Amendment 39-6207. Applicability: Model DHC-8-100 series airplanes, serial numbers up to and including 93, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To minimize the danger of lightning transient-induced damage to the electronic engine control units, accomplish the following: A. Prior to further flight, incorporate the following limitations into the Limitations Section of the Airplane Flight Manual (AFM). This may be accomplished by including a copy of this AD in the AFM: 1. To preclude unacceptable loss of power during critical phases of flight, takeoff is prohibited when lightning or thunderstorms are observed or reported within 5 nautical miles of the takeoff climb path of the airplane, or when existing weather conditions may reasonably be expected to result in a lightning strike. 2. Operating with engine ignition selected to manual is required when operating below 1500 feet AGL with 5 nautical miles of any observed or reported lightning or thunderstorms, of any weather condition that may reasonably be expected to result in a lightning strike. B. Within 12 months after the effective date of this amendment, install the following modifications. Installation of all four of these modifications constitutes terminating action for this AD, and the operating limitations required by paragraph A., above, may then be removed from the AFM. 1. Modification No. 8/0597, installation of left and right shielded harnesses incorporating electronic control unit (ECU) and signal conditioning unit (SCU) wiring, in accordance with de Havilland DHC-8 Service Bulletin 8-73-7, Revision E, dated October 14, 1988. 2. Modification No. 8/0598, installation of improved engine grounding jumpers, in accordance with de Havilland DHC-8 Service Bulletin 8-71-10, Revision B, dated October 14, 1988. 3. Modification 8/0964, replacement of the electrical wiring harness assembly, in accordance with de Havilland DHC-8 Service Bulletin 8-72-2, Revision A, dated October 14, 1988. 4. Modification 8/0813, installation of an SCU grounding strap on Pratt & Whitney PW120A engines, in accordance with de Havilland DHC-8 Service Bulletin 8-72-4, Revision A, dated October 14, 1988. C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, New York Aircraft Certification Office (ANE-170), FAA, Engine and Propeller Directorate, Aircraft Certification Service. NOTE: If appropriate, 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, New York Aircraft Certification Office. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing of Canada Ltd., de Havilland Division, Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at the FAA, New York Aircraft Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, 181 South Franklin Avenue, Room 202, Valley Stream, New York. Amendment 39-5185, AD 85-14-51 became effective December 26, 1985, as to all persons, except those persons to whom it was made immediately effective by telegraphic AD T85- 14-51 issued July 12, 1985. Amendment (39-5440, AD 85-14-51 R1) became effective on October 27, 1986. This amendment (39-6207, AD 85-14-51 R2) becomes effective on June 9, 1989.
85-07-10: 85-07-10 MCDONNELL DOUGLAS: Amendment 39-5034. Applies to McDonnell Douglas Model DC-9 and C-9 (Military) series airplanes, fuselage numbers 1 through 855, certificated in all categories. Compliance required as indicated unless previously accomplished. \n\n\tTo eliminate a potential ignition source from the forward and aft lavatories, accomplish the following: \n\n\tA.\tWithin 12 months after the effective date of this airworthiness directive (AD), reroute the toilet flush motor power wire harness in the forward and aft lavatories in accordance with the Accomplishment Instructions of McDonnell Douglas DC-9 Service Bulletin 24-76, dated November 7, 1984, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tB.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tC.\tSpecial 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. \n\n\tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-750 (54-60). These documents also 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. \n\n\tThis amendment becomes effective May 13, 1985.
87-05-01: 87-05-01 HARTZELL PROPELLER PRODUCTS DIVISION: Amendment 39-5554. Applies to Hartzell Model HC-B5MP-3( )/M10876( ) propellers installed on Short Brothers Ltd. Model SD3-60 aircraft. Compliance required prior to accumulating 3,000 hours time in service since new, or within 30 days after the effective date of this AD, whichever occurs later, unless already accomplished. To prevent propeller blade separation near the hub which could result in cabin penetration and/or engine separation from the aircraft, accomplish the following: (a) Remove propeller from aircraft. (b) Accomplish the following in accordance with Hartzell Service Bulletin No. 136C, dated March 3, 1986, or FAA approved equivalent: (1) Disassemble propeller and visually inspect the blade pilot tube bore area. Particular attention shall be made to the area between the inner needle bearing assembly and bearing spacer. (2) Remove all evidence of scratches, tool marks, corrosion, scrapes, pitting, or other surface irregularities in the blade pilot tube bore area. Do not exceed the maximum rework limitations defined in the service bulletin. (3) Etch the blade pilot tube bore area prior to penetrant inspection. Ensure removal of all etching solution. (4) Penetrant inspect the blade pilot tube bore area. (5) Coat the blade pilot tube bore area with alodine. (6) Install bearing spacer and inner needle bearing assembly. Pilot tube bore must be lubricated to facilitate bearing installation. (c) Replace, prior to further flight, all blades showing evidence of cracks or other unairworthy conditions with airworthy blades. NOTES: 1) Propeller blades with serial numbers subsequent to F75966 have had the requirements of this AD incorporated during manufacture and are not affected by this AD. 2) Compliance with Hartzell Service Bulletins 136, dated August 26, 1982, 136A, dated July 12, 1983, or 136B, dated January 28, 1986, does not constitute compliance with this AD. Aircraft may be ferried in accordance with the provisions of Federal Aviation Regulations (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, Chicago Aircraft Certification Office, FAA, 2300 East Devon Avenue, Des Plaines, Illinois 60018. Hartzell Service Bulletin No. 136C, dated March 3, 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 Hartzell Propeller Products Division, TRW Aircraft Components Group, 350 Washington Avenue, Piqua, Ohio 45356. This document also may be examined at the Office of the Regional Counsel, FAA, Attn: Rules Docket No. 87-ANE- 2, 12 New England Executive Park, Burlington, Massachusetts 01803, weekdays, except Federal holidays, between 8:00 a.m. and 4:30 p.m. This amendment becomes effective on March 12, 1987.
86-18-04: 86-18-04 BOEING: Amendment 39-5385. Applies to Model 737 series airplanes, line numbers 930 and above, listed in Boeing Service Letter 737-SL-27-38, dated January 16, 1986, certificated in any category. To detect nuts installed at the Body Buttock Line (BBL) 70.85 wing-to-body splice plate, the thrust reverser secondary deactivation pin, and the vertical fin front spar to closure rib attachments, that have insufficient self-locking torque characteristics, accomplish the following, unless already accomplished: \n\n\tA.\tWithin the next 18 months after the effective date of this AD, check the self- locking nuts, P/N BACN10JC12CM and P/N BACN10JC12CD, for proper self-locking torque in accordance with Paragraph II of Boeing Service Letter 737-SL-27-38, dated January 16, 1986, or later FAA-approved revision. If any self-locking nut does not meet the torque criteria specified in the service letter, replace it prior to further flight with an appropriate nut which meets the torque criteria. \n\n\tB.\tAn alternate means of the compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective September 11, 1986.
2000-15-13: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that currently requires a one-time inspection to verify correct wire terminations of certain circuit breakers in the cockpit overhead switch panel; and correction of incorrect wire termination. That AD also requires that operators submit a report of the inspection results to the FAA. That AD was prompted by incidents in which the wiring of circuit breakers on the overhead switch panel lighting were found to be terminated improperly during production of the airplane, which bypassed the circuit breaker protection. This amendment expands the applicability of the existing AD to include additional airplanes, and removes the reporting requirement. The actions specified in this AD are intended to prevent smoke and possible fire in the overhead switch panel lighting circuitry due to an overload condition, as a result of lack of circuit breaker protection. \n\n\tThe incorporation by reference of McDonnell Douglas Alert Service Bulletin MD11-33A027, dated March 10, 1999, as listed in the regulations, was approved previously by the Director of the Federal Register as of May 7, 1999 (64 FR 19695, April 22, 1999).\n\n\tThe incorporation by reference of certain other publications listed in the regulations is approved by the Director of the Federal Register as of August 23, 2000.\n\n\tComments for inclusion in the Rules Docket must be received on or before October 10, 2000.
85-07-02: 85-07-02 BOEING: Amendment 39-5036. Applies to Boeing Model 757 airplanes listed in the Boeing Service Bulletin 757-25A0036, Revision 1, dated September 21, 1984. To prevent degradation of fire protection capability in the cargo compartments, accomplish the following within 120 days after the effective date of this AD, unless already accomplished: \n\n\tA.\tReplace the existing cargo compartment blowout panels in accordance with Boeing Service Bulletin 757-25A0036, Revision 1, dated September 21, 1984, or later FAA approved revision. \n\n\tB.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of replacements required by this AD. \n\tAll persons affected by this directive who have not already received the above specified service bulletins from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents also may be examined at the FAA, Northwest Mountain Region, Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\tThis amendment becomes effective May 13, 1985.
97-20-05: This amendment adopts a new airworthiness directive (AD) that is applicable to all British Aerospace Model HS 748 series airplanes. This action requires installation of a modified aileron cable pulley guard and rubbing strips. 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 jamming or restricting of the aileron cable, which could lead to the loss of aircraft roll control.
98-21-07: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model Avro 146-RJ85A and RJ100A series airplanes, that requires a one-time inspection for evidence of machining (undercutting) into the web of the integral stringers of the bottom skin of the wings, and corrective actions, if necessary. 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 reduced wing strength and stiffness, and the onset of premature fatigue cracking, which could result in reduced structural integrity of the airplane.
98-04-48: This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model AS 332L2 helicopters. This action requires modifying the main rotor blade vibration absorber (vibration absorber) by replacing the weight support assemblies with reinforced weight support assemblies. This amendment is prompted by a report of the failure of a weight support assembly in-flight. The actions specified in this AD are intended to prevent failure of a vibration absorber weight support assembly, which could lead to adverse vibrations, contact between the fuselage and a main rotor blade or loss of a main rotor blade; and subsequent loss of control of the helicopter.
98-03-19: This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-120 series airplanes, that requires deactivation of certain circuit breakers, and a revision to the Airplane Flight Manual (AFM) to provide operational procedures to prevent loss of electrical power following an engine flameout. This AD also requires modifications of the electrical system, which terminate the requirement for the AFM revision and allow reactivation of the circuit breakers. This amendment is prompted by the issuance of mandatory continued airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent generator overload conditions that could result in loss of electrical power and failure of certain flight and landing control systems, and to prevent power interruption to the attitude heading reference system (AHRS) that could result in the display of erroneous heading information.