Results
2019-19-01: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A320-251N and -271N airplanes, and Model A321-251N, - 253N, -271N, and -272N airplanes. This AD was prompted by reports that the regulated bleed temperature was measured above the design target with a temperature regulation shift phenomenon, and investigation results show that incorrect temperature regulation can degrade pneumatic system components located downstream of the pre-cooler. This AD requires uploading improved bleed monitoring computer (BMC) software (SW), 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.
2006-03-01: The FAA is adopting a new airworthiness directive (AD) for all Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model ERJ 170 airplanes. This AD requires, when certain SmartProbes are installed, revising the Limitations section of the airplane flight manual to limit the maximum take-off weight of the airplane and increase the reference speed during certain landing conditions. This AD results from reports of variable calibration values of certain sensors of the SmartProbes, which could result in the transmission of erroneous information to the air data system. We are issuing this AD to prevent reduced controllability of the airplane.
2019-21-04: The FAA is adopting a new airworthiness directive (AD) for certain Saab AB, Saab Aeronautics Model SAAB 2000 airplanes. This AD was prompted by reports of loose and irregular fasteners at the forward end of the nacelle upper longeron, where the bulkhead frame and struts are attached to the engine mounting structure (EMS). This AD requires modification of the EMS and structural attachments. The FAA is issuing this AD to address the unsafe condition on these products.
2019-21-12: The FAA is adopting a new airworthiness directive (AD) for certain BRP-Rotax GmbH & Co KG (Rotax) 914 F2, 914 F3, and 914 F4 model engines. This AD requires removal of a certain exhaust valve and its replacement with a part eligible for installation. This AD was prompted by a report of a broken exhaust valve installed on a Rotax 914 model engine. The FAA is issuing this AD to address the unsafe condition on these products.
2019-21-02: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-200, -200F, and -300 series airplanes. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. The FAA is issuing this AD to address the unsafe condition on these products.
2006-02-09: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model Airbus Model A330-200, A330-300, A340-200, and A340-300 series airplanes. This AD requires inspecting for damage to certain actuators of the low-pressure shut-off valve (LPSOV), and related investigative and corrective actions if necessary. This AD results from a report of damage to the LPSOV pedestal. We are issuing this AD to ensure that, in the event of an engine fire, the LPSOV actuator functions properly to delay or block the fuel flow to the engine and prevent an uncontrollable fire.
78-23-03: 78-23-03 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-3337. Applies to Model SA 316C and 319 Alouette III helicopters, certificated in all categories, that do not incorporate SNIAS Modification AMS 07.2109 (covered in Service Bulletin No. 65.108). Compliance is required as indicated, unless already accomplished. To prevent a possible loss of helicopter control, accomplish the following: (a) Within the next 50 hours time in service after the effective date of this AD, and, thereafter, at intervals not to exceed 50 hours time in service since the previous inspection, inspect the left-hand and right-hand upper flight control bellcrack support attachment fittings, P/Ns 319A.84.10.118 and 319A.84.10.119, in accordance with Alouette SA316C and 319 Service Bulletin No. 05.57, dated September 29, 1975, or an FAA-approved equivalent (hereinafter referred to as Service Bulletin). (b) If a crack is found during an inspection required by paragraph (a)of this AD, replace the affected part with a new fitting, P/N 319A.84.10.120 or 319A.84.10.121, as appropriate, in accordance with the Service Bulletin before further flight, except that the helicopter may be flown in accordance with FAR 21.197 and 21.199 to a base where the work can be performed. (c) The inspections required by paragraph (a) of this AD may be discontinued upon the installation of new fittings, P/Ns 319A.84.10.120 and 319A.84.10.121, in accordance with the Service Bulletin. This amendment becomes effective December 4, 1978.
80-06-02: 80-06-02 GATES LEARJET: Amendment 39-3715. Applies to Models 35 (Serial Numbers 35-001 thru 35-066); 36 (Serial Numbers 36-001 thru 36-017); 35A (Serial Numbers 35-067 thru 35-288); and 36A (Serial Numbers 36-018 thru 36-044) airplanes. COMPLIANCE: Required as indicated, unless previously accomplished. To preclude takeoff, or continued flight after a starter assist air start, with an unannunciated failure in the electrical system, accomplish the following: A) Within the next 10 hours time-in-service after the effective date of this AD, insert the following information in the FAA Approved Airplane Flight Manual and operate the airplane in accordance with these insertions: 1) In Section 1, LIMITATIONS, add the following: ELECTRICAL SYSTEM The battery charging bus current limiter and starter disengagement checks, as outlined in STARTING ENGINES, STARTER ASSIST AIRSTART, and/or BEFORE TAKEOFF procedures in Sections II and III of this manual, must be accomplished whenever an engine start using a starter has been performed. These checks require that both engines be operating to perform the check. 2) In Section 2, NORMAL OPERATING PROCEDURES, under the heading STARTING ENGINES, add the following: (a) Starter Disengagement Check - After both engines are started, perform check as follows: 1. Air Conditioner and Auxiliary Heater - OFF. 2. Both Battery Switches - OFF. 3. Ammeters - Check total current indication less than 100 amps. 4. If total current indication is greater than 100 amps, shut down engines. NOTE: A total ammeter indication greater than 100 amps indicates that a starter has not disengaged. Subsequent starter and/or engine damage may occur. If total current indication is less than 100 amps, set both Battery Switches ON. (b) Battery Charging Bus Current Limiter Check (Serials 35-001 thru 35-147 and 36-001 thru 36-035): 1. Pull MAIN DC BUS TIE circuit breaker. 2. One Generator Switch - OFF. Check ammeter reading on opposite generator, approximately doubles, then switch back to GEN. 3. Opposite Generator Switch - OFF. Check ammeter reading on opposite generator, approximately doubles, then switch back to GEN. 4. Reset MAIN DC BUS TIE circuit breaker. CAUTION: Failure to meet the above check indicates a malfunction. Replace 275A Current Limiter prior to takeoff. Loss of 275A Current Limiters can lead to loss of essential DC power. Battery Charging Bus Current Limiter Check (Serials 35-148 thru 35-288 and 36-036 thru 36-044): 1. Test Switch - L CUR LIM. 2. Test Button - Press. Green current limiter light will illuminate and remain on while button is held. The light indicates continuity through the left current limiter. Also the L GEN light will come on and the right generator voltage may be reduced by approximately 2 VDC. 3. Test switch - R CUR LIM. 4. Test Button - Press. Green current limiter light will illuminate and remain on while button is held. The light indicates continuity through the right Current Limiter. Also the R GEN light will come on and the left generator voltage may be reduced by approximately 2 VDC. CAUTION: Failure of light to remain illuminated indicates a malfunction. Replace 275A Current Limiter prior to takeoff. Loss of 275A Current Limiters can lead to loss of essential DC power. 3) In Section 3, EMERGENCY PROCEDURES, under the headings, ENGINE FAILURE DURING CRUISE and OPERATIONS WITH ONE FUEL COMPUTER INOPERATIVE, add the following after all starter assist engine starts: (a) Starter Disengagement Check 1. Air Conditioner and Auxiliary Heater - OFF. 2. Both Battery Switches - OFF. 3. Ammeter - Check total current indication less than 100 amps. 4. If total current indication is greater than 100 amps: a. Both Battery Switches - ON. b. and as soon as practical. c. Do not attempt further flights until trouble has been corrected. NOTE: A total ammeter indication greater than 100 amps indicates that a starter has not disengaged and subsequent starter and/or engine damage may occur. If total current indication is less than 100 amps, set both Battery Switches ON. (b) Battery Charging Bus Current Limiter Check (Serials 35-001 thru 35-147 and 36-001 thru 36-035): 1. Pull MAIN DC BUS TIE circuit breaker. 2. One Generator Switch - OFF. Check ammeter reading on opposite generator, approximately doubles, then switch back to GEN. 3. Opposite Generator Switch - OFF. Check ammeter readings on opposite generator, approximately doubles, then switch back to GEN. 4. Reset MAIN DC BUS TIE circuit breaker. CAUTION: Failure to meet the above check indicates a malfunction. Loss of both 275A Current Limiters can lead to loss of essential DC power. Battery Charging Bus Current Limiter Check (Serials 35-148 thru 35-288 and 36-036 thru 36-044): 1. Test Switch - L CUR LIM. 2. Test Button - Press. Green current limiter light will illuminate and remain on while button is held. The light indicates continuity through the left current limiter. Also the L GEN light will come on and the right generator voltage may be reduced by approximately 2 VDC. 3. Test Switch - R CUR LIM. 4. Test Button - Press. Green current limiter light will illuminate and remain on while button is held. The light indicates continuity through the right current limiter. Also the R GEN light will come on and the left generator voltage may be reduced by approximately 2 VDC. CAUTION: Failure of light to remain illuminated indicates a malfunction. Loss of both 275A Current Limiters can lead to loss of essential DC power. B) Use Paragraph A of this AD, or a duplicate thereof, as an amendment to the FAA Approved Airplane Flight Manual until replaced by Change 9 or 10 to Gates Learjet 35/36 or 35A/36A FAA Approved Airplane Flight Manual, as applicable, both FAA approved February 15, 1980. C) This AD may be accomplished by the holder of a pilot certificate issued under Part 61 of the Federal Aviation Regulations on any airplane owned or operated by that person, who must make an entry in the airplane maintenance records indicating prescribed compliance with this AD. D) Any equivalent method of compliance with this Airworthiness Directive must be approved by the Chief, Wichita Engineering and Manufacturing District Office, Federal Aviation Administration, Room 238, Terminal Building No. 2299, Mid-Continent Airport, Wichita, Kansas 67209. This amendment becomes effective March 24, 1980.
64-11-03: 64-11-03 LOCKHEED: Amdt. 729 Part 507 Federal Register May 15, 1964. Applies to All Models 188A and 188C Series Aircraft. Compliance required as indicated. Cracks have been detected in the upper wing planks on both the inboard and outboard sides of the nacelle where the inboard nacelle skate angles attach to the wing planks. As a result of these cracks, accomplish the following: (a) Within the next 450 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 450 hours' time in service, externally inspect the wing planks in accordance with Section 2.A. of Lockheed Service Bulletin 88/SB-600 or FAA approved equivalent. The external inspections may be discontinued when the internal inspection program prescribed by (b) is initiated. (b) Within the next 900 hours' time in service after the effective date of this AD, unless accomplished within 2,100 hours' time in service prior to the effective date of this AD, and thereafter atintervals not to exceed 3,000 hours' time in service, internally inspect the wing planks by X-ray or visual means in accordance with Section 2.B. of Lockheed Service Bulletin 88/SB-600 or FAA approved equivalent. (c) Any cracks found during the accomplishment of (a) or (b) shall be repaired before further flight (except that the aircraft may be ferried in accordance with the provisions of CAR 1.76 to the base at which the repairs are to be accomplished) in accordance with the Lockheed Electra Structural Repair Manual, Section 57-2-1, or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region. (d) The repetitive inspections of (b) may be discontinued for those aircraft which exhibit no signs of cracks 6,000 hours' time in service after the initial internal inspection is accomplished. (e) For aircraft on which cracks are detected and repaired in accordance with (c), the repetitive inspections of (b) may be discontinued if no cracks are detected6,000 hours' time in service after the repair is accomplished. (f) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Engineering Division, FAA Western Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. (Lockheed Alert Bulletin 88/SB-600 dated June 24, 1963, covers this same subject.) This directive effective June 15, 1964.
2006-02-03: The FAA is adopting a new airworthiness directive (AD) for certain Raytheon Model Hawker 800XP airplanes. This AD requires inspecting to determine if the correct fuse is installed on the hydraulic over-temperature switch on panel ZK in the rear equipment bay, and replacing the existing fuse if necessary. This AD results from a report of the installation of an incorrect fuse on the over- temperature switch on panel ZK in the rear equipment bay during airplane maintenance. We are issuing this AD to prevent a short circuit in the fuse and consequent heat damage to associated wiring and surrounding equipment, which could result in smoke or fire on the airplane.
2008-18-03: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: During manufacturing of A330/A340 aircraft framework, cracks have been found on Frame (FR) 12, left (LH) and right (RH) sides. It has been confirmed that a defect of the FR12 forming tool press is the root cause of the cracks. If undetected such damage could affect, after propagation, the structural integrity of the aircraft. * * * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
81-02-08: 81-02-08 LOCKHEED-CALIFORNIA: Amendment 39-4023. Applies to all Model L-1011 series airplanes certificated in all categories. Compliance required within 300 hours time-in-service after the effective date of this AD. To assure availability of emergency passenger oxygen, accomplish the following: A. Replace all one-man fixed chemical oxygen generators, Scott Aviation P/N 801462-01 with Scott Aviation P/N 801462-04 oxygen generators, in accordance with a method approved by the Chief, Los Angeles Area Aircraft Certification Office. (NOTE: Accomplishment of Lockheed Service Bulletin 093-35-030, dated September 15, 1980, has been approved as a means of compliance with this requirement.) B. Alternative means of compliance or other actions which provide an equivalent level of safety may be used when approved by the Chief, Los Angeles Area Aircraft Certification Office, FAA Northwest Region. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199to operate airplanes to a base in order to comply with the requirements of this AD. This amendment becomes effective January 27, 1981.
81-20-04 R1: 81-20-04 R1 BOEING: Amendment 39-4225 as amended by Amendment 39-4250. Applies to Boeing Model 727-200 series and 737 airplanes, certificated in all categories, using the following Hamilton Standard electronic pressurization controllers that have not been previously modified to HS reference number P57: \n\n\nHS Part Number\nBoeing Part Number \n710204-7\n10-61209-13 \n710204-8\n10-61209-14 \n761260-7\n10-61209-19 \n761260-8\n10-61209-18 \n\n\tTo prevent inflight fires, on or before May 12, 1982, accomplish the following, unless already accomplished: Modify the Hamilton Standard pressurization controllers listed above in accordance with Boeing Service Bulletins 727-21 A96 and 737-21 A1064, published August 28, 1981, or later FAA approved revision, or in a manner approved by the Chief, Seattle Area Aircraft Certification Office. \n\tThe Assurance of Serviceability testing described in Paragraph B(16) of Hamilton Standard Service Bulletin 21-88, Revision 1, dated October 13, 1981, may be used in lieu of the complete functional test specified in the Boeing Service Bulletins listed above.\n \n\tThe manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received the above specified Alert Service Bulletin from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124, or it may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. \n\n\tAmendment 39-4225 became effective October 13, 1981. \n\tThis amendment 39-4250 becomes effective November 13, 1981.
2006-02-05: 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 replacing the Camloc fasteners on the sidewall of the center pedestal. This AD results from reports of the Camloc fasteners on the sidewall of the center pedestal disengaging and interfering with an inboard rudder pedal. We are issuing this AD to prevent these fasteners from disengaging and interfering with an inboard rudder pedal, which could reduce directional controllability of the airplane.
2002-26-10: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas DC-9-10, -20, -30, -40, and -50 series airplanes, that currently requires a one-time visual inspection to determine the modification status of the corners of the forward lower cargo doorjamb; low-frequency eddy current or X-ray inspections to detect cracks of the fuselage skin and doubler at all corners of the forward lower cargo doorjamb; various follow-on repetitive inspections; and modification, if necessary. This amendment retains those requirements but requires certain high-frequency, rather than low-frequency, eddy current inspections for certain conditions. The actions specified by this AD are intended to detect and correct cracking, which could result in rapid decompression of the fuselage and consequent reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
64-02-06 R1: 64-02-06 R1 SIKORSKY AIRCRAFT: Amendment 674 as amended by Amendment 39-6090. Applies to all Sikorsky Model S-58 series helicopters. Compliance is required as indicated unless already accomplished. Fatigue cracks have been found in the area of the rear three bolt holes of upper pylon folding hinge fitting P/N S1620-63130-2, the forward bolt holes of mating fitting P/N S1620-64127, the forward bolt hole of the lower pylon hinge fitting P/N S1620-64131, and the lug through which the hinge bolt passes of fittings P/N's S1620-64127 and S1620-64127-7. In order to preclude propagation of fatigue cracks in these areas and subsequent serious weakening of the pylon attachment, accomplish the following: (a) As of the effective date of this AD, conduct daily visual inspections of the area around the fitting bolt holes of all pylon and tail cone folding hinge fittings for cracks. Replace any cracked fittings before further flight. (b) Unless already accomplished, accomplish the following in accordance with Sikorsky Service Bulletin No. 58B20-11A within 100 hours' time in service after the effective date of this AD on all upper pylon hinge fittings P/N S1620-64127 with 1,900 hours' or more time in service, or prior to the accumulation of 2,000 hours' time in service on all fittings having less than 1,900 hours' time in service as of the effective date of this AD: (1) Remove all bushings from the hinges. (2) Rework and inspect the bore of each hole. (3) Install oversized replacement bushings P/N S1620-63129-7. (c) Upon request, an alternate means of compliance which provides an equivalent level of safety with the requirements of this AD may be used when approved by the Manager, Rotorcraft Standards Staff, Rotorcraft Directorate, Aircraft Certification Service, ASW-110, FAA, Fort Worth, Texas 76193-0110. (d) In accordance with Sections 21.197 and 21.199, the helicopter may be flown to a base where compliance may be accomplished. Airworthiness Directive 63-09-02 was superseded by AD 64-02-06 (Amendment 674; 29 FR 559; January 21, 1964) which was effective January 31, 1964. This amendment (39-6090, AD 64-02-06 R1) revises AD 64-02-06 and becomes effective December 27, 1988.
2001-08-14 R1: The FAA is revising an existing airworthiness directive (AD) for Turbomeca S.A. Arrius Models 2B, 2B1, and 2F turboshaft engines. That AD currently requires replacing the right injector half manifold, left injector half manifold, and privilege injector pipe. This AD requires the same actions, but relaxes the compliance time for the repetitive replacements on Arrius 2F engines. This AD results from Turbomeca relaxing the repetitive replacement interval for Arrius 2F engine fuel nozzles based on review of returned fuel nozzles to Turbomeca. We are issuing this AD to prevent engine flameout during rapid deceleration, or the inability to maintain the 2.5 minutes one engine inoperative (OEI) rating, and to prevent air path cracks due to blockage of the fuel injection manifolds.
99-07-06: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767 series airplanes. This action requires repetitive inspections to detect cracking or damage of the forward and aft lugs of the diagonal brace of the nacelle strut, and follow-on actions, if necessary. This action also provides optional terminating action for the repetitive inspections. This amendment is prompted by a report that a fractured diagonal brace lug was found during a routine maintenance inspection. The actions specified in this AD are intended to detect and correct cracking of the diagonal brace of the nacelle strut, which could result in failure of the diagonal brace, and consequent fatigue failure of a strut secondary load path and separation of the engine and strut.
99-04-15: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 99-04-15 that was sent previously to all known U.S. owners and operators of Porsche PFM3200N01, N02, and N03 reciprocating engines by individual letters. This AD requires replacement of valve springs prior to further flight on PFM3200N01, N02, and N03 engines. This amendment is prompted by reports of six cases of undetected fatigue failures of valve springs, with one valve spring failure causing an in-flight engine failure that ended in an emergency landing. The actions specified by this AD are intended to prevent an in-flight engine shutdown due to undetected fatigue failures of valve springs.
88-12-06: 88-12-06 BOEING: Amendment 39-5936. Applies to Model 767 series airplanes, listed in Boeing Service Bulletin 767-53-0025, dated June 4, 1987, certificated in any category. \n\n\tCompliance required within 12 months after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent structural failure of the vertical fin in the event of a failure of the aft pressure bulkhead, accomplish the following: \n\n\tA.\tInstall seal plates over the electrical wiring and hydraulic tubing cutouts on the fin-to-body skin in accordance with Boeing Service Bulletin 767-53-0025, dated June 4, 1987. \n\n\tB.\tAn 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, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region.\n \n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Seattle Aircraft Certification Office. \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 the appropriate service documents from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment, 39-5936, becomes effective July 1, 1988.
2006-02-01: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A330-200 and -300 series airplanes, Model A340-200 and - 300 series airplanes, and Model A340-541 and A340-642 airplanes. This AD requires revising the airplane flight manual by incorporating new procedures to follow in the event of a fuel leak. This AD results from a determination that, once a fuel leak is detected, fuel management procedures are a critical factor in limiting the consequences of the leak. We are issuing this AD to ensure that the flightcrew, in the event of a fuel leak, is advised of appropriate procedures to follow, such as isolating the fuel tanks, stopping any fuel transfers, and landing as soon as possible. Failure to follow these procedures could result in excessive fuel loss that could cause the engines to shut down during flight.
2019-03-20: We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by a determination that new and more restrictive maintenance requirements and airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new and more restrictive maintenance requirements and airworthiness limitations for airplane structures and systems. We are issuing this AD to address the unsafe condition on these products.
2002-26-05: This amendment supersedes Airworthiness Directive (AD) 2002-11-03, which applies to certain Air Tractor, Inc. (Air Tractor) Models AT-502, AT-502A, AT-502B, and AT-503A airplanes. AD 2002-11-03 lowered the safe life for the wing lower spar cap and further reduced the safe life for airplanes that incorporate or have incorporated Marburger Enterprises, Inc. winglets. AD 2002-11-03 also currently requires you to eddy-current inspect the wing lower spar cap immediately prior to the replacement/modification to detect and correct any crack in a bolthole before it extends to the modified center section of the wing and report the results of this inspection to the Federal Aviation Administration (FAA). Field inspections on the affected airplanes have revealed wings with cracks below the currently established safe life. This AD would further reduce the safe life of the Models AT502, AT-502B, and AT-503A airplanes and would add airplanes recently manufactured to the Applicability of theAD. The actions specified by this AD are intended to prevent fatigue cracks from occurring in the wing lower spar cap before the established safe life is reached. Fatigue cracks in the wing lower spar cap, if not detected and corrected, could result in the wing separating from the airplane during flight.
99-07-07: This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France (Eurocopter) Model SA 330J helicopters. This action requires the visual inspection and, if any crack is found, replacement of the affected main rotor head sleeve. This amendment is prompted by the discovery of a crack through the thickness of a lower lug of a blade sleeve. The actions specified by the proposed AD are intended to prevent failure of a main rotor head sleeve that could result in the loss of a main rotor blade and subsequent loss of control of the helicopter.
2009-18-04: We are adopting a new airworthiness directive (AD) for certain Air Tractor, Inc. Models AT-802 and AT-802A airplanes. This AD requires installing a rudder-aileron interconnect cable system shield kit and securing any items stowed in the baggage compartment, using tie downs and/or a cargo net until the cable shield kit is installed. We are issuing this AD to prevent jamming of the rudder-aileron interconnect cables by unsecured items in the baggage compartment, which could result in failure of the rudder-aileron interconnect cable system. This failure could lead to loss of control.