Results
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.