Results
2022-01-04: The FAA is adopting a new airworthiness directive (AD) for certain Rolls-Royce Corporation (RRC) AE 2100D3 model turboprop engines. This AD was prompted by an in-flight shutdown (IFSD) of an engine and subsequent investigation by the manufacturer that revealed a crack in the 3rd-stage compressor wheel. This AD requires replacement of the affected 3rd-stage compressor wheel. The FAA is issuing this AD to address the unsafe condition on these products.
78-12-09: 78-12-09 AVCO LYCOMING: Amendment 39-3238 as amended by Amendment 39-3414. Applies to O-320-H series engines with the following serial numbers, unless already accomplished. L-103-76, L-104-76, L-272-76, L-283-76, L-288-76, L-290-76, L-336-76, L-337-76, L-341-76, L-404-76, L-431-76, L-468-76, L-469-76, L-471-76, L-494-76, L-548-76, L-589-76, L-590-76, L-592-76, L-650-76, L-684-76, L-689-76, L-698-76, L-736-76, L-737-76, L-738-76, L-743-76, L-754-76, L-763-76, L-768-76, L-769-76, L-772-76, L-774-76, L-777-76, L-778-76, L-802-76, L-824-76, L-834-76, L-846-76, L-903-76, L-904-76, L-929-76, L-940-76, L-945-76, L-948-76, L-949-76, L-1054-76, L-1115-76, L-1119-76, L-1122- 76 THROUGH L-1129-76, L-1131-76 THROUGH L-1134-76, L-1144-76, L-1156-76, L-1181-76, L-1186- 76, L-1191-76, L-1200-76, L-1205-76, L-1207-76, L-1237-76, L-1255-76, L-1304-76, L-1305-76, L-1352-76, L-1354-76, L-1374-76, L-1375-76, L-1379-76, L-1460-76, L-1476-76, L-1489-76, L-1492-76, L-1513-76, L-1568-76, L-1577-76, L-1626-76, L-1630-76, L-1639-76, L-1644-76, L-1657-76, L-1658-76, L-1665-76, L-1668-76, L-1678-76, L-1679-76, L-1687-76, L-1693-76, L-1694-76, L-1697-76, L-1795-76, L-1796-76, L-1824-76, L-1825-76, L-1826-76, L-1870-76, L-1885-76, L-1934-76, L-2002-76, L-2007-76, L-2016-76, L-2025-76 THROUGH L-2032-76, L-2041-76, L-2047-76, L-2065-76 THROUGH L-2068-76, L-2071-76 THROUGH L-2077-76, L-2115-76, L-2148-76, L-2157-76, L-2159-76 THROUGH L-2163-76, L-2165-76, L-2167-76, L-2168-76, L-2171-76, L-2174-76 THROUGH L-2182-76, L-2189-76, L-2190-76, L-2191-76, L-2192-76, L-2198-76, L-2260-76, L-2293-76, L-2294-76, L-2308-76, L-2338-76, L-2339-76, L-2340-76, L-2343-76, L-2344-76, L-2350-76, L-2365-76, L-2556-76, L-2596-76, L-2635-76, L-2636-76, L-2637-76, L-2644-76, L-2666-76, L-2697-76, L-2728-76, L-2731-76, L-2758-76, L-2762-76, L-2763-76, L-2774-76, L-2777-76, L-2782-76, L-2784-76, L-2790-76, L-2816-76, L-2832-76, L-2837-76, L-2842-76, L-2843-76, L-2845-76, L-2857-76, L-2908-76, L-2914-76, L-2921-76, L-2922-76, L-2924-76, L-2930-76, L-2932-76 THROUGH L-2938-76, L-2942-76, L-2947-76, L-2948-76, L-2962-76, L-2963-76, L-2966-76, L-2975-76, L-2980-76, L-2985-76, L-2987-76, L-2988-76, L-2989-76, L-2992-76, L-2999-76, L-3004-76, L-3010-76, L-3016-76, L-3034-76, L-3035-76, L-3041-76, L-3047-76, L-3063-76, L-3067-76, L-3068-76, L-3155-76, L-3170-76, L-3172-76, L-3240-76, L-3262-76, L-3288-76, L-3289-76, L-3291-76, L-3292-76, L-3293-76, L-3295-76, L-3296-76, L-3308-76, L-3313-76, L-3319-76, L-3384-76, L-3395-76 THROUGH L-3400-76, L-3402-76, L-3403-76, L-3404-76, L-3406-76, L-3411-76, L-3412-76, L-3413-76, L-3414-76, L-3428-76, L-3467-76, L-3551-76, RL-114-76, RL-124-76, RL-133-76, RL-162-76, RL-176-76, RL-186-76, RL-205-76, RL-249-76, RL-254-76, RL-328-76, RL-332-76, RL-351-76, RL-367-76, RL-384-76, RL-408-76, RL-416-76, RL- 418-76, RL-419-76, RL-435-76, RL-442-76, RL-443-76, RL-477-76, RL-510-76, RL-543-76, RL-550-76, RL-612-76, RL-652-76, RL-673-76, RL-695-76, RL-832-76, RL-1022-76, RL-1082-76, RL-1173-76, RL-1218-76, RL-214-76. Compliance required before further flight except that the aircraft may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. a. To prevent possible crankshaft gear failure, remove and replace the crankshaft assembly and install crankshaft assembly P/N LW-15917 in accordance with AVCO Lycoming Service Bulletin No. 422, dated March 24, 1978, or FAA approved equivalent. b. Equivalent methods of compliance must be approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. Amendment 39-3238 was effective June 20, 1978. This Amendment 39-3414 is effective February 20, 1979.
94-06-01: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes and Model MD-88 airplanes, that requires inspection of the ceiling pressure relief panels in the cargo compartments to determine if slotted attach points are present and, if not, modification of the panels. This amendment is prompted by a report that certain panels were manufactured without the appropriate slotted attach points. The actions specified by this AD are intended to ensure that the action of the cargo compartment pressure relief panels will enable the airplane to withstand a rapid decompression caused by a hole below the compartment floor.
94-21-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Model ATR42-200 and -300 series airplanes, that requires a one-time dye penetrant inspection to detect cracking in certain hinge pins of the nose landing gear (NLG), and replacement of cracked pins with crack-free pins. This amendment is prompted by reports of cracking of certain hinge pins in the NLG. The actions specified by this AD are intended to prevent collapse of the NLG due to cracking of the hinge pins.
77-25-02: 77-25-02 ROCKWELL INTERNATIONAL: Amendment 39-3091. Applies to Sabreliner Model NA-265-70 Serial Numbers 370-1 and 370-7, and NA-265-80 Serial Numbers 380-1 through 380-58, certificated in all categories. Compliance required as indicated. To prevent deactivation of the engine fire detection system and/or crossed wires in the engine fire detectors to cockpit warning light, accomplish the following: Prior to the next flight after receipt of this telegram, unless already accomplished, A. Ensure that a proper ground exists between the engine fire detector element (Edison Cable P/N 244-12482) couplings and the engine, and B. Ensure that proper continuity exists between the elements and the fire detector control units in accordance with Rockwell International Sabreliner Service Bulletin No. 30 dated November 2, 1977, or later FAA approved revisions, or accomplish tests and modifications as follows: 1. Disconnect electrical power from airplane. 2. Openand remove engine access doors as required. 3. Locate and remove existing MS 21105-4 clamps securing fire detector element couplings to engine. (Ref. Aeronca Dwg. No. 234-22029 Rev. A). 4. Install new clamps (P/N AN 742-H3) on each fire detector element coupling. Tighten clamp fasteners. 5. Using a Volt/OHM meter (Simpson 260 or equivalent) set to read OHMS, connect negative (-) lead to AIRFRAME GROUND and positive (+) lead to fire detector element coupling. Check that meter reads one OHM or less. Remove Volt/OHM meter leads. 6. On RH engine, disconnect fire detector element from ONE coupling. Apply external power to airplane. 7. Using a suitable jumper wire, attach one end of jumper wire to inner conductor of receptacle, and the other end of jumper wire to ground. Check that the right hand "Fire Pull" handle lights illuminate. Remove jumper from receptacle inner conductor and insert in center conductor of fire detector element. Check that right hand"Fire Pull" handle lights illuminate. Remove jumper wire. 8. Connect and tighten fire detector element to couplings (element disconnected in Step 6). Lockwire coupling. 9. On LH engine, disconnect fire detector element from ONE coupling. 10. Using a suitable jumper wire, attach one end of jumper wire to inner conductor of receptacle, and the other end of jumper wire to ground. Check that the left hand "Fire Pull" handle lights illuminate. Remove jumper from receptacle inner conductor and insert in center conductor of fire detector element. Check that left hand "Fire Pull" handle lights illuminate. Remove jumper wire. 11. Connect and tighten fire detector element to coupling (element disconnected in Step 9). Lockwire coupling. NOTE: If the requirements of Step 7 thru Step 10 are not met, check fire detector wiring in accordance with Rockwell International Sabreliner Wiring Diagram Manual, Report No. SR-73-26. 12. Press "Fire Det Sys Push To Test"switch. Right and left "Fire Pull" overheat and fire-warning indicator lights should illuminate within one second after switch is pushed. Make sure both lights in each assembly illuminate. Release test switch. Both lights should go out within 5 seconds. Remove electrical power from airplane. 13. Close and/or install engine cowling. C. Equivalent modifications may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. D. Special flight permits may be issued in accordance with FAR's 21.197 and 21.199 to authorize operation of an airplane to a base for the accomplishment of the modifications required by this AD provided the following is accomplished: 1. Interim addition of a positive ground between the engine fire detector element couplings and the engine to ensure proper operation of the engine fire detection system, and 2. Check the fire warning system to ensure that the fire warning light operates correctly for the engine/engines involved. This amendment becomes effective December 12, 1977, for all persons except those to whom it was made effective by telegram dated November 4, 1977 which contained this amendment.
96-09-17: This amendment adopts a new airworthiness directive (AD) that applies to all Jetstream Aircraft Limited (JAL) Jetstream Models 3101 and 3201 airplanes. This action 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 freezing rain or freezing drizzle conditions by providing more clearly defined procedures and limitations associated with such conditions.
2010-17-03: We are adopting a new airworthiness directive (AD) for certain Model 767-300 series airplanes. This AD requires replacing a wire bundle clamp and installing a tetrafluoroethylene (TFE 2X) sleeve. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent chafing of a wiring bundle, which could result in a high-energy short and, consequently, a possible ignition source in the center auxiliary fuel tank.
2006-20-06: The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CF34-10E series turbofan engines. This AD requires removing the main fuel pump (MFP) inlet strainer from certain MFPs, installing a certain replacement flange as an interim repair, and performing initial and repetitive visual inspections of the main fuel filter. This AD results from three reports of release of the tripod support legs on the MFP inlet strainer, leading to engine in-flight shutdown. We are issuing this AD to prevent engine in-flight shutdown due to MFP malfunctions.
92-13-51: 92-13-51 CONSTRUCCIONES AERONAUTICAS S.A. (CASA): Amendment 39-8298. Docket No. 92-NM-131-AD. Applicability: All Model C-212 series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished within the last 300 hours time-in-service before the effective date of this AD. To ensure proper operation of the backup blocking device, accomplish the following: (a) Within 48 hours after the effective date of this AD, and thereafter at intervals not to exceed 300 hours time-in-service, accomplish the following: (1) Jack up the airplane so that both main landing gear shock absorbers are fully extended. (2) Move both power levers to the flight idle position or above. (3) Without power applied to the auxiliary battery busbar and/or with circuit breaker KA55 open, lift the flight idle stop gate triggers and move both power levers into the ground idle position or below. It should be possible to freely move the power levers below the flight idle gate in this step of the test. (4) Move the power levers to the flight idle position or above a second time. (5) Apply power to the auxiliary battery busbar and ensure that circuit breaker KA55 is closed. (6) Lift the flight idle stop gate triggers and attempt to move both power levers to ground idle position or below. It should be impossible to move the power levers below the flight idle position. If one or both power lever(s) can be moved below the flight idle position in this step of the test, the backup blocking device is not working properly. Prior to further flight, restore the backup blocking devices to the configuration described in CASA Service Bulletin 212-76-07, dated July 27, 1990; and re-test the system. (b) Within 10 days after accomplishing the functional tests required by paragraph (a) of this AD, report the results of those tests, positive or negative, to the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington 98055-4056; fax (206) 227-1320. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056. (c) 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, FAA, Transport 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, Standardization Branch. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (d) 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. (e) The restoration of the backup blocking devices to the proper configuration shall be done in accordance with CASA Service Bulletin 212-76-07, dated July 27, 1990. 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 Construcciones Aeronauticas S.A. (CASA), Getafe, Madrid, Spain. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. (f) This amendment becomes effective on July 31, 1992, to all persons except those persons to whom it was made immediately effective by telegraphic AD T92-13-51, issued June 16, 1992, which contained the requirements of this amendment.
2010-17-13: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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: A number of LPT casings have been found cracked during engine shop visit. Cracking of the LPT casing reduces the capability of the casing to contain debris in the event of an LPT stage 1 blade failure. Therefore, blade failure in an engine featuring a cracked LPT casing may result in release of uncontained high energy debris. For the reason described above, this AD requires repetitive inspections and corrective actions, depending on findings. We are issuing this AD to detect cracks in the low-pressure turbine (LPT) casings, which could result in the release of uncontained high- energy debris in the event of a stage 1 blade failure. Uncontained high-energy debris could result in damage to the airplane.
2010-17-04: 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: A crack has been found on the Droop Nose (DN) 1 master sidestay bracket on the inboard leading edge of an Airbus A380 flight test aeroplane. In case of failure of the master bracket, the sub-master bracket would be able to sustain limit loads but not ultimate loads. This condition, if not detected and corrected, could lead to a DN failure which would affect the structural integrity of that wing area. * * * * * This AD requires actions that are intended to address the unsafe condition described in the MCAI.
91-03-02: 91-03-02 BRITISH AEROSPACE: Amendment 39-6865. Docket No. 90-NM-191-AD. Applicability: Model ATP series airplanes equipped with AC generators, part numbers BA03301, BA03301-01, and BA03301-02; certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent a rupture in the AC generators' oil system and subsequent loss of electrical power, accomplish the following: A. Within 125 hours time-in-service after the effective date of this AD, and thereafter at intervals not to exceed 500 hours time-in-service, perform a visual inspection of the inlet oil strainer, and the outlet and vent oil filters, in accordance with Lucas Aerospace Service Bulletin BA03301-24-1, Revision 3, dated August 28, 1989. If evidence of debris is found, prior to further flight, replace the generator. B. On generators having part numbers BA3301-01 and BA3301-02, within 1,250 hours time-in-service after the effective date of this AD, install a new outlet filter and a new vent filter, in accordance with Lucas Aerospace Service Bulletin BA03301-24-2, Revision 3, dated August 14, 1989. Repeat the inspection required by paragraph A. of this AD at intervals not to exceed 500 hours time-in-service. C. Within 18 months after the effective date of this AD, install a new end plate, a new mainframe, and revised sealing features on the stator bolts and within the terminal block area, in accordance with Lucas Aerospace Service Bulletin BA03301-24-3, dated September 19, 1989. Incorporation of this modification terminates the requirement for the repetitive inspections and modifications required by paragraphs A. and B. of this AD. D. 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, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence 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 service documents from the manufacturer may obtain copies upon request to British Aerospace, PLC, Librarian for Service Bulletins, P. O. Box 17414, Dulles International Airport, Washington, D.C. 20041-0414. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6865, AD 91-03-02) becomes effective on February 25, 1991.
93-01-12: 93-01-12 SHORT BROTHERS, PLC: Amendment 39-8466. Docket 92-NM-159-AD. Applicability: Model SD3-60 series airplanes; as listed in Short Brothers Service Bulletin SD360- 33-23, dated June 1, 1992; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the emergency lights to illuminate during an emergency, accomplish the following: (a) Within 6 months after the effective date of this AD, modify the power supply to the emergency lighting system and perform a functional test of the system, in accordance with paragraph 2.A., Part A, B, C, or D, as applicable, of the Accomplishment Instructions of Short Brothers Service Bulletin SD360-33-23, dated June 1, 1992. (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, FAA, Transport Airplane Directorate. Operatorsshall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (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 modification and functional test shall be done in accordance with Short Brothers Service Bulletin SD360-33-23, dated June 1, 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 Short Brothers, PLC, 2011 Crystal Drive, Suite 713, Arlington, Virginia 22202-3719. 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 March 2, 1993.
90-26-03: 90-26-03 AIRBUS INDUSTRIE: Amendment 39-6828. Docket No. 90-NM-143-AD. Applicability: Model A300 B4-100 and B4-200, A310-200 and -300, and A300-600 B4- 600 series airplanes, without Messier Hispano Bugatti (MHB) Modification 784, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To detect and prevent corrosion and protection deterioration (paint and cadmium coating) and subsequent rupture of the main landing gear (MLG) bogie beam accomplish the following: A. Perform an inspection of the inner side of the bogie beam between the two axles in accordance with Airbus Industrie Service Bulletins A300-32-394, Revision 3, dated October 10, 1990 (for Model A300 Series Airplanes); A310-32-2053, Revision 1, dated March 5, 1990 (for Model A310 series airplanes); or A300-32-6031, Revision 1, dated March 5, 1990 (for Model A300-600 series airplanes); as follows: 1. For bogie beams which have never been subject to a general overhaul, prior to reaching 6 years and 6 months since new, or within 60 days after the effective date of this AD, whichever occurs later; or 2. For bogie beams which have been subject to a general overhaul, within 6 months after the effective date of this AD or prior to reaching 3 years and 6 months since overhaul, whichever occurs later. NOTE: These service bulletins reference MHB Service Bulletin 470-32-659, Revision 1, dated January 8, 1990, for additional instructions. B. If cracks or corrosion are found, prior to further flight, repair or replace bogie beam in accordance with Airbus Industrie Service Bulletins A300-32-394, Revision 3, dated October 10, 1990 (for Model A300 Series Airplanes); A310-32-2053, Revision 1, dated March 5, 1990 (for Model A310 series airplanes); or A300-32-6031, Revision 1, dated March 5, 1990 (for Model A300-600 series airplanes). NOTE: These service bulletins reference MHB Service Bulletin 470-32-659 for additional instructions.C. For bogie beams with traces of corrosion in a critical area, as defined in MHB Service Bulletin 470-32-659, Revision 1, dated January 8, 1990, replace bogie beam within 10 months following the repair or since the reinstallation on the airplane, whichever occurs later. D. For bogie beams having had paint restoration in a critical area, as defined in MHB Service Bulletin 470-32-659, Revision 1, dated January 8, 1990, perform repetitive inspections at intervals not to exceed 18 months. E. If no corrosion or defects are found, repeat the inspection, required by paragraph A., above, at intervals not to exceed 3 years and 6 months. F. Incorporation of MHB Modification 784, in accordance with MHB Service Bulletin 470-32-672, dated January 23, 1990, constitutes terminating action for the inspections required by paragraph A., D., and E., above. G. 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, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspection (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch. H. 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 Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6828, AD 90-26-03) becomes effective on December27, 1990.
2021-24-19: The FAA is adopting a new airworthiness directive (AD) for all DG Flugzeugbau GmbH Model DG-500MB and DG-1000M gliders with a Solo Kleinmotoren GmbH Solo Model 2625 02i engine installed. This AD was prompted by mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as an error in the engine control unit (ECU) software. This AD requires updating the ECU software. The FAA is issuing this AD to address the unsafe condition on these products.
2009-06-05 R1: We are revising an existing 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: [S]everal cases of wing anti-ice piccolo duct failure reported on CL-600-2B19 (CRJ) aircraft. Although there have been no failures reported on Challenger aircraft, similar ducts are installed on the * * * [other] Challenger models. * * * * * Cracking of the wing anti-ice piccolo ducts could result in air leakage, with an adverse effect on the anti-ice air distribution pattern and a possible unannunciated insufficient heat condition. * * * The unsafe condition is anti-ice system air leakage with a possible adverse effect on the anti-ice air distribution pattern and anti-ice capability without annunciation to the flightcrew, and consequentreduced controllability of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective April 1, 2010. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of April 1, 2010. On April 28, 2009 (74 FR 12225, March 24, 2009), the Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD.
80-19-18: 80-19-18 LOCKHEED - CALIFORNIA: Amendment 39-3920. Applies to Lockheed Model L-1011-385 series airplanes certificated in all categories. Compliance required within 25 hours' time in service from the effective date of this AD, unless already accomplished. To prevent possible fire damage to the forward electronic service center accomplish the following: a) Open the circuit breaker labeled "HEATERS JET PUMP LAV" (L-1011-385-1), "HEATERS LAV JET PUMP" (L-1011-385-3); collar the circuit breaker and install a tag labeled "Do Not RE-SET". NOTE: Lockheed Alert Service Bulletin 093-21-A180 dated March 12, 1980 refers to this subject. b) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. This amendment becomes effective September 29, 1980.
91-14-08: 91-14-08 AEROSPATIALE: Amendment 39-7049. Docket No. 91-NM-51-AD. Applicability: Model SN 601 Corvette series airplanes, which have incorporated Modification 1390, certificated in any category. Compliance: Required within 100 landings after the effective date of this AD, unless previously accomplished. To prevent ice formation in the fuel line and subsequent loss of engine power, accomplish the following: A. Remove the existing thermostatic element, Part Number 9914, and install thermostatic element Part Number 5497-1, in accordance with Aerospatiale Corvette Service Bulletin 73-3, Revision 1, dated July 30,1990. B. 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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. C. 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. This amendment (39-7049, AD 91-14-08) becomes effective on July 29, 1991.
2010-17-09: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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: Reports have been received indicating that, if the power control friction wheel is tightened, the reverse thrust latch may stick and subsequently allow the Power Control Lever (PCL) to be inadvertently retarded aft of the idle detent. This condition, if not corrected, could result in undesired reverse thrust activation which, especially during approach, could result in reduced control of the aeroplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
95-22-11: 95-22-11 AIRBUS: Amendment 39-9419. Docket 95-NM-194-AD. Applicability: Model A320 airplanes; having manufacturer's serial numbers (MSN) 006, 008, 011, 017, 018, 039, 042, 045, 046, and 047; certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (b) of this AD to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition; or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe conditionaddressed by this AD. In no case does the presence of any modification, alteration, or repair remove any airplane from the applicability of this AD. Compliance: Required as indicated, unless accomplished previously. To prevent the initiation and propagation of fatigue cracking in fuselage frame 20, which could adversely affect the structural integrity of this area of the fuselage, accomplish the following: (a) Prior to the accumulation of 14,000 total landings, or within 6 months after the effective date of this AD, whichever occurs later, reinforce the left fuselage frame (FR) 20 between stringers 30 and 32, in accordance with Airbus Service Bulletin A320-53-1017, Revision 1, dated September 7, 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, Standardization Branch, ANM-113, FAA, Transport 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, Standardization Branch, ANM-113. NOTE 2: 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 sections 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 reinforcement shall be done in accordance with Airbus Service Bulletin A320-53-1017, Revision 1, dated September 7, 1993, which contains the following list of effective pages: Page Number Revision Level Shown on Page Date Shown on Page 1, 3 1 September 7, 1993 2, 4-16 Original December 4, 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 Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 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 November 24, 1995.
67-33-03: 67-33-03 GENERAL DYNAMICS: Amdt. 39-528 Part 39 Federal Register December 29, 1967, as amended by Amendment 39-1528. Applies to Model 240/340/440 airplanes using turbo-propeller power which have been modified to incorporate underwing pressure fueling per STC Nos. SA1316WE, SA1132WE, SA1096WE or SA1054WE. Compliance required as indicated. Because of three reports of overpressurization of the wing fuel tank in affected airplane types that have been attributed to failure of the upper and lower diaphragm assemblies in the pressure fueling valves (P/N 2640644 or P/N 2650198), accomplish the following: (1) Before further flight from the next maintenance base where facilities and personnel are available, externally inspect each wing in the area of the fuel tank for fuel leakage; (2) If fuel leakage is found as a result of the inspection per Paragraph (1), before further flight internally inspect each wing fuel tank exhibiting fuel leakage for presence of structural damage; (3) If structural damage is found as a result of the inspection per Paragraph (2), before further flight repair portion of each wing exhibiting structural damage as necessary; and (4) Within thirty days after the effective date of this amendment to AD 67-33-03, unless already accomplished, install adjacent to each underwing refuel valve in clear view of ground fueling crews a placard stating, 'Remove the overwing filler cap(s) while fueling the tank above 80% capacity. If not, further inspection required per AD 67-33-03.' When fueling at or above 80% of the fuel tank capacity, perform all underwing fueling with overwing fuel tank filler cap(s) removed. The placard may be removed, and the procedure described in this paragraph may be discontinued after the accomplishment of (5) below. (5) Compliance with paragraph (4) is no longer required: (a) When underwing pressure fueling system as installed on the Model 240 aircraft is modified to incorporate a pressure vent valve in accordance with Aircraft Tank Service, Incorporated, Drawing 2036, Change "A", entitled 'Refueling Valve Installation-CV 240', dated April 23, 1966, or later FAA-approved revisions, or an equivalent modification approved by the Chief, Aircraft Engineering Division, Western Region. (b) When the underwing pressure fueling system as installed on the Model 340/440 aircraft is modified to incorporate a pressure vent valve in accordance with Aircraft Tank Service, Incorporated, Drawing 2363, Change "B", entitled 'Installation of Pressure Vent Valve-Wing Fuel Tanks - Convair 340/440', dated July 3, 1968, or later FAA-approved revisions, or an equivalent modification approved by the Chief, Aircraft Engineering Division, Western Region. (6) If either (a) fuel leakage or overpressurization is detected in operation, or (b), the aircraft is known to have been refueled not in accordance with the procedure set forth in paragraph (4) above, repeat the inspection described in paragraphs (1) and (2) above, and accomplish repairs, per (3) above, if applicable. Amendment 39-528 was effective December 29, 1967, for all persons except those to whom it was made effective immediately by telegram issued previously. This Amendment 39-1528 is effective October 3, 1972.
90-14-01: 90-14-01 FAIRCHILD AIRCRAFT CORPORATION (formerly Swearingen Aviation Corporation): Amendment 39-6866. Docket No. 90-CE-38-AD. Final rule of priority letter AD. Applicability: Models SA226-AT, SA226-TC, SA227-AT, and SA227-AC airplanes (all serial numbers), certificated in any category. Compliance: Required as indicated in the AD, unless already accomplished. To prevent rapid cabin decompression and passenger injury due to window breakage caused by ice shed from the propellers, accomplish the following: (a) Prior to further flight unless accomplished in accordance with AD 90-12-14, modify the passenger seat adjacent to the cabin window at Station 181 on the right side of the cabin on those airplanes whose propellers turn counterclockwise looking forward, or on the left side of the cabin on those airplanes whose propellers turn clockwise looking forward, by accomplishing one of the following actions: (1) Fabricate a placard using letters at least one inch in height on a contrasting background to read: "DO NOT OCCUPY THIS SEAT AT ANY TIME" and install this placard on the passenger seat closest to the cabin window at Station 181 of the passenger cabin in clear view of the occupants, or (2) Remove the passenger seat closest to the cabin window at Station 181 of the passenger cabin. (b) Within the next 30 calendar days after the effective date of this AD, unless accomplished in accordance with AD 90-12-14, reinforce the applicable cabin window located at Station 181 in the passenger cabin in accordance with either paragraph (b)(1) or (b)(2) of this AD. The restrictions required by paragraph (a) of this AD are no longer applicable when this modification has been accomplished. (1) Add an inner pane in accordance with the instructions in Fairchild Aircraft Corporation Service Bulletins 226-56-004, revised January 8, 1990, or 227-56-004, issued July 26, 1989, as applicable, or (2) Add a metal cover over the outside of the window in accordance with Fairchild Aircraft Corporation Kit 27K22005, Revision A, issued June 14, 1990. (c) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (d) An alternate method of compliance or adjustment of the compliance times which provide an equivalent level of safety may be approved by the Manager, Airplane Certification Office, Fort Worth, Texas 76193-0150 (facsimile number (817) 624-5988). NOTE: The request should be forwarded through an FAA Maintenance Inspector, who may add comments and then send it to the Manager, Airplane Certification Office, Fort Worth, Texas. Airworthiness Directive 90-14-01 supersedes priority letter AD 90-12-14. This amendment (39-6866, AD 90-14-01) becomes effective on February 11, 1991, as to all persons except those persons to whom it was made immediately effective by priority letter AD 90-14-01, issued June 29, 1990, which contained this amendment.
68-21-02: 68-21-02 AERO COMMANDER: Amdt. 39-669. Applies to Aero Commander Model 100, Serial Nos. 1 through 278, and Aero Commander Model 100-180, Serial Nos. 5001 through 5080 airplanes. Compliance required as indicated. To prevent the possibility of aileron cable failure caused by improper swaging of P/N 35606 Aileron Cable Assembly, accomplish the following prior to further flight: (a) Unless already accomplished, inspect P/N 35606 Aileron Cable Assembly in accordance with Aero Commander Service Bulletin No. 1015, dated October 4, 1968, or later FAA approved revisions or in a manner approved by the Chief, Engineering and Manufacturing Branch, Southern Region. (b) If indications of improper swaging or of cable slippage are found, replace the assembly with a new P/N 35606 aileron cable assembly that is properly swaged in accordance with the criteria specified in Figure I of the service bulletin. This amendment becomes effective October 15, 1968.
89-24-09: 89-24-09 BEECH: Amendment 39-6381. Applicability: The airplanes listed below, certificated in any category: MODELS SERIAL NUMBERS A23-19, 19A, M19A, B19 MB-1 through MB-816, except MB-814 23, A23, A23A, B23, C23 M-1 through M-1879, except M-1875 A23-24, A24 MA-1 through MA-368 A24R MC-2 through MC-150 B24R MC-152 through MC-451, except MC-311 and MC-449 Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To prevent the possibility of separation of aileron push rods and possible loss of aileron control, accomplish the following: (a) Within the next 100 hours time-in-service (TIS), accomplish the following in accordance with Beech Service Bulletin No. 2198, dated April 1989: (1) Install inspection openings in the wing lower skins. (2) Inspect the aileron rod ends for corrosion and freedom of movement. If serviceable, lubricate the rod end bearings. If corrosion is evident, prior to further flight replace the rod end with a new P/N 169-380082-3 rod end as specified in the above service bulletin. Corrosion is evident by restriction of movement of the rod ends. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where the AD may be accomplished. (c) An alternate method of compliance or adjustment of the compliance time which provides an equivalent level of safety, may be approved by the Manager, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, Kansas 67209; Telephone (316) 946-4400. NOTE: The request should be forwarded through an FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita Aircraft Certification Office. All persons affected by this directive may obtain copies of the documents referred to herein upon request to the Beech Aircraft Corporation, Commercial Service, Department 52, P.O. Box 85, Wichita, Kansas 67201-0085; or may examine these documents at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment (39-6381, AD 89-24-09) becomes effective on December 4, 1989.
72-14-06: 72-14-06 ROLLS-ROYCE: Amdt. 39-1479. Applies to series Dart Model 542-4, -4K, -10, -10J, and -10K engines. These engines are installed on but not necessarily limited to those Convair Model 340/440 airplanes (commonly known as Convair 600 and 640) which have the subject engines installed as a result of modification and NAMC YS-11 airplanes. Compliance is required as indicated. To prevent possible fatigue failure of first stage (low pressure) impellers, accomplish the following: (a) For a first stage (low pressure) impeller that does not incorporate Rolls Royce Dart Modification 1455, within the next 100 flights after the effective date of this AD or before the accumulation of 11,000 flights on that impeller, whichever occurs later, comply with subparagraph (c)(1) or (c)(2) and thereafter comply with paragraph (d) or (e) as applicable. (b) For a first stage (low pressure) impeller that incorporates Rolls Royce Dart Modification 1455, within the next 100 flights after the effective date of this AD or before the accumulation of 11,000 flights after the incorporation of Rolls Royce Dart Modification 1455, whichever occurs later, comply with subparagraph (c)(1) and thereafter comply with paragraph (d) or (e) as applicable. (c) Comply with subparagraph (1) or (2) of this paragraph as prescribed in paragraphs (a), (b), (d), and (e). (1) Remove the first stage (low pressure) impeller from service and replace it with - (i) A first stage (low pressure) impeller that does not incorporate Rolls Royce Dart Modification 1455 and which has accumulated less than 11,000 flights in service; or (ii) A first stage (low pressure) impeller that incorporates Rolls Royce Dart Modification 1455 and which has accumulated less than 11,000 flights in service since the incorporation of that modification. (2) For an impeller that does not have Rolls Royce Dart Modification 1455 incorporated, incorporate that modification. (d) For an impeller that has been installed in compliance with subparagraph (c)(1)(i), before the accumulation of 11,000 flights on that impeller comply with subparagraph (c)(1) or (c)(2). (e) For an impeller that has been installed in compliance with subparagraph (c)(1)(ii) or modified in accordance with subparagraph (c)(2), before the accumulation of 11,000 flights since the incorporation of Rolls Royce Dart Modification 1455 on that impeller comply with subparagraph (c)(1). (f) For the purpose of complying with this AD, a flight shall consist of an engine operating sequence consisting of an engine start, take-off operation, landing, and engine shutdown. The number of flights may be determined by actual count or, subject to acceptance by the assigned FAA Maintenance Inspector, may be calculated by dividing the compressor section's time in service by the operator's fleet average time per flight for airplanes equipped with the subject type engines. This AD supersedes the telegraphic ADon the same subject issued on April 13, 1972. NOTE: Rolls Royce Dart Alert Service Bulletin No. DA 72-391 Revision 1, dated May 1, 1972 refers to this matter. This amendment is effective upon publication in the Federal Register as to all persons except those persons to whom it was made immediately effective by the telegram dated May 31, 1972, which contained this amendment.