Results
92-08-09: 92-08-09 AIRBUS INDUSTRIE: Amendment 39-8220. Docket No. 92-NM-61-AD. Applicability: Model A320 series airplanes; manufacturer's serial numbers 002 through 122, 124 through 179, 183 through 194, 196 through 228, 230 through 245, and 247 through 255; on which the modification specified in Airbus Industrie Service Bulletin A320-34-1024, Revision 3, dated December 13, 1991, has not been accomplished; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent unsafe airspeeds, accomplish the following: (a) Within 30 days after the effective date of this AD, replace the hoses connecting the pitot probes to the air data modules with shorter hoses, in accordance with Airbus Industrie Service Bulletin A320-34-1024, Revision 3, dated December 13, 1991. (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. The request shall 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 the airplane to a location where the requirements of this AD can be accomplished. (d) The replacement shall be done in accordance with Airbus Industrie Service Bulletin A320-34-1024, Revision 3, dated December 13, 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, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, 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, 1100 L Street NW., Room8401, Washington, DC. (e) This amendment becomes effective on April 30, 1992.
2007-10-04: The FAA is adopting a new airworthiness directive (AD) for all McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD- 83), DC-9-87 (MD-87), and MD-88 airplanes. This AD requires repetitive inspections to detect cracks in the horizontal stabilizer, and related investigative/corrective actions if necessary. This AD results from reports of cracks found in the horizontal stabilizer--in the upper and lower aft skin panels at the aft inboard corner at station XH = 8.2, and in the rear spar upper caps adjacent to the aft skin panel at station XH = 10.0. We are issuing this AD to detect and correct cracks in the upper and lower aft skin panels and rear spar upper caps, which, if not corrected, could lead to the loss of overall structural integrity of the horizontal stabilizer.
91-15-02: 91-15-02 PRATT & WHITNEY CANADA, INC.: Amendment 39-7065. Docket No. 91-ANE-20. Applicability: Pratt & Whitney Canada (PWC) JT15D-4B turbofan engines, with the following serial numbers, installed on, but not limited to, Cessna model S550 (Citation S/II) series airplanes: Serial Numbers PC-E 102047 to PC-E 102050 inclusive, PC-E 102053 to PC-E 102066 inclusive, PC-E 102069, PC-E 102070, PC-E 102073, PC-E 102082, and PC-E 102089. Compliance: Required as indicated, unless previously accomplished. To prevent rupture of the gas generator case (GGC) which could result in an inflight shutdown, aborted takeoff, and/or damage to the aircraft, accomplish the following: (a) Perform a borescope inspection of GGC Part Number (P/N) 3106469-01 in accordance with PWC JT15D-4B Maintenance Manual (MM), P/N 3017542, Temporary Revision (TR) 72-95, dated January 16, 1991, and TR 72-96, dated January 16, 1991, paying particular attention to the spot welds, within 10days after the effective date of this AD, unless already accomplished within the previous 150 engine operating hours or 150 cycles in service, whichever is the shorter interval. (b) Thereafter, perform repetitive borescope inspections of GGC P/N 3106469-01 in accordance with PWC JT15D-4B MM TR 72-95, dated January 16, 1991, and TR 72-96, dated January 16, 1991, paying particular attention to the spot welds, at intervals not to exceed 150 engine operating hours or 150 cycles in service, since last inspection, whichever occurs first. (c) Borescope inspections performed in accordance with PWC Service Information Letter Number 7040, dated December 17, 1990, are considered to satisfy the requirements of paragraph (a) of this AD. (d) Remove from service prior to further flight, GGC's which are found to be cracked, and replace with a serviceable part, as defined in paragraph (e) of this AD. (e) Remove GGC P/N 3106469-01 and replace with a serviceable GGC P/N 3109069-01, 3110464-01or 3114407-01 during the next engine overhaul. (f) For the purpose of this AD an engine overhaul is defined as any engine maintenance action which includes separation of the GGC forward outer flange and aft flange. (g) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (h) Upon submission of substantiating data by an owner or operator through an FAA Inspector, (maintenance, avionics, or operations) an alternate method of compliance with the requirements of this AD or adjustments to the compliance times specified in this AD may be approved by the Manager, Engine Certification Office, ANE-140, Engine and Propeller Directorate, Aircraft Certification Service, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803-5299. The inspections shall be done in accordance with the following Pratt & Whitney Canada documents: Document Number Page Number Issue/Rev Date Temporary Revision 72-95 to PWC Maintenance Manual Part No. 3017542 1 Original 1/16/91 Temporary Revision 72-96 to PWC Maintenance Manual Part No. 3017542 1 Original 1/16/91 Total Pages: 2 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 Pratt & Whitney Canada, Inc., Publications Distribution Department, 03CA1, 1000 Marie Victorin, Longueuil, Quebec, Canada J4G 1A1. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Room 311, Burlington, Massachusetts, or at the Office of the Federal Register, 1100 L Street, NW, Room 8401, Washington, DC. This amendment (39-7065, AD 91-15-02) becomes effective on August 22, 1991.
96-25-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires modification of the thrust reverser doors, and replacement of the Collins multifunction display units (MFDU) with new MFDU's. This amendment also requires installation of a placard if the replacement of the MFDU is accomplished prior to modification of the thrust reverser door. This amendment is prompted by a report that cracks were found in the flanges of the main hinge fittings of the horizontal stabilizer, which were caused by higher than anticipated loads induced during thrust reverser operation. The actions specified by this AD are intended to ensure the structural integrity of the horizontal stabilizer by reducing the thrust reverser loads on the horizontal stabilizer.
2007-09-05: 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 CAP10B aircraft experienced a reduced elevator deflection by about 13[deg] due to an incorrect routing of the Push To Talk (PTT) wire bundle and improperly secured connectors which impeded the complete and free movement of the control stick. We are issuing this AD to require actions to correct the unsafe condition on these products.
2007-09-03: The FAA is adopting a new airworthiness directive (AD) for certain Learjet Model 45 airplanes. This AD requires deactivating the auxiliary power unit (APU), capping/plugging the fuel lines to the APU, and removing the APU fuel shutoff valve. This AD results from reports of fuel leaking from the APU fuel shutoff valve into a flammable fluid fire protection area that is also interconnected with the main landing gear's wheel well bay. We are issuing this AD to prevent fuel leaking from the fuel shutoff valve of the APU, which could result in an uncontrollable fire and adversely affect the airplane's continued safe flight and landing.
91-10-09: 91-10-09 BOEING: Amendment 39-6993. Docket No. 90-NM-238-AD. \n\n\tApplicability: Model 767 series airplanes, line number 300 through 307, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent structural failure of the vertical stabilizer from overpressurization in the event of a rupture of the fuselage under the dorsal fin, accomplish the following: \n\n\tA.\tWithin the next 18 months after the effective date of this amendment, install a cover plate and a panel assembly over the lightening and access holes in the vertical stabilizer forward closure rib, in accordance with Boeing Alert Service Bulletin 767-55A0007, dated June 22, 1989, or Revision 1, dated May 24, 1990. \n\n\tB.\tAn 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, Seattle Aircraft Certification Office (ACO), 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, Seattle ACO. \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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. \n\n\tThis amendment (39-6993, AD 91-10-09) becomes effective on June 17, 1991.
2007-08-06: 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: This Airworthiness Directive * * * is published in order to maintain the structural integrity of the applicable aircraft. The Service Bulletin provides life limits for critical landing gear components. Failure of such items could lead to unsafe conditions. We are issuing this AD to require actions to correct the unsafe condition on these products.
92-08-14: 92-08-14 McDONNELL DOUGLAS: Amendment 39-8225. Docket No. 91-NM-276-AD. \n\n\tApplicability: Models DC-8-61, -62, -63, and -73 series airplanes equipped with a cargo conversion modification installed in accordance with Supplemental Type Certificate (STC) SA1802SO, certificated in any category. \n\n\tCompliance: Required within 180 days after the effective date of this AD, unless accomplished previously. \n\n\tTo prevent reduced structural integrity of the cargo compartment and possible loss of cargo restraint capability during emergency landing conditions, accomplish the following: \n\n\t(a)\tModify the cargo area subfloor structure and install fuselage overhead external doubler straps, in accordance with Rosenbalm Aviation, Inc., Service Bulletin DC-8 51-01, dated May 1, 1991. \n\n\t(b)\tInstall transverse cusp membranes and re-attach the longitudinal cusp membrane to the seat track outboard flange, in accordance with Rosenbalm Aviation, Inc., Service Bulletin DC-8 51-02, dated June 1,1991. \n\n\t(c)\tAn 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, Atlanta Aircraft Certification Office (ACO), FAA, Small Airplane Directorate. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Atlanta ACO. \n\n\t(d)\tSpecial 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. \n\n\t(e)\tThe modifications shall be done in accordance with Rosenbalm Aviation, Inc., Service Bulletins DC-8 51-01, dated May 1, 1991, and DC-8 51-02, dated June 1, 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 Rosenbalm Aviation, Inc., c/o Zantop International Airlines, Macon Municipal Airport, P.O. Box 10138, Macon, Georgia 31297. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the FAA, Small Airplane Directorate, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. \n\n\t(f)\tThis amendment becomes effective on May 29, 1992.
75-17-35: 75-17-35 LOCKHEED: Amendment 39-2325. Applies to all Model 382 series airplanes through serial number 4610. Before further flight, unless already accomplished, perform the propeller torque check in accordance with Lockheed Alert Service Bulletin A 382-190. If the propellers do not pass the torque check, replace the propeller control with a control that will pass the above operational check prior to further flight. This amendment is effective August 13, 1975, and was effective on receipt for all recipients of the telegram dated July 25, 1975 which contained this amendment.
96-02-01: This amendment adopts a new airworthiness directive (AD) that applies to S.N. CentrAir Model 201 (all types) sailplanes. This action requires replacing all aileron balancing mass screws made of brass with screws made of steel, inspecting all steel screws for tightness, replacing any loose screws, and applying a normal screw thread safety bond. Incorrect fastening of the aileron balancing mass found on a Model 201 sailplane in France prompted this action. The actions specified in this AD are intended to prevent aileron failure and flutter caused by incorrect fastening of the aileron mass balance, which, if not detected and corrected, could result in loss of control of the sailplane.
2007-07-07: The FAA is superseding an existing airworthiness directive (AD) for General Electric Company (GE) CF34-1A, -3A, -3A1, -3A2, -3B, and -3B1 turbofan engines. That AD requires a onetime inspection of certain fan disks for electrical arc-out indications, replacing fan disks with electrical arc-out indications, and reducing the life limit of certain fan disks. This AD requires the same reduced life limit of certain fan disks, but requires on-wing inspection of certain fan disks installed on regional jets within 500 flight hours after the effective date of this AD. This AD also requires more enhanced shop-level inspections of all fan disks for electrical arc-out defects. This AD results from a report that in January 2007, a CF34-3B1 turbofan engine experienced an uncontained fan disk failure during flight operation. We are issuing this AD to prevent an uncontained fan disk failure and airplane damage.
90-16-03: 90-16-03 AEROSPATIALE: Amendment 39-6681. Docket No. 90-NM-51-AD. Applicability: All Model Corvette SN 601 series airplanes that have not incorporated Modification No. 1397, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent reduced structural integrity of the fuselage, accomplish the following: A. Prior to the accumulation of 9,800 landings or within 100 landings after the effective date of this AD, whichever occurs later, perform a high frequency eddy current inspection of the left-hand inner beam between Frame 16 and Frame 20, in accordance with Corvette SN 601 Service Bulletin, 53-18, Revision 1, dated January 22, 1990. B. If no cracks are found, repeat the inspection required by paragraph A., above, at intervals not to exceed 3,900 landings. C. If cracks are found, modify prior to further flight, in accordance with Corvette SN 601 Service Bulletin 53-11, Revision 2, dated January 15, 1990. Incorporation of this modification (No. 1397) constitutes terminating action for the repetitive inspections required by paragraph B., above. D. Within one year after the effective date of this AD, replace all left-hand inner beam stiffeners between Frame 16 and Frame 20, in accordance with Corvette SN 601 Service Bulletin 53-11, Revision 2, dated January 15, 1990. Incorporation of this modification (No. 1397) constitutes terminating action for the repetitive inspections required by paragraph B., above. E. 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, StandardizationBranch, ANM-113. F. 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 Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6681, AD 90-16-03) becomes effective on August 31, 1990.
2007-07-11: 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: Due to quality escape during serial production, the jumpers at the Right Fuel Standby Pump Connector 4Q1 were manufactured from 14 AWG electrical wiring instead of 12 AWG wires as required per approved drawing. The possible overheating of the 14 AWG jumpers routed in vicinity of the fuel tank may present the unsafe flight condition. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2007-06-01: We are adopting a new airworthiness directive (AD) that supersedes AD 62-24-01, which applies to all Raytheon Aircraft Company (RAC) Beech Models 45 (YT-34), A45 (T-34A, B45), and D45 (T-34B) airplanes. AD 62-24-01 currently requires you to repetitively inspect, using the dye penetrant method, the front and rear horizontal stabilizer spars for cracks and replace any cracked stabilizer. Since we issued AD 62-24-01, we determined that using the dye penetrant inspection method may not detect cracks before the crack grows to a critical length and causes failure of the horizontal stabilizer spars. Therefore, we are requiring the surface eddy current inspection method to detect cracks in the horizontal stabilizer spars. Consequently, this AD retains the actions required in AD 62-24-01 and changes the required inspection method from dye penetrant to surface eddy current. We are issuing this AD to prevent failure of the front and/or rear horizontal stabilizer spars caused by fatigue cracks. This failure could result in stabilizer separation and loss of control of the airplane.
95-25-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 and A300-600 series airplanes, that requires that certain flight control computers be modified so that the autopilot will disengage when the airplane is in the "go-around" mode under certain conditions. This amendment is prompted by an accident in which the flight crew may have initiated an inadvertent go-around which, following several subsequent actions by the crew and automated system, placed the airplane in a severe out-of-trim condition. The actions specified by this AD are intended to prevent an out-of-trim condition between the trimmable horizontal stabilizer and the elevator, which may severely reduce controllability of the airplane.
2007-06-11: 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: Cracks on a vertical stabilizer attachment fitting due to corrosion, have been found on an aircraft in service. We are issuing this AD to require actions to correct the unsafe condition on these products.
89-20-10: 89-20-10 BRITISH AEROSPACE: Amendment 39-6332. (Docket No. 89-NM-35-AD) Applicability: British Aerospace Model BAe 146 series airplanes, certificated in any category. Compliance Required as indicated, unless previously accomplished. To prevent loss of control of the airplane on the ground, accomplish the following: A. Within 100 landings after the effective date of this AD, or within 100 landings after the last inspection accomplished in accordance with AD 88-22-05, Amendment 39-6047, whichever occurs later, check the torque on and mark the nose wheel steering cuff ring nut, in accordance with the procedures in paragraph 2.A. of British Aerospace Service Bulletin 32-A95, Revision 1, dated December 2, 1988. 1. If the ring nut torque loading is found to be incorrect, prior to further flight, re-torque in accordance with paragraph 2.A.(2) of the service bulletin, and reinspect in accordance with paragraph 2.B. of the service bulletin within 30 days andthereafter at intervals not to exceed 300 landings. 2. If the ring nut torque loading is found to be within the limits specified in the service bulletin, repeat the inspections in accordance with paragraph 2.B. of British Aerospace Service Bulletin 32-A95, Revision 1, dated December 2, 1988, at intervals not to exceed 300 landings. NOTE: Paragraph 2.A. of British Aerospace Service Bulletin 32-A95 refers to British Aerospace Service Bulletin 32-29 for checking the steering friction damper torque. B. Within 2,800 landings after the effective date of this AD, modify the nose wheel steering ring nut locking means in accordance with British Aerospace Modification Service Bulletin 32-95-70409A, dated December 12, 1988. Installation of this modification constitutes terminating action for the inspection requirements of this AD. 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, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Standardization Branch, ANM-113. 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 British Aerospace PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This AD supersedes AD 88-22-05, Amendment 39-6047, which became effective on November 8, 1988. This amendment (39-6332, AD 89-20-10) becomes effective on October 30, 1989.
76-24-04: 76-24-04 MORANE SAULNIER (SOCATA): Amendment 39-2780. Applies to Models MS 892A-150, MS 892E-150, and MS 893A airplanes, all serial numbers, and Model MS 893E airplanes, serial numbers 12674 and below, certificated in all categories. Compliance is required as indicated, unless already accomplished. To detect rocker oil return pipe wear and prevent possible engine failure, accomplish the following: (a) Within the next 10 hours time in service after the effective date of this AD, inspect the rocker oil return pipes for wear in accordance with Socata Service Bulletin No. 124, GR 79-09, dated January 1976, or an FAA-approved equivalent. (b) If, during the inspection required by paragraph (a) of this AD, rocker oil return pipe wear is found to exceed 10% of pipe wall thickness, before further flight, replace the part with a new part of the same part number. (c) Within the next 25 hours time in service after the effective date of this AD, rework the cylinder cooling deflector spring in accordance with Socata Service Bulletin No. 124, GR 79-09, dated January 1976, or an FAA-approved equivalent. This amendment becomes effective on December 14, 1976.
2007-06-05: 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: * * * * ** * * updates [to the airplane maintenance manual (AMM), engine service manual (ESM), and quick engine change kit instruction manual (QECKIM)] have inadvertently introduced torque value errors for the bolts that attach the forward engine mount to the engine. * * * * * * * * Application of the incorrect torque to the forward engine mount bolts during maintenance could result in failure of the forward engine mount and possible separation of the engine from the airplane and damage to the wing or loss of control of the airplane. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2007-06-02: The FAA is superseding an existing airworthiness directive (AD), which applies to all Airbus Model A318-100 and A319-100 series airplanes, Model A320-111 airplanes, and Model A320-200, A321-100, and A321-200 series airplanes. That AD currently requires repetitive inspections of the upper and lower attachments of the trimmable horizontal stabilizer actuator (THSA) to measure for proper clearance and to detect cracks, damage, and metallic particles. The existing AD also requires corrective actions, if necessary, and reports of inspection findings. This new AD shortens the repetitive interval for inspecting the upper THSA attachment. This AD results from new test results on the secondary load path, which indicated the need to shorten the repetitive interval for inspecting the upper THSA attachment. We are issuing this AD to detect and correct failure of the THSA's primary load path, which could result in latent (undetected) loading and eventual failure of the THSA's secondary load path and consequent uncontrolled movement of the horizontal stabilizer and loss of control of the airplane. DATES: This AD becomes effective April 19, 2007. The Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A320-27-1164, Revision 04, including Appendix 01, dated July 17, 2006, as of April 19, 2007. On May 5, 2006 (71 FR 16203, March 31, 2006), the Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A320-27-1164, Revision 03, including Appendix 01, dated August 24, 2005.
93-10-04: 93-10-04 GULFSTREAM AEROSPACE CORPORATION: Amendment 39-8582. Docket 92-NM-222-AD. Supersedes AD 89-05-05, Amendment 39-6198. Applicability: All Model G1159 (G-II), G1159A (G-III), G1159B (G-IIB), and G-IV series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent fire bottles being discharged into the wrong nacelle, accomplish the following: (a) Within 3 days or 10 hours time-in-service after May 8, 1989 (the effective date of AD 89-05-05, Amendment 39-6198), whichever occurs later, perform an inspection to determine proper configuration of electrical power leads to the engine fire extinguishing system, in accordance with the following Gulfstream Alert Customer Bulletins, dated February 2, 1989: G-II Bulletin No. 20 (for Model G1159/G1159B series airplanes); G-III Bulletin No. 4 (for Model G1159A series airplanes); or G-IV Bulletin No. 5 (for Model G-IV series airplanes); as applicable. If the configuration is not correct, prior to further flight, correct the installation in accordance with the applicable alert customer bulletin. (b) Immediately following any maintenance performed on the engine fire extinguishing system, perform the inspection procedures required by paragraph (a) of this AD in accordance with the applicable alert customer bulletin to ensure that the system is functioning properly. (c) Within 2 years after the effective date of this AD, modify the electrical leads and plumbing connections to the fire extinguishers in accordance with the following Gulfstream Aircraft Service Changes: Gulfstream II/IIB Change No. 401, dated December 6, 1991 (for Model G1159/G1159B series airplanes); Gulfstream III Change No. 195, dated December 6, 1991 (for Model G1159A series airplanes); or Gulfstream Change No. 146, dated September 5, 1991 (for Model G-IV series airplanes); as applicable. Accomplishment of this modification constitutes terminating action for theinspection procedures required by paragraph (b) of this AD. (d) 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, Atlanta Aircraft Certification Office (ACO), FAA, Small Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta ACO. (e) 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. (f) The inspections shall be done in accordance with Gulfstream G-II Alert Customer Bulletin No. 20, dated February 2, 1989 (for Model G1159/G1159B series airplanes); Gulfstream G-III AlertCustomer Bulletin No. 4, dated February 2, 1989 (for Model G1159A series airplanes); or Gulfstream G-IV Alert Customer Bulletin No. 5, dated February 2, 1989 (for Model G-IV series airplanes); as applicable. The modification shall be done in accordance with Gulfstream II/IIB Aircraft Service Change No. 401, dated December 6, 1991 (for Model G1159/G1159B series airplanes); Gulfstream III Aircraft Service Change No. 195, dated December 6, 1991 (for Model G1159A series airplanes); or Gulfstream IV Aircraft Service Change No. 146, dated September 5, 1991 (for Model G-IV series airplanes); as applicable. 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 Gulfstream Aerospace Corporation, Technical Operations Department, P.O. Box 2206, Savannah, Georgia 31402-9980. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington;or at the FAA, Small Airplane Directorate, Atlanta Aircraft Certification Office, Suite 210C, 1669 Phoenix Parkway, Atlanta, Georgia; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on July 1, 1993.
95-21-20: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires a visual inspection to detect damage to the flexible fuel drain line of the auxiliary power unit (APU), and replacement of the drain line, if necessary. This amendment also requires installation of two additional clamps to secure the flexible fuel drain line to the fuel supply line of the APU. This amendment is prompted by reports of electrical arcing between the flexible fuel drain line and the APU starter motor. The actions specified by this AD are intended to prevent such electrical arcing, which could result in a fire in the APU.
2007-05-12: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330 airplanes and Model A340-200 and -300 series airplanes. This AD requires inspecting to determine the part number of certain S4- and MZ-type spoiler servo controls (SSCs). For certain other airplanes, this AD requires inspecting to determine the part number of all SSCs. This AD also requires replacing any affected SSC with a new SSC. This AD results from a new load duty cycle defined by the manufacturer. Additional fatigue tests and calculations done on this basis indicated that the spoiler valve manifold of the S4-type SSCs, and, on certain airplanes, the maintenance cover of the MZ-type SSCs, may crack during its service life due to pressure impulse fatigue. We are issuing this AD to prevent fatigue cracking of certain SSCs, which could result in hydraulic leakage and consequent loss of SSC function and loss of the associated hydraulic system. These conditions could affect all three hydraulicsystems, which could result in reduced controllability of the airplane.
95-23-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes. This action requires inspections to detect cracking, corrosion, and freeplay in the spherical washers located in certain assemblies where the aft flap track attaches to the wing trailing edge, and replacement of the washers, if necessary. This amendment is prompted by reports indicating that these washers can break under load. The actions specified in this AD are intended to prevent breakage of these washers, which could result in structural damage to the attachment assembly and eventually lead to separation of the flap from the airplane.