Results
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.