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2007-02-23: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 777-200, -300, and -300ER series airplanes. This AD requires replacement of the gimbal plates of the left and right outboard trailing edge flaps with improved gimbal plates and other specified actions. This AD results from a broken pivot link found on the inboard support for the outboard trailing edge flap. We are issuing this AD to prevent disconnection of the drive arm from its drive gimbal, due to a broken pivot link on an outboard flap support, which could result in unexpected roll of the airplane and loss of control of the airplane.
92-06-16: 92-06-16 BOEING: Amendment 39-8196. Docket No. 91-NM-191-AD. \n\n\tApplicability: Model 757 series airplanes, listed in Boeing Alert Service Bulletin 757- 53A0060, dated August 8, 1991, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent side-of-body floor panels from breaking away from the floor beams during a 9g forward load event, accomplish the following: \n\n\t(a)\tWithin the next 24 months after the effective date of this AD, examine the identification placards of each side-of-body floor panel to determine the manufacturer and date of manufacture of the panel, as specified in Figure 1 of Boeing Alert Service Bulletin 757-53A0060, dated August 8, 1991. \n\n\t\t(1)\tIf the panel was manufactured by Hexcel before January 7, 1991: Prior to further flight, repair all one-piece inserts in the panel or replace the panel, in accordance with Boeing Alert Service Bulletin 757-53A0060, dated August 8, 1991. \n\n\t\t(2)\tIf thepanel was manufactured by Hexcel panel on or after January 7, 1991, or if the panel was not manufactured by Hexcel: No further action is required. \n\n\t(b)\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. \n\n\tNOTE: 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\t(c)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base where the requirements of this AD can be accomplished. \n\n\t(d)\tThe inspection shall be done in accordance with Boeing Alert Service Bulletin 757-53A0060, dated August 8, 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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. 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. \n\n\t(e)\tThis amendment becomes effective on April 28, 1992.
2007-11-13: The FAA is superseding an existing airworthiness directive (AD), which applies to all McDonnell Douglas Model 717-200 airplanes. That AD currently requires revising the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness to incorporate new removal limits for certain components of the flap system and to reduce the interval of inspections for fatigue cracking of certain principal structural elements (PSEs). This new AD requires revising the ALS of the Instructions for Continued Airworthiness to incorporate reduced initial inspection and repeat inspection intervals for certain PSEs. This AD results from a revised damage tolerance analysis. We are issuing this AD to detect and correct fatigue cracking of certain PSEs, which could adversely affect the structural integrity of the airplane.
2007-03-02: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce Deutschland Ltd & Co KG (RRD) Tay 611-8, Tay 620-15, Tay 650-15, and Tay 651-54 series turbofan engines, with certain low pressure (LP) compressor modules installed. This AD requires an ultrasonic inspection (UI) of LP compressor fan blades for cracks, within 30 days after the effective date of the AD on certain serial number (SN) Tay 650-15 engines. This AD also requires initial and repetitive UIs of LP compressor fan blades on all engines. This AD also requires, for Tay 650-15 and Tay 651-54 engines, UIs of LP compressor fan blades whenever the blade set is removed from one engine and installed on a different engine. This AD results from a report that a set of LP compressor fan blades failed before reaching the LP compressor fan blade full published life limit. We are issuing this AD to prevent LP compressor fan blades from failing due to blade root cracks, leading to uncontained engine failure and damageto the airplane.
76-22-01: 76-22-01 BELLANCA AIRCRAFT CORPORATION: Amendment 39-2753. Applies to: MODEL SERIAL NUMBER 7 ECA 1126-76 thru 1173-76 7GCAA 324-76 thru 332-76 7GCBC 887-76 thru 942-76 7KCAB 551-76 thru 584-76 8KCAB 219-76 thru 265-76 8GCBC 188-76 thru 228-76 And all previous serial numbered airplanes in which the adjustable front seat has been installed per Bellanca Kit #252. Compliance required within the next 10 hours' time in service after the effective date of this AD, unless already accomplished. To detect permanent deformation and/or cracks in the lower frame side tubes on the adjustable front seat, accomplish the following: a. Inspect the left and right side lower seat frame side tubes for evidence of cracks and/or permanent deformation in an area just forward of the side brace and side tube junction. A permanent upward bow in the side tube at this junction is evidence of permanent deformation. The area can best be inspected after removal of theseat cushion. b. If cracks and/or permanent deformation are found, repair per AC 43.13-1 and install Bellanca Kit #253, or replace the seat frame with a new reinforced seat frame P/N 7-1513, before further flight. c. If cracks and/or permanent deformation are not found, install Bellanca Kit #253 within the next 20 hours' time in service after the effective date of this AD. Bellanca Service Letter #C-125 dated May 19, 1976 pertains to this subject. This amendment becomes effective November 2, 1976.
2007-10-13: 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: * * * the discovery of cracks on aileron spades of an in-service CAP 10B aircraft. The consequence on the aircraft of these cracks might be the loss of the airplane rolling control. We are issuing this AD to require actions to correct the unsafe condition on these products.
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.