Results
96-22-15: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 and A300-600 series airplanes, that requires repetitive Tap Test inspections to detect debonding of the elevator skins, and corrective actions, if necessary. This amendment is prompted by a report of a debonded area of the upper skin of an elevator that was discovered during a visual inspection. The actions specified by this AD are intended to prevent the presence of water in the elevator, which could cause debonding of the elevator skins and, consequently, adversely affect the structural integrity of the elevator.
2007-13-09: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model 717-200 airplanes. This AD requires modifying the fuel boost pump container of the center tank. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent exposing the fuel pump container vapor area to electrical arcing during a fuel pump motor case or connector burn through, which could result in a fuel tank explosion.
96-07-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 050 and Model F28 Mark 0100 series airplanes, that requires an inspection to verify that adequate clearance exists between the insulation screen and the two adjacent terminal bolts, and replacement of the circuit breaker terminal bolts with new bolts, if necessary. This amendment is prompted by a report that circuit breaker terminal bolts that were too long were discovered installed in the circuit breaker panels. The actions specified by this AD are intended to prevent damage to the insulation screen between adjacent rows of circuit breakers, as the result of a circuit breaker terminal bolt being too long; this condition could lead to electrical arcing and loss of the associated electrical system, which could result in the potential for an electrical fire.
2007-12-21: The FAA is adopting a new airworthiness directive (AD) to supersede AD 2006-26-08, which applies to all Hawker Beechcraft Corporation (HBC) Model 390 airplanes. AD 2006-26-08 currently requires you to repetitively inspect the hydraulic pump outlet tube on both engines and immediately replace the tube if damage is found. AD 2006- 26-08 also requires you to incorporate an airplane flight manual (AFM) change that limits operation of an engine with its associated firewall hydraulic shutoff valve closed. If an engine is operated with its firewall hydraulic shutoff valve closed, you must replace the hydraulic pump outlet tube. We issued AD 2006-26-08 as an interim action while we worked with the type certificate holder to develop a design change. HBC has now developed kits that incorporate design changes for the hydraulic pump outlet tubes and dampener supports so this AD retains the actions of AD 2006-26-08 until the new modification kits required by this AD are installed. We continued to receive additional reports of failures of the hydraulic pump outlet tube. We are issuing this AD to prevent failure of the hydraulic pump outlet tube and consequent leaking of hydraulic fluid. Such leakage could result in a fire. There is also a risk of loss of hydraulic system functions including normal gear extensions, speed brakes, roll spoilers, lift dump, and normal brakes. DATES: This AD becomes effective on June 20, 2007. On June 20, 2007, the Director of the Federal Register approved the incorporation by reference of Raytheon Aircraft Company Kit--Dampener Support Improvement, Drawing No. 390-5804 (Kit 390-5804-0001 Field Service Kit) and Raytheon Aircraft Company Kit--Hydraulic Pump Pressure Hose Installation No. 390-5805 (Kit 390-5805-0001 Field Service Kit), as referenced in Hawker Beechcraft Mandatory Service Bulletin 29-3800, Issued May 2007, as listed in this AD. As of February 2, 2006 (71 FR 5581, February 2, 2006), the Director of the Federal Register approved the incorporation by reference of Raytheon Mandatory Service Bulletin No. SB 29-3771, dated January 2006; and Raytheon Safety Communique No. 267, dated January 2006, as listed in this AD. We must receive any comments on this AD by August 20, 2007.
2007-12-17: The FAA is adopting a new airworthiness directive (AD) for certain EMBRAER Model EMB-135 airplanes and Model EMB-145, -145ER, - 145MR, -145LR, -145XR, -145MP, and -145EP airplanes. This AD requires replacing the metallic tubes enclosing the vent and pilot valve wires in the left- and right-hand wing fuel tanks with non-conductive hoses. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent an ignition source inside the fuel tank that could ignite fuel vapor and cause a fuel tank explosion and loss of the airplane.
96-18-15: This amendment supersedes an existing airworthiness directive (AD) 96-01-08, which superseded Priority Letter AD 95-23-02, both of which were applicable to certain serial-numbered Bell Helicopter Textron, A Division of Textron Canada Ltd. (BHT) Model 222, 222B, 222U, and 230 helicopters, that currently requires an initial check of both surfaces of each tail rotor blade (blade) for cracks; an inspection of the blade skin if a crack of a specified size or location is found in the paint; and replacement of the blade if a crack is found in the blade skin. This AD requires the same actions as required by the existing AD, but expands the applicability to include additional blade part numbers (P/N). This amendment is prompted by three incidents in which a crack developed in the stainless steel blade skins due to sanding marks on the blades that occurred during the manufacturing process on BHT Model 230 helicopters, which are similar in design to the Model 222, 222B and 222U helicopters. The actions specified by this AD are intended to prevent failure of a blade due to a fatigue crack, loss of the tail rotor and tail rotor gear box, and subsequent loss of control of the helicopter.
2007-12-10: 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: Two A330 operators have reported uncontained APU (auxiliary power unit) generator failures on ground. In both events, a loud noise was heard, followed by an APU automatic shutdown. Preliminary investigations confirmed an uncontained APU Generator failure with subsequent aircraft structural damages to the APU compartment and, in one case, to the stabiliser compartment. Loose APU generator parts can lead to damage to the APU fire wall which might reduce its fire extinguishing capability, possibly leading to a temporary uncontrolled fire which constitutes an unsafe condition. * * * This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2007-12-11: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747 airplanes. That AD currently requires repetitive inspections to detect cracks and/or corrosion of the girt bar support fitting at certain main entry doors (MED), and repair or replacement of the support fitting. The existing AD also provides for various terminating actions for the repetitive inspections. This new AD requires the following additional actions: An inspection, for certain airplanes, for correct installation of square and conical washers in the girt bar support fitting; an inspection, for certain other airplanes, to determine if the washers are installed; and related investigative and corrective action if necessary. This AD results from a report that the square and conical washers may be installed incorrectly in the girt bar support fitting on airplanes on which the support fitting was repaired or replaced in accordance with the requirements of the existing AD. We are issuing this AD to detect and correct corrosion of the girt bar support fitting, which could result in separation of the escape slide from the lower door sill during deployment, and subsequently prevent proper operation of the escape slides at the main entry doors during an emergency. We are also issuing this AD to detect and correct incorrect installation of the square and conical washers in the girt bar support fitting, which could result in failure of the escape slide when deployed. \n\nDATES: This AD becomes effective July 16, 2007. \n\n\tThe Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of July 16, 2007. \n\n\tOn December 16, 1996 (61 FR 58318, November 14, 1996), the Director of the Federal Register approved the incorporation by reference of Boeing Service Bulletin 747-53A2378, Revision 1, dated March 10, 1994.
92-01-08: 92-01-08 PRATT & WHITNEY CANADA: Amendment 39-8132. Docket No. 90-ANE-29. Applicability: Pratt & Whitney Canada (PWC) PW115, PW118, PW118A, PW120, PW120A, PW121, PW123, PW124B, and PW125B model turboprop engines, with specific engine serial numbers noted in the applicable service bulletins (SB). Affected engines are installed in, but not limited to, the Aerospatiale ATR-42, and ATR-72, British Aerospace ATP, DeHavilland of Canada DHC-8, Embraer EMB-120, Canadair CL-215T, and Fokker 50 aircraft. Compliance: Required at the next engine module overhaul, hot section inspection (HSI), or within 36 months from the effective date of this airworthiness directive (AD), whichever occurs first, unless accomplished previously. To prevent seizure of the high pressure rotor, and subsequent inability to restart the engine inflight, accomplish the following: (a) Rework or replace with a serviceable part, the high pressure turbine front cover in accordance with the requirements of anyof the following PWC SBs, as applicable: SB 20417, Revision 2, dated August 20, 1990, SB 20412, dated November 27, 1989; SB 20604, Revision 1, dated February 25, 1991; or SB 20979, dated April 29, 1991. (b) Rework the low pressure turbine stator vane assembly in accordance with the requirements of PWC SB 20456, Revision 3, dated August 20, 1990. (c) For engines incorporating the "triple segmented" high pressure vane ring segment assembly, Part Number (P/N) 3037761, rework or replace the high pressure vane segments as follows: (1) For PW115, PW118, PW120, PW120A, and PW121 model turboprop engines, rework or replace with a serviceable part in accordance with the requirements of either of the following PWC SBs, as applicable: SB 20419, Revision 3, dated November 26, 1990; or SB 20886, Revision 2, dated February 11, 1991. (2) For PW118A, PW123, PW124B, and PW125B model turboprop engines, rework or replace with a serviceable part in accordance with the requirements of any of the following PWC SBs, as applicable: SB 20419, Revision 3, dated November 26, 1990; SB 20726, dated February 19, 1990; SB 20742, Revision 4, dated June 12, 1991; SB 20886, Revision 2, dated February 11, 1991; or SB 20869, Revision 1, dated April 26, 1991. (d) For engines incorporating the "triple segmented" high pressure vane ring segment assembly, P/N 3037761, rework or replace with a serviceable part, the cooling air nozzle housing assembly as follows: (1) For PW115, PW118, PW120, PW120A, and PW121 model turboprop engines, rework or replace with a serviceable part in accordance with the requirements of any of the following PWC SB's, as applicable: SB 20341, Revision 2, dated September 3, 1991, SB 20436, dated March 6, 1989, or SB 20873, Revision 3, dated April 8, 1991. (2) For PW118A, PW123, PW124B, and PW125B model turboprop engines, rework or replace with a serviceable part in accordance with the requirements of any of the following PWC SB's, as applicable: SB 20341, Revision 2, dated September 3, 1991, SB 20436, dated March 6, 1989, SB 20873, Revision 3, dated April 8, 1991, SB 20896, Revision 3, dated August 26, 1991, or SB 20872, Revision 2, dated July 8, 1991. (e) 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, Engine Certification Office, Engine and Propeller Directorate. The request should be forwarded through an FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. (f) 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. (g) The engine modifications shallbe done in accordance with the following Pratt & Whitney Canada SB's: DOCUMENT NO. PAGE ISSUE/REVISION DATE SB 20341R2 1-4 Rev. 2 Sept. 3, 1991 Total Pages: 4 SB 20412 1-8 Original Nov. 27, 1989 Total Pages: 8 SB 20417R2 1-7 Rev. 2 Aug. 20, 1990 Total Pages: 7 SB 20419R3 1-6 Rev. 3 Nov. 26, 1990 Total Pages: 6 SB 20436 1-3 Original Mar. 6, 1989 Total Pages: 3 SB 20456R3 1-3 Rev. 3 Aug. 20, 1990 4 Rev. 1 Oct. 12, 1989 5 Rev. 2 Apr. 30, 1990 6-8 Original Jun. 21, 1989 Total Pages: 8 SB 20604R1 1-7 Rev. 1 Feb. 25, 1991 Total Pages: 7 SB 20726 1-3 Original Feb. 19, 1990 Total Pages: 3 SB 20742R4 1-4 Rev. 4 June 17, 1991 Total Pages: 4 SB 20869R1 1-6 Rev. 1 Apr. 26, 1991 Total Pages: 6 SB 20872R2 1-30 Rev. 2 July 8, 1991 Total Pages: 30 SB 20873R3 1-7 Rev. 3 Apr. 8, 1991 Total Pages: 7 SB 20886R21-6 Rev. 2 Feb. 11, 1991 Total Pages: 6 SB 20896R3 1-9 Rev. 3 Aug. 26, 1991 Total Pages: 9 SB 20979 1-7 Original Apr. 29, 1991 Total Pages: 7 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, Technical Publications Department, 1000 Marie Victorin, Longueuil, Quebec 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, D.C. (h) This amendment becomes effective on July 27, 1992.
2007-12-03: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-400 series airplanes. This AD requires revising the Limitations section of the airplane flight manual to include procedures for pulling the "HYD PWR XFER'' circuit breaker in the event of the loss of all hydraulic fluid in the No. 1 or No. 2 hydraulic system. This AD results from reports of fluid loss in the No. 2 hydraulic system, causing the power transfer unit to overspeed, increasing the fluid flow within the No. 1 hydraulic system. We are issuing this AD to prevent possible loss of both the No. 1 and No. 2 hydraulic systems, resulting in the potential loss of several functions essential for safe flight and landing of the airplane.
2007-12-01: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-100, DHC-8-200, and DHC-8-300 series airplanes. This AD requires, for certain airplanes, modification of the upper bearing of the main landing gear (MLG) shock strut. This AD also requires, for certain airplanes, revising the de Havilland DHC-8 Maintenance Program Manual to include the MLG shock strut servicing task. This AD results from reports of over-extension of the MLG shock strut piston, which allows the torque links to go over-center and rest on the piston. We are issuing this AD to prevent loss in shock absorption during touchdown and failure of the shock strut housing, which could result in a subsequent loss of directional control.
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.
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.