Results
2007-17-14: 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: Some operators have reported wheel corrosion, mainly under the heat-shield overlap area. In some cases a circular crack initiated from a corrosion pit. When the crack is initiated under the bead seat, it does not lead to tire pressure loss, and can cause a flange separation as experienced by few operators. This condition could result in separation of the wheel and consequent reduced controllability of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
76-18-07: 76-18-07 GATES LEARJET: Amendment 39-2714. Applies to Models 24 (Serial Numbers 24-230 thru 24-331 and 24-333); 25 (Serial Numbers 25-061 and 25-067 thru 25-207); 35 (Serial Numbers 35-001 thru 35-079); and 36 (Serial Numbers 36-001 thru 36-020) airplanes. Compliance: Required as indicated, unless already accomplished. To determine that each inverter is connected to the correct power bus, within the next 25 hours' time in service after the effective date of this AD, accomplish the following in accordance with Gates Learjet Service Bulletins SB 24/25-273, dated August 9, 1976, or SB 35/36-24-3, dated August 9, 1976, or later approved revisions, as applicable: A) Perform inverter operational check as outlined in the aforementioned Service Bulletins. B) If the electrical system does not operate as indicated re the operational checks required by Paragraph A, rewire the inverter input power wiring per the applicable manufacturer's Service Manual Wiring Diagram and repeat the operational check required by Paragraph A to verify proper operation of the electrical system. C) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective September 10, 1976.
2007-18-02: 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: [T]he FAA has published SFAR 88 (Special Federal Aviation Regulation 88). * * * Under this regulation, all holders of type certificates for passenger transport aircraft * * * are required to conduct a design review against explosion risks. This Airworthiness Directive (AD), which renders mandatory the modification of the fuel pump wiring against short circuit, is a consequence of this design review. The unsafe condition is chafing of the fuel pump cables, which could result in short circuits leading to fuel pump failure, intermittent operation, arcing, and possible fuel tank explosion. We are issuing this AD to require actions to correct the unsafe condition on these products.
2007-11-02: This amendment adopts a new airworthiness directive (AD) for Enstrom Helicopter Corporation (Enstrom) Model F-28A, F-28C, F-28F, TH- 28, 280, 280C, 280F, 280FX, 480, and 480B helicopters that requires determining the installation dates for each main rotor push-pull control rod (push-pull rod), inspecting the push-pull rods for corrosion, replacing any push-pull rod which has corrosion that is severe enough to cause pitting, or has visible moisture inside the rod, and repairing each push-pull rod that has corrosion but no pitting. This amendment is prompted by one reported incident in which the helicopter pilot encountered severe in-flight vibration due to the failure of a push-pull rod, requiring an emergency landing. The actions specified by this AD are intended to detect corrosion and prevent failure of a push-pull rod, and subsequent loss of control of the helicopter.
90-05-11: 90-05-11 BRITISH AEROSPACE: Amendment 39-6525. Docket No. 89-NM-233-AD. Applicability: Model BAe 146-100A and -200A series airplanes, as listed in British Aerospace Service Bulletin 57-24-00911A, Revision 1, dated May 1, 1988, certificated in any category. Compliance: Required within 180 days after the effective date of this AD, unless previously accomplished. To prevent inability of the flap system to sustain expected loads and prevent reduction of airplane controllability, accomplish the following: A. Install new roller bearing pins at the forward top position on the right and left flap track No. 3 lower carriage assemblies, in accordance with British Aerospace Service Bulletin 57-24-00911A, Revision 1, dated May 1, 1988. B. 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. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. 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, 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 amendment (39-6525, AD 90-05-11) becomes effective on April 9, 1990.
91-15-05: 91-15-05 ROLLS-ROYCE plc: Amendment 39-7068. Docket No. 91-ANE-19. Applicability: Rolls-Royce plc (RR) GEM Mk 530 series engines, installed on, but not limited to, Westland 30 aircraft. [[Dart]] Compliance: Required as indicated, unless previously accomplished. To prevent external fuel leakage from the hydromechanical fuel control unit (HMU) which could result in a fire hazard in the engine nacelle, accomplish the following: (a) For engines equipped with Hamilton-Standard Model JFC118-22 HMU, part numbers 779218-3, 779218-6, 779218-9, 779218-12, excluding HMU's marked "MS090-001" adjacent to the identification plate, perform the following: (1) Perform an HMU leak check inspection in accordance with RR Service Bulletin (SB) GEM- 73-24, dated October 29, 1990, within the next 15 hours time in service after the effective date of this AD. (2) Thereafter, reinspect the HMU daily for fuel leakage within 30 minutes of the last shut-down of the day, in accordance with RR SB GEM-73-24. (3) Remove from service, prior to further flight, HMU's exhibiting any fuel leakage when inspected in accordance with paragraphs (a)(1) or (a)(2) of this AD. (4) X-ray or disassemble inspect the HMU for correct assembly in accordance with the Accomplishment Instructions of Hamilton-Standard (HS) SB JFC118-22-73-10, dated November 21, 1990, at the next engine shop visit or HMU removal, or by December 31, 1991, whichever occurs first. (5) Remove from service, prior to further flight, HMU's confirmed incorrectly assembled when inspected in accordance with paragraph (a)(4) of this AD. (6) For HMU's determined to be correctly assembled when inspected in accordance with paragraph (a)(4) of this AD, the repetitive inspections of paragraphs (a)(1) or (a)(2) of this AD are no longer required. (b) For the purpose of this AD, shop visit is defined as the induction of an engine into a shop for the conduct of maintenance. (c) 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. (d) Upon submission of substantiating data by an owner or operator through an FAA Inspector (maintenance, avionics, or operations, as appropriate), 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, Aircraft Certification Service, Engine and Propeller Directorate, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803-5299. (e) The leak check inspection and the x-ray and disassembly inspection shall be done in accordance with the following documents: Document Page Revision Date RR SB GEM-73-24 1-4 Original October 29, 1990 Total Pages: 4 HS SB JFC118-22-73-10 1-12 Original November 21, 1990 Total Pages: 12 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 the United Technologies Corporation, Hamilton- Standard Division, Technical Publications Department, One Hamilton Road, Windsor Locks, Connecticut 06096- 1010, and Rolls-Royce plc, Leavesden, WD27BZ, England. 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. Airworthiness Directive 91-15-05 published in Federal Register on July 23 was not distributed to the public by FAA due to a clerical error in the AD. This corrected version of Airworthiness Directive 91-15-05, Amendment 39-7068, published in the Federal Register on August 8, 1991, becomes effective on August 19, 1991. This amendment (39-7068, AD 91-15-05) becomes effective on August 19, 1991.
96-19-14: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires replacement of certain flexible oxygen hoses, located in the flight compartment gangway and in the consoles, with insulated hose assemblies. This amendment is prompted by reports of either insufficient or no clearance between these hoses and adjacent structure or electrical wiring. The actions specified by this AD are intended to prevent chafing of the flexible oxygen hoses, which could result in an uncontrollable loss of oxygen from the flightcrew oxygen system, and could allow the presence of oxygen in areas where ignition is possible.
2007-16-17: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A300-600, A310-200, and A310-300 series airplanes. That AD currently requires inspecting for certain serial numbers on elevators, and doing a detailed inspection, visual inspection with a low-angle light, and tap-test inspection of the upper and lower surfaces of the external skins on certain identified elevators for any damage (i.e., debonding of the graphite fiber reinforced plastic/Tedlar film protection, bulges, debonding of the honeycomb core to the carbon fiber reinforced plastic, abnormal surface reflections, and torn-out plies), and doing corrective actions if necessary. This new AD also requires inspecting for damage of the identified elevators in accordance with a new repetitive inspection program, at new repetitive intervals; and would provide an optional terminating action for the repetitive inspections. This AD results from reports of damage caused by moisture/water inside the elevator. We are issuing this AD to detect and correct debonding of the skins on the elevators, which could cause reduced structural integrity of an elevator and reduced controllability of the airplane. DATES: This AD becomes effective September 18, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of September 18, 2007. On February 3, 2006 (70 FR 77301, December 30, 2005), the Director of the Federal Register approved the incorporation by reference of Airbus All Operators Telex A300-600-55A6032, dated June 23, 2004; and Airbus All Operators Telex A310-55A2033, dated June 23, 2004.
76-03-05: 76-03-05 BEECH: Amendment 39-2510. Applies to Models 35-B33, 35-C33, E-33, F-33 and G-33 (Serial Numbers CD-388 thru CD-981 and CD-983 thru CD-1304); and Model P-35 (Serial Numbers D-6842 thru D-7139 and D-7141 thru D-7309) airplanes. Compliance: Required as indicated unless already accomplished. To preclude contact of the tachometer cable housing with the battery relay, within the next 50 hours' time in service after the effective date of this AD, install a tachometer cable housing stand-off bracket on the battery box and secure the tachometer cable housing to this bracket in accordance with Beechcraft Service Instruction No. 0784-241 or later FAA-approved revisions or by any equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective February 17, 1976.
95-17-14: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model CL-600-1A11, CL-600-2A12, and CL-600-2B16 series airplanes. This action requires functional testing of the brake of the horizontal stabilizer trim actuator (HSTA); and exercising the pitch trim system, revising the FAA-approved Airplane Flight Manual (AFM), operational testing of the HSTA, and replacing the HSTA or horizontal stabilizer trim control unit, if necessary. This amendment is prompted by reports of overspeed annunciation of the pitch trim due to slippage of the no-back device on the HSTA. The actions specified in this AD are intended to prevent uncommanded movement of the HSTA due to failure of the no-back device on the HSTA to operate properly; this condition could adversely affect the controllability of the airplane.