Results
2006-06-08: The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) Model CF6-80C2D1F turbofan engines. This AD requires modifying the latching system of the fan reverser. This AD results from 13 reports of released thrust reverser hardware. We are issuing this AD to prevent release of the thrust reverser cascade on landing, which could result in runway debris and a possible hazard to other aircraft.
79-06-05: 79-06-05 DETROIT DIESEL ALLISON: Amendment 39-3436. Applies to Model 250-C28B and 250-C30 engines with overspeed controls DDA P/N's 6895582 and 6894611 respectively, installed in but not limited to Bell 206L-1 and Sikorsky S-76 rotorcraft certificated in all categories. Compliance required as indicated, unless previously accomplished. To preclude possible engine power loss resulting from moisture in the overspeed control system, accomplish the following: (A) Before further flight, accomplish the following: (1) Pull the N2 overspeed circuit breaker and secure by wrapping with tape, or placing a Ty-Wrap around the breaker stem. (2) Install placard which states "Eng Ovsp Circuit Deactivated" in 3/16" or larger letters adjacent to N2 overspeed circuit breaker on Bell Model 206L-1 rotorcraft. On Sikorsky Model S-76 rotorcraft, install the placard on the panel which contains the N2 circuit breaker and on the panel which contains the N2 overspeed circuit test switch. The engine overspeed test outlined in the RFM will no longer function with the circuit breaker deactivated. (B) Not later than September 1, 1979, replace the affected engine overspeed controls with new engine overspeed controls DDA P/N's 23001750 for 250-C28 series engines and 23001751 for 250-C30 engines, unless previously accomplished. Concurrent with the accomplishment of this replacement, reactivate the N2 overspeed control by engaging the N2 overspeed circuit breaker and removing the placard "Eng Ovsp Circuit Deactivated." (Commercial Engine Bulletins CEB 73-2009 for the 250-C28 series engines and CEB 73-3006 for the 250-C30 engines also pertain to this subject.) This amendment becomes effective March 26, 1979.
63-16-04: 63-16-04 GENERAL DYNAMICS: Amdt. 594 Part 507 Federal Register July 26, 1963. Applies to All Model 22 Aircraft. Compliance required as indicated. Cracks have been found in foreflaps P/N 22-18600-5/-807. Therefore, accomplish the following on all foreflaps P/N 22-18600-5/-807, which have not been modified in accordance with Section B(1)(a) or B(1)(b) of General Dynamics Service Bulletin No. 27-65: (a) Within the next 400 hours' time in service after the effective date of this AD unless already accomplished within the last 400 hours' time in service: (1) Conduct a close visual inspection for cracks in the external clips and entire skin area of the outboard foreflaps P/N 22-18600-5/-807. A dye penetrant or equivalent inspection process shall be used to verify suspected cracks. Any parts found cracked shall be replaced with uncracked parts before further flight. (2) Remove and disassemble the outboard foreflaps P/N 22-18600-5/-807, and conduct a close visual inspection for cracks in the interior clips. X-ray inspection may be used to inspect those interior clips not visible after disassembly. A dye penetrant or equivalent inspection process shall be used to verify suspected cracks. Any parts found cracked shall be replaced with uncracked parts before further flight. (b) Within 500 hours' time in service after conducting the inspection specified in (a), repeat the inspection specified in (a) (1). Any parts found cracked shall be replaced with satisfactory parts before further flight. (c) Within 500 hours' time in service after conducting the inspection specified in (b), the outboard foreflaps, P/N 22-18600-5/-807, shall be replaced with foreflaps modified in accordance with Section B(1)(a) or B(1)(b) of General Dynamics Bulletin No. 27-65. (General Dynamics Service Bulletin No. 27-65 covers this same subject.) This directive effective August 27, 1963.
99-15-10: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 777 series airplanes. This action requires replacement of a certain engine-driven pump (EDP) supply shutoff valve, which is located in the aft strut fairing, with a new shutoff valve. This amendment is prompted by reports of failure of the shutoff valve due to corrosion in the direct current motor in the shutoff valve. The actions specified in this AD are intended to prevent failure of an EDP supply shutoff valve. Such failure, in the event of an engine fire, could result in an uncontrolled fire in the engine compartment.
84-10-02: 84-10-02 SIKORSKY AIRCRAFT: Amendment 39-4802. Applies to Model S-76A series helicopters certificated in all categories. To prevent operation with a cracked main rotor spar, accomplish the following: Applies to main rotor blades, Part Number (P/N) 76150-09000 or 76150-09100, with more than 600 hours time in service. Compliance required within the next 25 hours time in service after the effective date of this AD, unless previously accomplished and thereafter at intervals not to exceed 500 hours time in service. (a) Inspect the main rotor blade spar for cracks in accordance with the Sikorsky S-76 Composite Materials Manual, SA-4047-76-5, paragraph 2-7 or 2-7A. (b) If a spar crack is found, replace the main rotor blade with a new or serviceable component before further flight. (c) Paragraphs 2-7 and 2-7A of the Sikorsky S-76 Composite Materials Manual, that are specified in paragraph (a) of this AD, are incorporated herein and made a part hereof pursuantto 5 U.S.C. 552(a)(1). All persons affected by this directive, who have not already received these documents from the manufacturer, may obtain copies upon request to Sikorsky Aircraft, Division of United Technologies Corporation, North Main Street, Stratford, Connecticut 06602. These documents may also be examined at the FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, and at the Office of the Regional Counsel, FAA, Southwest Region, Fort Worth, Texas. (d) Upon request from the operator, an FAA maintenance inspector may adjust the repetitive inspection interval in this AD if the request contains data to justify the increase and provided the Manager, Boston Aircraft Certification Office, FAA, New England Region, approves the increase. This amendment supersedes Amendment 39-4019 (46 FR 3498), AD 80-23-51, that was effective January 15, 1981, for all persons except those to whom it was made effective by telegram dated November 7, 1980.This amendment becomes effective June 18, 1984.
2006-06-04: The FAA is superseding an existing airworthiness directive (AD), which applies to certain McDonnell Douglas Model DC-9-10, -20, - 30, -40 and -50 series airplanes, and Model DC-9-81 (MD-81), and DC-9- 82 (MD-82) airplanes. That AD currently requires installing a water drain system for the slant pressure panels in the left and right wheel wells of the main landing gear (MLG). This new AD also requires inspecting the seal assemblies of the overwing emergency exit doors for defects and constant gap; replacing defective door seals; performing repetitive operational checks of the water drain system auto drain valve and corrective actions if necessary; and, for certain airplanes, modifying the insulation blankets on the slant pressure panels in the left and right MLG wheel wells. This AD results from reports of water runoff from the slant pressure panels in the left and right MLG wheel wells, which subsequently froze on the lateral control mixer and control cable assemblies. We areissuing this AD to prevent ice from forming on the lateral control mixer and control cable assemblies, which could reduce controllability of the airplane.
2009-18-05: 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: Several incidents have been reported where an electrical burning smell was noted in the cockpit, originating from the Electrical Power Centre. Troubleshooting revealed a partly molten terminal, which normally attaches a wire or bus bar to a stud of an Electrical Power Contactor, Part Number (P/N) SG02206. Furthermore, heat damage to the contactor stud itself was found. * * * * * * * * This condition, if not corrected, could lead to further cases of overheating of terminals and studs of Electrical Power Contactors P/ N SG02206, possibly resulting in the loss of electrical power systems, electrical arcing and fire/smoke in the cockpit. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
99-15-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Pratt & Whitney (PW) JT9D series turbofan engines, that requires initial and repetitive in-shop eddy current and on-wing ultrasonic inspections of the Combustion Chamber Outer Casing (CCOC) forward flange (L-flange) fillet radius for cracking, and replacing cracked L-flanges with serviceable parts. Replacement with an improved L-flange constitutes terminating action to the repetitive inspections. This amendment is prompted by reports of CCOC rupture due to cracking in the L-flange fillet radius. The actions specified by the proposed AD are intended to prevent CCOC rupture due to cracking, which could result in an uncontained engine failure and damage to the aircraft. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of August 16, 1999.
79-17-03: 79-17-03 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-3530. Applies to all L-1011-385-1, L-1011-385-1-14 and L-1011-385-1-15 series airplanes certificated in all categories. To ensure the integrity of the main landing brakes input straps, accomplish the following: (a) Within the next 200 hours' time in service from the effective date of this AD, unless already accomplished within the last 600 hours' time in service, perform a visual inspection of the four input straps P/N 1545026 (-129, -130, -131, -132) located in the forward electronics service center compartment. If any obvious structural deformations and/or cracks are found, replace the strap(s) prior to the next flight in accordance with the Lockheed-California Company Service Bulletin 093-32-153, Revision 1. (b) Repeat the visual inspections and replacement of straps as necessary, of paragraph (a) above, at intervals of 800 hours' time in service, unless paragraph (c) below has already been accomplished. (c) Onor before December 31, 1979, install the new type design steel input straps P/N 1617522 (-101, -102, -103, -104) in accordance with the Lockheed-California Company Service Bulletin 093-32-153, Revision 1. This constitutes terminating action for the inspection requirements of paragraphs (a) and (b) of this AD. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections required by this AD. (e) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. (f) Upon request of operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Engineering Division, FAA Western Region may adjust the initial and repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if therequest contains substantiating data to justify the increase for that operator. This amendment becomes effective September 24, 1979.
2006-06-01: This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (ECF) model helicopters that requires inspecting an electrical cable bundle for wear. If wear is present, the AD requires installing an airworthy cable bundle and modifying the routing of the electrical cable bundles. This amendment is prompted by reports of a short circuit in the wiring, which led to failure of the normal and emergency landing gear operation modes. The actions specified by this AD are intended to prevent interference of the wiring with the structure resulting in an electrical short circuit, failure of the landing gear to extend, and an emergency landing.
79-04-02: 79-04-02 COSTRUZIONI AERONAUTICHE GIOVANNI AGUSTA: Amendment 39-3407 as amended by Amendment 39-3434. Applies to Model A109A helicopters, certificated in all categories, serial numbers 7135 and below. Compliance is required within the next 50 hours time in service after the effective date of this AD, unless already accomplished. To prevent possible failure of the tailboom attachment provisions, remove and discard the nuts MS 21042-L6, the bolts NAS 626-20, and washers MS 20002-C6 and AN 960-616, and install in their place new nuts 42-FLW-624, bolts NAS 626-20, washers MS 20002-C6 and, as needed, one or more washers AN 960-616 and AN 960-616L, torque bolts, inspect bolts for torque, and if necessary retorque and re-inspect torque, all in accordance with Agusta Bollettino Tecnico No. 109-8, dated February 6, 1978, or an FAA-approved equivalent approved by the Chief, Aircraft Certification Staff, Federal Aviation Administration, Europe, Africa, and Middle East Region, c/o American Embassy, APO New York, N.Y. 09667. Amendment 39-3407 became effective March 5, 1979. This amendment 39-3434 became effective March 5, 1979.
2006-05-11: The FAA is superseding an existing airworthiness directive (AD) that applies to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. The existing AD currently requires revising the airworthiness limitations section of the Instructions for Continued Airworthiness of the aircraft maintenance manual (AMM) by incorporating procedures for repetitive functional tests of the pilot input lever of the pitch feel simulator (PFS) units. This AD requires new repetitive functional tests of the pilot input lever of the PFS unit, and corrective actions if necessary. After initiating the new tests, this AD also requires removal of the existing procedures for the repetitive functional tests from the AMM. This AD results from a report that the shear pin located in the input lever of two PFS units failed due to fatigue. We are issuing this AD to prevent undetected failure of the shear pin of both PFS units simultaneously, which could result in loss of pitch feel forcesand consequent reduced control of the airplane. DATES: This AD becomes effective March 27, 2006. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of March 27, 2006. On February 13, 2004 (69 FR 4234, January 29, 2004), the Director of the Federal Register approved the incorporation by reference of Bombardier Temporary Revision 2B-1784, dated October 24, 2003, to the CL-600-2B19 Canadair Regional Jet Maintenance Requirements Manual, Part 2, Appendix B, "Airworthiness Limitations.'' We must receive any comments on this AD by May 9, 2006.
99-14-04: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747-300 and -400 series airplanes. This action requires repetitive inspections of the E-42 satellite communications (SATCOM) rack and fuselage (supporting) structure to detect cracking in the area surrounding the fastener holes, and to detect broken and missing fasteners; and corrective actions, if necessary. This amendment is prompted by reports indicating that cracking and broken and/or missing fasteners were found on the E-42 SATCOM equipment rack structure that attaches to the fuselage structure. The actions specified in this AD are intended to detect and repair cracking of the E-42 SATCOM rack and its supporting structure, which could result in the SATCOM equipment falling from the rack, loss of SATCOM capabilities, injury to passengers, and reduced controllability of the airplane.
2020-02-21: The FAA is superseding Airworthiness Directive (AD) 2018-19-25 and AD 2014-03-12, which applied to all Dassault Aviation Model FALCON 2000 airplanes. Those ADs required revising the existing maintenance or inspection program, as applicable, to incorporate new maintenance requirements and airworthiness limitations. Since the FAA issued AD 2018-19-25, the FAA has determined that new or more restrictive airworthiness limitations are necessary. This AD continues to require those maintenance or inspection program revisions, and also requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2001-24-10: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Fokker Model F.28 Mark 0100 series airplanes. This action requires repetitive inspections of certain main landing gear (MLG) main fittings to detect forging defects, and rework of the main fittings if necessary. This action is necessary to detect forging defects of the MLG main fittings, which could lead to cracking and result in significant structural damage to the airplane and possible injury to the occupants.
2020-02-16: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the lower skin of the fuselage skin lap splices along the lower fastener row of a certain stringer lap splice on certain body station skin panels may be subject to widespread fatigue damage (WFD). This AD requires inspections of the lower skin of the fuselage skin lap splices along the lower fastener row of a certain stringer lap splice on certain body station skin panels and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2020-03-11: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 707 airplanes and Model 720 and 720B series airplanes. This AD was prompted by the FAA's analysis of the Model 707 and 720 fuel system reviews conducted by the manufacturer. This AD requires modifying the fuel quantity indicating system (FQIS) to prevent development of an ignition source inside the center fuel tank due to electrical fault conditions. The FAA is issuing this AD to address the unsafe condition on these products.
2020-02-11: The FAA is superseding Airworthiness Directive (AD) 2015-04-04 for Bell Helicopter Textron Inc. (Bell) Model 412 and 412EP helicopters. AD 2015-04-04 required revising the Rotorcraft Flight Manual (RFM) for your helicopter and installing a placard to limit flights to visual flight rules (VFR) and prohibit night operations because of failing inverters. This AD requires replacing the affected inverter with a new inverter. This AD was prompted by numerous failures of inverters. The FAA is issuing this AD to address the unsafe condition on these products.
2001-24-07: This amendment supersedes an existing airworthiness directive (AD) that applies to Agusta S.p.A. (Agusta) Model A109C, A109E, and A109K2 helicopters and currently requires inspecting the main rotor blade (blade) tip cap for bonding separation and a crack. This amendment contains the same requirements as the existing AD but also requires a tap inspection of the tip cap for bonding separation in the blade bond area and a dye penetrant inspection of the tip cap leading edge along the welded joint line of the upper and lower tip cap skin shells for a crack. This amendment is prompted by three occurrences in which the blade tip cap leading edge opened in flight due to cracks, resulting in excessive helicopter vibration. The actions specified by this AD are intended to prevent failure of a blade tip cap, excessive vibration, and subsequent loss of control of the helicopter.
2020-02-17: The FAA is adopting a new airworthiness directive (AD) for certain Sikorsky Aircraft Corporation (Sikorsky) Model S-70, S-70A, S- 70C, S-70C(M), and S-70C(M1) helicopters. This AD was prompted by four incidents of disbonding between the tail rotor (T/R) blade pitch horn and the torque tube. This AD requires recurring visual and tap inspections of the T/R blade, and depending on the outcome, replacing the T/R blade. The FAA is issuing this AD to address the unsafe condition on these products.
2019-10-01: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-2A12 (601) airplanes. This AD was prompted by a report of damage to the anti-rotation tab on a main landing gear (MLG) side brace fitting due to the installation of an incorrect side brace fitting shaft. This AD requires an inspection of the MLG side brace fitting for damage, a verification of the side brace fitting shaft part number, and replacement of the side brace fitting shaft if necessary. It also requires the installation of an anti- rotation bracket. We are issuing this AD to address the unsafe condition on these products.
58-11-03: 58-11-03 LOCKHEED: Applies to All Models 18 Series and PV-1 Aircraft. Compliance required as soon as possible, but not later than December 1, 1958. Numerous reports have been received of cracks occurring at the base of the rudder cable attachment tangs, on rudder control quadrant, Lockheed P/N 53026. There is evidence that excessive clearance may exist between the tangs and the rudder cable attach fittings which permits a bending load to be applied at the base of the tangs, when the AN 5 attach bolts are tightened. P/N 53026 should be inspected by means of a dye penetrant or equivalent inspection means in the areas noted above. If cracks are found, the parts must be replaced. Furthermore, the means of attaching the rudder cables to the quadrant must be modified to preclude over-loading the attach tangs and subsequent occurrence of cracks due to the tightening of the attach bolts. Two acceptable means of accomplishing the modification are noted below: 1. Replace both the AN 5 bolts with AN 4-12A bolts, AN 365 nuts and AN 960-516 washers, under the head and nut in conjunction with a 5/16 x 0.032-inch wall cadmium plated steel spacer 1-inch long as a sleeve. The length of the sleeve may protrude past the thickness of the washers a maximum of 1/16-inch or a minimum of 0.003 inch so that when tightened, the nut will bottom against the spacer and not on the washers. NOTE: To compensate for machining tolerances and casting variation, additional washers or various length sleeves may be used to obtain the proper sleeve exposure. 2. Replace the AN 5 bolts with AN 25-20 clevis bolts, AN 516 washers, AN 320-5 nuts and AN 380-2-3 cotter pins. NOTE: If more than 1/16-inch of bolt grip is exposed after installing the nut and washer, due to machining tolerances and casting variation, place additional washers under the head of the bolt to reduce the grip exposure to a minimum of 0.003-inch. (Lockheed Service Bulletin No. 18/SB-150 covers this same subject.)
80-15-07: 80-15-07 SHORT BROTHERS LIMITED: Amendment 39-3846. Applies to Model SD3-30 series airplanes, certificated in any category, serial numbers SH 3000 to SH 3027 inclusive. Compliance required as indicated. To prevent loss of fuel flow to an engine due to failure of a fuel system gravity feed check valve, comply with following, unless already accomplished. (a) Within 100 hours time in service after the effective date of this AD, or before the accumulation of 1300 hours total time in service, whichever occurs later, and thereafter in accordance with paragraph (b) of this AD, inspect and service the fuel system aft gravity feed check valve associated with fuel cell number 4 in accordance with paragraph 2, "ACCOMPLISHMENT INSTRUCTIONS," of Short Brothers Limited Service Bulletin No. SD 3-28-12, revision 1, dated February 1, 1980, (hereinafter referred to as the service bulletin) or an FAA-approved equivalent. (b) At intervals not to exceed 1200 hours total time in service since the last inspection, accomplish the inspection and servicing required in paragraph (a) of this AD. (c) The inspection interval required in paragraph (b) of this AD may be increased to 2400 hours upon the installation of a new or serviceable gravity feed check valve, P/N 984109/F. (d) Before the accumulation of 2400 hours total time in service and thereafter at intervals not to exceed 2400 hours time in service since the last inspection, inspect and service the fuel system aft gravity feed check valves associated with fuel cells numbers 1, 2 and 3, and the forward valve on cell number 4 in accordance with paragraph 2, "ACCOMPLISHMENT INSTRUCTIONS," of Short Brothers Limited Service Bulletin No. SD 3-28-12, revision 1, dated February 1, 1980, or an FAA-approved equivalent. NOTE: Short Brothers Limited Service Bulletin No. SD 3-28-13, dated December 19, 1979, refers to this subject. (e) Airplanes may be flown in accordance with FAR 21.197 and 21.199 to a basewhere the inspections and parts replacement required in this AD can be accomplished. (f) Upon request of an operator, the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium, may adjust the inspection intervals specified in this AD or approve equivalent means of compliance with this AD provided such requests are made through the assigned FAA maintenance inspector and the request contains substantiating data to justify the request for that operator. This amendment becomes effective July 28, 1980.
2006-05-09: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-200C, -200F, -400, -400D, and -400F series airplanes. This AD requires repetitive inspections for cracks in the overlapping (upper) skin, upper fastener row of the lap joints of the fuselage skin in sections 41, 42, and 46; and related investigative and corrective actions, if necessary. This AD results from fatigue tests and an analysis that identified areas of the fuselage lap joints where fatigue cracks can occur. We are issuing this AD to detect and correct fatigue cracks in the overlapping (upper) skin, upper fastener row of the lap joints of the fuselage skin in sections 41, 42, and 46, which could adversely \naffect the structural integrity of the airplane.
99-13-13: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9, DC-9-80, and C-9 (military) series airplanes; Model MD-88 airplanes; and Model MD-90 airplanes, that requires a one-time inspection of the forward attach pins of the outboard flight spoiler actuators to determine whether the pins are of correct length, and follow-on corrective actions. This amendment is prompted by a report that forward attach pins of incorrect length were found to be installed in the flight spoiler actuators on several in-service and in-production airplanes. The actions specified by this AD are intended to prevent failure of the piston of the flight spoiler actuator and consequent puncturing of the aft spar web, which could result in fuel leakage and reduced structural integrity of the wings.