Results
2011-25-07: We are adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model 4101 airplanes. 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: A door failure mode has been reported by an operator. Investigation has shown that the passenger/crew entry door pin- guide plates can fail prior to the expected fatigue life. A metallurgical examination of the failed component (lower guide plate) concluded that the occurred failure was due to exfoliation corrosion. The current inspection regime is not adequate to identify early stages of this corrosion. This condition, if not corrected, can lead to the sudden depressurisation of the aeroplane and consequently may injure the occupants. * * * * * We are issuing this AD to require actions to correct the unsafecondition on these products.
99-15-14: This amendment adopts a new airworthiness directive (AD), applicable to Sikorsky Aircraft-manufactured Model CH-54B helicopters, that requires initial and recurring inspections and rework or replacement, if necessary, of the second stage lower planetary plate (plate). This amendment is prompted by two reports of cracked plates that have been found during overhaul and inspections. The actions specified by this AD are intended to prevent failure of the main gearbox plate due to fatigue cracking, which could lead to failure of the main gearbox and subsequent loss of control of the helicopter.
78-25-09: 78-25-09 MCDONNELL DOUGLAS: Amendment 39-3372. Applies to DC-10-10, -10F, -30, -30F, and -40 airplanes certificated in all categories which have Universal Oil Products Company Model 900-400-C3C seats through Serial No. 3860, installed. \n\n\tCompliance required within the next 30 days after the effective date of this AD, unless already accomplished. \n\n\tTo assure that the seatback tray table retention clip cannot be rotated to a position in which it prevents automatic deployment of oxygen masks during depressurization, accomplish the following: \n\n\t(a)\tModify the Universal Oil Products Company Model 900-400-C3C seat through Serial No. 3860, in accordance with Universal Oil Products Service Bulletin No. 25-494, original issue dated September 18, 1978. \n\n\t(b)\tEquivalent modification may be used when approved by the Chief, Aircraft Engineering Division, FAA, Western Region. \n\n\t(c)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanesto a base for the accomplishment of the modifications required by this AD. \n\n\tThis amendment becomes effective December 22, 1978.
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.