Results
2013-19-02: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200, -200 Freighter, and -300 series airplanes. This AD was prompted by a report that a certain wire harness located in the tail cone has wiring of a narrower gauge than design requires. This AD requires replacing the affected wire harness. We are issuing this AD to prevent damage to the affected wiring, which could create an ignition source in an area that might contain fuel vapors, possibly resulting in an uncontrolled fire and subsequent loss of the airplane.
2013-16-03: We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model AS350 and AS355 helicopters, to require inspecting for a crack in the control lever attachment yokes, and if needed, replacing the tail rotor gearbox (TGB). This AD is prompted by improper casting of TGB casing assemblies, which may lead to cracking. A crack in the control lever attachment yokes could cause a loss of tail rotor pitch control, and consequently, loss of control of the helicopter.
2012-12-13: We are adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ airplanes. This AD was prompted by reports of baggage bay fire bottles that can be misassembled such that two squib electrical connectors can be cross- connected. This AD requires a general visual inspection of certain baggage bay fire bottles for correct connection and for the length of the wiring loom, modification of the wiring loom to certain squib connectors, and corrective actions if necessary. We are issuing this AD to detect and correct excessive wiring loom length and improper connection of the squib connecters, which in conjunction with a fire in one of the baggage bays, could result in the fire extinguishing agent being discharged into a wrong compartment and consequent damage to the airplane.
78-07-02: 78-07-02 HAWKER SIDDELEY AVIATION, LTD: Amendment 39-3168. Applies to Model HS-125 Series 700A airplanes, S/N NA0201 through NA0210, certificated in all categories. Compliance is required as indicated. To detect cracking and possible failure of the attaching lugs of the tee pieces, P/N 25- 7PA41, that are mounted on the master refuel valve, accomplish the following: (a) Within 10 days after the effective date of this AD, unless already accomplished, inspect the attachment lugs for cracking and the area of attachment to the main refuel valve for evidence of fuel leakage in accordance with Part A of the section entitled "Accomplishment Instructions" of Hawker Siddeley Aviation, Ltd. Alert Service Bulletin 28-A65, dated November 30, 1977 (service bulletin), or an FAA-approved equivalent. (b) If during the inspection required by paragraph (a) of this AD, evidence of lug cracking or fuel leakage is found, before further flight, except that the airplane may be flown in accordance with FARs 21.197 and 21.199 to a base where the repairs can be performed, remove and destroy both tee pieces and replace with the improved parts, P/N 25-7PA125A, in accordance with Part B of the section entitled "Accomplishment Instructions" of the service bulletin, or an FAA-approved equivalent. (c) If during the inspection required by paragraph (a) of this AD, no evidence of lug cracking or fuel leakage is found, continue to inspect the area in accordance with paragraph (a) of this AD, at intervals not to exceed three calendar months from the initial inspection, except that both tee pieces must be replaced in accordance with the installation instructions of paragraph (b) of this AD no later than August 1, 1978. Compliance with the repetitive inspection requirements of this paragraph may be terminated after the replacement required by this paragraph is accomplished. This amendment becomes effective April 14, 1978.
2013-18-05: We are adopting a new airworthiness directive (AD) for Eurocopter Deutschland GmbH (ECD) Model EC135P1, EC135P2, EC135P2+, EC135T1, EC135T2, and EC135T2+ helicopters with certain fire extinguishing systems installed. This AD requires modifying the fire extinguishing system injection tubes. This AD is prompted by a report that the injection tubes are deforming due to heat. The actions required by this AD are intended to prevent deformation of the fire extinguishing system injection tubes during a fire, which could result in impaired distribution of the fire extinguishing agent, failure of the fire extinguishing system to contain an engine fire, and subsequent loss of control of the helicopter.
77-17-03: 77-17-03 BELL: Amendment 39-3009. Applies to Model 212 helicopters, S/N 30502 through 30804, 30806 through 30810, 30812, 30814, 30815, 30817, 30818, 30820 through 30825, 30827, 30828, 30829, and to Model 205A-1 helicopters, S/N 30001 through 30247, equipped with tail rotor blades, P/N 212-010-750, certificated in all categories. Compliance required within 25 hours' time in service after the effective date of this AD unless already accomplished and thereafter at intervals not to exceed 100 hours' time in service from the last inspection. To detect possible cracks in each tail rotor blade pitch change horn, P/N 212-010-716-5 and -9, accomplish the following: (a) Remove the bolt and barrel nut of the control rod and clean the external surfaces of the pitch change horns. (b) Inspect the horns for cracks, particularly in the barrel nut and bushing area using a dye penetrant or equivalent inspection method. (c) If a crack is found, replace the affected pitch change horn before further flight in accordance with the Model 212 Overhaul Manual, paragraphs 65-58 and 65-63, or Models 205A/205A-1 Maintenance and Overhaul Instructions, paragraphs 3-41 and 3-43, as appropriate. (d) Install the blade's control rod bolt and barrel nut as specified in the instructions in paragraphs 65-57 Model 212 Maintenance Manual or 3-40 Models 205/205A-1 Maintenance and Overhaul Instructions, as appropriate. (e) After installation of pitch change horns, P/N 212-010-716-11, this AD is no longer applicable. (f) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA, Southwest Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. (g) The manufacturer's instructions identified and described in this directive are incorporated herein and made a part hereof pursuant to 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 the Service Manager, Bell Helicopter Textron, P. O. Box 482, Fort Worth, Texas 76101. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and at the Southwest Regional Office in Fort Worth, Texas. (Bell Helicopter Textron Service Bulletin Nos. 212-77-7 and 205-77-5 dated March 11, 1977, pertain to this subject.) This amendment becomes effective August 19, 1977.
76-13-06: 76-13-06 DEHAVILLAND: Amendment 39-2654. Applies to DeHavilland Model DHC- 6 series Twin Otter aircraft serial nos. 1 thru 430 incorporating wing tip strobe lighting. Compliance required as indicated: To restore the aircraft lightning strike protection to its original status, as a result of excessive removal of lightning strike protection bonding strap material, during the installation of the wing tip strobe lights, accomplish the following: (a) Within the next 100 hours in service after the effective date of this AD, accomplish the alteration to the aircraft wing tips in accordance with "Accomplishment Instructions" in DeHavilland DHC-6 Service Bulletin No. 6/318, dated January 3, 1975, or later revision, or equivalent alteration approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (b) Upon request with substantiating data submitted through an FAA inspector, the compliance time specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment is effective July 6, 1976.
2013-16-24: We are superseding airworthiness directive (AD) 90-23-14 for certain The Boeing Company Model 747 series airplanes. AD 90-23-14 required inspections of the fuselage skin lap splice between body station (BS) 340 and BS 400 at stringers (S)-6L and S-6R, and repair if necessary. This new AD adds new repetitive inspections for cracking in the S-6 skin lap splice, which terminates the inspections required by AD 90-23-14; eventual modification of the lap splice, which terminates the repetitive inspections; post-modification inspections; and corrective actions if necessary. This AD also adds airplanes to the applicability. This AD was prompted by a report of cracks up to 18.5 inches that were found at S-6L and S-6R on several airplanes, and subsequent analysis results that indicated that the protruding head fastener modification and related post-modification inspections required by AD 90-23-14 are not adequate to prevent cracking at the upper row of fasteners in the S-6 lap joint before the cracks reach a critical length. We are issuing this AD to detect and correct cracking at the upper row of fasteners in the S-6 lap joint, which could result in a sudden loss of cabin pressurization and the inability of the fuselage to withstand failsafe loads.
77-15-15: 77-15-15 BRITISH AIRCRAFT CORPORATION: Amendment 39-2986. Applies to BAC 1- 11 200 and 400 series airplanes, certificated in all categories. Compliance is required within the next 200 hours time in service after the effective date of this AD, unless already accomplished. To prevent the inadvertent loss of cabin pressure due to failure of the light alloy stop on the cabin pressure discharge valve manual control, replace the light alloy stop, P/N AB55-2301, on the gear wheel and drum assembly of the air conditioning discharge valve manual control (P/N AB55A-2425 or ED55A779) with an improved strength stop, P/N AB55-3433, or an FAA-approved equivalent. (British Aircraft Corporation Service Bulletin No. 21-PM 5139, Revision 2, dated September 5, 1973, applies to this same subject.) This amendment becomes effective August 29, 1977.
51-03-01: 51-03-01 MOONEY: Applies to Model M-18 Series Aircraft, Serial Numbers 1 Through 82 and 201 Through 236. Compliance required not later than March 15, 1951. There have been reported failures of the fuel line due to vibration and relative motion between the fuel tank and the fuel shutoff valve. To preclude the possibility of recurrence of this type failure, cut the fuel line at a point approximately 4 inches from the fuel tank outlet and install a 4-inch length of 3/8-inch ID approved aromatic resistant flexible hose and hose clamps at this point. (Mooney Service Bulletin No. 6 covers this same subject.)