Results
59-10-10: 59-10-10 VICKERS: Applies to All Viscount Model 745D Aircraft. Compliance required as soon as possible but not later than July 1, 1959. A case has occurred of the failure of flap telescopic tie rod end, Vickers P/N 70103-3139. The investigation revealed that the depth of the drilling for the internal thread had been extended beyond the normal drawing dimension of 0.95 inch which resulted in a reduction in wall thickness and strength across the shoulder. Inspect flap telescopic tie rod ends, Vickers P/N 70103-3139, assembled on No. 3 and 4 flap telescopic tie rods. If the depth of the internal threads exceeds 0.95 inch measured from the end face of the tie rod end, the part must be replaced. The above inspection must also be made on all stocks of parts prior to installation on an aircraft. (Vickers-Armstrongs PTL 207 covers this subject.)
2024-17-02: The FAA is adopting a new airworthiness directive (AD) for all Bell Textron Inc. (Bell) Model 204B, 205A, 205A-1, 205B, and 210 helicopters. This AD was prompted by an accident and incidents involving failure of the tail boom attachment structure. This AD requires inspecting the tail boom assembly hardware, replacing tail boom attachment hardware, greasing the bolt shanks, and inspecting torque. This AD also prohibits installing steel alloy nuts on any helicopter. The FAA is issuing this AD to address the unsafe condition on these products.
2016-19-06: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200, Model A330-300, Model A340-200, and Model A340- 300 series airplanes. This AD requires an inspection to determine the part number and serial number of certain escape slides on the left and right sides of the airplane, and replacement if necessary. This AD was prompted by a report indicating that the aspirator on certain escape slides might have been damaged because of incorrect packing during overhaul. We are issuing this AD to detect and correct damaged aspirators on escape slides. Failure of an aspirator to inflate an escape slide could prevent deployment of the escape slide during an emergency, possibly resulting in reduced evacuation capacity from the airplane and consequent injury to occupants.
59-16-02: 59-16-02 LOCKHEED: Applies to Models 18, PV-1 and B-34 Series Aircraft Except Those Incorporating Spar Reinforcement as Covered in Lockheed Aircraft Service Bulletin 18/SB- 112. Compliance required as indicated. Numerous reports have been received wherein fatigue cracks have been found in the horizontal stabilizer spars in the area of the vertical fin attachments. In order to determine if this condition has developed, the following inspection is required. Within the next 50 hours of flight and at 300-hour intervals thereafter inspect the horizontal stabilizer front and rear spar flanges and webs for cracks in the region of the vertical fin attaching angles. If cracks are found, stop-drill, install spar flange and web doublers and flange filler blocks extending beyond the fin attaching angles. Add doubler plates on the forward face of rear spar in region of rudder hinge bracket attachment holes. Visual inspections of the area with a 10-power glass are adequate. The 300 hour inspection may be discontinued after incorporation of the reinforcements. One approved method of accomplishing the above spar reinforcement is contained in Lockheed Aircraft Service Bulletin 18/SB-112 dated September 18, 1944, pertaining to this same subject. Revised May 27, 1965.
79-25-04: 79-25-04 SWEARINGEN : Amendment 39-3620. Applies to Models SA226-T, SA226-AT, and SA226-TC airplanes, certificated in all categories, that incorporate Rosemount SAS Servo P/N 9-50D1001. Compliance is required within the next 10 hours time in service unless already accomplished. (NOTE: The compliance time given here is, in some instances, different from SB A27-024.) To prevent the possible jamming of the elevator, accomplish the following: Remove, disassemble, inspect, modify if necessary, and reidentify servos in accordance with the accomplishment instructions in Swearingen Aviation Corporation Service Bulletin SB A27-024 dated November 13, 1979. All Rosemount P/N 9-50D1001 servos not presently installed must also be disassembled, inspected, modified if necessary, and reidentified prior to installation. Aircraft may be flown in accordance with FAR 21.197 to a base where this AD can be accomplished. The manufacturer's specifications and procedures 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 Swearingen Aviation Corporation, P.O. Box 32486, San Antonio, Texas 76284. These documents may also be examined at Office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas 76101, and at FAA Headquarters, 800 Independence Avenue S.W., Washington, D.C. 20591. This amendment becomes effective December 10, 1979.
2024-20-02: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 717-200 airplanes and Model DC-9-10, DC-9-20, DC-9-30, DC-9-40, and DC-9-50 series airplanes. This AD was prompted by a report of cracked and severed structure found in the aft fuselage cant bulkhead at a certain station (STA) and the vertical stabilizer rear spar installation. This AD requires a one-time inspection of the aft fuselage cant bulkhead at certain STAs and vertical stabilizer rear spar structure, and corrective actions and an inspection report if necessary. This AD also requires an inspection of that same structure if certain conditions occur during any phase of flight. The FAA is issuing this AD to address the unsafe condition on these products.
2016-18-08: We are superseding Airworthiness Directive (AD) 90-11-05 for certain Airbus Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4- 203 airplanes and Model A300 B4-600 series airplanes. AD 90-11-05 required repetitive detailed inspections for cracking in the aft hinge brackets of the outer shroud box that is located in the outer wing box, and related investigative and corrective actions if necessary. This new AD changes certain compliance times and adds airplanes to the applicability. This AD was prompted by reports of cracks in the aft hinge brackets of the outer shroud box that is located in the outer wing box, which were found during routine maintenance checks, and our subsequent determination that a change in inspection compliance times is needed. We are issuing this AD to detect and correct cracking of the aft hinge brackets of the outer shroud box; such cracking could affect the structural integrity of the airplane.
2016-18-15: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, and -900 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the aft pressure bulkhead is subject to widespread fatigue damage (WFD). This AD requires repetitive inspections of the aft pressure bulkhead web for any cracking, crack indications, discrepant fastener holes, and corrosion; and corrective actions if necessary. We are issuing this AD to detect and correct cracks in the aft pressure bulkhead web, which could result in an uncontrolled decompression of the fuselage.
69-01-03: 69-01-03 FAIRCHILD-HILLER: Amendment 39-705. Applies to Fairchild Hiller F-27 Type and FH-227 type airplanes certificated in all categories. For airplanes having 5,000 or more hours time in service as of the effective date of this Airworthiness Directive, accomplish the following: (a) Before further flight, install the following placard in the cockpit in full view of the pilot. "Do not operate aircraft above 180 knots IAS" Such placard to be removed upon completion of inspections as noted in (b). (b) To detect cracks in the lower wing outer panel skin, access door land, and stringers at wing stations 194, 197 and 204, accomplish the following within the next 25 hours time in service after the effective date of this Airworthiness Directive, unless already accomplished within the last 25 hours time in service. (1) Inspect for cracks both the left and right lower wing access door area using X-Ray inspection procedures in accordance with Fairchild Service Bulletin 51-2 for X-Ray Pictures No. 1AL and 1AR with the X-Ray head located at the intersection of wing stations 194, 197 and 204 with both door edges for a total of six X-Ray pictures per side. Particular attention should be given for cracks propagating from the access door-land attach screw holes. (c) Prior to further flight cracks must be repaired in accordance with a repair approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region or replaced with a part of the same part number that has been inspected in accordance with (b) or with an equivalent part approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (d) Report the results of inspection findings required by this A.D. to the Chief, Engineering and Manufacturing Branch, FAA Eastern Region (Reporting approved by the Bureau of the Budget under BOB No. 04-R0174). This amendment is effective January 4, 1969, and was effective upon receipt by all recipients of the telegram dated December 19, 1968 which contained this amendment.
65-26-03: 65-26-03 LEARJET: Amdt. 39-160 Part 39 Federal Register November 25, 1965. Applies to Model 23 Airplanes. Compliance required before further flight, unless already accomplished. To eliminate the possibility of smoke accumulation in the cabin due to improper ducting, accomplish the following: (a) Remove necessary interior side panels on right side of baggage compartment near Fuselage Frame 22 (Station 271). (b) Inspect the one-inch diameter flexible duct (Figure 90-11, Lear Parts Catalog) to ensure that it is the high temperature silicone type (reddish color). (c) Replace any black duct with high temperature silicone type (reddish color) duct, P/N 2319148-017 (airplane Serial Numbers 004 through 034), or P/N 2319148-022 (airplane Serial Numbers 035 and higher), before further flight. This directive effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated November 18, 1965.