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66-09-02: 66-09-02 DOWTY ROTOL: Amdt. 39-215 Part 39 Federal Register March 23, 1966. Applies to Dowty Rotol Propellers, (c) R.193/4-30-4/50, installed on Fairchild F-27; (c) R.184/4- 30-4/50, installed on Grumman G-159; and (c) R.179/4-20-4/33, installed on Viscount 810. Compliance required within the next 200 hours' time in service after the effective date of this AD unless already accomplished. To prevent further improper operation of the propeller pitch lock under high oil temperature conditions, rework the existing Lock Support Sleeve, Dowty Rotol P/N RA.61236, in accordance with Dowty Rotol Service Bulletin No. 61-185 (Modification No. (c) VP.2032) or later ARB-approved revision. This directive effective April 22, 1966. Revised June 16, 1966.
83-10-03: 83-10-03 CESSNA: Amendment 39-4655. Applies to the following airplanes certificated in any category: \n\n\nModel\nSerial Numbers \n172M\n17266940 thru 17267584\n172N\n17267585 thru 17274009\n172P\n17274010 thru 17275762, 17275764, 17275765, 17275769, 17275770, 17275788, 17275792, 17275793, 17275796, 17275798, 17275800 thru 17275803, 17275806, and 17275818\nR172K\nR1722000 thru R1723454\nF172\nF17201445 thru F17202194\nFR172\nFR17200591 thru FR17200675\n\n\tCOMPLIANCE: Required as indicated unless already accomplished. \n\n\tTo prevent possible jamming of the elevator control, accomplish the following: \n\n\ta)\tWithin the next 100 hours time-in-service, modify the right-hand control wheel yoke guide in accordance with the instructions in Cessna Single-Engine Customer Care Service Information Letter SE82-38, dated August 13, 1982, and SE82-38 Revision # 1 dated October 29, 1982. \n\n\tb)\tAirplanes may be flown in accordance with FAR 21.197 to a base where this AD may be accomplished.c)\tAn equivalent method of compliance with this AD may be used if approved by the Manager, Wichita Aircraft Certification Office, Federal Aviation Administration, Room 238, Terminal Building 2299, Wichita, Kansas 67209, telephone (316) 269-7000. \n\n\tThis amendment becomes effective on June 30, 1983.
2005-24-01: The FAA adopts a new airworthiness directive (AD) for all CENTRAIR 101 series gliders. This AD requires you to make pen and ink changes to the Limitations Section of the glider maintenance manual to eliminate contradictory information concerning the structural life limit. This AD results from a review by FAA of the Limitations Section of the CENTRAIR Model 101AP glider maintenance manual that revealed conflicting information concerning the structural life limit. We are issuing this AD to assure that the published life limit is adhered to and to prevent structural failure of the glider once this life limit is reached.
2018-23-12: We are adopting a new airworthiness directive (AD) for Zodiac Aero Evacuation Systems (also known as Air Cruisers Company) fusible plugs installed on emergency evacuation equipment for various transport category airplanes. This AD was prompted by reports indicating that affected fusible plugs activated (vented gas) below the rated temperature. This AD requires an inspection of the fusible plugs to determine the part number and lot number, and replacement of all affected fusible plugs. We are issuing this AD to address the unsafe condition on these products.
98-20-25: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747-100 series airplanes. This action requires repetitive inspections to detect cracking of the outer chord of the Body Station (BS) 1480 upper and lower bulkhead and longeron splice fitting, and repair, if necessary. Alternatively, this action requires other repetitive inspections to detect cracking of the BS 1480 upper and lower bulkhead, bulkhead outer chord, web, skin, splice components, and lower bulkhead/stringer interface; and modification of the skin splice plate, the outer chord splice fitting, and the stringer interface of the lower bulkhead, if necessary. This amendment is prompted by a report indicating that fatigue cracking was found in the outer chord of the BS 1480 bulkhead at the overwing longeron splice, and that the longeron splice fitting was completely severed. The actions specified in this AD are intended to detect and correct fatigue cracking of theBS 1480 bulkhead outer chord and longeron splice fitting, which could result in reduced structural integrity of the fuselage and the inability to carry limit load.
89-03-13: 89-03-13 SAAB-SCANIA: Amendment 39-6136. Applicability: Model SF-340A series airplanes, serial numbers -003 through -138, inclusive, certificated in any category. Compliance: Required within 30 days after the effective date of this AD, unless previously accomplished. To prevent erroneous airspeed readings due to ice in the pitot system, accomplish the following: A. Install water traps and insulation pads in the main and standby pitot systems, in accordance with SAAB-Scania Service Bulletin SF340-34-056, dated August 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 may add any comments and then send it to the Manager, Standardization Branch, ANM-113. C. Special flightpermits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of 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 SAAB-Scania, Product Support, S-58188, Linkoping, Sweden. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6136, AD 89-03-13) becomes effective March 15, 1989.
85-09-04: 85-09-04 BELL HELICOPTER TEXTRON, INC.: Amendment 39-5055. Applies to Model 206L, 206L-1, and 206L-3 helicopters that have main rotor blades, Part Number (P/N) 206-015-001-001 or 206-015-001-103, with inboard trim tabs, P/N 206-015-516-101, installed. Compliance is required within the next 50 hours time in service after the effective date of this AD, unless already accomplished. To prevent possible loss of the main rotor blade, accomplish the following: (a) Remove all main rotor inboard trim tabs, P/N 206-015-516-101, in accordance with Part II, paragraph A of BHTI Alert Service Bulletin 206L-85-35, dated February 26, 1985. (b) Accomplish the inspection and repair procedures as necessary in accordance with Part II, paragraphs B & C of BHTI Alert Service Bulletin 206L-85-35, dated February 26, 1985. (c) Any equivalent method of compliance with this AD must be approved by the Manager, Helicopter Certification Branch, Southwest Region, Federal Aviation Administration, P.0. Box 1689, Fort Worth, Texas 76101. (d) In accordance with FAR Sections 21.197 and 21.199, flight is permitted to a base where the inspection and repair procedures required by this AD may 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 Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, Texas 76101. This amendment becomes effective May 20, 1985.
2005-23-16: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-600, -700, -700C, -800, and -900 series airplanes. This AD requires modification of certain wire bundles located above the center fuel tank. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent chafed wire bundles near the center fuel tank, which could cause electrical arcing through the tank wall and ignition of fuel vapor in the fuel tank, and result in a fuel tank explosion.
2018-25-15: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 727 airplanes. This AD was prompted by a report of cracking in the inboard lower flange and adjacent web near the forward attachment of the outboard flap track at a certain position on a Model 737-300 airplane. The flap tracks of Model 737-300 airplanes are similar to the flap tracks of Model 727 airplanes. This AD requires repetitive detailed inspections and surface high frequency eddy current (HFEC) inspections of each outboard flap track at certain positions for any crack and discrepancy, and applicable on-condition actions. We are issuing this AD to address the unsafe condition on these products.
98-19-20: This amendment adopts a new airworthiness directive (AD) that is applicable to CFM International CFM56-7B and -7B/2 series turbofan engines. This action requires initial and repetitive inspections of certain hydromechanical unit (HMU) overspeed governor (OSG) spool valves for out-of-specification conditions or the presence of heavy contact or galling on the spool valve, and optional installation of an improved HMU as a terminating action to the inspections. This amendment is prompted by a report of a flameout that occurred on a flight test engine due to a failed HMU OSG spool valve shaft. The actions specified in this AD are intended to prevent failure of the HMU OSG spool valve shaft, and subsequent engine flameout.