Results
98-04-33: This amendment adopts a new airworthiness directive (AD), applicable to all Gulfstream American (Frakes Aviation) Model G-73 (Mallard) and G-73T series airplanes, that requires revising the Airplane Flight Manual (AFM) to specify procedures that would prohibit flight in severe icing conditions (as determined by certain visual cues), limit or prohibit the use of various flight control devices while in severe icing conditions, and provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions. This amendment is prompted by results of a review of the requirements for certification of the airplane in icing conditions, new information on the icing environment, and icing data provided currently to the flight crews. The actions specified by this AD are intended to minimize the potential hazards associated with operating the airplane in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
2012-12-04: We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 737-300, -400, and -500 series airplanes. That AD currently requires repetitive external detailed inspections or non-destructive inspections to detect cracks in the fuselage skin along the chem-mill steps at stringers S-1 and S-2R, between station (STA) 400 and STA 460, and repair if necessary. This new AD adds inspections for cracking in additional fuselage skin locations, and repair if necessary. This new AD also reduces the inspection thresholds and repetitive intervals for certain airplanes. This AD was prompted by reports of additional crack findings of the fuselage skin at the chem-mill steps. We are issuing this AD to detect and correct fatigue cracking of the fuselage skin panels at the chem- mill steps, which could result in sudden fracture and failure of the fuselage skin panels, and consequent rapid decompression of the airplane.
2010-10-11: 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: It was reported that after commanding the landing gear lever to down the three green landing gear positioning indication was displayed followed by the LG/LEVER DISAGREE EICAS [engine indicating and crew alerting system] message. The crew decided to continue the approach and landing procedure. As soon as the crew identified that the landing gear was not extended properly, a go-around procedure was successfully performed. During maneuver, the airplane settled momentarily onto the flaps and belly. * * * * * The unsafe condition is the landing gear remaining in the up and locked position during approach and landing. This condition could be accompanied by an invalid EICAS landing gear position indication, which could result in landing with gear in the up position and eliminate controllability of the airplane on the ground. This may consequently result in structural damage to the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
2010-10-08: 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 occurrences of loss of the AC [alternating current] BUS 1 have been reported which led in some instances to the loss of the AC ESS [essential] BUS and DC [direct current] ESS BUS and connected systems. The affected systems include multiple flight deck Display Units (Primary Flight Display, Navigation Display and Upper Electronic Centralised Aircraft Monitoring display). * * * * * The loss of multiple display units, if not corrected expediently during a high workload period, potentially affects the capability of the flight crew and could contribute to a loss of situational awareness and consequent control of the aeroplane, which would constitute an unsafe condition. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
75-08-19: 75-08-19 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-2167. Applies to Lockheed-California Company Model L-1011-385-1 series airplanes, certificated in all categories. To prevent possible hangups of the rudder pedals due to insufficient clearance in the side panel kickshield splice areas, accomplish the following: (A) Within 200 hours additional time in service, and at intervals not to exceed 200 hours time in service thereafter, after the effective date of this AD, perform a visual inspection of the flight station side panel kickshield joint areas to determine potential rudder pedal interference with the sidewall trim and center-console trim, per the instructions of Part I Lockheed Service Bulletin 093-25-155, dated June 15, 1973, or later FAA-approved revisions. (1) If adequate clearance exists, repeat the inspections at intervals not to exceed 200 hours time in service thereafter until the modifications described in (B), below, is accomplished. (2) If inadequate clearance is found as a result of any of the inspections, either (i) Perform the interim modifications described in Part I, paragraphs (2) or (3), Lockheed Service Bulletin, 093-25-155, dated June 15, 1973, or later FAA-approved revisions, and repeat the inspections of (A), above; or (ii) Perform the modifications described in Part II of the referenced Service Bulletin. (B) On or before July 1, 1975, perform the modification to the side and center/kickshield described in Part II of the referenced Service Bulletin. This modification, when accomplished, constitutes terminating action for this AD. (C) Equivalent inspections and modifications and replacement may be approved by the Chief, Aircraft Engineering Division, FAA Western Region. (D) Airplanes may be flown to a base for the accomplishment of the inspections and replacements required by this AD, per FAR's 21.197 and 21.199. This amendment becomes effective April 17, 1975
75-03-06: 75-03-06 MITSUBISHI HEAVY INDUSTRIES LIMITED: Amendment 39-2072. Applies to Mitsubishi Models MU-2B-26 (S/N 328 and below) and MU-2B-36 (S/N 673 and below) airplanes, except those airplanes modified in accordance with Mitsubishi Service Recommendation No. 027, dated September 12, 1974, or an FAA approved equivalent. Compliance required as indicated. To detect cracks and optical distortion in the front windshield outer panes that could result from the discharge of unusually hot defogging air caused by an air conditioning system failure, accomplish the following: (a) Before further flight and thereafter prior to the first takeoff each day, from outside the aircraft, visually check the outer lower edge of the left hand and right hand front windshield outer panes for cracks and small oval shaped optical distortions. The check required by this AD may be performed by the pilot. NOTE: Distortions generally appear at the same intervals as those of the defogging air outlet holes,approximately 0.5 inches apart, and in an area approximately 0.8 inches above the top of the outside bottom windshield retainer edge. Particular attention should be given to these areas during the checks required by paragraph (a). (b) If cracks or small oval shaped optical distortions are found during a check required by paragraph (a), before further flight, accomplish the following and continue to check in accordance with paragraph (a) of this AD: (1) Replace the windshield outer pane in which a crack or optical distortion is found in accordance with the performance rules of FAR 43.13. NOTE: Mitsubishi replacement windshield part numbers are as follows: Aircraft with electrically heated windshields incorporated in accordance with Mitsubishi Service Recommendation No. 014 - Windshield part numbers 010A-931026-11 and -12. Other aircraft - Serial numbers 4 through and including 7 - Windshield part numbers 010A-31026-1 and -2; Serial numbers 8 and up - Windshield part numbers010A-31450-1 and -2. (2) Correct the malfunctioning of the air conditioning system in accordance with the performance rules of FAR 43.13. (c) The inspections required by paragraphs (a) and (b) of this AD may be discontinued upon the incorporation of the modification specified in Mitsubishi Service Recommendation No. 027, dated September 12, 1974, or an FAA approved equivalent. (d) Notwithstanding the compliance time for repair specified in paragraph (b) of this AD, the aircraft may be flown in accordance with FAR 21.197 to a base where the repair can be performed; provided that, the aircraft is not pressurized. This amendment is effective upon publication in the Federal Register as to all persons except those persons to whom it was made effective upon receipt of the airmail letter dated November 13, 1974, that contained this amendment.
2012-11-05: We are superseding an existing airworthiness directive (AD) for Enstrom Helicopter Corporation (Enstrom) Model F-28C, F-28C-2, F- 28F, 280C, 280F, 280FX, TH-28, 480, and 480B helicopters to add another trim relay to the applicability and to revise the modification instructions. This AD is prompted by the discovery that another part- numbered trim relay, inadvertently omitted from the current AD, may contain the same unsafe condition. These actions are intended to prevent failure of the cyclic trim system and subsequent loss of control of the helicopter.
98-04-32: This amendment adopts a new airworthiness directive (AD), applicable to all Lockheed Model L-14 and L-18 Series Airplanes series airplanes, that requires revising the Airplane Flight Manual (AFM) to specify procedures that would prohibit flight in severe icing conditions (as determined by certain visual cues), limit or prohibit the use of various flight control devices while in severe icing conditions, and provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions. This amendment is prompted by results of a review of the requirements for certification of the airplane in icing conditions, new information on the icing environment, and icing data provided currently to the flight crews. The actions specified by this AD are intended to minimize the potential hazards associated with operating the airplane in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
87-12-10: 87-12-10 BRITISH AEROSPACE (BAe): Amendment 39-5653. Applies to all BAe Model 125-800 series airplanes listed in BAe Service Bulletin 53-62-(3127), Revision 1, dated October 15, 1986, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent failure of the ventral fuel tank aft support fitting, accomplish the following: A. Within the next 45 days after the effective date of this AD, unless accomplished within the last 45 days, and thereafter at intervals not to exceed 90 days, until replaced in accordance with paragraph C., below, visually inspect the ventral fuel tank aft attachment for corrosion and cracking in accordance with BAe Service Bulletin 53-62-(3127), Revision 1, dated October 15, 1986. B. Parts showing evidence of corrosion or found cracked must be replaced before further flight with a steel fitting in accordance with BAe Service Bulletin 53-63-(3127), Revision 1, dated October 15, 1986. C. Within oneyear after the effective date of this AD, unless already accomplished, replace the ventral tank aft attachment fittings with a new steel part in accordance with paragraph B., above. This constitutes terminating action for the inspections required by paragraph A., above. D. 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. E. 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 the inspections and/or modification required by this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to British Aerospace, Inc., Service Bulletin Librarian, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective July 30, 1987.
90-23-04: 90-23-04 AIRBUS INDUSTRIE: Amendment 39-6793. Docket No. 90-NM-208-AD. Applicability: All Model A320 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent the loss of pitch electronic control and resultant reduced controllability of the airplane in the event of the trimmable horizontal stabilizer (THS) actuator control jamming, accomplish the following: A. Within 7 days after the effective date of this AD, and thereafter at intervals not to exceed 7 days, perform a test to check the availability of pitch control through both the SEC 1 and SEC 2, in accordance with Airbus Industrie Service Bulletin A320-27-1031, Revision 1, dated August 15, 1990. B. If electrical pitch control is not available through both SEC 1 and SEC 2, repair prior to further flight and test again, in accordance with Airbus Industries Service Bulletin A320- 27-1031, Revision 1, dated August 15, 1990. Following repair, repeat the test required by paragraph A. of this AD at intervals not to exceed 7 days. C. 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, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700Blagnac, France. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6793, AD 90-23-04) becomes effective on November 19, 1990.