Results
2008-23-01: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A318, A319, A320, and A321 airplanes. That AD currently requires inspecting to determine the part number and serial number of the fuel tank boost pumps and, for airplanes with affected pumps, revising the airplane flight manual (AFM) and the FAA-approved maintenance program. The existing AD also provides for optional terminating action for compliance with the revisions to the AFM and the maintenance program. This new AD requires modifying or replacing the fuel tank boost pumps, which would terminate the AFM limitations and the maintenance program revisions. This AD results from a report that a fuel tank boost pump failed in service, due to a detached screw of the boost pump housing that created a short circuit between the stator and rotor of the boost pump motor and tripped a circuit breaker. We are issuing this AD to prevent electrical arcing in the fuel tank boost pump motor, which, in the presence of a combustible air-fuel mixture in the pump, could result in an explosion and loss of the airplane. DATES: This AD becomes effective December 19, 2008. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of December 19, 2008. On July 3, 2006 (71 FR 34814, June 16, 2006), the Director of the Federal Register approved the incorporation by reference of a certain other publication.
2008-22-17: The FAA is superseding an existing airworthiness directive (AD) that applies to certain Boeing Model 747 series airplanes. That AD currently requires repetitive inspections for cracking and corrosion of all exposed surfaces of the carriage spindles (including the inner bore and aft links) of the trailing edge flaps, and additional inspection and corrective action if necessary. That AD also currently requires repetitive overhaul of the carriage spindle and aft link, which terminates the repetitive inspections. This new AD adds a repetitive inspection to detect broken parts, and revises the overhaul threshold and repetitive intervals. This AD results from analysis that showed additional inspections should be done to prevent the loss of a flap, and that the flight-hour-based interval should be revised to a flight- cycle-based interval, because the greatest loads on the spindles happen during takeoff and landing. We are issuing this AD to detect and correct failed carriage spindles or aft links of the inboard or outboard trailing edge flaps. Such failure could cause the flap to depart the airplane, reducing the flightcrew's ability to maintain the safe flight and landing of the airplane.
85-19-08: 85-19-08 BRITISH AEROSPACE: Amendment 39-5313. Applies to Model 3101 (includes Model 3100) airplanes (serial numbers 601 through 666) certificated in any category. Compliance: Required within seven days after receipt of this AD unless already accomplished. To prevent the possibility of wing droop development and structural damage to the forward wing spar fuselage attachment and resulting loss of control of the airplane, accomplish the following: (a) Remove wing-to-fuselage fairing panels numbers F19 and F20. (b) Using as a reference BAe Model 3100 Illustrated Parts Catalog, Chapter 57-00- 00 Figure 3 wing installation and using a suitable light source, visually inspect and repair as required item number 210 spigot (pin) Part No. 13781B7 (LH and RH), in accordance with the following criteria: (i) If no gap exists between the spigot flange and the fuselage post, and if the locking bolt, washer and nut (items 205, 200 and 195 respectively) securing the spigotare in position and secure, install panel numbers F19 and F20 and return the airplane to service. (ii) If little or no gap exists between the spigot flange and the fuselage post, and if the locking bolt, washer and nut are not secure, prior to further flight accomplish the following: (A) Remove the loading from the wing to the fuselage joint and push the spigot (pin) into the spigot housing, and (B) Install the locking bolt (Part No. A102-18D) with the head forward, the nut (Part No. A126 D66) and the washer (Part No. SP124D). Replace panels F19 and F20 and return the airplane to service. (C) If the locking bolt (Part No. A102-18D) cannot be installed without rotation of the spigot, prior to further flight accomplish the repair procedures described in paragraph (c) of this AD. (iii) If a large gap exists between the spigot flange and the fuselage post which results in loss of engagement with the spigot housing plate (item 215 LH and 220 RH), prior to further flight accomplish the repair procedures described in paragraph (c) of this AD. (iv) If other structural deformation or damage is observed relating to improper spigot installation, prior to further flight obtain and accomplish the repair procedures in accordance with paragraph (c) of this AD. (v) If the fuselage vertical post outboard bushing is found to be displaced, prior to further flight repair in accordance with the instructions in Figure 1 of British Aerospace Service Bulletin No. 57-A-JA 840917 dated January 25, 1985. (c) Alternate methods of compliance and repair procedure may be used if approved by either the Manager of the FAA Brussels Aircraft Certification Office, FAA, AEU-100, c/o American Embassy, 1000 Brussels, Belgium, or the Manager of the Small Aircraft Certification Division, FAA, Central Region, ACE-100, 601 East 12th Street, Kansas City, Missouri 64106. (d) Report, in writing, all defects found to the Manager, Small Aircraft Certification Division, FAA, Central Region, within 48 hours of the inspection. (Reporting approved by the Office of Management and Budget under OMB No. 2120-0056.) This amendment becomes effective May 26, 1986, as to all persons except those persons to whom it was made immediately effective by priority letter AD 85-19-08, issued September 26, 1985, which contained this amendment.
2021-10-18: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Deutschland GmbH Model MBB-BK117 D-2 helicopters. This AD was prompted by reports that collective lever switch units having certain part numbers did not have retaining rings installed in the cable cut switch guard. This AD requires inspecting certain collective lever switch units for discrepancies (missing retaining rings, incorrectly installed retaining rings, and a missing axis in the cable cut switch guard), doing all applicable corrective actions, and marking affected parts, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
85-05-04: 85-05-04 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-5010. Applies to Lockheed Model L-1011-385 series airplanes, certificated in all categories. Compliance required as indicated unless previously accomplished. To minimize potential for the loss of flight control capability due to the loss of three out of four hydraulic systems accomplish the following: A. Within one year after the effective date of this AD, modify hydraulic system "C" by installing a hydraulic fuse and associated hydraulic tubing and replace aluminum return lines with steel lines in accordance with Lockheed L-1011 Service Bulletins Number 093-29-065, Revision 4, dated August 9, 1983, and 093-29-085, dated December 8, 1983, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. B. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office,FAA, Northwest Mountain Region. C. 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 these documents from the manufacturer may obtain copies upon request to Lockheed-California Company, P.O. Box 551, Burbank, California 91520, Attention: Commercial Support Contracts, Dept. 63-11, U-33, B-1. These documents also may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. This amendment becomes effective April 1, 1985.
2003-19-06: The FAA is adopting a new airworthiness directive (AD) for Turbomeca S.A. Arrius 2 B1, 2 B1A, 2 B1A 1, and 2 K1 turboshaft engines. This AD requires replacement of the gas generator high pressure (HP) turbine disk before further flight after the engine has accumulated 5 minutes of operating time at the 2 1/2 minute one engine inoperative (OEI) power rating. This amendment is prompted by a failure of an HP turbine blade during accelerated aging simulation tests performed by the manufacturer on an Arrius 2 B1A engine. We are issuing this AD to prevent engine failure of the only operating engine while experiencing an OEI condition.
2008-23-09: We are adopting a new airworthiness directive (AD) for certain Boeing transport category airplanes. This AD requires replacing any insulation blanket constructed of polyethyleneteraphthalate (PET) film, ORCON Orcofilm® AN-26 (hereafter "AN-26''), with a new insulation blanket. This AD results from reports of in-flight and ground fires on certain airplanes manufactured with insulation blankets covered with AN-26, which may contribute to the spread of a fire when ignition occurs from sources such as electrical arcing or sparking. We are issuing this AD to ensure that insulation blankets constructed of AN-26 are removed from the fuselage. Such insulation blankets could ignite and propagate a fire that is the result of electrical arcing or sparking.
98-13-02: This amendment adopts a new airworthiness directive (AD) that applies to Raytheon Aircraft Company (Raytheon) Models 35, A35, B35, and 35R airplanes (commonly referred to as Beech Models 35, A35, B35, and 35R airplanes). This AD requires fabricating a placard that restricts the never exceed speed (Vne) to no more than 144 miles per hour (MPH) or 125 knots (KTS) indicated airspeed (IAS), and installing this placard on the instrument panel within the pilot s clear view. This AD also requires marking a red line on the airspeed indicator glass at 144 MPH (125 KTS), marking a white slippage mark on the outside surface of the airspeed indicator between the glass and case, and inserting a copy of this AD into the Limitations Section of the airplane flight manual (AFM). This AD is the result of several occurrences of in-flight vibration on the affected airplanes. The actions specified by this AD are intended to prevent in-flight vibrations caused by the affected airplanes operating at excessive speeds, which could result in airplane damage and possible loss of control of the airplane. Comments for inclusion in the Rules Docket must be received on or before August 10, 1998.
2020-15-09: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-941 airplanes. This AD was prompted by a report that seven spoiler servo-controls (SSCs) lost hydraulic locking function due to a sheared seal on the blocking valve. This AD requires repetitive operational tests of the hydraulic locking function on each SSC and replacement if necessary, as specified in a European Union Aviation Safety Agency (EASA), which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
85-14-07: 85-14-07 AEROSPATIALE (formerly SUD): Amendment 39-5094. Applies to all Caravelle SE-210 Models I, III, and VIR airplanes, certificated in any category, which do not embody Modification 1753. Accomplish the following, unless previously accomplished: A. Prior to the accumulation of 7000 landings or before the next 100 landings after the effective date of this AD, whichever occurs later, inspect the wing rib 44 web and angle doubler in accordance with SUD Service Bulletin 57-64 dated December 12, 1978. B. Repeat the inspections of paragraph A., above, at intervals not to exceed: 1. rib 44 lower cap - 10,000 landings 2. webs and doublers - 3,000 landings. C. Parts found cracked must be repaired prior to further flight. D. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, 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 inspections and/or modifications required by this AD. This amendment becomes effective August 16, 1985.