Results
2015-08-04: We are superseding Airworthiness Directive (AD) 99-01-05 R1, which applied to certain aircraft equipped with wing lift struts. AD 99-01-05 R1 required repetitively inspecting the wing lift struts for corrosion; repetitively inspecting the wing lift strut forks for cracks; replacing any corroded wing lift strut; replacing any cracked wing lift strut fork; and repetitively replacing the wing lift strut forks at a specified time for certain airplanes. This new AD retains all requirements of AD 99-01-05R1 and adds additional airplane models to the Applicability section. This AD was prompted by a report that additional Piper Aircraft, Inc. model airplanes should be added to the Applicability section. We are issuing this AD to correct the unsafe condition on these products.
2005-07-18: The FAA is adopting a new airworthiness directive (AD) for the airplanes listed above. For certain airplanes, this AD requires inspecting to determine the airplane's cargo configuration, and reporting findings to the FAA. For airplanes modified in accordance with a certain STC or with a cargo configuration that deviates from the as-delivered configuration, this AD requires revising certain manuals and manual supplements to specify certain cargo limitations. This AD also requires relocating all cargo restraints on the main cargo deck. This AD is prompted by reports that deficiencies related to the cargo loading system may exist on all McDonnell Douglas Model DC-9-15F airplanes modified in accordance with STC SA1993SO. We are issuing this AD to ensure that cargo in the main cabin is adequately restrained and to prevent failure of components of the cargo loading system, failure of the floor structure, or shifting of cargo. Any of these conditions could cause cargo to exceed loaddistribution limits or cause damage to the fuselage or control cables, which could result in reduced controllability of the airplane.
88-23-02: 88-23-02 MESSERSCHMITT-BOLKOW-BLOHM (MBB) GmbH: Amendment 39- 6027. Applies to MBB BK-117 A-1, A-3, and A-4 series helicopters certificated in any category. (Docket No. 85-ASW-1) Compliance is required within 30 days after the effective date of this AD, unless already accomplished. To prevent possible hazards in flight associated with operation outside of approved operating limits, accomplish the following: (a) Apply new VNE placards Part Numbers 117-740131.97, 117-740131.98, 117- 740131.99, or 117-740131.100, in place of the existing VNE placard in accordance with instructions contained in MBB Alert Service Bulletin MBB-BK 117-70-101, dated April 11, 1988. (b) The placard required by paragraph (a) may be installed by a pilot who makes the appropriate maintenance record entries required by FAR Parts 43 and 91. (c) An equivalent method of compliance with this AD may be used when approved by the Manager, Rotorcraft Directorate, Aircraft Certification Service, FAA, Fort Worth, Texas 76193-0100, or by the Manager, Brussels Aircraft Certification Office, AEU-100, c/o American Embassy, Brussels, Belgium, APO New York 09667-1011. This procedure shall be accomplished in accordance with MBB Helicopter Alert Service Bulletin ASB-MBB-BK 117-70-101, dated April 11, 1988. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552 (a) and 1 CFR Part 51. Copies may be obtained from MBB, GmbH, Abt, Drehflugler, Postfach 801140, D-8000 Munchen 80, Federal Republic of Germany. Copies may be inspected at the Office of the Regional Counsel, FAA, 4400 Blue Mound Road, Fort Worth, Texas, or at the Office of the Federal Register, 1100 L Street, N.W., Room 8401, Washington, D.C. This amendment, 39-6027, supersedes AD 85-02-04, Amendment 39-4989 as amended by AD 85-02-04 R1, Amendment 39-5793. This amendment, 39-6027, becomes effective on November 28, 1988.
2023-26-06: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300- 600 series airplanes). This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, 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.
2005-07-08: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 757-200 and -200PF series airplanes. This AD requires repetitive inspections and audible tap tests of the upper and lower skins of the trailing edge wedges on certain slats, and related investigative and corrective actions if necessary. This AD also provides an optional terminating action for the repetitive inspections and audible tap tests. This AD is prompted by a report of damage to the No. 4 leading edge slat. We are issuing this AD to prevent delamination of the leading edge slats, possible loss of pieces of the trailing edge wedge assembly during flight, reduction of the reduced maneuver and stall margins, and consequent reduced controllability of the airplane.
2015-13-11: We are adopting a new airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 430 helicopters to require inspecting the tail rotor control tube assembly (control tube) and either repairing or replacing the control tube. This AD was prompted by two reports of failure of the control tube bonded clevis. The actions of this AD are intended to prevent failure of a control tube bonded clevis, which could lead to failure of the control tube and subsequent loss of helicopter control.
2015-08-01: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 757-200, -200PF, -200CB, and -300 series airplanes. This AD was prompted by numerous reports of unintended lateral oscillations during final approach, just before landing. This AD requires, depending on airplane configuration, installing new relays and bracket assemblies, inspecting to ensure that the new relays do not contact adjacent wire bundles, torquing the bracket assembly installation nuts and ground stud nuts, doing bond resistance tests between the bracket assemblies and the terminal lugs on the ground studs, and related investigative and corrective actions if necessary. We are issuing this AD to reduce the chance of unintended lateral oscillations near touchdown, which could result in loss of lateral control of the airplane, and consequent airplane damage or injury to flightcrew and passengers.
79-05-08: 79-05-08 BELL: Amendment 39-3429. Applies to Bell Model 212 helicopters, Serial Numbers 30501 through 30888, equipped with emergency flotation (ditching) equipment, certificated in all categories. (Airworthiness Docket No. 78-ASW-44.) Compliance required with 600 hours' time in service or six months after the effective date of this airworthiness directive (AD), whichever comes first, unless already accomplished. To preclude possible tearing, puncturing, and deflation of a float bag after a ditching, accomplish the following: Remove the four emergency float bags and install modified or new float bags having the following part numbers: Air Cruisers Number D24650-105, -106, -107, and -108 (Bell Number 212-050-207-5, -6, -7, and -8 respectively) or a B. F. Goodrich Number 7MA1002-5, -6, -7, and -8 (Bell Number 212-050-207-9, -10, -11, and -12 respectively). Air Cruisers or B. F. Goodrich float bags may be modified and reidentified as prescribed by Air Cruisers CompanyService Bulletin No. 120-78-1 dated May 5, 1978, or later FAA approved revision or by B. F. Goodrich, Engineered Systems Division, Service Bulletin No. 01 dated May 8, 1978, or later FAA approved revision, respectively. 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 the Product Support Department, 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 Region Office in Fort Worth, Texas. (Bell Helicopter Textron Service Bulletin No. 212-78-9 pertains to this subject.) This amendment becomes effective April 16, 1979.
2005-07-06: The FAA is superseding an existing airworthiness directive (AD) for General Electric Company (GE) CF34-8C1 series and CF34-8C5 series turbofan engines, with certain serial number (SN) master variable geometry (VG) actuators installed. That AD currently requires initial and repetitive reviews of the airplane Maintenance Data Computer (MDC) for master VG actuator fault messages, and if the MDC is inoperative, reviews of the Engine Indication and Crew Alerting System (EICAS) for fault messages. That AD also requires replacing actuators reported faulty by the Full Authority Digital Engine Control (FADEC). This ad requires those same actions, and expands the applicability to additional actuators by part number (P/N) and SN. This AD also prohibits installation of affected master VG actuators onto any CF34- 8C1 and CF34-8C5 engine after the effective date of this AD. This AD results from the need to add to the list of affected parts, master VG actuators made by parts manufacturer approval (PMA). We are issuing this AD to prevent dual-channel electrical signal faults in the VG master actuator, which will cause an uncommanded reduction of thrust to idle with a subsequent loss of the ability to advance thrust above idle, and which will result in a multiengine loss of thrust if dual- channel faults occur on more than one engine simultaneously.
2024-01-07: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 777 airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) that found the force limiter assemblies for the lateral control mechanism are not breaking out within the maximum design force requirements. This AD requires replacing affected force limiter assemblies and prohibits the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.