Results
2014-15-21: We are superseding Airworthiness Directive (AD) 2006-26-06 for certain The Boeing Company Model 777-200 and -300 series airplanes equipped with Rolls-Royce engines. AD 2006-26-06 required repetitive inspections to detect cracks of the outer V-blades of the thrust reverser, and corrective action if necessary. AD \n\n((Page 48025)) \n\n2006-26-06 also provided for an optional terminating action for the repetitive inspections. This new AD adds, for airplanes on which the optional terminating action is done, repetitive inspections for cracking in the outer V-blade fittings of the hinge beam and latch beam ends of each thrust reverser half, and replacement of an affected thrust reverser half if necessary. This new AD also adds airplanes to the applicability. This AD was prompted by reports of cracked outer V- blade fittings at the hinge beam end of Rolls-Royce engine thrust reversers, on airplanes on which the optional terminating action was done. We are issuing this AD to preventseparation of a thrust reverser from the airplane during normal reverse thrust or during a refused takeoff, which could result in unexpected thrust asymmetry and a possible runway excursion.
2000-01-17: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-90 series airplanes, that requires a one-time detailed visual inspection to detect fatigue cracking of certain longerons and the attaching frames of the lower left nose; and repair, if necessary. This amendment also requires installation of a preventive modification. This amendment is prompted by several reports of fatigue cracking of certain longerons and the attaching frames. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in reduced structural integrity of the fuselage, and consequent loss of pressurization of the airplane.
2000-01-15: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 050 series airplanes. For certain airplanes, this action requires modification of the electrical power supply of the landing gear anti-skid unit. For certain airplanes, this action also requires a revision to the Airplane Flight Manual (AFM) to provide the flight crew with procedures for calculating the accelerate-stop distance for certain conditions, and installation of a new ground idle stop assembly and new placards on the top cover of the pedestal, which terminates the requirements for the AFM revision. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent interruption of the anti-skid system function, or inadvertent selection of reverse thrust during a rejected takeoff. Either of these conditions could result in reduced controllability of the airplane.
87-07-08: 87-07-08 LOCKHEED-GEORGIA COMPANY: Amendment 39-5592. Applies to Lockheed JetStar Model 1329 and JetStar Model 1329-25 series airplanes, equipped with an AiResearch Aviation Company Model GTCP 30-92 Auxiliary Power Unit (APU) in accordance with STC SA1043WE or STC SA3297WE, certificated in any category. Compliance required as indicated, unless previously accomplished. To minimize the potential for fuel fumes entering the passenger compartment, accomplish the following: A. Within the next 600 hours time-in-service or 12 months after the effective date of this AD, whichever occurs earlier: 1. Install an improved APU fuel supply shutoff valve, Valcor P/N V4700- 130, in accordance with AiResearch Aviation Company Service Bulletin No. 11.37, dated December 19, 1984, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. 2. Visually inspect the sealing joint of the fuel control governor cover for fuelleaks, seal (O-ring) extrusion, and cover distortion, and replace, if necessary, prior to further flight, in accordance with the AiResearch Aviation Company Service Bulletin mentioned above. B. 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. C. 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. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to the Lockheed-Georgia Company, 86 South Cobb Drive, JetStar Customer Support, Dept. 64-26, Zone 668, Marietta, Georgia, 30063; or AiResearch Aviation Company, Customer Support Department, 6201 West Imperial Highway, Los Angeles, California 90045. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at 4344 Donald Douglas Drive, Long Beach, California. This amendment becomes effective May 1, 1987.
2014-12-51: We are publishing a new airworthiness directive (AD) for Airbus Helicopters Model EC130B4 and EC130T2 helicopters, which was sent previously to all known U.S. owners and operators of these helicopters. This AD requires repetitively inspecting the Fenestron to tailboom junction frame (junction frame) for a crack. This AD is prompted by reports of a crack propagating through the junction frame on two EC130B4 helicopters. These actions are intended to detect a crack and to prevent failure of the junction frame, which could result in loss of the Fenestron and subsequent loss of control of the helicopter.
2014-15-04: We are adopting a new airworthiness directive (AD) for certain Saab AB, Saab Aerosystems Model SAAB 2000 airplanes. This AD was prompted by a report of rudder pedal restriction which was the result of water leakage at the inlet tubing of an in-line heater in the lower part of the forward fuselage. This AD requires deactivating the potable water system, or alternatively filling and activating the potable water system. We are issuing this AD to prevent rudder pedal restriction due to the pitch control mechanism becoming frozen as the result of water spray, which could prevent disconnection and normal pitch control, and consequently result in reduced controllability of the airplane.
2000-01-12: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 and 200) series airplanes, that currently requires repetitive inspections to detect cracks of a certain bulkhead web of the fuselage at certain locations, and repair, if necessary. This amendment revises the repetitive inspection intervals for certain airplanes, and requires modification or repair, as applicable. This amendment is prompted by the development of a modification that will adequately address the identified unsafe condition. The actions specified by this AD are intended to detect and correct fatigue cracking, which could result in uncontrolled depressurization of the airplane and/or reduced structural integrity of the fuselage.
85-10-05 R1: 85-10-05 R1 ROLLS-ROYCE LIMITED: Amendment 39-5063 as amended by Amendment 39-5239. Applies to Rolls-Royce RB211-22B and RB211-524B, -524C, and -524D series turbofan engines. Compliance is required as indicated unless already accomplished. To prevent an internal oil fire, failure of the low compressor rotor shaft, and subsequent low turbine rotor overspeed leading to an uncontained rotor failure, accomplish the following: Prior to December 31, 1987, incorporate low pressure rotor location bearing area modifications as specified in Rolls-Royce Mandatory SB RB211-72-6847, Revision 2, dated March 30, 1984, or FAA approved equivalent. Upon request, an alternate means of compliance may be approved by the Manager, Engine Certification Office, Aircraft Certification Division, New England Region, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Engine Certification Office, New England Region, may adjust the compliance time specified in this AD. The manufacturer's SB identified and described in this directive is 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 the SB from the manufacturer may obtain copies upon request to Rolls-Royce Limited, Technical Publications Department, P.O. Box 31, Derby DE2 8BJ, England. The SB may also be examined at the office of the Regional Counsel, New England Region, Federal Aviation Administration, Rules Docket No. 84-ANE-14, 12 New England Executive Park, Burlington, Massachusetts 01803, weekdays between the hours of 8:00 a.m. and 4:30 p.m. except Federal holidays. Amendment 39-5063 became effective on July 23, 1985.This Amendment 39-5239 becomes effective on March 28, 1986.
78-18-06: 78-18-06 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-3296 is further amended by amendment 39-3498. Applies to Lockheed-California Company Model L-1011-385 Series airplanes certificated in all categories. Compliance required as indicated, unless previously accomplished. To prevent the transfer of potentially hazardous quantities of vapors from the engine compartment into the afterbody of the airplane, accomplish the following: (a) For airplanes with 7500 or more hours total time in service on the effective date of this AD, within the next 1000 hours time in service, inspect the center engine "S" duct flexible fire seal Part No. 1506933-101 per paragraph (c) below. (b) For airplanes with less than 7500 hours total time in service on the effective date of this AD, prior to the accumulation of 8500 hours total time in service, inspect the center engine "S" duct flexible fire seal per paragraph (c) below. (c) Visually inspect the center engine "S" duct flexible fire seal for depth of groove and/or tears per the procedures set forth in paragraph 2.A of Lockheed California Service Bulletin 093-54-030 dated March 28, 1978 (hereinafter referred to as SB 093-54-030). NOTE: Service Bulletin 093-54-030 dated March 28, 1978 and Service Bulletin 093-54-030, Revision 1, are suitable for demonstrating compliance with paragraphs (c) through (h) of this AD. (d) If there are no tears, and evidence of grooving is observed, or if groove depth is determined to be less than 0.035 inch using the procedures of paragraph 2.A of SB 093-54-030, the seal may be retained in service with performance of repetitive inspections at intervals not to exceed 1500 hours total time in service. (e) If there are no tears and seal is worn to a groove depth greater than 0.035 inch but less than 0.050 inch: (1) Continue worn part in service and reinspect within 1000 hours additional time in service; or (2) Repair seal per paragraph 2.C of Service Bulletin 093-54-030dated March 28, 1978 or per paragraph 2.D of Service Bulletin 093-54-030, Revision 1, and reinspect within 8500 hours additional time in service; or (3) Replace seal with like serviceable part per paragraph 2.B of SB 093-54- 030 and reinspect per paragraph 2.A of SB 093-54-030 within 8500 hours additional time in service. (f) If seal is worn to a groove depth equal to or greater than 0.050 inch but is intact, within 500 hours additional time in service, repair seals per paragraph 2.C of SB 093-54-030 or replace seal per paragraph 2.B of SB 093-54-030 and reinspect per paragraph 2.A of SB 093-54- 030 within 8500 hours additional time in service. (g) If seal is worn through or torn, within 250 hours additional time in service repair seal per paragraph 2.C of SB 093-54-030 or replace seal per paragraph 2.B of SB 093-54-030 and reinspect per paragraph 2.A of SB 093-54-030 within 8500 hours additional time in service. (h) Actions required per this AD may be terminated whenchafing protection (Belt Assembly Part Number 1619429-101) is installed per paragraph 2.D of SB 093-54-030 in conjunction with a new, used, or repaired center engine "S" duct flexible fire seal which meets the criteria of paragraph (d) or (e)(2) of this AD. Revert to routine maintenance/inspection practices. (i) Equvalent inspection procedures and repairs may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. (j) Special flight permits may be issued in accordance with FARs 21.197 and 21.199 to operate aircraft to a base for accomplishment of inspections and/or maintenance required by paragraph (b) of this AD. (k) Upon request of operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Engineering Division, FAA Western Region may adjust the initial and repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. Amendment 39-3296 became effective October 13, 1978. This amendment, 39-3498, becomes effective June 25, 1979.
2000-01-08: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace BAe Model ATP airplanes, that requires a one-time inspection of the orientation of certain bolts of the rudder standby control system (SCS), and reinstallation of the bolts, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent uncommanded engagement of the rudder SCS, which could result in reduced controllability of the airplane.