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99-19-19: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 series airplanes and Model F27 Mark 050 series airplanes, that requires revising the Airplane Flight Manual (AFM) to include requirements for activation of the airframe pneumatic deicing boots. This amendment is prompted by reports of inflight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to ensure that flightcrews activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. This action will prevent reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
82-18-09: 82-18-09 AIRCRAFT TANK SERVICE, INC.: Amendment 39-4449. Applies to Lockheed Model 1329 series airplanes, Avions Marcel Dassault Model Fan Jet Falcon series airplanes, and British Aerospace (Aircraft Group) Model DH-125 series airplanes which have been modified in accordance with STC SA2603WE, SA3221WE, SA3324WE, SA1851WE, or SA3382WE, certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent possible engine fuel starvation, accomplish the following: A. Within the next 30 calendar days after the effective date of this AD, or before the accumulation of two years calendar time since the installation of tygothane tubing, whichever occurs later, inspect to determine the condition of the tygothane components in accordance with the appropriate service bulletin listed in the table below. 1. If there is cracking or brittleness, discontinue use of the single point refueling system and within 90 calendar days after the inspection, remove tygothane tubing systems components and replace with like serviceable components in accordance with Part III of the appropriate service bulletin. The appropriate service bulletin for each type airplane is shown below. Model STC No. Aircraft Tank Service, Inc. Service Bulletin Fan Jet Falcon SA1851WE A28-01 Rev. 1 dated January 21, 1982 DH-125 SA3382WE A28-02 Rev. 1 dated February 5, 1982 1329 SA2603WE A28-04 Rev. 1 dated January 29, 1982, or A28-05 Rev. 1 dated February 5, 1982 (see Service Bulletin effectivity) 1329 SA3221WE A28-05 Rev. 1 dated February 5, 1982 1329 SA3324WE A28-05 Rev. 1 dated February 5, 1982 2. If there is no cracking or brittleness but a chocolate brown color noted, continue operation and repeat inspection at six months from initial inspection and replace tygothane components per appropriate service bulletin within one year from initial inspection. 3. If the tygothane components are light colored, continue toinspect in accordance with paragraph A. of this AD at intervals not to exceed six months until such time as the tygothane components are replaced in accordance with Part III of the appropriate service bulletin. B. After the effective date of this AD, if difficulty in pressure refueling or spillage out of the vent line is encountered, inspect per paragraph A. of this AD, and: 1. If the tygothane tubing has started to break up and there is evidence of tygothane particles in the tank which could cause fuel system contamination, replace the tygothane tubing prior to next flight per Part III of the appropriate Service Bulletin. 2. If cracking or embrittlement is found without evidence of loose particles, discontinue use of the single point fueling system and replace the tygothane tubing within 90 days after the inspection in accordance with Part III of the appropriate Service Bulletin. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 tooperate aircraft to a base for the accomplishment of inspections or modifications required by this AD. D. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Chief, Western Aircraft Certification Field Office, FAA Northwest Mountain Region, Hawthorne, California. 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 proposal who have not already received these documents from the manufacturer may obtain copies upon request to Aircraft Tank Service, Inc., Product Support Engineering, P.O. Box 1307, Sun Valley, California 91352. These documents may also be examined at FAA Northwest Mountain Region, 17900 Pacific Highway South, C-68966, Seattle, Washington 98168; or Western Aircraft Certification Field Office, 15000 Aviation Boulevard, Hawthorne, California 90261. This amendment becomes effective October 4, 1982.
2014-07-09: We are adopting a new airworthiness directive (AD) for British Aerospace Regional Aircraft Jetstream Series 3101 and Jetstream Model 3201 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued 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 inadequate instructions for inspection for corrosion on the rudder upper hinge bracket and certain internal wing and drainage paths. We are issuing this AD to require actions to address the unsafe condition on these products.
99-19-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Fairchild Model F-27 and FH-227 series airplanes, that requires revising the Airplane Flight Manual (AFM) to include requirements for activation of the airframe pneumatic deicing boots. This amendment is prompted by reports of inflight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to ensure that flightcrews activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. This action will prevent reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
99-24-04: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes and Model MD-88 airplanes, that requires a one-time visual inspection to determine whether self-aligning nuts are installed at certain locations of the aft pressure bulkhead tee; and corrective actions, if necessary. This amendment is prompted by reports of failures of certain Hi-Lok pin fasteners of the aft pressure bulkhead tee due to installation of non-self-aligning nuts. The actions specified by this AD are intended to prevent failure of certain Hi-Lok pin fasteners and subsequent gouging of the aft pressure bulkhead tee, which could result in fatigue cracking and reduced structural integrity of the airplane.
99-23-24: This amendment adopts a new airworthiness directive (AD), applicable to certain instrument landing system (ILS) navigation receivers manufactured by AlliedSignal. This action requires replacement of certain resistors in the ILS navigation receiver with higher ohm resistors and replacement of the nameplate on the receiver with a new nameplate. This amendment is prompted by reports of ILS navigation receivers incorrectly indicating signals from the glideslope ground station during final approach. The actions specified in this AD are intended to ensure the ILS receiver provides the flight crew with accurate glideslope data. Inaccurate glideslope data could result in an approach off the glideslope, and, consequently, a landing short of the runway or a runway overrun.
2014-08-04: We are superseding Airworthiness Directive (AD) 2012-03-04 for certain Airbus Model A310 series airplanes. AD 2012-03-04 required for certain airplanes, modifying the wire routing and installing additional protective sleeves. This new AD continues to require the actions in AD 2012-03-04, and requires additional work for certain airplanes. This AD was prompted by reports of new interferences of newly routed wire bundle 2S. We are issuing this AD to prevent short circuits leading to arcing, and possible fuel tank explosion.
99-24-03: This amendment supersedes two existing airworthiness directives (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that currently require inspections in the lower center cargo compartment at frame 1681 to verify that a certain bracket and a certain open face nylon clamp were installed to a specific wire bundle support and to detect damage of the subject wire bundle; and corrective actions, if necessary. This amendment requires a similar inspection and corrective actions required by the existing AD's and removes certain airplanes from the applicability of the existing AD's. This amendment also adds a requirement to install a wire assembly support bracket, clamp, and spacer, or revise the wire assembly support bracket and clamp installation; as applicable. This amendment is prompted by an incident in which the insulation blanket in the lower center cargo compartment was found to be burnt due to a missing wiring harness support bracket/clamp on a wirebundle. The actions specified by this AD are intended to prevent sparks, smoke, and possible fire in the lower center cargo compartment.
87-23-02: 87-23-02 AEROSPATIALE: Amendment 39-5761. Applies to Model ATR-42-300 series airplanes fitted with SOCEA flight attendants' seats, Part Numbers 2510132 and 2510137, certificated in any category. Compliance is required within 30 days after the effective date of this AD, unless already accomplished. To prevent collapse of the seat pan of the flight attendant's seats, accomplish the following: A. Modify seats in accordance with Aerospatiale Service Bulletin No. ATR42-25- 0003, Revision 2, dated November 5, 1986, or SOCEA Service Bulletin No. 25-73, dated June 1, 1986. 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. C. 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 modifications 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 Aerospatiale, 316 Route de Bayonne, 31060 Toulouse Cedex 03, France. 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 December 16, 1987.
80-14-16 R1: 80-14-16 R1 SIKORSKY AIRCRAFT: Amendment 39-3837 as amended by Amendment 39-3941. Applies to S-76A series helicopters certificated in all categories. To prevent operation with a displaced shear bearing inner race and a possible cracked main rotor blade spindle accomplish the following: 1. Compliance required as indicated, unless already accomplished under the requirements of telegraphic airworthiness directive (TAD) T80NE-21, or accomplished prior to issuance of the original FAA airworthiness certificate. a. Prior to further flight, inspect the P/N 76102-08000-041 main rotor blade spindle assemblies in accordance with Sikorsky Alert Service Bulletin 76-65-13A, Paragraph G(1) through G(3), dated April 24, 1980. b. Prior to further flight, remove from service any P/N 76102-08001 main rotor blade spindles found to have a missing or displaced (beyond 1/2 inch) P/N SB 5206-102/-103 spindle shear bearing inner race. Spindle assemblies, where the spindle sear bearing has been previously found, prior to April 24, 1980, missing, displaced (any dimension), or reworked in any manner, must also be replaced prior to further flight in accordance with the applicable procedures described in this AD. c. Within the next 25 hours time in service, after July 12, 1980, modify and repetitively inspect the P/N 76102-08000 main rotor blade spindle assemblies in accordance with Sikorsky Alert Service Bulletin 76-65-13A, Paragraphs G(4) and G(5), dated April 24, 1980. Note: The requirements of this paragraph are an interim action which must be utilized until the components for the required modification described in paragraph 1d herein become available. d. Prior to February 15, 1981, remove from service all "Cable-TYs" installed on main rotor blade spindle assemblies in accordance with Sikorsky Alert Service Bulletin 76-65-13A, Paragraph G(4), and replace with sleeve type retainers 76102-08055-101 and sleeve straps 76102-08055-103 in accordance with Paragraph 2C of Sikorsky Service Bulletin 76-65-15, dated September 17, 1980. Accomplishment of the modification in accordance with paragraph 1d contained herein constitutes terminating action for this AD. Refer to Chapters 4 and 5 of the Sikorsky S-76 Maintenance Manual, SA 4047-76-2, for mandatory inspections. 2. Applies to main rotor blade spindles, P/N 76102-08001-041, with 200 or more hours time in service, compliance required within the next 5 hours time in service after July 12, 1980, unless already accomplished under the requirements of TAD T80NE-21. a. Remove and inspect the main rotor blade spindles for cracks in accordance with Sikorsky Alert Service Bulletin 76-65-13A, Paragraph G(6), dated April 24, 1980. b. If a crack indication is found, replace the main rotor blade spindle with a new or serviceable main rotor blade spindle, prior to next flight, in accordance with Sikorsky S-76 Maintenance Manual, SA 4047-76-2, Section 65-12-02. c. If nocrack indication is found, reinstall the main rotor blade spindle in accordance with the procedures in Paragraph 2.b of this AD. 3. Report within 24 hours any discrepancies found and the main rotor blade spindle times in service, to the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. Reporting approved by the Office of Management and Budget under OMB No. 04-R0174. 4. Aircraft may be ferried to a base for maintenance, except for aircraft found to have a missing spindle shear bearing inner race, in accordance with Section 21.197 of the Federal Aviation Regulations. NOTE: Sikorsky references noted herein pertain to this AD: a. Sikorsky Alert Service Bulletin 76-65-13A, dated April 24, 1980. b. Sikorsky S-76 Maintenance Manual, SA 4047-76-2, Section 65-12-O2. c. Sikorsky Service Bulletin 76-65-15, dated September 17, 1980. 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 Sikorsky Aircraft, Division of United Technologies Corporation, Stratford, Connecticut 06602. These documents may also be examined at FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, 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 FAA, New England Region Headquarters, Burlington, Massachusetts. Amendment 39-3837 became effective July 12, 1980, as to all persons except those persons to whom it was made immediately effective by the telegram dated April 24, 1980.This amendment 39-3941 becomes effective October 9, 1980.