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84-18-05: 84-18-05 FOKKER VFW B.V.: Amendment 39-4911. Applies to all Model F27 Series airplanes, serial numbers 10102 to 10611, inclusive, that are equipped with pylon tanks and the maximum certificated takeoff weight is above 41,000 pounds, certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent wing structural failure, accomplish one of the following (A, B, or C): A. Within the next 100 hours time in service after the effective date of this airworthiness directive (AD): 1. Remove the existing airspeed limitation placards and install new placards in accordance with paragraph 2.A and 2.B of the Accomplishment Instructions of Fokker Service Bulletin No. 11/3 dated October 1, 1981. 2. Incorporate changes to the FAA approved Airplane Flight Manual in accordance with paragraphs 1.C and 3 of Fokker Service Bulletin No. 11/3 dated October 1, 1981. 3. Modify the airspeed indicators and overspeed aural warning system to provide a switchable maximum operating speed (VMO) that allows selecting a VMO of 204 knots I.A.S. for operation when the maximum takeoff weight exceeds 41,000 pounds, in a manner approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. B. Within the next 100 hours time in service after the effective date of this AD, modify as follows: 1. Revise the redline marking of the airspeed indicator or replace the airspeed indicator to reflect the new maximum airspeed limitation of 204 knots I.A.S. 2. Post a placard on the left and right hand instrument panel to read as follows: "MAXIMUM AIRSPEED, 204 KIAS." 3. Adjust the overspeed aural warning device or install a new device so as to comply with the new maximum airspeed limitation; i.e., 204 knots I.A.S., within the tolerances specified by FAR 25.1303(c)(1). C. Apply for and obtain a supplement to the Airplane Flight Manual which will provide for an operating limitation of 41,000 pounds takeoff weight. Applications may be made to the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. D. Alternate means of compliance which provide an equivalent 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 modifications required by this AD. This amendment becomes effective October 15, 1984.
87-03-03: 87-03-03 BRITISH AEROSPACE: Amendment 39-5504. Applies to Model 3101 Jetstream (S/N 642 to 646, 648 to 655, 657, 658 and 660 to 666 inclusive) airplanes certificated in any category. Compliance: Required within 600 hours time-in-service (TIS) after the effective date of this AD, unless already accomplished. To ensure operation of fuel/hydraulic and water methanol system valves during critical flight operations, accomplish the following: (a) Modify the HiTemp Valves Part Number (P/N) HTE 4925-001 as follows: (1) Gain access to the valves in accordance with Section 2. "ACCOMPLISHMENT INSTRUCTIONS", paragraph A PREPARATION", in British Aerospace (BAe) S/B 28-JA850911 dated June 13, 1986. (2) Replace valve spindles P/N 4925-005 with strengthened spindles P/N 4925-013 in HiTemp Model HTE 1" Actuated Ball Valves in accordance with Section 2. "ACCOMPLISHMENT INSTRUCTIONS" in HiTemp SB HTE 4925/1-SB-1 dated August 19, 1985, on those valves located as follows:(i) Fuel system - left and right LP cocks at wing leading edges outboard of the engines, and crossfeed cock on fuselage center section. (ii) Hydraulic System - left and right LP cocks in the hydraulic installations below fuselage center section. (iii) Water Methanol System (if fitted) - stop valves in the left and right main landing gear bays. (3) Carry out functional tests of the valves in accordance with Section 2. "ACCOMPLISHMENT INSTRUCTIONS", paragraph B "ACCOMPLISHMENT", in BAe S/B 28-JA850911 dated June 13, 1986. (b) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. (c) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, B-1000, Brussels, Belgium. All persons affected by this directive may obtain a copy of the document referredto herein upon request to British Aerospace plc, Manager, Product Support Civil Aircraft Division, Prestwick Airport, Ayrshire, KA9 2RW, Scotland; or British Aerospace, Inc., Librarian, Box 17414, Dulles International Airport, Washington, D.C. 20041; or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on February 17, 1987.
2005-13-22: The FAA is superseding an existing airworthiness directive (AD) that applies to all EMBRAER Model EMB-135 and -145 airplanes. The existing AD currently requires repetitive inspections of the electrical connectors of the electric fuel pumps to detect discrepancies, application of anti-corrosion spray, replacement of all fuel pumps with improved fuel pumps, repetitive inspections after all six fuel pumps are replaced, and applicable corrective actions. This new AD retains those requirements but revises the initial compliance time for an inspection for certain airplanes. This new AD is prompted by the need to correct a compliance time in the existing AD. We are issuing this AD to prevent an ignition source in the fuel tank or adjacent dry bay, which could result in fire or explosion. DATES: Effective July 7, 2005. On May 19, 2005 (70 FR 19685, April 14, 2005), the Director of the Federal Register approved the incorporation by reference of EMBRAER Service Bulletin 145-28-0013, dated April 25, 2001. On October 3, 2000 (65 FR 56233, September 18, 2000), the Director of the Federal Register approved the incorporation by reference of EMBRAER Alert Service Bulletin S.B. 145-28-A013, dated August 16, 2000. We must receive any comments on this AD by August 22, 2005.
2005-15-02: The FAA is adopting a new airworthiness directive (AD) that applies to certain Airbus Model A320-111 airplanes and Model A320-200 series airplanes. This AD requires post-maintenance bleeding of accumulated air from, or ground functional testing of, the ram air turbine (RAT) system; modifying and reidentifying the airborne ground check module of the RAT system; and replacing the RAT reducer assembly if applicable. This AD is prompted by reports of unsuccessful in-flight RAT tests during which a deployed RAT failed to pressurize the blue hydraulic circuit of the RAT system. We are issuing this AD to prevent failure of the RAT during an in-flight emergency, which could lead to loss of hydraulic and electrical power and reduced controllability of the airplane.
2016-14-01: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200 Freighter series airplanes; Model A330-200 and A330-300 series airplanes; Model A340-200 and A340-300 series airplanes; Model A340-500 series airplanes; and Model A340-600 series airplanes. This AD was prompted by a report indicating that, during an operational test of a ram air turbine (RAT), the RAT did not deploy in automatic mode. This AD requires identification of the manufacturer, part number, and serial number of the RAT, and re-identification and modification of the RAT if necessary. We are issuing this AD to prevent non-deployment of the RAT, which, if preceded by a total engine flame- out, or during a total loss of normal electrical power generation, could result in reduced control of the airplane.
71-21-07: 71-21-07 de HAVILLAND: Amendment 39-1310. Applies to de Havilland Model DHC- 6 Airplanes, Serial Numbers 6 through 289 certificated in all categories and incorporating Flitetronic Type PC 15 or PC 15A Inverters. Compliance required within the next 250 hours' time in service after the effective date of this AD unless already accomplished. To prevent a total loss of AC power in the event of a fault occurring in an AC circuit, accomplish the following: (a) Comply with Accomplishment Instructions 1 and 2 (a) through 2(e) of de Havilland Service Bulletin No. 6/263 dated 5 October 1970, Revision B dated 29 January 1971. (b) Remove slow-blow fuses not replaced in (a) and replace with: (1) Littlefuse type 312 of the same rating for the 26-volt supply except that ratings greater than 2 amps shall be replaced with Littlefuse 312002. (2) Littlefuse type 312 or Bussman type MB of the same rating for the 115 Volt supply, except that ratings greater than 1 amp shallbe replaced with Littlefuse 312001 or Bussman MB01. (c) Comply with Accomplishment Instructions 3 through 6 of de Havilland Service Bulletin No. 6/263 dated 5 October 1970, Revision B dated 29 January 1971 for PC 15 and PC 15A inverter without a suffix letter after the serial number. Inverters which do not meet the requirements of the overload function test must be replaced, prior to further flight, with an inverter with a suffix letter after the serial number. Equivalent methods may be used provided they are approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. Upon request with substantiation data submitted through an FAA maintenance inspector, the compliance time specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment is effective October 12, 1971.
89-18-05: 89-18-05 BRITISH AEROSPACE: Amendment 39-6298. (Docket No. 89-NM-53-AD) Applicability: Model BAC 1-11 200 and 400 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent uncommanded thrust reverser selection, accomplish the following: A. Prior to the accumulation of 1,500 landings or within 3 months after the effective date of this AD, whichever occurs first, inspect the thrust reverser cables to determine correct installation, in accordance with British Aerospace Alert Service Bulletin 76-A-PM5978, Issue No. 1, dated November 14, 1988. B. If thrust reverser cables are found to be worn or damaged, or if cables are found to be incorrectly routed, replace prior to further flight, in accordance with the maintenance manual referenced in British Aerospace Alert Service Bulletin 76-A-PM5978, Issue No. 1, dated November 14, 1988. 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, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it 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 documents from the manufacturer may obtain copies upon request to British Aerospace, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6298, AD 89-18-05) becomes effective on September 21, 1989.
74-21-04: 74-21-04 HUGHES HELICOPTERS: Amendment 39-1987 as amended by Amendment 39-2147. Applies to Hughes 269A, 269A-1, 269B, 269C Helicopters certificated in all categories, including military TH-55A equipped with canopy slat P/N 269A2297 or 269A2297-7. Compliance required as indicated. To detect possible cracks in canopy slat surfaces, and the condition and security of slat attachment hardware and canopy attachment areas, and provide for modification of the canopy slat, accomplish the following: (a) On each day the helicopter is flown, conduct a close visual check by the pilot in command or an inspection by a certificated mechanic of the canopy slat surfaces over the entire length for cracks, slat attachment hardware and canopy attachment areas for condition and security. Note: The person who performs the check or inspection shall record it in the appropriate aircraft records per FAR 91.173. (1) If cracks or other damage are found, replace prior to further flight with: (i) P/N 269A2297 or 269A2297-7 modified in accordance with (b), below; or (ii) P/N 269A2214; or (iii) If the 50 hour limitation specified by (b), below, has not been exceeded, an unmodified part P/N 269A2297 or 269A2297-7 may be used, provided, it is modified at the time specified by (b), below; or (iv) A part approved by Chief, Aircraft Engineering Division, FAA Western Region. (b) Prior to the next 50 hours time in service after the effective date of this amendment, 39-2147, unless already accomplished, modify the canopy slat, P/N 269A2297 or 269A2297-7, in accordance with the instructions contained in Hughes Service Information Notice N-127, dated March 5, 1975, or later FAA-approved revisions, or equivalent procedure approved by the Chief, Aircraft Engineering Division, FAA Western Region. (c) Upon installation of P/N 269A2297 or 269A2297-7 modified in accordance with (b), above, or P/N 269A2214 or other part approved by the Chief, AircraftEngineering Division, FAA Western Region, the daily visual check or inspection in accordance with (a) above may be discontinued. Amendment 39-1987, was effective October 16, 1974, for all persons except those to whom it was made effective immediately by airmail letter dated September 23, 1974. This Amendment 39-2147, to AD 74-21-04 becomes effective April 4, 1975.
70-01-02: 70-01-02 CESSNA: Amdt. 39-906. Applies to Models 177 and 177A, Serial Numbers 177- 00001 thru 177-01160, 177-01165 thru 177-01168, 177-01171, 177-01174 thru 177-01178 and 177-01180, airplanes. Compliance: Required as indicated, unless already accomplished. To prevent possible damage to the fuel quantity transmitter float arm during refueling, which can result in inaccurate quantity indication, accomplish the following: Within 50 hours' time in service after the effective date of this AD but no later than March 1, 1970, remove the fuel quantity transmitter from each fuel tank and install new Cessna P/N 12341-667-1 and 12341-667-2 fuel gauge transmitters in accordance with the instructions contained in Cessna Service Letter No. SE69-25. dated December 9, 1969, or any other method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective January 3, 1970.
2005-14-12: The FAA is adopting a new airworthiness directive (AD) for Hartzell Propeller Inc. models HC-B3TN-2, HC-B3TN-3, HC-B3TN-5, HC- B3MN-3, HC-B4TN-3, HC-B4TN-5, HC-B4MN-5, HC-B4MP-3, HC-B4MP-5, and HC- B5MP-3 propellers, installed with propeller mounting bolts, part number (P/N) B-3339. This AD requires initial and repetitive visual inspections and torque checks of certain manufacture lot numbers of propeller mounting bolts, P/N B-3339, and eventual removal from service of those bolts. This AD results from the discovery during routine propeller installation that a bolt from a certain manufacture lot did not properly absorb the installation torque. This AD also results from the discovery that other bolts of the same part number from a different manufacture lot had material surface pitting. We are issuing this AD to prevent propeller attaching bolt failures or improperly secured propellers, which could lead to separation of the propeller from the airplane.