Results
2005-15-10: The FAA adopts an airworthiness directive (AD) to supersede AD 2003-11-14, which applies to certain The New Piper Aircraft, Inc. (Piper) Models PA-34-200T, PA-34-220T, PA-44-180, and PA-44-180T airplanes that have a model 91E92-1 or model 91E93-1 combustion heater fuel pump installed. AD 2003-11-14 currently requires you to do a one- time inspection of the combustion heater fuel pumps for fuel leakage. If leakage is found, repair or replace the fuel pump. This AD retains all the actions of AD 2003-11-14 and includes additional serial numbers for the Models PA-34-220T and PA-44-180 airplanes in the applicability section. This AD results from an investigation that concluded that after the issuance of AD 2003-11-14, additional fuel pumps that did not meet the quality control (inspection or design) requirements of the AD had been installed in Models PA-34-220T and PA-44-180 airplanes. We are issuing this AD to correct quality control problems with the heater fuel pump, which couldresult in failure of the heater fuel pump. Such failure could lead to fire or explosion in the cockpit. DATES: This AD becomes effective on August 26, 2005. On June 20, 2003 (68 FR 33356, June 4, 2003), the Director of the Federal Register approved the incorporation by reference of The New Piper Aircraft, Inc. Service Bulletin No. 1127, dated February 26, 2003, and Kelly Aerospace Power Systems Service Information Letter Bulletin No. A-110A, dated March 6, 2003. As of August 26, 2005, the Director of the Federal Register approved the incorporation by reference of the following: --The New Piper Aircraft, Inc. Service Bulletin No. 1127B, dated April 18, 2005; and --Kelly Aerospace Power Systems Service Information Letter Bulletin No. A-110B, dated December 20, 2004. We must receive any comments on this AD by September 26, 2005.
2005-15-05: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A300-600 series airplanes. This AD requires an inspection for evidence of chafing between the hydraulic flexible hose and the ram air turbine (RAT) hub, and related investigative and corrective actions if necessary. This AD is prompted by reports of holes in the RAT hub cover. We are issuing this AD to prevent a hole in the RAT hub cover. A hole in the RAT hub cover could allow water to enter the RAT governing mechanism, freeze during flight, and jam the governing mechanism. In addition, the metal particles that result from chafing between the hydraulic flexible hose and the RAT could mix with the lubricant grease and degrade the governing mechanism. In an emergency, a jammed or degraded RAT could result in its failure to deploy, loss of hydraulic pressure or electrical power to the airplane, and consequent reduced controllability of the airplane.
75-25-01: 75-25-01 BEECH: Amendment 39-2442. Applies to Model 200 (Serial Numbers BB-2, BB-6 thru BB-76 and BB-78 thru BB-80) airplanes. Compliance: Required as indicated, unless already accomplished. To preclude shorting of the generator output leads at the air conditioner pulley housing and/or the oil line coupling nut, accomplish the following: A) Within the next 10 hours' time in service after the effective date of this AD, unless previously accomplished, visually inspect the generator output leads for chafing or discoloration in the area of the air conditioner compressor pulley housing and oil line coupling nut or for positive clearance of these components, in the engine compartment: 1) If chafing has occurred, prior to further flight, comply with Paragraph B. 2) If chafing has not occurred but positive clearance does not exist between the generator leads and the air conditioner pulley housing and the oil line coupling nut, reinspect every 25 hours' time in service until Paragraph B is accomplished. 3) If positive clearance exists between the generator leads and the air conditioner pulley housing and oil line coupling nut, reinspection is not required. B) Within the next 100 hours' time in service after the effective date of this AD or as required by Paragraph A, modify the generator lead routing in accordance with Beechcraft Service Instruction No. 0768-358/Kit No. 101-3011-1S or later approved revisions. Upon compliance with this Paragraph the inspections in Paragraph A are no longer required. C) Any alternate method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. D) Aircraft may be flown in accordance with FAR 21.197 to a place where the modification can be accomplished, if clearance or insulation is provided between the chafed portions of the generator leads and adjacent components. This amendment becomes effective December 1, 1975, to all persons except those to whom it was made effective earlier by air mail letter issued November 10, 1975.
2016-16-10: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes. This AD was prompted by reports of fatigue cracks in the station 320 crown frame and in window post number 3. This AD requires repetitive inspections for cracks and missing fasteners of the station 320 crown frame, cracks in the web and flange surfaces of the forward segment of window post number 3, and missing fasteners and cracks of the window upper sill; post-modification inspections for cracks of the window upper sill; a one-time fastener rework; and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct fatigue cracking and missing fasteners of the station 320 crown frame, cracking of the window post number 3, and cracking of the window upper sill, which could result in an in-flight decompression and a loss of structural integrity of the fuselage.
72-23-02: 72-23-02 ROLLS ROYCE (1971) LTD: Amendment 39-1547. Applies to Rolls Royce Dart Models 542-4, -4K, -10, -10J, and -10K engines. These engines are installed on, but not necessarily limited to, Convair 340/440 airplanes that have had subject engines installed by modification, and NAMC YS-11 and YS-11A airplanes, all series. (NOTE: Subject Convair 340/440 airplanes are also known as Convair 600 and 640 airplanes.) Compliance is required as indicated. To prevent damage to the rear face of the first stage impeller that could lead to impeller disintegration in service, accomplish the following: (a) Within the next 300 flights after the effective date of this AD, or before the accumulation of 2,000 flights on the compressor since installed new or since last compressor overhaul, as applicable, whichever occurs later, unless already accomplished, modify the oil drain plug, P/N RK.35189, and refit it to the engine in accordance with Rolls Royce Dart Aero Engine Service Bulletin Number DA 72-383, Revision 1, dated November 30, 1971, or an FAA-approved equivalent. Identify the modified drain plug as P/N RK. 46404. (b) Within the next 300 flights after incorporation of the modification specified by paragraph (a), and thereafter at intervals not to exceed 300 flights from the last inspection visually inspect the surfaces of the drain plug, P/N RK.46404, for the presence of aluminum particles. If aluminum particles are found during an inspection required by this paragraph, before further flight comply with paragraph (e). NOTE: During inspections required by paragraph (b) particular attention should be directed to the sealing ring recess. (c) For an engine that is subject to an FAA-approved continuous airworthiness maintenance program that includes periodic inspection for freedom of engine rotation and periodic inspection of the oil filter, comply with the following: (1) At each inspection for freedom of engine rotation, listen for unusualnoises from the compressor area; and (2) At each inspection of the oil filter, visually inspect the filter for traces of fine aluminum dust in the bottom of the filter cap or in suspension in the residual oil in the filter cap. (3) If any unusual noise emanates from the compressor area during an inspection required by subparagraph (c) (1) or if any trace of fine aluminum dust is found during an inspection required by subparagraph (c) (2), before further flight comply with paragraph (e). Change to an approved program that affect either the interval or performance of inspections required by this AD must be approved by the assigned FAA Maintenance Inspector. (d) For engines that are not subject to an FAA-approved continuous airworthiness maintenance program that includes periodic inspection for freedom of engine rotation and periodic inspection of the oil filter comply with the following: (1) At each inspection required by paragraph (b) - (i) Inspect thefirst stage impeller for freedom of rotation by rotating it at least one full turn in each direction, and listen for unusual noises from the compressor area. (ii) Visually inspect the oil filter for traces of fine aluminum dust in the bottom of the filter cap or in suspension in the residual oil in the filter cap. (2) If the first stage impeller does not rotate freely in each direction or if any unusual noise emanates from the compressor area during an inspection required by subparagraph (d)(1)(i), or if any trace of fine aluminum dust is found during an inspection required by subparagraph (d)(1)(ii), before further flight comply with paragraph (e). (e) Remove one combustion chamber and visually inspect the compressor outlet elbow, flame tube, discharge nozzle, H.P. nozzle guide vanes, and H.P. turbine blades for evidence of metal spatter and surface roughness or impact damage due to the passage of a foreign object. If any of these indications are found, before further flight rebuild the engine in accordance with Rolls Royce Dart Aero Engine Service Bulletin Da 72-383, Revision 1, dated November 30, 1971, or an FAA-approved equivalent. (f) For the purpose of complying with this AD, a flight is an operating sequence consisting of an engine start, takeoff operation, landing, and engine shutdown. The number of flights may be determined by actual count or, subject to acceptance by the assigned FAA Maintenance Inspector, may be calculated by dividing the compressor section's time in service by the operator's fleet average time for airplanes equipped with the subject type engines. (g) At the request of the operator, an FAA Maintenance Inspector, subject to prior approval of the Chief, Aircraft Certification Staff, FAA Europe, Africa, and Middle East Region, may adjust the 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. (h) The repetitive inspections required by this AD may be discontinued on engines that have been rebuilt in accordance with paragraph (e). This amendment supersedes Amendment 39-1381 (37 F.R. 666), AD 72-02-04. This amendment becomes effective October 26, 1972.
71-02-04: 71-02-04 BOEING: Amdt. 39-1146. Applies to all Boeing Model 747 Series airplanes. \n\tCompliance required within the next 300 hours' time in service after the effective date of this AD, unless already accomplished. \n\n\tTo prevent the failure of the load evener indicator tube resulting in passenger injury: \n\tReplace the existing body gear indicator tube cover with a new tube cover in accordance with Boeing Service Bulletin 32-2031, dated July 24, 1970, or later FAA approved revision, or an equivalent modification approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\tThis amendment becomes effective January 23, 1971.
2005-15-06: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-200C and 747-200F series airplanes. This AD requires one-time inspections for cracks and material loss in the fuselage skin above the stringer (STR) 23 lap splice, between Body Station (BS) 282 and BS 298, and repair if necessary. This AD is prompted by a report of a crack above the STR 23 lap splice on one airplane. We are issuing this AD to detect and correct cracks or material loss in the fuselage skin, and consequent reduced structural integrity of the skin panel, which could result in rapid depressurization of the airplane.
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.