Results
2005-16-07: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 727 airplanes. This AD requires determining whether any float switches are installed in the fuel tanks, and corrective actions if necessary. This AD results from reports of contamination of the fueling float switch by moisture or fuel, and chafing of the float switch wiring against the fuel tank conduit. We are issuing this AD to prevent such contamination and chafing, which could present an ignition source inside the fuel tank that could cause a fire or explosion.
2001-24-12: This amendment supersedes an emergency airworthiness directive (AD) that was sent previously to all known U.S. owners and operators of Rolls-Royce Corporation (formerly Allison Engine Company) models 250-C20, -C20B, -C20F, -C20R, -C20R/1, -C20R/2, -C20S, and -C20W turboshaft engines, and 250-B17, -B17C, -B17D, -B17E, -B17F, -B17F/1, and -B17F/2 turboprop engines by individual letters. That action required replacement of any helical torquemeter gearshaft assembly with 100 hours or less time-since-new (TSN) with a serviceable helical torquemeter gearshaft assembly, before further flight. That amendment was prompted by a report of uncontained release of power turbine blades and disk fragments caused by engine overspeed, resulting in an uncommanded engine shutdown, engine fire, and damage to the aircraft. This amendment requires the same replacement, and adds engine model -250-C20J to the applicability section of this AD. The actions specified by this AD are intended to prevent uncontained release of power turbine blades and disk fragments caused by engine overspeed, resulting in an uncommanded engine shutdown, engine fire, and damage to the aircraft.
83-22-09: 83-22-09 BRITISH AEROSPACE AIRCRAFT GROUP (HATFIELD-CHESTER DIVISION): Amendment 39-4754. Applies to Model HS 125 (pre-Modification 251600) with serial numbers listed in the Planning Information of the service bulletin. Compliance required as indicated, unless already accomplished. To protect the main engine beam from a burst failure of the cold air unit fan, accomplish the following: A. Install a fragmentation guard around the fan housing of the cold air unit in accordance with the Accomplishment Instructions of British Aerospace Aircraft Group, Hatfield- Chester Division, 125 Series Aircraft Service Bulletin 21-123-(2815), Revision 2, dated October 29, 1982, within 120 days after the effective date of this AD. B. 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. 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 inspections and/or modifications required by this AD. This amendment becomes effective December 1, 1983.
2005-16-01: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-200B, 747-300, 747-400, and 747-400D series airplanes. This AD requires modifying the lateral shear beam for the Door 5 crew rest and, for certain airplanes, replacing Zone E tie rods and modifying the Zone E stowbin ladder. This AD results from a report indicating that the lateral shear beam for the Door 5 crew rest does not meet the 9G forward loading requirement. We are issuing this AD to prevent the structural support for the Door 5 crew rest and Zone E stowbins from failing, which could result in the crew rest or stowbins falling during an emergency and consequent injury to crew and passengers.
97-17-02: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 777-200 series airplanes. This action requires repetitive torquing of the bushing retainer nuts of the pivot pins in the horizontal stabilizer hinge assembly to tighten loose nuts to the new torque value; and repetitive visual inspections, if necessary, to detect bushing migration or damage to adjacent structures, and repair of any damage. This proposal also provides for an optional terminating action for the repetitive inspections. This amendment is prompted by a report of a loose bushing retainer nut, which may be attributed to low nut torque. The actions specified in this AD are intended to detect and correct loose bushing retainer nuts of the pivot pins in the horizontal stabilizer hinge assembly, which could result in bushing migration and consequent damage to the adjacent structure, and reduced controllability of the airplane.
97-16-10: 97-16-10 RAPCO, Inc.: Priority Letter issued on July 31, 1997. Docket No. 97-CE-71-AD. Applicability: Filter Part Numbers (P/N) RA-1J4-4, RA-1J4-6, and RA-1J4-7 (Lot Numbers 05597, 07797, and 12597) installed on but not limited to the following airplanes, certificated in any category: Cessna Aircraft Company (Cessna) Models 310R and T310R Airplanes; Raytheon Aircraft Company (Raytheon) (formerly known as Beech Aircraft Corporation) Models E33A, F33A, V35A, V35B, 36, A36, 58, 65-B80, 70, 95-B55, D55, E55 Airplanes; and, The New Piper Aircraft, Inc. (Piper) Models PA-31-300, PA-31-325, PA-31P, PA-31P-350, PA-31T, PA-34-200T Airplanes. NOTE 1: This AD applies to each airplane with one or more of these filters installed that is identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (d) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required within the next 2 days after the receipt of this priority letter AD or prior to further flight, whichever occurs later, unless already accomplished. To prevent failure of the flight instruments during flight because of a failed in-line pressure filter, which could cause loss of control of the airplane, accomplish the following: (a) Remove any filter with an applicable part number and lot number and replace with an FAA-approved filter that incorporates a part number (P/N) and lot number not covered by thisAD. (b) Upon the effective date of this AD, no person may equip an aircraft with any RAPCO filters marked with P/N RA-1J4-4, RA-1J4-6, or RA-1J4-7 from Lot Numbers 05597, 07797, or 12597. NOTE 2: Production of the affected filters has ceased. The affected lots were produced in February 1997, and a check of the aircraft records will give a good indication as to whether these filters have been installed on an aircraft. (c) Special flight permits may be issued for daytime visual flight rules (VFR) flight only, in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location to accomplish the requirement of this AD. (d) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Chicago Aircraft Certification Office, 2300 E. Devon, Des Plaines, Illinois 60018. The request shall be forwarded through anappropriate FAA Maintenance Inspector, who may concur or comment and then send it to the Manager, Chicago Aircraft Certification Office. NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Chicago Aircraft Certification Office. (e) Information related to this AD may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. (f) Priority Letter AD 97-16-10, issued July 31, 1997, becomes effective immediately upon receipt.
83-23-04: 83-23-04 GENERAL DYNAMICS (Convair): Amendment 39-4772. Applies to General Dynamics (Convair) Models 240-27 converted from T-29B and 240-52 converted from T29D aircraft for civil passenger or cargo use by Hamilton Aviation Company STC SA4025WE or SA4026WE, certificated in all categories. Compliance is required within 30 days or 100 hours time in service, whichever occurs first, after the effective date of this AD, unless already accomplished. To prevent undetected failure of the door open warning system, accomplish the following: A. Install the secondary lock warning switch on the main entrance door and connect it in series with the other two main entrance door open warning switches in accordance with Hamilton Aviation Company Drawing 3623015, Revision D, or Convair Drawing No. 240- 0067361, Change G of Sheet 2, dated 9/18/53. B. Reconfigure the 28 volts DC and ground circuits associated with the aft cargo door open warning switch, the door open warning relay, the lower forward compartment door open warning switch, and the main entry door warning switches in accordance with Hamilton Aviation Company Drawing No. 3623015, Revision D, or Convair Drawing No. 240-0067361, Change G of Sheet 2, dated 9/18/53. C. Perform a functional check of door open warning system as follows: 1. Inspect and check main entrance door (MED) primary lock door open warning switch. 2. Inspect and check MED secondary lock door open warning switch. 3. Check all door open warning light circuitry for proper operation. D. 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 inspections required by this AD. E. Alternative inspections, modifications, or other actions which provide an equivalent level of safety may be used when approved by the Manager, Western Aircraft Certification Office, FAA, Northwest Mountain Region, Hawthorne, California. All persons affected by this directive who have not already received these documents may obtain copies upon request to General Dynamics, Convair Division, P.O. Box 80877, San Diego, California 92138, Attn: Larry Hayes, Manager, Product Support; and Hamilton Aviation Company, Attn: Gordon Hamilton, P.O. Box 11746, Tucson, Arizona 85734. These documents also may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington. This amendment becomes effective November 28, 1983.
2005-15-15: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 757-200, -200PF, and -200CB series airplanes. This AD requires inspecting to determine the part number of the upper link forward fuse pins of the engine struts and replacing the fuse pins as necessary. This AD is prompted by a report indicating that, due to an incorrect listing in the illustrated parts catalog, persons performing maintenance on the engine strut(s) could have installed an incorrect upper link forward fuse pin. We are issuing this AD to prevent a ruptured wing box, due to the engine not separating safely during certain emergency landing conditions, which could lead to a fuel spill and consequent fire.
83-14-04: 83-14-04 CESSNA: Amendment 39-4684. Applies to all Model 172RG airplanes certificated in any category. Compliance: Required as indicated, unless already accomplished. To reduce the possibility of carbon monoxide contamination entering the cabin area, accomplish the following: a) Within the next 25 hours time-in-service after the effective date of this AD. 1) Modify the cabin heater shroud in accordance with Cessna Service Letter SE83-13 dated May 27, 1983. Additionally, prior to reinstallation of the cabin heater shroud, visually inspect the flanges on the outer diameter of the ends of the muffler for cracks and repair or replace any cracked components. 2) Within 50 hours time-in-service after the modification required by paragraph a)1) of this AD and each 50 hours time-in-service thereafter, visually inspect the shroud for security and proper location and the flanges on the outer diameter of the ends of the muffler for cracks and prior to further flight, repair or replace any cracked components. Removal of the shroud for this inspection is not required. 3) Reinspect any repaired component within 25 hours time-in-service after the repair and, if defective, repair or replace. If no defects are found, continue inspection of this component in accordance with paragraph a)2) of this AD. b) As an alternative to complying with paragraph a) of this AD, deactivate the cabin heat system by removing the cabin heat control cable from the control arm on the cabin heat valve located on the firewall at the right upper side of the engine compartment. Ensure that the valve spring mechanism is functioning and that the cabin heat valve is spring loaded to the closed position or safety wire the valve to the closed position. c) The airplane may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. This amendment supersedes AD 81-05-05 R1, Amendments 39-4075 and 39-4332. This Amendment 39-4684 becomes effective on July 20, 1983.
75-26-01: 75-26-01 BRITTEN NORMAN, LTD: Amendment 39-2453. Applies to BN-2A airplanes, all series, certificated in all categories. Compliance is required as indicated. To prevent possible failure of the rudder top, center, and bottom hinge brackets with consequent loss of rudder control, accomplish the following: (a) This paragraph applies to BN-2A airplanes that have not been altered in accordance with both Britten Norman Modifications NB/M/705 and NB/M/777. (1) Within the next 50 hours' time in service after the effective date of this AD, unless already accomplished within the last 50 hours' time in service, inspect the rudder top, center, and bottom hinge structures for cracks in accordance with Part A and Part B of the section entitled "Inspection" of Britten Norman Service Bulletin No. BN-2/SB.76, Issue 4, dated February 4, 1975, or an FAA-approved equivalent. (2) Repeat the inspection required by sub-paragraph (a)(1) of this AD at intervals not to exceed 100hours' time in service from the last inspection until the action required by sub-paragraph (a)(4) of this AD is accomplished, at which time the inspection interval may be increased to 500 hours. (3) If cracks are found in any of the bearing mounting plates as a result of the initial inspection required by sub-paragraph (a)(1) of this AD or any of the 100 hour repetitive inspections required by sub-paragraph (a)(2) of this AD, before further flight, either - (i) Replace the cracked mounting plates with new or serviceable plates of the same part number, or FAA-approved equivalent parts, and continue to inspect in accordance with the provisions of sub-paragraph (a)(2) of this AD; or (ii) Alter the rudder hinge areas in accordance with Part A and Part B of the section entitled "Rectification" of Britten Norman Service Bulletin No. BN-2/SB.76, Issue 4, dated February 4, 1975, or an FAA-approved equivalent, following which inspect the hinge structure at intervals not toexceed 500 hours' time in service from the last inspection. (4) Within 500 hours' time in service after the accomplishment of the inspection required by sub-paragraph (a)(1) of this AD, alter the rudder hinge areas in accordance with Part A and Part B of the Section entitled "Rectification" of Britten Norman Service Bulletin No. BN-2/SB.76, Issue 4, dated February 4, 1975, or an FAA-approved equivalent. (b) This paragraph applies to BN-2A airplanes that have been altered in accordance with both Britten Norman Modifications NB/M/705 and NB/M/777. (1) Within 500 hours' time in service after the accomplishment of both modifications NB/M/705 and NB/M/777, or within 25 hours' time in service after the effective date this AD, whichever occurs later, inspect the rudder top, center, and bottom hinge structures for cracks in accordance with Part A and Part B of the section entitled "Inspection" of Britten Norman Service Bulletin No. BN-2/SB.76, Issue 4, dated February 4, 1975,or an FAA-approved equivalent. (2) Repeat the inspection required by sub-paragraph (b)(1) of this AD at intervals not to exceed 500 hours time in service from the last inspection. (3) If cracks are found in any of the bearing mounting plates as a result of the inspections required by sub-paragraphs (b)(1) or (b)(2) of this AD, before further flight, replace the cracked mounting plates with new or serviceable plates of the same part number or FAA-approved equivalent parts and continue to inspect the rudder hinge structures at intervals not to exceed 500 hours' time in service from the last inspection. This amendment becomes effective December 23, 1975.