Results
2005-04-14 R1: The FAA is revising an existing airworthiness directive (AD), which applies to certain Boeing Model 757-200, 757-200CB, and 757-200PF series airplanes. That AD currently requires repetitive inspections to detect horizontal or vertical movement of the shims at the joint of the mid-bulkhead and the upper link fittings; repetitive inspections for cracking of the mid-bulkhead; and corrective action if necessary. That AD also provides optional terminating action for the repetitive inspections. This AD continues to require the existing requirements and optional actions and clarifies certain terminating actions. This AD results from comments received in response to an existing AD, requesting clarification. We are issuing this AD to detect and correct migration of shims at the joint of the mid-bulkhead and the upper link fittings and cracking of the mid-bulkhead, which could result in cracking of the strut and consequent loss of the strut and engine. \n\nDATES: Effective March 15, 2005. \n\n\tOn March 15, 2005 (70 FR 9511, February 28, 2005), the Director of the Federal Register approved the incorporation by reference of Boeing Service Bulletin 757-54A0039, Revision 2, dated December 2, 2004; and Boeing Service Bulletin 757-54A0039, Revision 3, dated January 13, 2005. \n\n\tOn April 18, 2003 (68 FR 16200, April 3, 2003), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 757-54A0039, Revision 1, dated June 20, 2002. \n\n\tWe must receive any comments on this AD by October 11, 2005.
97-18-02: This amendment supersedes four existing airworthiness directives (ADs), applicable to Hartzell Propeller Inc. ( )HC-( )(2,3)(X,V)( )-( ) series propellers with aluminum blades, that currently require inspections for cracks in blade shanks and clamps. This amendment requires initial and repetitive dye penetrant and eddy current inspections of the blade and an optical comparator inspection of the blade retention area, and, if necessary, replacement with serviceable parts. In addition, this AD requires initial and repetitive visual and magnetic particle inspection of the blade clamp, dye penetrant inspection of the blade internal bearing bore, and, if necessary, replacement with serviceable parts. Also, for all HC-(1,4,5,8)(2,3)(X,V)( )-( ) steel hub propellers, this AD requires an additional initial and repetitive visual and magnetic particle inspection of the hub and, if necessary, replacement with serviceable parts. This amendment is prompted by reports of cracked blades,blade clamps, and hubs and reports of blade separations. The actions specified by this AD are intended to prevent blade separation due to cracked blades, hubs, or blade clamps, which can result in loss of control of the airplane.
2016-19-02: We are superseding Airworthiness Directive (AD) 2005-15-07 for certain Airbus Model A320-111 airplanes and Model A320-200 series airplanes. AD 2005-15-07 required installing insulator and cable ties to the electrical cables of the S routes at the gaps in the raceway in the wing trailing edge and the wing tip and wing root areas. This new AD requires additional modifications in the trailing edges of both wings. This new AD also removes airplanes from the applicability. This AD was prompted by reports of wire chafing in the left-hand wing trailing edge. We are issuing this AD to prevent wire chafing in the trailing edge of the wings, which could result in a short circuit in the vicinity of the fuel tanks, consequently resulting in a potential source of ignition in a fuel tank vapor space and consequent fuel tank explosion.
2016-19-01: We are adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F28 Mark 0070 and Mark 0100 airplanes. This AD was prompted by reports of cracking in a certain area of the pressure bulkhead webplate and skin connection angle. This AD requires a one-time inspection of the affected pressure bulkhead webplate and skin connection angle, and corrective actions if necessary. We are issuing this AD to detect and correct cracking of the pressure bulkhead webplate and skin connection angle that could lead to sudden inflight decompression of the airplane, resulting in injury to occupants.
2016-17-09: We are adopting a new airworthiness directive (AD) for all Bombardier, Inc. Model CL-600-2D15 (Regional Jet Series 705) and CL- 600-2D24 (Regional Jet Series 900) airplanes. This AD was prompted by two in-service incidents reported on Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) airplanes regarding a loss of all air data information in the flight deck. This AD requires revision of the airplane flight manual (AFM) to provide procedures to guide the crew to stabilize the airplane's airspeed and attitude for continued safe flight. We are issuing this AD to prevent loss of air data information that may affect continued safe flight.
2001-24-29: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires a one-time inspection for chafing between the hose for the passenger oxygen system (hereinafter called the "oxygen hose") and adjacent electrical wire bundles at certain passenger service units, and corrective actions, if necessary. This AD also requires rerouting or reorienting the oxygen hose to ensure sufficient clearance between the hose and electrical wire bundles. This action is necessary to prevent chafing between the oxygen hose and adjacent electrical wire bundles, which could result in arcing of a chafed electrical wire bundle and consequent burn-through of the oxygen hose. If this occurs when the oxygen system is pressurized, such arcing could represent a potential ignition source in an oxygen-enriched environment. This action is intended to address the identified unsafe condition.
71-04-04: 71-04-04 CANADAIR AIRCRAFT: Amdt. 39-1156. Applies to all CL-215-1A10 airplanes certificated in all categories. Compliance required as indicated. To prevent hazards in flight associated with fatigue failure of water door tension rod, P/N 215-26058-12, accomplish either (a) or (b): (a) Before further flight, replace water door tension rods, P/N 215-26058-12, which have accumulated a maximum of 700 water drops and at each 700 water drops thereafter, with unused parts of the same part number or with equivalent unused parts approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. For the purpose of this Airworthiness Directive, a water drop is defined as the operation of the water door mechanism with the tanks fully or partially filled, and does not include operations performed for checking the mechanism with the water tanks empty. (b) Before further flight, replace water door tension rods, P/N 215-26058-12, which have accumulated a maximum of 700 water drops, with water door tension rods P/N 215-26105-3 or with equivalent new parts approved by the Chief, Engineering & Manufacturing Branch, FAA Eastern Region. (c) The replacement schedule specified in (a) may be decreased by the Chief, Engineering & Manufacturing Branch, FAA Eastern Region, upon receipt of substantiating data submitted through an FAA Maintenance Inspector. This amendment is effective February 25, 1971.
2010-10-25: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: In the door 2 area, the hat-racks are supplied with a basic wire harness which includes "Oxygen Masks'' activation. In case of a monument installation, the respective non-used hat- rack connections between monument and outer skin are put on stow. It was noticed in production, that the distance between the stowed wire harness and the monument could be too small. This condition, if not corrected, could lead to the short circuit of wires dedicated to oxygen, which, in case of emergency, could result in a large number of passenger oxygen masks not being supplied with oxygen, possibly causing personal injuries. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2005-16-05: This amendment adopts a new airworthiness directive (AD) for the specified Robinson Helicopter Company (Robinson) Model R-22 series helicopters that have been modified in accordance with Supplemental Type Certificate (STC) No. SR09189RC. This action requires inspecting the left-hand door and right-hand door for a crack in the door assembly integral frame, and replacing the door assembly if a crack is found. This AD also requires inspecting each door assembly to determine if the weather seal set is airworthy and installed properly, inspecting each door hinge for the proper installation of a cotter pin, and thereafter, at intervals not to exceed 100 hours time-in-service (TIS), inspecting each door assembly integral frame for a crack. This amendment is prompted by one accident and one incident involving Robinson Model R-22 series helicopters. The actions specified in this AD are intended to prevent separation of a door window or door assembly from the helicopter, which could damage the tail rotor during flight and result in loss of control of the helicopter.
70-18-03: 70-18-03 PILATUS AIRCRAFT WORKS, LTD: Amdt. 39-1071. Applies to Model PC-6/B1-H2 airplanes, serial numbers up to and including 711; 2001, 2004 through 2010, and 2040. Compliance is required as indicated, unless already accomplished. (a) Within the next 25 hours' time in service after the effective date of this AD, revise the approved Airplane Flight Manual in accordance with Pilatus Service Bulletin No. 100, dated March 1970, or later Swiss Federal Air Office issue or an FAA-approved equivalent, to incorporate the Emergency Procedures to be followed in case of inadvertent propeller feathering. (b) For antireversing switches, P/N 973.10.11.101, with 975 or more hours' time in service on the effective date of this AD, within 25 hours' time in service from the effective date of this AD, and thereafter at intervals not to exceed 2,000 hours' time in service from the last replacement, replace the antireversing switch with a new switch of the same part number and readjust the antireversing and reversing system in accordance with Pilatus Service Bulletin No. 100, dated March 1970, or later Swiss Federal Air Office approved issue or an FAA-approved equivalent. (c) For antireversing switches, P/N 973.10.11.101, with less than 975 hours' time in service on the effective date of this AD, within the next 25 hours' time in service from the effective date of this AD perform the functional tests on the antireversing switch in accordance with Pilatus Service Bulletin No. 100, dated March 1970, or later Swiss Federal Air Office approved issue or an FAA-approved equivalent. If the switch does not malfunction, readjust the antireversing and reversing system in accordance with that service bulletin and thereafter comply with paragraph (d). If the switch malfunctions, comply with paragraph (c). (d) If the antireversing switch does not malfunction during the functional tests required by paragraph (c), before the accumulation of 1,000 hours' total time in service on theantireversing switch, and thereafter at intervals not to exceed 2,000 hours' time in service from the last replacement, replace the switch with a new switch of the same part number and readjust the antireversing and reversing system in accordance with Pilatus Service Bulletin No. 100, dated March 1970, or later Swiss Federal Air Office approved issue or an FAA-approved equivalent. (e) If the antireversing switch malfunctions during the functional tests required by paragraph (c), before further flight, and thereafter at intervals not to exceed 2,000 hours' time in service from the last replacement, replace the antireversing switch with a new switch of the same part number and readjust the antireversing and reversing system in accordance with Pilatus Service Bulletin No. 100, dated March 1970, or later Swiss Federal Air Office approved issue or an FAA-approved equivalent. This amendment becomes effective August 31, 1970.
2005-16-10: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-400 and 747-400D series airplanes. This AD requires an inspection for corrosion and cracks of the station 980 upper deck floor beam, and repair and related investigative actions if necessary. This AD results from reports of corrosion under the cart lift threshold at the station 980 upper deck floor beam. We are issuing this AD to detect and correct such corrosion, which could result in a cracked or broken floor beam, extensive damage to adjacent structure, and possible rapid decompression of the airplane.
87-01-01: 87-01-01 BOEING: Amendment 39-5493. Applies to the Model 757 series airplanes specified in Boeing Alert Service Bulletin 757-24A0032, dated May 16, 1986, certificated in any category. To minimize the fire hazard associated with overheating of the transformer rectifier unit of the auxiliary power unit starter motor, accomplish the following within 7 months after the effective date of this AD, unless previously accomplished: \n\n\tA.\tReplace the 50-ampere circuit breaker used for the auxiliary power unit starter transformer rectifier unit with a 35-ampere circuit breaker in accordance with Boeing Service Bulletin 757-24A0032, dated May 16, 1986, or later FAA-approved revision. \n\n\tB.\tAn 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, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197and 21.199 to operate airplanes to a base for the accomplishment of the modification required by this AD. \n\n\tAll persons affected by this directive who have not already received copies of the appropriate service document from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124-2207. 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. \n\n\tThis amendment becomes effective January 20, 1987.
75-22-21: 75-22-21 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: (S.N.I.A.S., formerly SUD AVIATION). Amendment 39-2393. Applies to Model SA316B Alouette III helicopters, certificated in all categories, incorporating main rotor transmission gearbox (MGB), Serial Number 9,999 or lower, P/N 3160S.62.00.000.10 through .12 incorporating Modification AM1212, or P/N 3160S.62.00.000.13 or .14. Compliance is required as indicated, unless already accomplished. To prevent possible failure of the main gearbox, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this AD, install a temporary operating limitations placard on the instrument panel in full view of the pilot reading as follows: "Operate in accordance with the limitations specified in the Alouette III SE.3160 Helicopter Flight Manual. Limitations or performance specified in Appendix 2 of that manual are not applicable to this helicopter." (b) Within the next 450 hours' time inservice after the effective date of this AD, replace the MGB with a serviceable MGB having a part number specified in Subparagraph 1C of Alouette Service Bulletin No. 01.34 dated June 24, 1974, or an FAA-approved equivalent. (c) After complying with paragraph (b) of this AD, the placard required by paragraph (a) may be removed. This amendment becomes effective October 30, 1975.
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.
2005-15-07: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A320-111 airplanes and Model A320-200 series airplanes. This AD requires installing insulator and cable ties to the electrical cables of the S routes at the gaps in the raceway in the wing trailing edge and the wing tip and wing root areas. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent injection of high voltage current into the low voltage wiring that passes through the fuel tanks, which could result in a possible fuel tank explosion.
88-05-07: 88-05-07 BOEING: Amendment 39-5867. Applies to Model 747 series airplanes, as listed in Boeing Service Bulletin 747-49-2051, dated November 5, 1987, certificated in any category. \n\tCompliance required as indicated, unless previously accomplished. \n\n\tTo eliminate the potential for a fire due to fuel leaking from the auxiliary power unit (APU) drain system, accomplish the following: \n\n\tA.\tWithin the next 30 days after the effective date of this AD, and at intervals not to exceed 30 days thereafter, inspect the APU fuel supply line for fuel leaks, in accordance with Boeing Model 747 Maintenance Manual Section 28-25-00, page 601, dated August 25, 1987, or later FAA-approved revision. If leakage is detected, repair in accordance with the Maintenance Manual, before further flight. \n\n\tB.\tModification of the APU fuel line drain system, fuel pump drain, and turbine drain assembly, in accordance with Boeing Service Bulletin 747-49-2051, dated November 5, 1987, or later FAA-approvedrevision, constitutes terminating action for the repetitive inspection requirement of paragraph A., above. \n\n\tC.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety and which has the concurrence of an FAA Principal Maintenance Inspector, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tD.\tSpecial 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. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. This information may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective March 25, 1988.