Results
2010-21-18: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires inspecting the wings for internal and external damage, repairing any damage found, installing an operational limitation placard in the cockpit, adding limitations to the flight manual supplement, and reporting the results of the inspection to the FAA if damage is found. This AD was prompted by a wing overload failure and by reports of cracks in the upper wing skins on certain Cessna airplanes that are or have ever been modified by Aviation Enterprises Supplemental Type Certificate (STC) SA02055AT, SA02056AT, SA02307AT, or SA02308AT. We are issuing this AD to detect and correct damage in the wings and to prevent overload failure of the wing due to the installation of the STCs. Damage in the wing or overload failure of the wing could result in structural failure of the wing, which could result in loss of control.
2001-07-11: This amendment adopts a new airworthiness directive (AD) that is applicable to all Learjet Model 23, 24, 25, 28, 29, 31, 35, 36, and 55 series airplanes. This action requires an inspection to determine if tires on the main landing gear have a certain part number and certain serial numbers, and replacement with a tire having a part number that does not contain those certain serial numbers, if necessary. This action is necessary to prevent separation of the tread of main landing gear tires, which could cause damage to the structure and major systems of the airplane, and consequent reduced controllability of the airplane on the ground during takeoff and landing. This action is intended to address the identified unsafe condition.
2016-11-17: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 airplanes. This AD was prompted by a report of wire chafing caused by a left wing spoiler actuator wire not having enough separation from a certain bracket when the spoiler is in the deployed position. This AD requires measuring the separation between a certain electro-mechanical actuator wire of the left wing, spoiler 4, and the support bracket of the flap variable camber trim unit; and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct wire chafing. Such chafing could result in an electrical short and potential fire in a flammable fluid leakage zone and possible loss of several functions essential for safe flight.
2001-07-07: This amendment supersedes an existing airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 0070 and Mark 0100 series airplanes, that currently requires revising the Airplane Flight Manual (AFM) to provide the flightcrew with instructions not to arm the liftdumper system prior to commanding the landing gear to extend. For Model F.28 Mark 0100 series airplanes, the existing AD also requires modification of the grounds of the shielding of the wheelspeed sensor wiring of the main landing gear (MLG) and installation of new electrical grounds for the wheelspeed sensor channel of the anti-skid control box of the MLG. This amendment removes the previous revision of the AFM and requires a new limitation and a new warning. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent inadvertent deployment of the liftdumpers during approach for landing or reduced brake pressure during low speed taxiing, and consequent reduced controllability and performance of the airplane.
2001-07-08: This amendment adopts a new airworthiness directive (AD) that is applicable to all McDonnell Douglas Model MD-11 series airplanes equipped with Pratt & Whitney Model PW4400 series engines. This action requires revising the Airplane Flight Manual (AFM) to advise the flight crew of applicable operational limits. This action is necessary to ensure that the flight crew is informed of applicable limitations in airplane performance, and to prevent reduced acceleration and climb performance relative to performance data in the AFM, which could result in the airplane overrunning the end of the runway during takeoff or landing, or impacting obstacles or terrain. This action is intended to address the identified unsafe condition.
93-01-10: 93-01-10 BRITISH AEROSPACE: Amendment 39-8464. Docket 92-NM-90-AD. Applicability: Model DH/HS/BAe 125 series airplanes equipped with Garrett engines; as listed in British Aerospace Service Bulletin SB.24-289-3267A,B,C,D,E, F & G, Revision 1, dated April 10, 1992; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent battery overheating and/or damage of voltage sensitive avionics equipment, accomplish the following: (a) Within 180 days after the effective date of this AD, modify the Generator Control Circuit (GCU) circuitry in accordance with British Aerospace Service Bulletin SB.24-289-3267A,B,C,D,E,F & G, Revision 1, dated April 10, 1992. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The modification shall be done in accordance with British Aerospace Service Bulletin SB.24-289-3267A,B,C,D,E,F & G, Revision 1, dated April 10, 1992. (NOTE: The issue date of this British Aerospace Service Bulletin SB.24-289-326-7A,B,C,D,E,F & G is indicated only on "page 1 of 57"; no other page of this document is dated.) This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, DC. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on March 2, 1993.
47-10-22: 47-10-22 LOCKHEED: (Was Mandatory Note 24 of AD-763-3.) Applies to Model 49 Serials 1975, 1976, 1977, and 2021 Through 2065. Compliance required prior to March 1, 1947. Install steel retainer washer (American LaFranch P/N 2CD-3054C) in place of existing aluminum alloy retainer washer on fire extinguisher selector valve. (LAC Service Bulletin 49/SB-27 covers this same subject.)
2016-11-21: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model EC135P1, EC135P2, EC135P2+, EC135T1, EC135T2, and EC135T2+ helicopters. This AD requires reducing the life limit of certain parts and removing each part that has reached its life limit. The actions of this AD are intended to reduce the life limits of certain critical parts to prevent failure of a part and subsequent loss of control of the helicopter.
2001-07-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes powered by General Electric or Pratt & Whitney engines, that requires repetitive inspections to detect discrepancies of the aft-most fastener holes in the horizontal tangs of the midspar fitting of the strut, and corrective actions, if necessary. This AD also provides an optional terminating action for the repetitive inspections. These actions are necessary to prevent fatigue cracking in primary strut structure and reduced structural integrity of the strut, which could result in separation of the strut and engine. This action is intended to address the identified unsafe condition.
68-01-01 R1: 68-01-01 R1 BRITISH AEROSPACE: Amendment 39-998 as amended by Amendment 39-5956. Applies to Model BAC 1-11 200 and 400 series airplanes. Compliance required within the next 50 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent heat damage or fire in the airframe plenum of the auxiliary power unit (APU) installation, accomplish the following: A. For use of the APU on the ground, accomplish the following: 1. Visually check the fiberglass surround of the APU intake of the fuselage immediately behind the intake grill for evidence of heat discoloration. If evidence of heat is present, remove the non-return valve located in the APU air delivery duct, Part No. 525180, and replace with a serviceable Part No. 525180 or modified Part No. 1398B000, 1398B000/1398B999, or 3031B000. 2. Install a placard adjacent to the APU control panel in clear view of the pilot and amend the airplane flight manual limitations Section 2,to read as follows: "Close APU air delivery valve when starting an engine from an external supply or by cross-feeding air from an operating engine. Close APU air delivery valve and shut down APU for takeoff and flight operations." When all actions required by paragraph B., below, are accomplished, the placard may be removed or the foregoing amendment to the airplane flight manual should be deleted, as appropriate. 3. Remove all APU plenum chamber sound proofing. B. For operational use of the APU in flight, accomplish the following: 1. Remove non-return valve, Part No. 525180, located in the APU air delivery duct and replace with non-return valve, Part No. 1398B000, 1398B000/1398B999, or 3031B000, in accordance with British Aerospace BAC 1-11 Service Bulletins 36-PM3254 or 36-PM4912. 2. Perform the following modifications in accordance with British Aerospace BAC 1-11 Service Bulletin 53-PM3148: a. Install additional fire-proof, stainless steel skin overexisting light alloy outer skin on top of the fuselage, between Stations 936 and 958 to isolate the APU plenum chamber from the fin structure. b. Replace the light alloy wall separating the APU plenum chamber from the hydraulic compensator unit compartment by installing a stainless steel wall enlarging the hydraulic compensator box and replacing light alloy structural parts with stainless steel. c. Install revised spring loaded door in the bulkhead at Station 936 and modify the hydraulic compensator drain box and drain outlet. 3. Install sealing plates around the control guard, located above the rudder power control units, and over the hole in the fin rear spar, to provide restriction to the airflow into the fin, in accordance with British Aerospace BAC 1-11 Service Bulletin 55-PM3177. 4. Install an additional bi-metallic temperature sensor in parallel with the existing mercury sensor in circuitry for controlling the electrically actuated primary temperaturevalve located in the low pressure bleed flow duct to the heat exchanger, in accordance with British Aerospace BAC 1-11 Service Bulletin 21-PM 2780A, or install Graviner bi-metallic sensor in accordance with BAC 1-11 Modification 21-PM-2545 Part A. 5. Perform a magnetic check to identify "felt metal" jet pipe installed on the APU manufactured from type "430" stainless steel post PM 209 in accordance with British Aerospace BAC 1-11 Service Bulletin 49-A-PM3313. Thoroughly inspect the jet pipes thus identified for cracks adjacent to the weld. Replace cracked pipes with serviceable pipes manufactured from 430 or 347 material. Jet pipes identified as manufactured from "430" stainless steel and found by inspection to be in a serviceable condition, may continue in operation provided that the inspection is performed thereafter at intervals not to exceed 160 hours time in service. Type "430" jet pipes must be removed from service upon accumulating 3,000 hours time in service. 6.Add a new paragraph at the end of Section 2, Page 15, of the BAC 1-11 airplane flight manual entitled "APU Supply and Air Conditioning," to read as follows: "The following limitations on the use of the APU air supply and integrated air system shall be observed to limit the time of exposure of the common duct to the simultaneous delivery of air from the engines and the APU. a. Whenever an engine is being started by air from an external supply or by cross-feeding air from the other engine, the APU air delivery valve shall be closed. b. When one or both engines are running and the APU is supplying air for both air conditioning systems, the master valve switch for each system must be set to APU. If the APU is only supplying air for one system, the master valve switch for that system must be set to APU and, for the system not in use, the master valve switch must be set to CLOSE and isolation valve switch must be set to CLOSE. c. After take-off and whenchanging the source of supply from the APU to the engines, the APU air delivery valve switch must be set to CLOSE immediately on completion of the change-over drill. Refer to Section 4." 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 may add any comments 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 for the accomplishment of the modifications required by 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, Inc., 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, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This Amendment, 39-5956, revises AD 68-01-01, Amendment 39-998. This Amendment, 39-5956, becomes effective July 18, 1988.