Results
2002-11-01: This amendment adopts a new airworthiness directive (AD) for Eurocopter Deutschland (Eurocopter) Model EC135 helicopters with Turbomeca Arrius 2B1 engines installed. This action requires modifying the engine electrical control unit (FADEC) software and the collective linear transducer (LVDT). This amendment is prompted by a parameter discrepancy within the engine fuel main metering unit that is transmitted to the FADEC. This condition, if not corrected, could result in deactivation of the engine main fuel-metering valve, loss of automatic control of the affected engine, and subsequent loss of control of the helicopter.
2002-10-15: This amendment adopts a new airworthiness directive (AD), that is applicable to Rolls-Royce plc RB211 Trent 875, 877, 884, 892, 892B, and 895 series turbofan engines. This amendment requires reapplication of dry film lubricant to low pressure compressor (LPC) fan blade roots. This amendment is prompted by an aborted take-off resulting from LPC fan blade loss. Since this event, four additional cracked LPC fan blade roots have been reported. The actions specified by this AD are intended to prevent LPC fan blade loss, which could result in an uncontained engine failure and possible aircraft damage.
2002-10-07: This amendment adopts a new airworthiness directive (AD), that is applicable to Pratt & Whitney (PW) JT9D-59A, -70A, -7Q, and -7Q3 turbofan engines. This amendment requires fluorescent penetrant inspection of the high pressure turbine (HPT) second stage airseal knife edges for cracks, each time the airseal is accessible. This amendment is prompted by reports of cracks found in the knife edges of HPT second stage airseals during HPT disassembly. The actions specified by this AD are intended to prevent failure of HPT second stage airseals due to cracks in the knife edges, which if not detected could result in uncontained engine failure and damage to the airplane.
2023-11-01: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by multiple reports of erratic electrical system status on the push button annunciators (PBAs) and the engine instrument and crew alerting system (EICAS) while on-ground and during flight. This AD requires a records check and replacement of affected left-hand (LH) direct current power center (DCPC) units. The FAA is issuing this AD to address the unsafe condition on these products.
2023-12-16: The FAA is adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) Model Trent 1000 engines. This AD was prompted by reports of excessive wear on the inner seal fins of certain high-pressure turbine (HPT) triple seals. This AD requires an inspection of the HPT triple seal for excessive wear and, depending on the results of the inspection, replacement of the HPT triple seal and the intermediate-pressure turbine (IPT) disk, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2002-10-11: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 737 series airplanes, that currently requires repetitive inspections for cracking and corrosion of the pressure bulkhead at body station (BS) 1016, and follow-on actions. This amendment expands the applicability of the existing AD, and requires new repetitive inspections to detect cracking and corrosion of the aft pressure bulkhead at BS 1016, and follow-on actions. This action is necessary to detect and correct corrosion or cracking of the aft pressure bulkhead at BS 1016, which could result in loss of the aft pressure bulkhead web and stiffeners and consequent rapid decompression of the fuselage. This action is intended to address the identified unsafe condition.
93-23-13: 93-23-13 PIPER AIRCRAFT CORPORATION: Amendment 39-8749. Docket No. 93-CE- 32-AD. Supersedes AD 93-02-13, Amendment 39-8496 which superseded AD 92-26-02, Amendment 39-8429 and AD 80-20-04, Amendment 39-3925. Applicability: Model PA31, PA31-300, and PA31-325 airplanes (serial numbers 31-2 through 31-8012089), and Model PA31-350 airplanes (serial numbers 31-5001 through 31-8052199), certificated in any category. Compliance: Required initially within the next 50 hours time-in-service (TIS) after the effective date of this AD, unless already accomplished (compliance with AD 80-20-04, Amendment 39-3925, AD 92-26-02, Amendment 39-8429, or AD 93-02-13, Amendment 39- 8496), and thereafter as indicated. To prevent improper sealing of the baffle seals to the engine cowling, which could result in high engine operating temperatures, accomplish the following: (a) Visually inspect the engine baffle seals for proper positioning by using a light and looking in air inlets andaccess doors to ensure that forward seals and lower aft seals are all facing forward and not blown back. (b) If baffle seals are improperly positioned (blown back), prior to further flight, accomplish one of the following: (1) Install thicker baffle seals in accordance the instructions to Piper Kit 764 093, dated November 10, 1980; or NOTE 1: Piper Kit 764 093 includes the entire baffle assembly consisting of both baffles and baffle seals. Replacing the baffle seals included in this kit is the only requirement of paragraph (b)(1) or (c)(2) of this AD. (2) Install baffles of one of the following materials in accordance with Figure 1 of this AD: (i) Brown Aircraft Supply Engine Baffle Material, part number (P/N) BA71646-1 and BA71646-2, temperature range -40 to 300 degrees Fahrenheit. (ii) Brown Aircraft Supply, Fiber Reinforced High Temperature Silicone Engine Baffle Material (red), P/N T-95182, temperature range -65 to 550 degrees Fahrenheit; and(iii) Brown Aircraft Supply, Engine Baffle Material, P/N T-8071, temperature range -40 to 300 degrees Fahrenheit. FIGURE 1 BROWN AIRCRAFT SUPPLY BAFFLE SEAL INSTALLATION PROCEDURES 1. Inspect the existing baffle seals through the front of the cowl to ensure existing seals are of sufficient length to provide at least 1-inch of contact with upper and lower cowls when properly positioned. Mark areas that need lengthening, and note the minimum length needed to meet requirements. 2. Remove the cowls in accordance with the applicable maintenance manual. Remove rivets, wire, and screws, as applicable, that secure baffle seals (fabric) to the engine baffles (metal). Retain any metal strips that are used to secure seals to the engine baffles. 3. Remove existing baffle seals and lay against Brown Aircraft Supply baffle seal material. 4. Cut new seals around the layout, ensuring that seals are lengthened as noted in procedure 1. 5. Reattach new seals to the engine baffles with the original screws, rivets, and wires, as applicable, or new hardware of the same part number. NOTE: The front upper cowl baffle seal is most critical, especially at the inboard and outboard corners. If the old material can be removed intact, and the curve can be transferred to the new flat material, then it may not be necessary to slit the material where it curves from vertical to horizontal contact with the cowl. If the curve requires a slit in the material at the corner, then it is recommended that the slit be tied with ty-raps or safety wire to ensure contact with the cowl around the radius. (c) If baffle seals are properly positioned (not blown back), within the next 50 hours TIS, accomplish one of the following: (1) Reinspect the engine baffle seals as specified in paragraph (a) of this AD, and continue to reinspect thereafter at intervals not to exceed 50 hours TIS; or (2) Install thicker baffle seals as specified in either paragraph (b)(1) or (b)(2) of this AD. This installation terminates the inspection requirements of this AD. (d) The inspections required by this AD may be performed by the owner/operator holding at least a private pilot certificate as authorized by FAR 43.7, and must be entered into the aircraft records showing compliance with this AD in accordance with FAR 43.11. (e) 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. (f) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta Aircraft Certification Office. (g) The installation (using Piper Aircraft Corporation parts) required by this AD shall be done in accordance with Piper Kit 764 093, dated November 11, 1980. 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 the Piper Aircraft Corporation, 2926 Piper Drive, Vero Beach, Florida 32960. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (h) This amendment (39-8749) supersedes AD 93-02-13, Amendment 39-8496 which superseded AD 92-26-02, Amendment 39-8429 and AD 80-20-04, Amendment 39-3925. (i) This amendment becomes effective on January 21, 1994.
94-01-05: This amendment adopts a new airworthiness directive (AD) that applies to certain Allied Signal Aerospace Company, Air Transport Avionics (Allied Signal) Traffic Alert and Collision Avoidance System (TCAS) II processors that are installed on aircraft. This action requires replacing the existing TCAS II processor with a new processor that incorporates updated computer logic. The development of candidate enhancements to TCAS II logic that improves its utility and increases its overall operational acceptance prompted the proposed action. The actions specified by this AD are intended to prevent collisions or near misses caused by incompatibility between the TCAS II processors and the current air traffic control system.
93-06-02: 93-06-02 PIPER AIRCRAFT CORPORATION: Amendment 39-8527. Docket No. 92- CE-48-AD. Applicability: Models PA-23-150, PA-23-160, PA-23-235, and PA-23-250 airplanes (all serial numbers) that have Met-Co-Aire 48-gallon fuel tip tanks installed in accordance with Supplemental Type Certificate SA1480WE, certificated in any category. Compliance: Required within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished. NOTE 1: The compliance time referenced in this AD takes precedence over that referenced in Met-Co-Aire (MCA) Service Bulletin No. 23-001, dated July 1992. To prevent fuel leakage and possible fire, which could result in passenger injury, accomplish the following: (a) Replace any existing Parker "Push-Lok" flexible fuel hose, MCA part number (P/N) 11059-4 or Parker-Hannifin P/N 801-6/250PSI, with a Stratoflex hose, MCA P/N 11059-10 or Parker-Hannifin P/N 130001-6S-0154, in accordance with the instructionsin Met-Co-Aire Service Bulletin No. 23-001, dated July 1992. (b) 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. (c) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Los Angeles Aircraft Certification Office, FAA, 3229 E. Spring Street, Long Beach, California 90806-2425. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Los Angeles Aircraft Certification Office. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles Aircraft Certification Office. (d) The replacement required by this AD shall be done in accordance with Met-Co-Aire Service Bulletin No. 23-001, datedJuly 1992. 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 Met-Co-Aire, P.O. Box 2216, Fullerton, California 92633. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on May 12, 1993.
2002-10-08: This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company (GE) CF6-80E1 series turbofan engines installed on Airbus Industrie A330 series airplanes. This action requires initial and repetitive thrust reverser inspections and checks, and allows extended threshold and repetitive inspection intervals for certain inspections if an optional double p-seal configuration is installed. This amendment is prompted by reports of service-induced hardware deterioration that reduces the overall thrust reverser system protection against inadvertent deployment, which can result in loss of control of the airplane. The actions specified in this AD are intended to prevent inadvertent in-flight thrust reverser deployment, which can result in loss of control of the airplane.