Results
2000-05-18: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300, A310, and A300-600 series airplanes, that requires repetitive eddy current inspections to detect cracking on the door edge frames of the fuselage bulk cargo compartment, and repair, if necessary. 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 detect and correct cracks in the door edge frames of the fuselage bulk cargo compartment, which could result in reduced structural integrity of the airframe.
2021-17-06: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 747-100, -100B, -100B SUD, -200B, -200C, - 200F, -300, -400, -400D, -400F, 747SR, and 747SP airplanes. This AD was prompted by reports of cracks found in the front spar shear tie and at the intercostal lug fitting at certain locations. This AD requires repetitive detailed and surface high frequency eddy current (HFEC) inspections of the front spar shear tie and intercostal lug fitting at certain locations for any cracking, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2014-23-02: We are adopting a new airworthiness directive (AD) for certain Agusta Model A109E, A109K2, A119, and AW119 MKII helicopters. This AD requires repetitively performing a magnetic particle inspection of the Gleason crown for a crack. This AD was prompted by a report of a crack that was found on a Gleason crown, which if not detected, could cause damage to or loss of the main rotor drive and subsequent loss of control of the helicopter.
2000-05-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737 series airplanes, that requires a one-time inspection of the main landing gear (MLG) axle flange to detect cracking, and follow- on corrective actions. For certain airplanes, this amendment also requires replacement of the original brake mounting gasket with a more durable aluminum-nickel-bronze gasket, and installation of new shear studs, if necessary. For certain airplanes, this amendment requires modification of the mounting flange holes of the brake torque tube. This amendment is prompted by reports of cracking in the axle flange and by reports of deterioration of the brake mounting gasket. The actions specified by this AD are intended to prevent fracture of the MLG axle and separation of the wheel from the MLG, and consequent reduced controllability of the airplane.
91-11-07: 91-11-07 FOKKER: Amendment 39-7003. Docket No. 90-NM-291-AD. Applicability: Model F-28 series airplanes, Serial Numbers 11003 through 11013, 11991, and 11992; certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent reduced structural integrity of the fuselage, accomplish the following: A. Within one year after the effective date of this AD, remove the cold-bonded lap joint rivets, and perform detailed visual and high frequency eddy current inspections to detect cracks and damage to the areas adjacent to the rivet holds, in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/53-109, dated October 24, 1990. 1. If no cracks or damage are found, prior to further flight, install 3/16-inch protruding-head rivets in accordance with the Accomplishment Instructions of the service bulletin. 2. If cracks or damage are found, prior to further flight, repair and install 3/16-inch protruding-head rivets in accordance with the Accomplishment Instructions of the service bulletin. B. An alternative method 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, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. C. Special 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. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. These documents may be examined at the FAA, Northwest MountainRegion, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-7003, AD 91-11-07) becomes effective on June 24, 1991.
88-20-08: 88-20-08 HAMILTON STANDARD: Amendment 39-6009. Applies to Hamilton Standard Model 14SF-5 and 14SF-7 propellers equipped with plastic "Rynite" retaining rings, P/N 785540, installed on, but not limited to, Dehavilland Dash 8 and Aerospatiale/ Aeritalia ATR-42 aircraft. Compliance is required as indicated, unless already accomplished. To prevent loss of the plastic "Rynite" blade retaining rings, P/N 785540, and severe damage to the blade retention system with resultant propeller unbalance, accomplish the following: (a) Within the next 50 hours time in service after May 21, 1987, and thereafter at intervals not to exceed 200 hours time in service, until accomplishment of paragraph (c), inspect the plastic "Rynite" blade retaining rings, P/N 785540, on all four blades in accordance with Hamilton Standard Alert Service Bulletin (ASB) 14SF-61-A21, Revision 2, dated March 27, 1987. (b) If any evidence of cracks is discovered as a result of an inspection required by paragraph (a), prior to further flight remove from service both halves of blade retaining rings and replace with new or serviceable retaining ring halves in accordance with Hamilton Standard ASB 14SF-61-A21, Revision 2, dated March 27, 1987, or accomplish paragraph (c) below prior to further flight. (c) Replace, not later than July 31, 1989, the plastic "Rynite" blade retaining rings, P/N 785540, with aluminum blade retaining rings, P/N 794345, on all four blades in accordance with Hamilton Standard Service Bulletin 14SF-61-17, Revision 1, dated October 1, 1987. (d) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (e) Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Boston Aircraft Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. (f) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, the Manager, Boston Aircraft Certification Office, may adjust the compliance time specified in this AD. Hamilton Standard ASB 14SF-61-A21, Revision 2, dated March 27, 1987, and ASB 14SF-61-17, Revision 1, dated October 1, 1987, identified and described in this document, are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Hamilton Standard Division of United Technologies Corporation, Windsor Locks, Connecticut 06096. These documents may also be examined at the Office of the Assistant Chief Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Room 311, Docket 87-ANE-13, between the hours of 8:00 a.m.and 4:30 p.m., Monday through Friday, except federal holidays. This amendment, 39-6009, supersedes AD 87-10-05, Amendment 39-5609. This amendment, 39-6009, becomes effective on October 31, 1988.
2014-23-03: We are superseding Airworthiness Directive (AD) 76-06-09 for certain Piper Aircraft, Inc. Model PA-31P airplanes. AD 76-06-09 required repetitive inspection of certain exhaust system parts with replacement of parts mating with the turbocharger, as necessary, and allowed installation of a certain tailpipe v-band coupling as terminating action. This new AD requires the use of new service information and expands the scope of the inspections of the turbocharger exhaust system. This AD was prompted by reports of exhaust system failures, new service information, and the tailpipe v-band coupling used for terminating action is obsolete. We are issuing this AD to correct the unsafe condition on these products.
2000-05-11: This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model SA.315B, SA.316B, SA.316C, SA 318B, SA 318C, SA.319B, SE 313B, SE 3130, SE.3160, and SA 3180 helicopters that have certain tail rotor blades (blades) installed. This action requires reducing the service life of those blades to 400 hours time-in-service (TIS). This amendment is prompted by the discovery that 10 blades were manufactured incorrectly. This condition, if not corrected, could result in failure of a blade and subsequent loss of control of the helicopter.
93-02-07: 93-02-07 BELL HELICOPTER TEXTRON, INC., (BHTI): Amendment 39-8489. Docket Number 92-ASW-39. Supersedes AD 85-17-03R1, Amendment 39-5194, Docket Number 85- ASW-37. Applicability: BHTI Model 412 helicopters, serial numbers 33001 through 33120 and serial numbers 34001 through 34012, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the vertical fin spar cap assembly, which could result in loss of the vertical fin and subsequent loss of control of the helicopter, accomplish the following: (a) Within 25 hours time in service after the effective date of this AD, inspect the vertical fin spar cap assembly, P/N 212-030-447-001, in accordance with the Accomplishment Instructions, Part I, of BHTI Alert Service Bulletin (ASB) No. 412-92-65, dated August 17, 1992, and every 25 hours time in service thereafter until it is replaced with a vertical fin spar cap assembly, P/N 212-030-447-101, in accordancewith the Accomplishment Instructions, Part II, of the ASB. If any cracks, corrosion or doubler debonding is found, replace the spar cap assembly before further flight with an airworthy part in accordance with the Accomplishment Instructions, Part II, of the ASB. (b) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Rotorcraft Certification Office, ASW-170, 4400 Blue Mound Road, Fort Worth, Texas 76106. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Rotorcraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Manager, Rotorcraft Certification Office. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the helicopterto a location where the requirements of this AD can be accomplished. (d) The inspection and replacement of the fin spar cap shall be done in accordance with the Accomplishment Instructions, Parts I and II, of BHTI ASB No. 412-92-65, dated August 17, 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 Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, Texas 76101-0482. Copies may be inspected at the FAA, Office of the Assistant Chief Counsel, 4400 Blue Mound Road, Bldg. 3B, Room 158, Fort Worth, Texas; or at the Office of the Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC. (e) This amendment becomes effective on March 22, 1993.
2022-17-04: The FAA is adopting a new airworthiness directive (AD) for certain De Havilland Aircraft of Canada Limited Model DHC-8-400 series airplanes. This AD was prompted by reports of broken P-clamps on the pressure relief line and the motive flow line in the fuel tanks, and a subsequent determination that certain service information lacked instructions for maintaining appropriate clearance between certain fuel tubes and their support brackets, and may also have led to incorrect installation of certain Teflon<SUP>TM</SUP> sleeves. This AD was also prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires inspecting the motive flow line, vent line, and related parts, and adding support or additional clearance if necessary. This AD also requires inspection, and replacement or relocation if necessary, of affected Teflon<SUP>TM</SUP> sleeves on the vent line, and installation of Teflon<SUP>TM</SUP> sleeves on the vent line at additional wing stations. This AD also requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. The FAA is issuing this AD to address the unsafe condition on these products.