Results
99-22-13: This amendment adopts a new airworthiness directive (AD), applicable to BHTC Model 407 helicopters, that requires visually inspecting the vertical fin (fin) for reduced skin thickness; repairing or replacing the fin, if necessary; and identifying fins that have been inspected or repaired. This amendment is prompted by a report of an inboard skin damaged during production. The actions specified by this AD are intended to detect fin assemblies with reduced skin thickness which, if not corrected, reduce the strength of the skin and could lead to failure of the fin and loss of control of the helicopter.
2015-17-19: We are adopting a new airworthiness directive (AD) for all Rolls-Royce plc (RR) RB211 Trent 768-60, 772-60, and 772B-60 turbofan engines. This AD was prompted by fuel leaks caused by damage to the fan case low-pressure (LP) fuel tube. This AD requires inspection of the fan case LP fuel tubes and associated clips and the fuel oil heat exchanger (FOHE) mounts and associated hardware. We are issuing this AD to prevent failure of the fan case LP fuel tube, which could lead to an in-flight engine shutdown, loss of thrust control, and damage to the airplane.
98-11-29: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model BAe 146 series airplanes and Model Avro 146-RJ series airplanes, that requires a one-time inspection to detect corrosion of the threads of the eyebolt and piston rod on the retraction jack of the main landing gear (MLG); 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 prevent corrosion of the threads of the eyebolt and piston rod on the retraction jack of the MLG, which may cause the eyebolt to detach from the jack, and consequent unrestrained MLG deployment or inability to retract the MLG.
89-25-02: 89-25-02 BOEING: Amendment 39-6402. Docket No. 89-NM-225-AD. \n\n\tApplicability: Model 737-300 and -400 series airplanes, identified in Boeing Alert Service Bulletins 737-77A1026, Revision 2, dated October 27, 1989, and 737-77A1025, dated October 12, 1989, certificated in any category. \n\n\tCompliance: Required within 60 days after the effective date of this AD, unless previously accomplished. \n\n\tTo reduce the risk of engine flameout during inadvertent airplane immersion into thunderstorm activity, accomplish the following: \n\n\tA.\tFor Model 737-300 series airplanes: Modify the engine idle circuitry in accordance with Boeing Alert Service Bulletin 737-77A1026, Revision 2, dated October 27, 1989. \n\n\tNOTE: This action is in addition to the actions required by AD 88-13-51 R1, Amendment 39-6088, for the Model 737-300 series airplanes. \n\n\tB.\tFor Model 737-400 series airplanes: Modify the engine idle circuitry in accordance with Boeing Alert Service Bulletin 737-77A1025, dated October 12, 1989. \n\n\tC.\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\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment, and then send it to the Manager, Seattle Aircraft Certification Office. \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 information from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6402, AD 89-25-02) becomes effective on December 11, 1989.
2025-01-05: The FAA is superseding Airworthiness Directive (AD) 2022-25- 07, which applied to all Embraer S.A. Model ERJ 170-100 LR, -100 STD, - 100 SE, and -100 SU airplanes; and Model ERJ 170-200 LR, -200 SU, -200 STD, and -200 LL airplanes. AD 2022-25-07 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require all actions in AD 2022-25-07 and requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, and certain structural modifications, as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2015-18-05: We are superseding Airworthiness Directive (AD) 97-07-14, for certain Airbus Model A320-111, -211, and -231 airplanes. AD 97-07-14 required modification of an area on the front spar of the wing center section by installing shims and new fasteners to reinforce pressure floor fittings. This new AD continues to require modifying the rib flange on the front spar of the wing center section by installing shims and new fasteners to reinforce pressure floor fittings; and requires repetitive high frequency eddy current inspections for cracking of the radius of the rib flanges and vertical stiffener at frame 36, a rototest inspection for cracking of the fastener holes of the rib flanges, repair if needed, and adding additional airplanes to the applicability. This AD was prompted by the need for repetitive inspections on airplanes on which the modification of the rib flange on the front spar of the wing center section has been done. We are issuing this AD to prevent fatigue cracking on the rib flange area of the front spar of the wing center section, which can reduce the structural integrity of fuselage frame 36 and the wing center section.
98-25-14: 98-25-14 Rolls-Royce plc: Amendment 39-10940. Docket 98-ANE-06-AD. Applicability: Rolls-Royce plc (R-R) Viper Mk. 521, 522, 526 and 601 series turbojet engines, installed on but not limited to Raytheon (formerly British Aerospace, Hawker Siddeley) Models BH.125 and DH.125 series aircraft. Note 1: This airworthiness directive (AD) applies to each engine 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 engines 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 as indicated, unless accomplished previously. To prevent a high pressure fuel leak, which could result in an engine nacelle fire and damage to the aircraft, accomplish the following: (a) For R-R Viper Mk. 521, and 522 series engines, perform a one-time inspection of the barometric flow control unit (BFCU) augmentor and bypass valve joint washer for joint washer integrity, and replace, if necessary, with serviceable parts, in accordance with R-R Alert Service Bulletins (ASBs) Nos. 73-A120 and 73-A121, as applicable, dated November 1997, as follows: (1) For engines with less than 200 hours time in service (TIS) since new, overhaul, or repair of the BFCU, inspect within 2 months, or 100 hours TIS after the effective date of this AD, whichever occurs first. (2) For engines with 200 or more hours TIS since new, overhaul, or repair of the BFCU, inspect at the next engine removal after the effectivedate of this AD. (b) For R-R Viper Mk. 526 series engines, perform a one-time inspection of the barometric flow control unit (BFCU) augmentor and bypass valve joint washer for joint washer integrity, and replace, if necessary, with serviceable parts, in accordance with R-R ASBs Nos. 73-A68 and 73-A69, as applicable, dated November 1997, as follows: (1) For engines with less than 200 hours time in service (TIS) since new, overhaul, or repair of the BFCU, inspect within 2 months, or 100 hours TIS after the effective date of this AD, whichever occurs first. (2) For engines with 200 or more hours TIS since new, overhaul, or repair of the BFCU, inspect at the next engine removal after the effective date of this AD. (c) For R-R Viper Mk. 601 series engines, perform a one-time inspection of the BFCU augmentor and bypass valve joint washer for joint washer integrity, and replace, if necessary, with serviceable parts, in accordance with R-R ASBs Nos. 73-A35 and 73-A36, as applicable, dated November 1997, as follows: (1) For engines with less than 200 hours TIS since new, overhaul, or repair of the BFCU, inspect within 2 months, or 100 hours TIS after the effective date of this AD, whichever occurs first. (2) For engines with 200 or more hours TIS since new, overhaul, or repair of the BFCU, inspect at the next engine removal after the effective date of this AD. (d) 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, Engine Certification Office. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. Note 2: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. (e) Special flight permits may beissued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the aircraft to a location where the requirements of this AD can be accomplished. (f) The actions required by this AD shall be done in accordance with the following R-R ASBs: Document No Pages Date 73-A35 1-6 November 1997 Total Pages: 6. 73-A36 1-6 November 1997 Total Pages: 6. 73-A68 1-6 November 1997 Total Pages: 6. 73-A69 1-6 November 1997 Total Pages: 6. 73-A120 1-6 November 1997 Total Pages: 6. 73-A121 1-6 November 1997 Total Pages: 6. 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 Rolls-Royce Limited, Bristol Engines Division, Technical Publications Department CLS-4, P.O. Box 3, Filton, Bristol, BS34 7QE England; telephone 117-979-1234, fax 117-979-7575.Copies may be inspected at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street NW., suite 700, Washington, DC. (g) This amendment becomes effective on February 12, 1999.
97-06-11: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) 35 series airplanes (formerly referred to as Beech 35 series airplanes). This action requires inspecting the ruddervator differential tail control rod assembly for corrosion or cracks, repairing or replacing any cracked or corroded part, and applying anti-corrosion sealant to the ruddervator control pushrods. This action results from a report of a split in the ruddervator control push rod on an affected airplane that was found during a routine inspection. The split occurred when water froze in the internal area of the control push rod and then expanded. The actions specified by this AD are intended to prevent failure of the differential tail control rod assembly, which could result in loss of control of the airplane.
2025-02-13: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 757-200, -200CB, and -200PF series airplanes. This AD was prompted by a report indicating an operator has found cracks on three Model 757-200PF airplanes at the main deck cargo door cutout forward and aft hinge attachment holes. This AD requires a maintenance record check for repairs at the forward and aft hinge areas of the main deck cargo door cutout; repetitive open-hole high frequency eddy current (HFEC) inspections for cracks in the unrepaired areas of the bear strap, skin, doubler, and upper sill chord at the main deck cargo door forward and aft hinge attachment holes; and applicable corrective actions. The FAA is issuing this AD to address the unsafe condition on these products.
92-17-09: 92-17-09 BRITISH AEROSPACE: Amendment 39-8338. Docket No. 92-NM-62-AD. Applicability: Model BAe 125-800A series airplanes on which Modification 259283C thrust reversers have been installed, and on which Modification 259949A or BAe Repair Instruction Leaflet (RIL) 25-8ES16 has not been installed, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent damage that may cause unsymmetrical thrust, accomplish the following: (a) Within 9 months after the effective date of this AD, install Modification 259949A, in accordance with British Aerospace Service Bulletin SB.78-4-9949A, dated January 20, 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, 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. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (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.78-4-9949A, dated January 20, 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 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., 7th Floor, Suite 700, Washington, DC. (e) This amendment becomes effective on September 28, 1992.