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.
92-02-10: 92-02-10 AEROSPATIALE: Amendment 39-8146. Docket 91-NM-185-AD. Applicability: Model ATR42-200, -300, and -320 series airplanes; Serial Numbers 16, 17, 19, 20, 22 through 34, 36 through 39, 41 through 45, 47 through 49, 54, 59, and 107; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent collapse of the nose landing gear (NLG), accomplish the following: (a) Perform a dye penetrant inspection to detect cracks of the four hinge pins of the left-hand and right-hand NLG leg and drag braces, and accomplish emergency extension functional tests, in accordance with Aerospatiale Service Bulletin ATR42-32-0039, Revision 1, dated August 1, 1991, at the applicable time specified below: (1) For airplane serial numbers 17, 19, 22, 23, 24, 26, 28, 30, 31, 33, 37, 39, 41, 44, 45, 47, 48, and 59: Within 30 days after the effective date of this AD, or prior to the accumulation of 250 hours time-in-service, whicheveroccurs first. (2) For airplane serial numbers 16, 20, 25, 27, 29, 32, 34, 36, 38, 42, 43, 49, 54, and 107: Within 60 days after the effective date of this AD, or prior to the accumulation of 500 hours time-in-service, whichever occurs first. (b) If a cracked hinge pin is found as a result of the inspection required by paragraph (a) of this AD, replace it with a new hinge pin or with a hinge pin that previously has been inspected and found to be free of cracks, in accordance with Aerospatiale Service Bulletin ATR42- 32-0039, Revision 1, dated August 1, 1991. (c) As of the effective date of this AD, no hinge pin shall be installed on any airplane unless that hinge pin is new or has been inspected in accordance with Aerospatiale Service Bulletin ATR42-32-0039, Revision 1, dated August 1, 1991, and found to be free of cracks. (d) 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. (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) The inspection and replacement of hinge pins required by this AD shall be done in accordance with Aerospatiale Service Bulletin ATR42-32-0039, Revision 1, dated August 1, 1991, which incorporates the following list of effective pages: Page Numbers Revision Number Date 1, 12, and 13-14 1 August 1, 1991 2, 3, 4, 5-6, 7, 8, 10, 11, and 15 Blank July 18, 1991 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 Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. (g) This amendment (39-8146, AD 92-02-10) becomes effective on March 2, 1992.
2021-02-20: The FAA is adopting a new airworthiness directive (AD) for all Helicopteres Guimbal Model Cabri G2 helicopters. This AD was prompted by a report of a crack in a rotating scissor fitting. This AD requires an initial and repetitive inspections of certain rotating and non-rotating scissor fittings, and depending on the results, replacing the affected assembly. This AD also prohibits installing certain main rotor hubs (MRHs) and swashplate guides unless the initial inspection has been accomplished. The FAA is issuing this AD to address the unsafe condition on these products.
91-21-13: 91-21-13 BOEING: Amendment 39-8060. Docket 91-NM-80-AD. Supersedes AD's 89-13-05 and 89-23-05. \n\n\tApplicability: Model 737-300, -400, and -500 series airplanes, listed in Boeing Service Bulletin 737-76-1023, dated February 14, 1991, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo minimize the potential for cable separation due to the Number 2 engine throttle cable chafing against the right wing front spar bracket, and to prevent Number 1 and Number 2 engine throttle control cable ratcheting feedback, accomplish the following: \n\n\tA.\tFor Model 737-300 series airplanes: Prior to the accumulation of 300 flight hours after July 24, 1989 (the effective date of Amendment 39-6240), unless previously accomplished within the previous 700 flight hours, and thereafter at intervals not to exceed 1,000 flight hours, gain access to the fuel shutoff cable pulley bracket near the right wing front spar station 124 and inspect thenumber two engine throttle cable for wear. Replace the cable, before further flight, if cable wear exceeds acceptable wear limits specified in Section 20-20-31 of the Model 737 Maintenance Manual. \n\n\tB.\tFor Model 737-400 series airplanes: Prior to the accumulation of 300 flight hours after November 27, 1989 (the effective date of Amendment 39-6367), unless previously accomplished within the previous 700 flight hours, and thereafter at intervals not to exceed 1,000 flight hours, gain access to the fuel shutoff cable pulley bracket near the right wing front spar station 124 and inspect the number two engine throttle cable for wear. Replace the cable, before further flight, if cable wear exceeds acceptable wear limits specified in Section 20-20-31 of the Model 737 Maintenance Manual. \n\n\tC.\tFor all airplanes: Within 36 months after the effective date of this AD, modify the engine throttle control cable system in accordance with Boeing Service Bulletin 737-76-1023, dated February 14, 1991. This modification constitutes terminating action for the repetitive inspections required by paragraphs A. and B. of this AD. \n\n\tD.\tAn 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, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO. \n\n\tE.\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\tF.\tThe inspections and modifications shall be done in accordance with Boeing Service Bulletin 737-76-1023, dated February 14, 1991. 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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. Copies may be inspected at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, D.C. \n\n\tAirworthiness Directive 91-21-13 supersedes AD 89-13-05, Amendment 39-6240; and AD 89-23-05, Amendment 39-6367. \n\tThis amendment (39-8060, AD 91-21-13) becomes effective on November 29, 1991.
2025-02-02: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by a report indicating cracks in the frame inner chord and web at station (STA) 727. This AD requires an inspection for any repair installed, repetitive inspections of the frame inner chord and web at STA 727 for any crack, and applicable on- condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2003-15-08: This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (ECF) model helicopters that requires replacing the main gearbox (MGB) opening neoprene cowling seals (seals) with airworthy glass/silicone seals. This amendment is prompted by the discovery that neoprene seals currently installed on the MGB opening cowlings do not provide the fire protection required by the airworthiness standards. The actions specified by this AD are intended to prevent a fire in the engine compartment from reaching the MGB compartment that contains parts that are not fire resistant and subsequent loss of control of the helicopter.
90-15-01: 90-15-01 ROGERSON HILLER CORPORATION (HILLER, FAIRCHILD HILLER): Amendment 39-6879. Docket No. 90-ASW-39. Final Rule of priority letter AD. Applicability: All Model UH-12E, UH-12E-L, UH-12L, and UH-12L4 series helicopters, certificated in any category. Compliance: Required prior to further flight, unless already accomplished. To prevent failure of a tail rotor blade assembly, which could result in loss of controllability of the helicopter, accomplish the following: (a) Determine the part number and serial number of the tail rotor blade assemblies installed on the helicopter. The serial number is located on a raised rectangular boss on the barrel section of the blade root fitting. (b) If any tail rotor blade assembly installed is P/N 55073 and is identified with any of the serial numbers listed below, regardless of the hours' time in service, remove and replace the blade assembly with an airworthy part before further flight: Serial Numbers: 3028 3089 9506 9584 9607 10245 10516 10917 13278 14715 14898 15073 15285 15978 16114 20918 NOTE: Any unairworthy blade assemblies found as a result of this AD should be permanently marked as unairworthy. (c) If any of the tail rotor blade assemblies listed in paragraph (b) are found, report the helicopter registration number, serial number, and tail rotor blade assembly serial number to the Manager, Seattle Aircraft Certification Office (ACO), FAA, Northwest Mountain Region, Transport Airplane Directorate, within 10 days of the inspection required by paragraph (a) of this AD. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate helicopters to a base in order to comply with the requirements of this AD. (e) Record compliance with paragraph (b) in the AD compliance record and in the maintenance record of the helicopter log book. This record must include the serial number of any deficient blade assembly foundduring compliance with this AD. (f) An alternate means of compliance or adjustment of the compliance time, which provides an equivalent level of safety, may be used when approved by the Manager, Seattle ACO, FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. Note: The request should be submitted directly to the Manager, Seattle ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Seattle ACO. This amendment (39-6879, AD 90-15-01) becomes effective on March 7, 1991, as to all persons, except those persons to whom it was made immediately effective by Priority Letter AD 90-15-01, issued on July 11, 1990, which contained this amendment.
2020-26-16: The FAA is adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. (Piper) Models PA-28-151, PA-28-161, PA- 28-181, PA-28-235, PA-28R-180, PA-28R-200, PA-28R-201, PA-28R-201T, PA- 28RT-201, PA-28RT-201T, PA-32-260, PA-32-300, PA-32R-300, PA-32RT-300, and PA-32RT-300T airplanes. This AD was prompted by a report of a wing separation caused by fatigue cracking in a visually inaccessible area of the lower main wing spar cap. This AD requires calculating the factored service hours for each main wing spar to determine when an inspection is required, inspecting the lower main wing spar bolt holes for cracks, and replacing any cracked main wing spar. The FAA is issuing this AD to address the unsafe condition on these products.
86-19-11: 86-19-11 CESSNA: Amendment 39-5407. Applies to Models R172 thru R172K, FR172E thru FR172K, 177 thru 177B and 177RG, F177RG, 185 thru 185E, A185E, A185F, A188, A188A, A188B, T188C, 205 and 205A, 206, U206, U206A thru U206G, TU206A thru TU206G, P206, P206A thru P206E, TP2O6A thru TP206E, 207 and 207A, T207 and T207A, 210B thru 210R, T210F thru T210R, P210N and P210R (all Serial Numbers (S/N)) airplanes equipped with fuel reservoir(s) certified in any category. \n\n\tCompliance: Within 100 hours time-in-service or at the next annual inspection, whichever comes first after the effective date of this AD, unless already accomplished. \n\n\tTo eliminate the possibility of engine power reduction due to contaminated fuel, accomplish the following: \n\n\t(a)\tOn Cessna Models R172, R172E thru R172H, (S/Ns R172-0001 thru R1720625) FR172E thru FR172J (S/Ns FR17200001 thru FR17200530) 177 thru 177A (S/Ns 17700001 thru 17702123) Model 177RG (S/Ns 177RG0001 thru 177RG0592) F177RG (S/Ns F177RG0001 thru F177RG0122) 210G and T210G thru 210L and T210L (S/Ns 21058819 thru 21060539 and T210-0198 thru T2100454) airplanes, install quick drains in the fuel reservoirs and wing fuel tanks if not presently equipped in accordance with Cessna Single Engine Customer Care Service Information Letters SE79-45 dated September 10, 1979, and SE84-8 dated March 16, 1984, or using equivalent aircraft standard hardware. \n\n\t(b)\tOn all Cessna Models R172, R172E, R172F, R172G, R172H, R172J, R172K, (S/Ns R172-0001 thru R172-0409 and R1720410 and on) FR172E, FR172F, FR172G, FR172H, FR172J, FR172K (S/Ns FR17200001 thru FR17200675) 177, 177A, 177B (S/Ns 17700001 and on), 177RG (S/Ns 177RG0001 and on) F177RG (S/Ns F177RG0001 thru F177RG0177) 185, 185A, 185B, 185C, 185D, 185E, A185E, A185F (S/Ns 632, 185-0001 thru 185-1599, 18501600 and on) A188 (S/Ns 653, 188-0001 thru 188-0572) A188A (S/Ns 18800573 thru 18800832) A188B (S/Ns 678T, 18800833 and on) T188C (S/Ns T18803307T, T18803308T, T18803325T and on) 205,205A, (S/Ns 205-0001 and on) 206, U206, U206A, U206B, U2O6C, U206D, U206E, U2O6F, U206G, TU206A, TU206B, TU206C, TU206D, TU206E, TU206F, TU2O6G ((S/Ns 206-0001 thru 206-0275, U206-0276 and on) P206, P206A, P206B, P206C, P206D, P2O6E, TP206A, TP206B, TP206C, TP206D, TP2O6E, (S/Ns P206-0001 thru P20600647) 207, 207A, T207, T207A (S/Ns 20700001 and on) 210B, 210C, 210D, 210E, 210F, 210G, 210H, 210J, 210K, 210L, 210M, 210N, 210R, T210F, T210G, T210H, T210J, T210K, T210L, T210M, T210N, T210R (S/Ns 21057841 and on) P210N and P210R (S/Ns P21000001 and on) airplanes, attach the information that is included in the appendix to this AD (entitled PILOT OPERATING PROCEDURES - PREFLIGHT FUEL SYSTEM CHECK) to the airplane documents. \n\n\t(c)\tAn equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Office, FAA, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. \n\n\tAll persons affected by this directive may obtain copies ofthe document(s) referred to herein upon request to Cessna Aircraft Company, Piston Aircraft Marketing Division, Post Office Box 1521, Wichita, Kansas, 67201; or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. \n\n\tThis amendment becomes effective October 4, 1986.\n\n\t\t\t\t\t APPENDIX 86-19-11 \n\nPILOT OPERATING PROCEDURES-PREFLIGHT FUEL SYSTEM CHECK \n\nFuel sampling: Fuel strainer, wing tank and reservoir quick drains. \n\n\t1.\tPlace a suitable container under the fuel strainer drain outlet prior to operating the strainer drain control for at least 4 seconds. Check strainer drain closed. \n\n\t2.\tInspect the fluid drained from the fuel strainer and each wing tank quick drain for evidence of fuel contamination in the form of water, rust, sludge, ice or any other substance not compatible with fuel. Also check for proper fuel grade before the first flight of each day and after each refueling. If any contamination is detected, comply with4 below. \n\n\t3.\tRepeat Steps 1 and 2 on each wing tank quick drain. \n\n\t4.\tIf the airplane has been exposed to rain, sleet or snow, or if the wing fuel tanks or fuel strainer drains produce water, the fuel reservoir(s) must be checked for the presence of water by operating the fuel reservoir quick drains. The airplane fuel system must be purged to the extent necessary to insure that there is no water, ice or other fuel contamination.\n\n NOTE 1: The fuel reservoir(s) are located under the fuselage between the firewall and forward door post on all airplane models. Consult the pilots Operating Handbook or Owners Manual in order to determine if one or two reservoir(s) are installed.\n\n NOTE 2: A check for the presence of water using the fuel reservoir quick drains prior to the first flight of each day is considered good operating practice.
91-06-02: 91-06-02 PRATT & WHITNEY CANADA: Amendment 39-6888. Docket No. 90-ANE-31. Applicability: Pratt & Whitney Canada (PWC) PW115, PW118, PW118A, PW120, PW120A, PW121, PW123, PW124, PW124A, PW124B, PW125B and PW126A turboprop engines installed on, but not limited to, Aerospatiale ATR-42 and ATR-72, British Aerospace ATP, DeHavilland of Canada DHC-8, Embraer EMB-120, Fokker F-50, and Canadair CL-215T type aircraft. Compliance: Required within the next 1,200 hours time in service after the effective date of this AD, unless already accomplished. To prevent fuel leakage from the fuel filter cover assembly which could result in a fire hazard in the engine nacelle, accomplish the following: (a) For PWC PW115, PW118, PW118A, PW120, PW120A, PW121, PW124, PW124A, PW124B, PW125B and PW126A engines, incorporate a new fuel pump filter cover assembly in accordance with either PWC Service Bulletin (SB) No. 20897, Revision 1, dated October 15 1990, or PWC SB No. 20907, dated August 20, 1990, as applicable. (b) For PWC PW123 engines, incorporate a new fuel pump in accordance with PWC SB No. 20355, Revision 1, dated August 1, 1990. (c) For PWC PW123 engines, incorporate a new fuel pump filter cover assembly in accordance with PWC SB No. 20897, dated August 20, 1990. (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 submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, an alternate method of compliance with the requirements of this AD, or adjustments to the compliance schedule specified in this AD, may be approved by the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803-5299. The initial and repetitive inspection program shall be done in accordance with the following PWC documents: DOCUMENT PAGEREVISION DATE PWC SB 20897 ALL Revision 1 Oct. 15, 1990 PWC SB 20907 ALL Original Aug. 20, 1990 PWC SB 20355 ALL Rev. 1 Aug. 1, 1990 This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 522(a) and 1 CFR Part 51. Copies may be obtained from Pratt & Whitney Canada, Technical Publications Department, 1000 Marie Victorin, Longueuil, Quebec J4G 1A1. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Room 311, Burlington, Massachusetts 01803-5299, or at the Office of the Federal Register, 1100 L Street, NW, Room 8401, Washington, D.C. 20591. This amendment (39-6888, AD 91-06-02) becomes effective on March 29, 1991.
2025-02-05: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company (Boeing) Model 747-100, 747-100B, 747-100B SUD, 747- 200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SP, and 747SR series airplanes. This AD was prompted by a report of improper inner diameter grinding of landing gear outer cylinders, resulting in possible heat damage to the outer cylinder of the nose landing gear (NLG), body landing gear (BLG), and wing landing gear (WLG). This AD requires replacing any affected outer cylinders. The FAA is issuing this AD to address the unsafe condition on these products.
2003-15-07: This amendment adopts a new airworthiness directive (AD) that is applicable to Honeywell International Inc. (formerly AlliedSignal) model RE220 (RJ) auxiliary power units (APUs) part number (P/N) WE3800770-2. This amendment requires replacing the existing fuel nozzles with new design fuel nozzles, making reidentification updates to the APU identification plate, and operating the APU to perform a visual inspection for fuel leaks. This amendment is prompted by reports received by the FAA of cracks occurring in the existing APU fuel nozzles leading to fuel leaks. The actions specified by the AD are intended to prevent APU compartment fires and fuel vapor explosion.
2015-17-03: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400, -401, and -402 airplanes. This AD was prompted by a report of a main landing gear (MLG) parking brake becoming dislodged from its mounting bracket due to an improperly installed quick release pin of the hand pump lever. This AD requires removing the hand pump lever of the parking brake from the right-hand side nacelle. We are issuing this AD to prevent an unsecured lever from migrating from its stowed position, fouling against the MLG, and subsequently puncturing the nacelle structure, which could adversely affect the safe landing of the airplane.
86-26-03: 86-26-03 BOEING: Amendment 39-5500. Applies to Model 757 series airplanes equipped with Pratt and Whitney Aircraft PW2037 engines, as listed in Boeing Alert Service Bulletin 757- 78A0006, dated August 7, 1986, certificated in any category. \n\n\tTo minimize the potential for uncommanded deployment of a thrust reverser in flight, accomplish the following within 30 days after the effective date of this AD, unless previously accomplished: \n\n\tA.\tInspect and, if necessary, install a restrictor check valve on the control port of both thrust reverser isolation valves in accordance with Boeing Alert Service Bulletin 757- 78A0006, dated August 7, 1986, or later FAA-approved revision. \n\n\tB.\tModify the unlock and auto-restow proximity sensors' installation in accordance with Boeing Alert Service Bulletin 757-78A0006, dated August 7, 1986, or later FAA-approved revision. \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\tD.\tSpecial 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. \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 98124-2207. These documents 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 12, 1987.
96-17-03: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Jetstream Model 4101 airplanes. This action requires an inspection to determine the serial number of the leg assemblies of the main landing gear (MLG), and replacement of defective pins with serviceable pins. This amendment is prompted by a report indicating that pins installed on certain leg assemblies of the MLG s were heat treated incorrectly during manufacture. The actions specified in this AD are intended to prevent failure of the pins due to incorrect heat treatment, and subsequent structural failure of the MLG.
2025-02-01: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by uncommanded horizontal stabilizer motion during several in- service events caused by a problem with the trim switch wiring. This AD requires installing the pitch/roll trim switch relays. The FAA is issuing this AD to address the unsafe condition on these products.