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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.